effectivity: md900 - MD Helicopters

BENDIXIKING" IFR AVIONICS I KFC goo 

006-00757-0000 MAINTENANCE MANUAL SUPPLEMENT 

HONEYWELL - CONFIDENTIAL 

THlS DOCUMENT AND ALL INFORMATION AND EXPRESSION CONTAINED HEREIN ARE THE 

PROPERTY OF HONEYWELL INTERNATIONAL INC., ARE PROVIDED IN CONFIDENCE, AND 

MAY BE USED BY PERSONS REQUIRED BY 14 CFR 21.50 TO COMPLY WITH ANY OF THE 

TERMS OF THESE INSTRUCTIONS. EXCEPT AS SET FORTH ABOVE, NO PERSON MAY, IN 

WHOLE OR IN PART, USE, DUPLICATE OR DISCLOSE THlS INFORMATION FOR ANY 

PURPOSE WITHOUT THE PRIOR WRITTEN PERMISSION OF HONEYWELL INTERNATIONAL 

INC. 

BENDlXlKlNGQ and WINGMANO are registered Trademarks of Honeywell International Inc. 

For further information contact Honeywell at: 

Honeywell International Inc. 

One Technology Center 

23500 West 105'~ Street 

Olathe KS 66061 

Telephone: (913) 712-0400. 

Prior to Export of this Document, review for export license requirement is needed. 

Revisions to this manual may be ordered from the Technical Publicafions section of the 

www. bendixkinn.com website

BENDIX/KINGG" IFRAVIONICS I KFC goo 


MD Helicopters MD900 Rotorcraft 

Maintenance Manual Supplement 

IFR Avionics with KFC 900 

Automatic Flight Control System (AFCS) 

Registration. No. 

Serial. No. 

This supplement shall be attached to the Model MD900 Rotorcraft Maintenance Manual when the 

BendixlKing IFR Avionics with KFC 900 Automatic Flight Control System is installed per STC 

SR00436WI-D. The information contained herein supplements or supersedes the basic 

Maintenance Manual only in those areas listed herein. For Limitations, Procedures and 

Performance Data not contained in this supplement, consult the basic Maintenance Manual. 

I EFFECTIVITY: MD900 

I 

I 

I TITLE 

T-I 

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BENDIX/KlNG@ IFR AVIONICS I KFC goo 


THIS PAGE INTENTIONALLY LEFT BLANK 

T-2 

Revision AD 

TITLE 

EFFECTIVITY: MD900



I 

FAA APPROVED MAINTENANCE MANUAL SUPPLEMENT 

for the 

BENDIWKING KFC 900 AFCS AND IFR AVIONICS PACKAGE 

in the 

MD Helicopters Model MD900 

(including the 902 configuration) 

Serial Numbers 900-00010 and Subsequent 

Log of Revisions 

I Rev. I Page($) I Description 

0 

I 

AA 

AB 

AC 

- 

AD 

All 

All 

All 

All 

All 

Original Issue 

Deleted chapters 22, 23, 24 and 34. Added Chapters 96 and 97 to include 

autopilot maintenance information. 

Revised all pages to Rev AA due to format change. Revised pages as 

required due to company name changes. 

Revised chapters 96 and 97 to include 902 configuration (sln 52 and 

subsequent) and Category A equipment. 

Changed AlliedSignal to Honeywell. 

Added new power distribution schematics to 96-00-00. 

Added ~haiter 98, subchapters 98-10-00 and 98-40-00. 

Minor changes were incorporated to all sections. Added Section 11-00-00. 

Section 97-00-00 and subparts changed to add part numbers and 

I procedures for the configuration, alignment and checkout of 1 

1 1 repairedtreplaced avionics components. Section 98-40-00 was completely I I 

All 

cover 

changed to add new formatting for the wiring diagrams. 

Changed all sheets to revision AD. 

Revised Honeywell Confidential statement. 

Made minor revisions to section 98-40-00. 

Date 

4-15-96 

10-30-96 

1-4-99 

12-1 7-00 

5-3-02 

02-06-07 

I I 

LOR 

LOR-1 

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BENDIX/KlNG@ IFRAVIONICS I KFC goo 



LOR-2 

Revision AD

BENDIXIKINGIG IFRAVIONICSI KFC goo 


Discrepancy Notification 

This manual is maintained by Honeywell Certification Engineering Department. This manual supports the maintenance 

of the BENDIX/KlNG@ equipment and systems for the aircraft type and Supplemental Type Certificate designated on the 

cover of this manual. If a discrepancy is found in this manual, please mail or fax this form (or a copy) as well as copy of 

the page(s) with the discrepancy noted. The recommended change(s) will be evaluated and incorporated into the manual 

as necessary at the time of the next revision. 

Name: 

Company: 

Phone: 

Fax: 

Address: 

Honeywell 

Electronic & Avionics Systems 

One Technology Center 

23500 W 105'~ Street 

Olathe, KS 66061 

Attention: Certification Engineering 

Mail Drop # 1 

FAX (9 13) 782-0345 or (9 13) 7 12-6099 

Manual Number and Revision: 

Discrepancy:




DN-2 

Revision AD

BENDIX/KlNG@ IFRAVIONICSI KFC goo 


Table of Contents 

Section Title Page 

Title ..................................................................................................................................................... T-1 

Log of Revisions ........................................................................................................................... LOR-1 

Discrepancy Notification ................................................................................................................ DN-1 

01-00-00 Introduction . Description and Operation ..................................................................... 1 

1 . Description ............................................................................................................. 1 

2 . Aircraft Configuration ............................................................................................ 1 

A Configuration A ..................................................................................................... 1 

B . Configuration B ...................................................................................................... 1 

C . Configuration C ...................................................................................................... 1 

3 . Type Design Change .............................................................................................. 1 

A . Major Components ................................................................................................. 1 

B . Rotorcraft Flight Manual Supplement(s) ................................................................ 2 

4 . Manual Revisions ................................................................................................... 2 

01-00-00 Introduction - Maintenance Practices ......................................................................... 201 

1 . Maintenance and Operational Test Requirements and Precautions .................... 201 

2 . Operational Tests ............................................................................................... 201 

3 . Cleaning and Lubrication ................................................................................... 201 

4 . Inspections ...................................................................................................... 2 1 

5 . Maintenance Information Requests .................................................................... 201 

04-00-00 Airworthiness Limitations ................................................................................................ 1 

1 . Airworthiness Limitations ...................................................................................... 1 

05-00-00 Continued Airworthiness Inspections .............................................................................. 1 

1 . General ................................................................................................................... 1 

2 . Scheduled Inspection Program Overview .............................................................. 1 

3 . Documentation ....................................................................................................... 1 

4 . Electrical Bonding .................................................................................................. 1 

5 . Special Tools .......................................................................................................... 2 

05-20-00 Continued Airworthiness Scheduled Inspection ............................................................. 1 

1 General ................................................................................................................... 1 

2 . Scheduled Inspections ............................................................................................ 1 

A . Airframe Periodic Inspection Program ................................................................... 1 

B . Airframe Segmented Inspection Program .............................................................. 1 

3 . Definitions .............................................................................................................. 2 

05-20-20 Airframe Periodic Inspection ........................................................................................... 1 

05-20-50 Airframe Segmented Inspection Program ....................................................................... 1 

11-00-00 Placards and Markings ..................................................................................................... 1 

1 . General ................................................................................................................... 1 

2 . Decals and Placard ................................................................................................. 1 

A . Decal and Placard Application ............................................................................... 1 

............................................................... 

96-00-00 Electrical Power - Description and Operation 1 

1 . Electrical System .................................................................................................... 1 

A . Aircraft S/N 900-00010 thru 900-00051 ............................................................. 1 

B . Aircraft S/N 900-00052 and Subsequent ................................................................ 1 

C . External Power Box Assembly (S/N 900-00010 thru 900-00051 only) ................. 6 

D . Essential Bus Circuit Breaker Panel ....................................................................... 6 

E . Electrical Load Center ........................................................................................... 7 

. ..................................................................................... 

. 

................................................................................ 

. 

........................................................................ 

............................................................................ 

2 Battery Power Subsystem 10 

3 External Power Subsystem 1 0 

4 DC Power Generation Subsystem 10 

5 . DC Power Distribution System 10 

EFFECTIVITY: MD900 

CONTENTS 

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Page ii 

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Table of Contents (continued) 


A Essential Busses .................................................................................................. 12 

B . Battery Bus .......................................................................................................... 12 

C . Lighting Bus ...................................................................................................... 13 

D . Left Generator Bus ............................................................................................. 13 

E . Right Generator Bus ............................................................................................ 13 

F . Left Avionics Bus ............................................................................................ 13 

G . Right Avionics Bus .............................................................................................. 13 

H . 26VAC 400 HZ Bus ............................................................................................ 13 

96-30-00 DC Power Systems - Fault Isolation ........................................................................... 101 

............................................................. 

. 

........................ 

A . PCRl Failure Verification Procedure ................................................................ 104 

B . PCR2 Failure Verification Procedure ................................................................ 105 

1 Power Busses System Troubleshooting 101 

2 Verification of Rectifiers, Essential Bus Circuit Breaker Panel 104 

.............................................................. 

96-30-00 DC Power Systems - Removal I Installation 401 

1 . Circuit Breaker Panel ....................................................................................... 401 

A . Circuit Breaker Panel Removal ....................................................................... 401 

B . Circuit Breaker Panel Installation ...................................................................... 401 

C . Side Circuit Breaker Panel Removal (sln 900-00052 and subsequent) ............. 402 

D . Side Circuit Breaker Panel Installation (sln 900-00052 and subsequent) .......... 402 

. 

.......................................................................................... 

A Rectifier PCRlICRI Removal ........................................................................... 406 

B . Rectifier PCRIICRI Installation ....................................................................... 406 

C . Rectifier PCR2lCR2 Removal ........................................................................... 406 

D . Rectifier PCR2lCR2 Installation ....................................................................... 407 

. 

.......................................................................................... 

A . Master Switch Panel Removal ........................................................................... 407 

B . Master Switch Panel Installation ....................................................................... 407 

C . RT EFS Master Switch Removal ...................................................................... 408 

D . RT EFS Master Switch Installation ................................................................... 409 

E . AP Master Switch Removal ............................................................................... 409 

F . AP Master Switch Installation ........................................................................... 409 

G LT EFS Master Switch Removal (Four Tube configured aircraft only) ............ 409 

H . LT EFS Master Switch Installation (Four Tube Configured Aircraft Only) ...... 410 

. .................................................................................. 

A . Left Generator Field RCCB Removal ............................................................... 410 

B . Left Generator Field RCCB Installation ............................................................ 411 

C . Right Generator Field RCCB Removal ............................................................. 411 

D . Right Generator Field RCCB Installation .......................................................... 411 

. ......................................................... 

A . Left Generator Field Control Circuit Breaker Removal .................................... 412 

B . Left Generator Field Control Circuit Breaker Installation ................................. 412 

C . Right Generator Field Control Circuit Breaker Removal .................................. 413 

D . Right Generator Field Control Circuit Breaker Installation ............................ 413 

2 Rectifier PCRlICRl 406 

3 Master Switch Panel 407 

4 Generator Field RCCB's 410 

5 Generator Field Control Circuit Breakers 412 

....................................................................... 

96-30-00 DC Power Systems - Inspection / Test 601 

1 . DC Power Systems Inspections ......................................................................... 601 

A . Essential Bus Circuit Breaker Panel .................................................................. 601 

B . Master Switch Panel .......................................................................................... 601 

97-00-00 Avionics - Description and Operation ............................................................................ 1 

.................................................................................................................. 

. .................................................................................................. 

. 

..................................... 

1 General 1 

2 Avionics Systems 1 

3 VHF Navigation And Communications (NAVICOMM) 12 


BENDIX/KING" IFR AVIONICS I KFC goo 




A . KX 1651165A VHF NAVICOMM Transceiver ................................................... 14 

B KN 40 NAV Converter ....................................................................................... 15 

C . KI 206 Navigation Indicator ............................................................................... 15 

D . Navigation Antennas .......................................................................................... 1 6 

4 . Distance Measuring Equipment (DME)............................................................... 

16 

5 . Marker Beacon Receiver ...................................................................................... 16 

6 . Automatic Direction Finder (ADF)...................................................................... 17 

A KR 87 ADF Receiver .......................................................................................... 17 

B . KA 44B ADF Antenna ........................................................................................ 19 

7 . Global Positioning System (GPS) ........................................................................ 19 

A . KLN 90B GPS Receiver ...................................................................................... 20 

B . KA 92 GPS Antenna ............................................................................................ 22 

8 . Radar Altimeter .................................................................................................... 22 

A . KRA 4051405B Radar Altimeter Transceiver ...................................................... 22 

B . KA 54A Radar Altimeter Antenna ....................................................................... 23 

9 . Transponder (XPDR) ........................................................................................... 23 

10 . Attitude and Heading Reference System (pAHRS) ............................................. 25 

A . LCR-92s AHRU .................................................................................................. 25 

B . KMT 112 Flux Valve ........................................................................................... 28 

11 . Digital Air Data System ....................................................................................... 29 

A . KAV 485 AltimeterIVertical Speed Indicator ...................................................... 29 

B . KDC 481 T Air Data Computer ............................................................................ 31 

12 . Electronic Flight Information System (EFIS or EFS) .......................................... 31 

A . SG 465 Symbol Generator ................................................................................... 34 

B . ED 461 EHSI Display .......................................................................................... 34 

C . ED 462 EADI Display ......................................................................................... 37 

D . CP 470 Control Panel ........................................................................................... 40 

E . Composite Switch ................................................................................................ 40 

F . Pitch Sync Switch ................................................................................................. 40 

13 . Automatic Flight Control System (AFCS) ........................................................... 40 

A . KCP 520 Flight Control Computer ...................................................................... 45 

B . KCM 100 Configuration Module ......................................................................... 45 

C . KMS 540 Mode Select Panel ............................................................................... 45 

D . KSM 575 Linear Actuator .................................................................................... 46 

E . Trim Actuators ..................................................................................................... 47 

F . Cable Transducer And KSC 573 Yaw Spring Cartridge ...................................... 47 

G . Position Resolvers ................................................................................................ 47 

H . KRG 333 Triaxial Rate And Acceleration Sensor ............................................... 48 

I . APISAS Annunciator Panel .................................................................................. 48 

J . Flight Director LeWRight Switch ......................................................................... 49 

K . Diagnostic Plug .................................................................................................... 49 

14 . Weather Radar System ......................................................................................... 49 

A . ART 2000 Transceiver ......................................................................................... 51 

B . Flat Plate Antenna ................................................................................................ 52 

C . CM 2000 Configuration Module .......................................................................... 52 

D . KMD 540 MFD .................................................................................................... 52 

E . IN- 182A Indicator ................................................................................................ 53 

15 Avionics Cooling Fans ......................................................................................... 53 

16 . Standby Attitude Indicator and Standby Altimeter ............................................... 56 


A . STANDBY ATTITUDE INDICATOR ............................................................... 56 

B . STANDBY ALTIMETER ................................................................................... 56 

CONTENTS 

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Section 


Title 

Page 

17 . Mechanical Gyro System .................................................................................... 56 

A . Attitude Gyro ....................................................................................................... 57 

B . Directional Gyro .................................................................................................. 58 

C . KI 525A Pictorial Navigation Indicator (or HSI) ................................................ 58 

D . Slaving Accessory ............................................................................................... 59 

E . KMT 112 Flux Valve .......................................................................................... 59 

18 . AC Power System ..............,............................................................................... 59 

A . SPC-5(B) Static Inverter ..................................................................................... 60 

19 . Category A Equipment ........................................................................................ 61 

A . Aural Warning Generator .................................................................................... 61 

B . GH-3000 Indicator .............................................................................................. 61 

C . DCM-3000 Configuration Module ...................................................................... 61 

D . ADC-3000 Air Data Computer ........................................................................... 62 

E . MAG-3000 Magnetometer .................................................................................. 62 

20 . Emergency Locator Transmitter (ELT) ............................................................... 63 

............................................................. 

Avionics - Fault Isolation 1 Troubleshooting 101 

1 . General ............................................................................................................ 101 

2 . Attitude and Heading Reference System (pAHRS)........................................... 101 

A . TROUBLESHOOTING .................................................................................... 101 

3 . Digital Air Data System .................................................................................... 103 

A . KAV 485 POWER UP TEST SEQUENCE ..................................................... 103 

B . SELF TEST SEQUENCE (Push-to-Test) ......................................................... 103 

C . LOOPBACK TEST ........................................................................................... 104 

D . PITOT - STATIC SYSTEM CHECKS ............................................................. 104 

4 . Electronic Flight Instrumentation System (EFIS or EFS) .................................. 105 

A . EFS 40 SYSTEM FAILURES .......................................................................... 105 

B . TROUBLESHOOTING .................................................................................... 106 

C . MAINTENANCE PAGES ................................................................................ 109 

5 . Automatic Flight Control System (AFCS)......................................................... 120 

A . TROUBLESHOOTING ................................................................................... 120 

B . FCC ANNUNCIATIONS ................................................................................. 124 

C . AFCS DISCONNECT AURAL ALERT ........................................................... 127 

D . MANUAL TESTS ............................................................................................. 127 

E . FCC ERROR CODES ....................................................................................... 131 

F . FAILURE ANNUNCIATION .......................................................................... 166 

6 . Avionics Cooling Fans ...................................................................................... 174 

7 . Annunciators and Bulb Replacement ................................................................ 174 

A . AnnunciatorISwitches ........................................................................................ 174 

. .................................................................................................... 

B Annunciators 175 

Avionics - Removal / Installation ...................................... , ......................................... 401 

1 . General .............................................................................................................. 401 

2 . VHF Navigation and Communications (NAVICOMM).................................... 401 

A . KX 165lKX 165A NAVICOMM ...................................................................... 401 

B KI 206 NAV Indicator ....................................................................................... 402 

C . CI-1 125 Quadraplexer ....................................................................................... 402 

D . CI- 120 VORILOCIGS Antenna ....................................................................... 402 

E . CI-29 1 COMM Antenna (either antenna) .......................................................... 403 

3 . Distance Measuring Equipment (DME) ............................................................ 403 

A . KN 63 DME ...................................................................................................... 403 

B . CI- 105-6 DME Antenna .................................................................................. 404 

4 . Marker Beacon Receiver ................................................................................... 404 


BENDIX/KlNG@' IFR AVIONICS I KFC goo 



Section Title Paqe 

A . KMR 675 Marker Beacon Receiver ................................................................... 404 

B . KA 26 Marker Antenna ...................................................................................... 404 

5 . Automatic Direction Finder (ADF).................................................................... 

405 

A . KR 87 ADF Receiver ......................................................................................... 405 

B . KA 44B ADF Antenna ....................................................................................... 405 

6 . Global Positioning System (GPS) ...................................................................... 406 

A . KLN 90B GPS Receiver .................................................................................... 406 

B . KA 92 GPS Antenna .......................................................................................... 406 

7 . Radar Altimeter .................................................................................................. 407 

A . KRA 405lKRA 405B Radar Altimeter .............................................................. 407 

B . KA 54A Antenna ................................................................................................ 407 

8 . Transponder (XPDR)......................................................................................... 

408 

A . KT 70 I KT 71 Transponder .............................................................................. 408 

B . CI- 105-6 XPDR Antenna ................................................................................... 408 

9 . Attitude and Heading Reference System (pAHRS) ........................................... 408 

A . LCR-92s AHRU ................................................................................................ 408 

B Calibration Prom (either unit) ............................................................................ 409 

C . KMT 112 Flux Valve ......................................................................................... 409 

10 . Digital Air Data System ..................................................................................... 410 

A KDC 481T Adapter Module .............................................................................. 410 

B . KDC 481T Air Data Computer .......................................................................... 412 

C . KAV 485 AltimeterNSI .................................................................................... 412 

D . Temperature Probe ............................................................................................. 413 

11 . Electronic Flight Instrumentation System (EFIS or EFS) .................................. 413 

A . SG 465 Symbol Generator ................................................................................. 413 

B . ED 4611462 EHSIIEADI ................................................................................ 1 3 

12 . Automatic Flight Control System (AFCS) ......................................................... 414 

A . KCP 520 Flight Control Computer .................................................................... 414 

B . KMS 540 Mode Select Panel ............................................................................. 415 

C . KRG 333 Triaxial Rate And Acceleration Sensor ............................................. 415 

D . KSM 575 Linear Actuator (Lateral Axis) .......................................................... 416 

E . KSM 575 Linear Actuator (Longitudinal Axis) ................................................. 418 

F . KSA 572 Trim Actuator ..................................................................................... 420 

G Pitch Position Resolver ...................................................................................... 420 

H . Roll Position Resolver ....................................................................................... 421 

I . Directional Position Resolver ............................................................................ 421 

J . Collective Position Resolver .............................................................................. 421 

K . Cable Transducer ............................................................................................... 422 

L . Directional Spring Cartridge .............................................................................. 422 

M . T-BAR Trim Switching Relay ............................................................................ 423 

N . LEDEX Trim Switch .......................................................................................... 423 

0 . APISAS Annunciator Panel ................................................................................ 423 

P . Cyclic Trim Switch Assembly ............................................................................ 424 

13 . Weather Radar System ....................................................................................... 424 

A . ART 2000 Transceiver ....................................................................................... 424 

B Flat Plate Antenna .............................................................................................. 425 

C . CM 2000 Configuration Module ........................................................................ 425 

D . IN- 182A Weather Radar Indicator ..................................................................... 425 

E . KMD 5501850 Multi-Function Display .............................................................. 426 

14 . Avionics Cooling Fans ....................................................................................... 426 

A . No . 1 KA 33 Cooling Fan .................................................................................. 426 


CONTENTS 

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BENDIXlKIN6" IFRAVIONICSI KFC 900 


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B . No . 2 KA 33 Cooling Fan ................................................................................. 427 

C . Instrument Panel Forward Cooling Fan ............................................................. 427 

D . Instrument Panel Lower Cooling Fan ................................................................ 427 

E . KCP 520 Cooling Fan ....................................................................................... 428 

15 . Standby Attitude Indicator and Standby Altimeter ............................................ 428 

A . Standby Attitude Indicator ................................................................................ 428 

B . Standby Altimeter .............................................................................................. 428 

16 . Mechanical Gyro System .................................................................................. 429 

A . Attitude Indicator .............................................................................................. 429 

B . KI 525A HSI .................................................................................................... 429 

C . KA 51 B Slaving Accessory ............................................................................... 429 

D . KG 102A Directional Gyro ............................................................................... 430 

E . KMT 112 Flux Valve ........................................................................................ 430 

17 . AC Power System .............................................................................................. 431 

A . SPC-5(B) Inverter ............................................................................................. 431 

18 . Accessories ....................................................................................................... 431 

A . Annunciator Power Supply ................................................................................ 431 

B . Avionics Switch Panel ....................................................................................... 431 

19 . Category A ........................................................................................................ 432 

A . Aural Warning Generator .................................................................................. 432 

B . GH-3000 Standby Indicator .............................................................................. 432 

C . ADC-3000 Air Data Computer .......................................................................... 432 

D . MAG-3000 Magnetometer ................................................................................ 433 

20 . ELT ................................................................................................................... 433 

......................................................................................... 

97-00-00 Avionics - Inspection / Test 601 

1 . General .............................................................................................................. 601 

2 . VHF Navigation and Communications (NAVICOMM).................................... 

601 

A . NAVICOMM Inspection ................................................................................... 601 

B . COMM Operational Test ................................................................................... 601 

C . NAV Operational Test ....................................................................................... 602 

3 . Distance Measuring Equipment (DME) ............................................................ 602 

A . DME Inspection ................................................................................................ 602 

B . DME Operational Test ...................................................................................... 602 

4 . Marker Beacon Receiver ................................................................................... 603 

A . Marker Beacon Inspection ................................................................................. 603 

B . Marker Operational Test ................................................................................... 603 

5 . Automatic Direction Finder (ADF) ................................................................... 603 

A . ADF Inspection ................................................................................................. 603 

B ADF Operational Test ....................................................................................... 603 

C . ADF Quadrantal Error Adjustment ................................................................... 604 

6 . Global Positioning System (GPS) ..................................................................... 605 

A . GPS Inspection .................................................................................................. 605 

B . GPS Operational Test ........................................................................................ 606 

7 . Radar Altimeter System (RALT)....................................................................... 607 

A . RALT Inspection ............................................................................................... 607 

B . KRA 405 Operational Test ................................................................................ 607 

C . KIM 405B Operational Test ............................................................................. 607 

8 . Transponder (XPDR) ........................................................................................ 607 

A . XPDR Inspection ............................................................................................... 607 

B . XPDR Operational Test .................................................................................... 607 

C . XPDR Ramp Test .............................................................................................. 608 


BENDIXIKING" IFRAVIONICSI KFC goo 



Section Title Pane 

D . EEPROM Test ................................................................................................... 608 

9 . Attitude and Heading Reference System (AHRS).............................................. 

609 

A AHRS Inspection ............................................................................................... 609 

B . AHRS Operational Test .................................................................................. 1 0 

C . MSU and CAL PROM Operational Test ........................................................... 610 

10 . Digital Air Data System (DADS).................................................................... 

6 3 

A . DADS Inspection ............................................................................................... 613 

B . DADS Operational Test ..................................................................................... 614 

C . Air Data Computer Operational Test ................................................................. 614 

D . TEMPERATURE PROBE ................................................................................. 615 

11 . Electronic Flight Information System (EFIS)..................................................... 

615 

A . EFIS Inspection .................................................................................................. 615 

B . EFIS Operational Test ........................................................................................ 615 

C . SG 465 Symbol Generator Configuration ...................................................... 6 16 

D . CP 470 Operational Test .................................................................................... 618 

E . EFIS Configuration Procedure ...................................................................... 6 18 

12 . Automatic Flight Control System (AFCS) ......................................................... 621 

A . AFCS Inspection ................................................................................................ 621 

B . AFCS Operational Test ...................................................................................... 622 

C . AFCS Configuration .......................................................................................... 624 

13 . Weather Radar System (WX)............................................................................. 

645 

A . WX Inspection ................................................................................................... 645 

B . WX Operational Test ......................................................................................... 645 

C . CM 2000 CONFIGURATION MODULE PROGRAMMING .......................... 646 

14 . Weather Radar System (WX)............................................................................. 

649 

A . WX Inspection ................................................................................................... 649 

B . WX Operational Test ......................................................................................... 649 

C . CM 2000 CONFIGURATION MODULE PROGRAMMING .......................... 650 

D . MFD Configuration Operational Test ................................................................ 651 

15 . Avionics Cooling Fans ....................................................................................... 659 

A . Inspection ........................................................................................................... 659 

B . Avionics Cooling Fan Operation ........................................................................ 660 

16 . Standby Attitude Gyro ....................................................................................... 660 

A . Inspection ........................................................................................................... 660 

B . Standby Attitude Operation ................................................................................ 660 

17 . Mechanical Gyro System ................................................................................... 661 

A . Inspection ........................................................................................................... 661 

B . Mechanical Gyro System Operation .............................................................. 661 

18 . AC Power System ............................................................................................ 663 

A . Inspection ........................................................................................................... 663 

B . AC Power System Operation ............................................................................. 663 

19 . Avionics Accessories ......................................................................................... 664 

A Inspection ........................................................................................................... 664 

B . Avionics Accessories Operation ........................................................................ 664 

C . Avionics Switch Panel Operation ....................................................................... 665 

20 . Instrument and Console Lighting ....................................................................... 666 

A . Instrument and Console Lighting Operation ...................................................... 666 

2 1 . Aural Warning Generator ................................................................................... 667 

A . Inspection ........................................................................................................... 667 

B . Aural Warning Unit Operation ........................................................................... 667 

22 . Electronic Standby Instrument System (ESIS)................................................... 

668 


_I 

I 

CONTENTS 

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A Ins~ection .......................................................................................................... 668 

B . ESIS Operation .................................................................................................. 668 

23 . Emergency Locator Transmitter (ELT)............................................................. 

674 

........................................................................... 

98-00-00 WIRING . Description and Operation 1 

1 . Effectivity .............................................................................................................. 1 

A . Aircraft S/N 900-00010 thru 900-00051 ............................................................. 1 

B . Aircraft S/N 900-00052 and Subsequent ............................................................... 1 

2 . Chapter Content ..................................................................................................... 1 

3 . Section Content ..................................................................................................... 1 

4 Illustration Layout Convention .............................................................................. 1 

5 . Wiring Diagram Symbology .................................................................................. 2 

................................................................................................ 

.................................................................................................. 

............................................................................................ 

98-10-00 Electrical Equipment List 1 

1 . Equipment List Usage .......................................................................................... 1 

98-40-00 System Wiring Diagrams 1 

Index to Wiring Diagrams 129 

Page viii 

Revision AD 


CONTEWTS 1 s ' 

I



01 -00-00 

Introduction - 

Description and Operation 

1. Description 

The MD Explorer (MD900) is a light twin engine utility helicopter manufactured by MD Helicopters, Inc. 

The basic aircraft is certified for Visual Flight Rules operation only. The incorporation of the IFR avionics 

and KFC 900 Rotorcraft Flight Control System installation (STC No. SR00436WI-D) allows the MD 

Explorer to be operated in the IFR environment. 

2. Aircraft Configuration 

The STC No. SR00436WI-D approves the following three configurations: 

A. Configuration A 

The Configuration A approval is for VFR operations only. All aircraft previously approved under this 

configuration have been upgraded to either Configuration B or Configuration C. 

B. Configuration B 

The Configuration B approval is for Category B Helicopter lnstrument Flight. Configuration B applies 

to the MD900 serial numbers 900-0010 and subsequent. 

C. Configuration C 

The Configuration C approval is for Category A Helicopter Instrument Flight. Configuration C applies 

to the MD900 serial numbers 900-0052 and subsequent. 

Type Design Change 

The incorporation of the IFR avionics and KFC 900 Automatic Flight Control System requires 

modifications to the basic aircraft DC electrical system and the aircraft structure. A majority of the 

required DC electrical system changes have already been incorporated into the basic aircraft DC electrical 

system on MD900 serial numbers 900-0052 and subsequent. Reference Sections 96-00-00 and 97-00-00 

for a complete description of the changes. 

A. Major Components 

Electrical System - The IFR avionics installation incorporates a splitlredundant bussing structure that 

can accommodate IFR operations. Modifications have been made to the Electrical Load Center, the 

External Power Box Assembly and the Essential Bus Circuit Breaker Panel. Existing DC power bus 

wires were replaced and new DC power bus wiring was added. Reference Section 96-00-00 for a 

complete description of the changes. 

Avionics Systems - The avionics systems installed as part of the IFR STC enable the aircraft to be 

operated in the IFR environment. Reference Section 97-00-00 for a complete description of changes. 

Configurations B and C require the installation of the following avionics systems: Dual VHF 

NAVICOMM transceivers, a single DME transceiver, a single marker receiver, a single ABF receiver, 

a radar altimeter, a Two-Tube EFS 40 with EADIIEHSI, a single AHRS attitude and heading reference 


Page I 

@yi~iqn AD

BENBIX/KING" IFR AVIONICS I KFC goo 


system, a GPS long range NAV sensor, a single digital air data system, a standby attitude indicator, a 

standby altimeter and an inverter powering the AC power system. 

The following existing aircraft systems are also part of the IFR avionics package: a single nondiversity 

Mode S transponder or a ATCRBS transponder (Modes A and C), an audio system with ICS 

capability and a dual vertical stabilizer control system (VSCS). 

Configurations B and C require the installation of the KFC 900 Automatic Flight Control System 

(AFCS) that includes the following: flight control computer, mode select panel, rate sensor, linear 

actuators, trim actuator, position resolvers, cable transducers, directional spring cartridge, trim switch 

and annunciator panel. 

The following systems are optional: a second EFS 40 system with a second AHRS or a mechanical 

gyro system for the copilot (AD1 and HSI), a weather radar system, a Multi-Function Display System 

and an emergency locator transmitter (ELT). 

Configuration C requires these additional systems: a standby altimeter, an aural warning tone 

generator (and an electronic standby instrument system for 2-Tube configurations.) 

B. Rotorcraft Flight Manual Supplement(s) 

There are three (3) rotorcraft flight manual supplements for the IFR avionics installation. A 

supplement for the standard Category B IFR operation and limitations, a supplement for the Category 

A IFR operation and limitations (902 configuration only) and a supplement for the KLN 90B GPS 

operations and limitations. 

4. Manual Revisions 

Changes to this manual are incorporated by issuing a complete manual revision. A List of Effective Pages 

(LEP) is not necessary because all pages are at the same revision level. Temporary revisions are not 

used. 

There is no program for the distribution of changes to this manual. It is the responsibility of the 

maintenance facility to use the most current manual when performing aircraft maintenance. The revision 

level of this document may be found in the Technical Publicafions section on the www.bendixking.com 

website. Revisions to this manual can be obtained by calling Honeywell Order Administration (1-800-757- 

8999 USA) or by accessing the BendixIKing website at www.bendixking.com. 

Page 2 

Revision AD 

I EFFECTIVITY: MD9OO 

I



01 -00-00 

Introduction - 

Maintenance Practices 

1. Maintenance and Operational Test Requirements and Precautions 

In addition to the MD Helicopters, Inc. Rotorcraft Maintenance Manual(s) (RMM), all avionics maintenance 

is to comply with the following requirements and precautions. 

This manual is intended to be a supplement to the RMM provided by MD Helicopters, Inc. for the model 

MD900 (MD Explorer). The information provided here is for the items, which have been added by the 

Honeywell lnternational Inc. certification for the IFR avionics. This manual will supersede information from 

MD Helicopters, Inc. only for the specific items addressed. 

2. Operational Tests 

After maintenance, modification, removal, installation, inspection, test or repair; the affected parts, 

assemblies, installations or systems must be examined and an operational test must be performed before 

release of the helicopter for flight. 

3. Cleaning and Lubrication 

There are no cleaning or lubrication requirements associated with this design change. 

4. lnspections 

Inspection requirement procedures are supplied in the appropriate chapter text. lnspections must be 

made in accordance with Chapter 05, Continued Airworthiness. 

lnspections in this manual are visual inspections for cracks, corrosion, distortion, correct installation and 

other obvious defects or damage. 

Replace components that exhibit damage or wear, or that change the correct operation or integrity of an 

assembly. 

5. Maintenance Information Requests 

Address all questions regarding the IFR avionics maintenance to the Honeywell Field Service 

Representative assigned to the geographical area in which the helicopter is operated. If a representative 

is not available, refer all questions to Honeywell lnternational Inc. Product Support, (USA) 913-782-0400 

or by accessing the BendixIKing website at www.bendixking.com. 

When any of the IFR avionics systems exhibit a failure not described in the following sections, it must be 

taken to an Honeywell lnternational Inc. Approved Sales and Service Center for repair. These Approved 

Sales and Service Centers have maintenance manuals, test sets, tools and trained personnel approved by 

Honeywell lnternational Inc. to perform troubleshooting and repair on the equipment on which they are 

rated. Maintenance and troubleshooting information available at ttiese Approved Sales and Service 

Centers is not duplicated in this document. A list of Honeywell lnternational Inc. Approved Sales and 

Service Centers can be obtained from Honeywell lnternational Inc. Product Support, (USA) 913-782-0400 

or by accessing the BendixIKing website www.bendixking.com. 


I 

Page 201 

Revision AD




Page 202 

Revision AD 




04-00-00 

Airworthiness Limitations 

1. Airworthiness Limitations 

No airworthiness limitations associated with this type design change. 


Page 1 

Revision AD




Page 2 

Revision AD 




05-00-00 

Continued Airworthiness Inspections 

1. General 

This section contains scheduled inspections for the KFC 900 AFCS and IFR avionics in the MD900. This 

section is to be added to the approved scheduled inspection for the aircraft. It is assumed that the aircraft 

access panels are open for inspection. 

2. Scheduled lnspection Program Overview 

There are two inspection programs for the KFC 900 AFCS and IFR avionics in the MD900 which align with 

the manufacturer developed airframe inspection programs. They are the Periodic lnspection and 

Segmented lnspection Programs. 

The ownerloperator is responsible for the selection of an inspection program and for its approval by the 

governing aviation authority. 

3. Documentation 

For Category B Helicopter Instrument Flight aircraft, ensure that the Rotorcraft Flight Manual Supplements 

006-00845-0000 (IFR AvionicsIKFC 900) and 006-00845-0001 (KLN 90B) are inserted in the Pilot's 

Operating Handbook and accessible to the pilot during flight. 

For Category A Helicopter Instrument Flight aircraft, ensure that the Rotorcraft Flight Manual Supplements 

006-00845-0004 (Category A IFR AvionicsIKFC 900) and 006-00845-0001 (KLN 90B) are inserted in the 

Pilot's Operating Handbook and accessible to the pilot during flight. 

4. Electrical Bonding 

Electrical bonding is important for the reliable and continued safe use of many components of the IFR and 

AFCS equipment. Several of the following inspections require visual inspection of units for general 

condition and security. These examinations should include checking the unit rack and all brackets for 

security. Loose and chaffing brackets will increase the resistance between parts. Also check for signs 

that the racks or brackets have been removed or otherwise tampered with. If any of these indications are 

present, an electrical bonding test should be performed. An electrical bonding test requires the use of a 

milli-ohm meter to confirm that there is a maximum resistance of 2.5 milli-ohms between the unit rack and 

airframe ground. If a resistance is found to be too high, disassembly of the brackets will be required. 

Check each metal mating surface to be sure it is clear of paint and primer. If necessary, lightly sand the 

mating areas to clean them. Always treat bare aluminum with a corrosion preventative, such as Alodine or 

Iridite, before reassembly. 


05-00-00 

Page 1 

Revision AD

BENDIXIKINNG" IFR AVIONICS I KFC goo 


5. Special Tools 

There are no special tools required to perform the normal inspection on the IFRIAFCS equipment or 

installation. Special tools may be required to perform some maintenance on components of the system 

on an as-required basis. These tools are as follows: 

TOOL: Biddell Milliohm Meter 

REASON: Electrical bonding checks 

TOOL: Laptop Computer wl RS232 connection 

REASON: For AFCS Installation Setup procedures. Example, replacing a failed position resolver will 

require running the setup procedure. 

Page 2 

Revision AD 05-00-00 




05-20-00 

Continued Airworthiness Scheduled lnspection 

General 

This section contains requirements for scheduled inspection. This section is to be added to the approved 

scheduled inspection for the aircraft. It is assumed that the aircraft access panels are open for inspection. 

Scheduled Inspections 

This section contains requirements for scheduled inspection 

A. Airframe Periodic lnspection Program 

The Airframe Periodic lnspection Program must be completed within twelve (12) calendar months of 

the last Airframe Periodic lnspection or initial certification of the helicopter. 

This inspection can be used when aviation authority regulations require periodic inspections such as 

an annual or 100 hour inspection. 

B. Airframe Segmented lnspection Program 

The Airframe Segmented lnspection Program may be used in place of the Airframe Periodic 

lnspection Program. If the Airframe Segmented lnspection Program is used, it must be used in its 

entirety. 

Routine lnspection -A Routine lnspection is to be performed at one hundred (100) hour intervals. 

Performance Schedule - The Airframe Segmented lnspection Program is implemented on a twentyfour 

month completion cycle. 

Month 2 - inspection 7 is to be completed. 

















I 

Page 1 

, Revision AD



3. Definitions 

This section defines the inspection criteria listed in the periodic and segmented inspection programs. 

General Condition - This term refers to the overall appearance of the item(s) under consideration. 

lnspect for chafing, rubbing, interference to surrounding structure, corrosion, wear, etc. Make any 

necessary repairs. 

Security - This term refers to installed equipment, wiring harnesses, hoses and tubes. lnspect for 

loose attaching and/or mounting hardware, Adel clamps, broken Ty-raps, etc. Make any necessary 

repairs. 

Electrical Bonding - This term refers to the electrical bonding of equipment, mounting trays or racks, 

shelves and other structure that supports the avionics equipment. lnspect for loose attaching 

hardware or mounting hardware and evidence of corrosion or deterioration of hardware, sheet metal 

etc. Refer to section 05-00-00 for electrical bonding testing methods. Make any necessary repairs. 

Page 2 

, Revision AD 


I



05-20-20 

Airframe Periodic Inspection 

Model 

900 

900 

General 

Ensure all placards and markings are installed 

Review and correct operational squawks on aircraft 

related to the IFR and AutopilotISAS systems 

RMMS Section 

1 1-00-00 

Initial 

Model 

900 

900 

Electrical Bus 

Ensure that it is safe to put electrical power on aircraft 

Perform the following procedure to test the power 

rectifiers in the Essential Circuit Breaker Panel: 

I. Apply ground power to the aircraft. 

2. Place the power switch in the "BATIEXT" position. 

3. Verify that the right and left essential busses are 

powered. Verify the right and left DC busses are 

powered. 

4. Pull the 40 amp "RH BUS FDR and "LH BUS FDR" 

circuit breakers located in the Electrical Load Center. 

5. Verify that the right and left DC busses have no 

power. 

On ships sln 900-000 10 thru 900-0005 1, the 

transponder, GPS, avionics annunciators, No. 2 

NAVICOMM, L VSCS, and the instrument flood 

lights should not be operational. 

On ships sln 900-00052 and subsequent, the 

transponder, bleed air heat, avionics annunciators, 

No. 2 NAVICOMM, L VSCS, and the instrument 

flood lights should not be operational. 

6. Verify that the right and left essential busses are still 

powered. 

7. If either one or both of the DC busses have power, 

replace the appropriate rectifier per the procedures 

outlined in section 96-30-00 DC Power Systems 

RemovalIInstallation. 

8. Otherwise, reset the 40 amp "RH BUS FDR" and "LH 

BUS FDR" circuit breakers located in the Electrical 

Load Center. Place the power switch in the "OFF" 

position and remove ground power from the aircraft 

RMMS Section 

N/A 

96-30-00 

Initial 


I

BENDX/KINGG" IFR AVIONICS I KFC goo 


AIRFRAME PERIODIC INSPECTION (CONT'D) 

Model 

900 

900 

900 

900 

900 

Air Data System 

Visually inspect pitotlstatic lines for general condition and 

security 

Visually inspect the KDC 48 1 T for general condition, 

security and evidence of poor electrical bonding 

Visually inspect the KAV 485 for general condition, 


Visually inspect the temperature probe for general 

condition and security. 

Test the pitotlstatic system and transponder per FAR 

91.41 1 and FAR 91.413. 

RMMS Section 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

Initial 

Model I CNI & Miscellaneous Cockpit Instruments I RMMS Section I Initial 

J;**J;* DO NOT USE MAGNETIZED TOOLS NEAR THE 

ED 4611462 DISPLAY UNITS 

900 Remove glare shield and top panel, and visually inspect: 

glare shield and top panel for general condition and 

apparent defects 

e KLN 90B GPS unit and cooling hose for general 

condition and security 

annunciators1switches for general condition and 

security 

cooling fans for general condition and security 

e electrical wiring installation for proper installation 

and security 

900 Visually inspect the KI 206 CDI for proper markings, 

general condition and security of instrument mounting: 

900 Visually inspect the KMD 540 MFD (if installed) for 


900 Visually inspect electrical wiring installation within 

console for chafing and security 

900 Visually inspect installation of the following console 

installed equipment for proper markings, general 

condition, and security: 

0 KX 165lA NAVICOMM (2 units) 

KR 87 ADF receiver 

KT 70171 transponder 

Avionics switch panel 

Master switch panel 

Circuit breaker panel 

Side circuit breaker panel (if installed) 

Generator field RCCB - 

*****J~**J; 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

96-30-00 

96-30-00 

96-30-00 

96-30-00 

Page 2 

Revision AD




Model I Autopilot/SAS I RMMS Section I Initial 

FOLLOW THE MD HELICOPTERS RECOMMENDED 

1 ***** PROCEDURE FOR OPERATING THE FLIGHT ********* 

I 

CONTROLS USING A HYDRAULIC MULE 

1 Linear Actuators (KSM 575) I 

Visually inspect for apparent defects, evidence of 

failure or interference, and general condition and 

security 

With hydraulic pressure on, visually inspect for 

clearance through the operating range of both the 

longitudinal and lateral KSM 575 linear actuators 

Visually inspect the harnesses for general condition 

and security 

Visually inspect the roof structure surrounding the 

KSM 575 actuators for security 

Trim 

Visually inspect the trim actuator (KSA 572) for 

general condition and security 

Visually inspect the cable transducers for proper 

installation, general condition and security 

Visually inspect the yaw spring cartridge (KSC 573) 

for evidence of failure or. interference, and general 


* Visually inspect the manual trim1FS sync switch for 


900 

900 

900 

900 

900 

900 

900 

900 

Visually inspect the trim switchlrelay (T-Bar or 

~edex)-for proper installation and condition. 

Check force required to move directional pedals per the 97-00-00 

manufacturer's specifications with the fdlowing 

exception: Maximum force should be 5 lbs +/- 2 

Visually inspect position resolvers (4 places) for proper 97-00-00 

installation,~eneral condition, and security 

Visually inspect the Flight Control Computer (KCP 520) 97-00-00 

and harness for general condition, security and evidence 

of poor electrical bonding 

Visually inspect the pitch sync and go-around switches 97-00-00 

(collective head) for general condition and security. 

Visually inspect the AP Annunciator Panel for general 97-00-00 


Visually inspect the KMS 540 Mode Select Panel for 97-00-00 

general condition and security. 

Visually inspect the AFCS disconnect switch (cyclic) for 97-00-00 


Visually inspect the Rate Gyros (KRG 333) and harness 97-00-00 

for general condition, security and evidence of poor 

electrical bonding 

. 


Page 3 

, Rexjsion AD

BENDIX/KINGG" IFRAVIONICSI KFC 900 



Model 

900 

900 

900 

900 

900 

ATTIHDG System 

Visually inspect the AHRS (LCR 92S), cal prom, 

mounting tray, fan and harness for general condition, 


Visually inspect the Flux Valve(s) (KMT 1 12) and 

harness for general condition and security 

Visually inspect the KI 525A HSI, KA 5 1 B Slaving Unit, 

KG 102 Directional Gyro and harness, if installed, for 

general condition, security, and evidence of poor 


Visually inspect the attitude gyro (AI-360) and IVSI for 


Visually inspect the standby attitude gyro and standby 

altimeter (if installed) for general condition and security. 

RMMS Section 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

Initial 

Model 

900 

EFIS 

Visually inspect the Symbol Generator(s) (SG 465) and 

harness for general condition, security and evidence of 

poor electrical bonding. 

RMMS Section 

97-00-00 

*J;J;** DO NOT USE MAGNETIZED TOOLS NEAR THE ********* 

900 

900 


Visually inspect the Display Units (ED 461 and ED 462) 


of poor electrical bonding. 

Visually inspect the EFIS control panel (CP 470) for 

general condition, security and evidence of poor electrical 

bonding. 

97-00-00 

97-00-00 

Initial 

Model 

900 

Antennas 

Visually inspect the following antennas for general 

condition and security: 

CI- 120 VORILOCIGS antenna and CI- 1 125 

quadraplexer 

CI-29 1 VHF COMM antenna 

CI-105-6 DME antenna 

CI-118-9 (or KA 26) marker beacon antenna 

KA 44B ADF antenna 

KA 92 GPS antenna 

KA 54A radar altimeter antennas 

RMMS Section 

97-00-00 

Initial 

Page 4 

Revision AQ 


I

BENDIXIKINNG" IFRAVIONICS I KFC 900 



Model 

900 

900 

900 

900 

900 

Category A (If Installed) 

Visually inspect the GH-3000 standby indicator and 

DCM-3000 config module for general condition and 

security of instrument mounting 

Visually inspect the ADC-3000 air data computer 

pitotlstatic lines for general condition and security 

Visually inspect the ADC-3000 air data computer and 


poor electrical bonding 

Visually inspect the MAG-3000 magnetometer and 


Visually inspect aural warning generator (Model 630) and 



RMMS Section 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

Initial 

Model 

900 

900 

900 

ELT (If Installed) 

Visually inspect the ELT and mounting brackets for 


Visually inspect the ELT coax and antenna for general 


Test per FAR 9 1.207 (d) 

RMMS Section 

97-00-00 

97-00-00 

Initial 

Model 

900 

900 

900 

900 

900 

Weather Radar (If Installed) 

Visually inspect the radome for defects and general 

condition 

Visually inspect the lightning diverter strips on the 

radome for defects, general condition, and evidence of 

poor electrical bonding (NOTE: The diverter strips should 

not have continuity along the thin portion in front of the 

radar, however, they should have good electrical bonding 

at the aft attach point to airframe ground) 

Visually inspect the Receiver Transmitter (RT2000), the 

config module (CM 2000) and harness for general 

condition, security, and evidence of poor electrical 

bonding 

Visually inspect the radar antenna (AA20 12V) for 

evidence of interference and for proper installation 

Visually inspect the Radar Display (IN 182) or MFD 

(KMD 850) and harness for general condition and security 

RMMS Section 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

Initial 


I 

Page 5 

Revision AD




Model 

900 

Miscellaneous Avionics Equipment 

Visually inspect the following equipment for general 

condition, security of unit mounting and evidence of poor 

electrical bonding: 

KN63 DME 

SPC-5B power inverter 

Avionics cooling fans 

KMR 675 marker beacon receiver 

KN 40 NAV converter 

KA 172 annunciator power supply 

KRA 4051405B radar altimeter 

RMMS Section 

97-00-00 

Initial 

Page 6 

Revision AD 

05-20-20 


BENDIX/KINGG" IFR AVIONICS I KFC goo 


05-20-50 

Airframe Segmented lnspection Program 

Routine 

Model 

900 

900 

General 

Ensure all placards and markings are installed 

Review and correct operational squawks on aircraft 

related to the IFR and AutopilotISAS systems 

RMMS Section 

1 1-00-00 

Initial 

lnspection 1 - Nose Section and Cockpit (Area 1) 

Model 

900 

900 

Electrical Bus 

Ensure that it is safe to put electrical power on aircraft 

Perform the following procedure to test the power 

rectifiers in the Essential Circuit Breaker Panel: 

9. Apply ground power to the aircraft. 

10. Place the power switch in the "BATIEXT" position. 

1 1. Verify that the right and left essential busses are 

powered. Verify the right and left DC busses are 

powered. 

12. Pull the 40 amp "RH BUS FDR" and "LH BUS FDR" 

circuit breakers located in the Electrical Load Center. 

13. Verify that the right and left DC busses have no 

power. The transponder, GPS (sln 900-0001 0 thru 

900-0005 1 only), bleed air heat (sln 900-00052 and 

subsequent only), avionics annunciators, No. 2 

NAVICOMM, L VSCS and the instrument flood 

lights should not be operational. 

14. Verify that the right and left essential busses are still 

powered. 

15. If either one or both of the DC busses have power, 

replace the appropriate rectifier per the procedures 

outlined in section 96-30-00 DC Power Systems 

Removal/Installation. 

16. Otherwise, reset the 40 amp "RH BUS FDR" and "LH 

BUS FDR" circuit breakers located in the Electrical 

Load Center. Place the power switch in the "OFF" 

position and remove ground power from the aircraft 

RMMS Section 

NIA 

96-30-00 

Initial 

Model 

900 

Antennas 

Visually inspect the following antennas for defects and 

general condition: 

CI-105-6 DME antenna 

CI-118-9 (or KA 26) marker beacon antenna 

KA 44B ADF antenna 

KA 54A radar altimeter antennas 

RMMS Section 

97-00-00 

Initial 


05-20-50 

Page 1 

Revision AD

BENDIXIKING" IFRAVIONICSI KFC 900 


Inspection 1 - Nose Section and Cockpit (Area I ) (cont'd) 

Model 

900 

900 

900 

900 

900 

Air Data System 

Visually inspect pitotlstatic lines for general condition and 

security 

Visually inspect the KDC 48 1 T for general condition, 


Visually inspect the KAV 485 for general condition, 


Visually inspect the temperature probe for general 


Test the pitotlstatic system and transponder per FAR 

91.411 andFAR91.413. 

RMMS Section 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

Initial 

Model I CNI & Miscellaneous Cockpit Instruments I RMMS Section I Initial 

***** DO NOT USE MAGNETIZED TOOLS NEAR THE **~;***ik** 

900 

900 

900 

900 

900 


Remove glare shield and top panel, and visually inspect: 

glare shield and top panel for general condition and 

apparent defects 

KLN 90B GPS unit and cooling hose for general 


annunciators1switches for general condition and 

security 

cooling fans for general condition and security 

electrical wiring installation for proper installation 

and security 

Visually inspect the KI 206 CDI for proper markings, 


Visually inspect the KMD 540 MFD (if installed) for 


Visually inspect electrical wiring installation within 

console for chafing and security 

Visually inspect installation of the following console 

installed equipment for proper markings, general 

condition, and security: 

KX 165lA NAVICOMM (2 units) 

KR 87 ADF receiver 

KT 7017 1 transponder 

Avionics switch panel 

Master switch panel 

Circuit breaker panel 

Side circuit breaker panel (if installed) 

Generator field RCCB 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

96-30-00 

96-30-00 

96-30-00 

96-30-00 

Page 2 

Revision AD

BENDIX/KlNNG" IFR AVIONICS I KFC goo 


Inspection 1 - Nose Section and Cockpit (Area I) (cont'd) 

Model 

900 

900 

900 

900 

900 

900 

900 

900 

AutopilotISAS 

Trim 

Visually inspect the trim actuator (KSA 572) for 


Visually inspect the cable transducers for proper 

installation, general condition and security 

Visually inspect the yaw spring cartridge (KSC 573) 

for evidence of failure or interference, and general 


Visually inspect the manual trim1FS sync switch for 


Visually inspect the trim switchlrelay (T-Bar or 

Ledex) for proper installation and condition. 

Check force required to move directional pedals per the 

manufacturer's specifications with the following 

exception: Maximum force should be 5 lbs +I- 2 

Visually inspect position resolvers (4 places) for proper 

installation, general condition, and security 

Visually inspect the Flight Control Computer (KCP 520) 



Visually inspect the pitch sync and go-around switches 

(collective head) for general condition and security. 

Visually inspect the AP Annunciator Panel for general 


Visually inspect the AFCS disconnect switch (cyclic) for 


Visually inspect the KMS 540 Mode Select Panel for 


RMMS Section 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

Initial 

Model 

900 

900 

900 

900 

ATTIHDG System 

Visually inspect the AHRS (LCR 92S), cal prom, 

mounting tray, fan and harness for general condition, 


Visually inspect the KI 525A HSI, KA 5 1B Slaving Unit, 

KG 102 Directional Gyro and harness, if installed, for 

general condition, security, and evidence of poor 


Visually inspect the attitude gyro (AI-360) and IVSI for 


Visually inspect the standby attitude gyro and standby 

altimeter (if installed) for general condition and security. 

RMMS Section 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

Initial - 

I EFFECTNIN: MD900 

I 

Page 3 

Revision AD

BEAIDXIKING@ IFR AVIONICS I KFC 900 


Inspection 1 - Nose Section and Cockpit (Area I ) (cont'd) 

Model 

900 

900 

900 

900 


Visually inspect the GH-3000 standby indicator and 

DCM-3000 config module for general condition and 

security of instrument mounting 

Visually inspect the ADC-3000 air data computer 

pitotlstatic lines for general condition and security 

Visually inspect the ADC-3000 air data computer and 



Visually inspect aural warning generator (Model 630) and 



RMMS Section 

97-00-00 

97-00-00 . 

97-00-00 

97-00-00 

Initial 

Model 

900 

900 

900 

900 

900 

Weather Radar (If Installed) 

Visually inspect the radome for defects and general 

condition 

Visually inspect the lightning diverter strips on the 

radome for defects, general condition, and evidence of 

poor electrical bonding (NOTE: The diverter strips should 

not have continuity along the thin portion in front of the 

radar, however, they should have good electrical bonding 

at the aft attach point to airframe ground) 

Visually inspect the Receiver Transmitter (RT2000), the 

config module (CM 2000) and harness for general 

condition, security, and evidence of poor electrical 

bonding 

Visually inspect the radar antenna (AA2012V) for 

evidence of interference and for proper installation 

Visually inspect the Radar Display (IN 182) or MFD 

(KMD 850) and harness for general condition and security 

RMMS Section 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

97-00-00 

Initial 

Model 

900 

Miscellaneous Avionics Equipment 

Visually inspect the following equipment for general 

condition, security of unit mounting and evidence of poor 

electrical bonding: 

KN63 DME 

SPC-5B power inverter 

Avionics cooling fans 

KMR 675 marker beacon receiver 

KN 40 NAV converter 

KA 172 annunciator power supply 

KRA 4051405B radar altimeter 

CI-1125 quadraplexer 

RMMS Section 

97-00-00 

Initial 

Page 4 

Revision AD



lnspection 1 - Nose Section and Cockpit (Area I) (cont'd) 

Model I EFIS I RMMS Section I Initial 

**J;** DO NOT USE MAGNETIZED TOOLS NEAR THE 


900 Visually inspect the Display Units (ED 461 and ED 462) 



900 Visually inspect the EFIS control panel (CP 470) for 

condition, security and evidence of poor electrical bonding. 

********a 

97-00-00 

97-00-00 

lnspection 2 - Cabin (Area 2) 

Model ( AutopilotISAS I RMMS Section I Initial 

FOLLOW THE MD HELICOPTERS RECOMMENDED 

***** PROCEDURE FOR OPERATING THE FLIGHT ********* 

900 

900 

CONTROLS USING A HYDRAULIC MULE 

Linear Actuators (KSM 575) 

Visually inspect for apparent defects, evidence of 

failure or interference, and general condition and 

security 

With hydraulic pressure on, visually inspect for 

clearance through the operating range of both the 

longitudinal and lateral KSM 575 linear actuators 

e Visually inspect the harnesses for general condition 

and security 

Visually inspect the roof structure surrounding the 

KSM 575 actuators for security 

Visually inspect the Rate Gyros (KRG 333) and harness 

for general condition, security and evidence of poor 


97-00-00 

97-00-00 

lnspection 3 - Main Rotor and Upper Transmission Deck (Area 3 and 4) 

There are no additional inspection requirements for this area associated with the installation of the 

KFC 900 AFCS and IFR avionics. 

lnspection 4 - Landing Gear 

There are no additional inspection requirements for this area associated with the installation of the 

KFC 900 AFCS and IFR avionics. 

EFFECTIVITY: WID900 

.05-20-50 , 

Page 5 

, Revision AD



lnspection 5 - Powerplant (Area 5) 

Model 

900 

900 

900 

ELT (If Installed) 

Visually inspect the ELT and mounting brackets for 


Visually inspect the ELT coax and antenna for general 


Test per FAR 91.207 (d) 

RMMS Section 

97-00-00 

97-00-00 

Initial 

lnspection 6 - Baggage Compartment (Area 6) 

Model 

900 

ATT/HDG System 

Visually inspect the Flux Valve(s) (KMT 1 12) and 


RMMS Section 

97-00-00 

Initial 

Model 

900 

EPIS 

Visually inspect the Symbol Generator(s) (SG 465) and 



RMMS Section 

97-00-00 

Initial 

Model 

900 


Visually inspect the MAG-3000 magnetometer and 


RMMS Section 

97-00-00 

Initial 

lnspection 7 - Tail (Area 7) 

Model 

900 

Antennas 

Visually inspect the following antennas mounted on the 

tail for general condition and security: 

CI-120 VOR/LOC/GS antenna 

CI-291 VHF COMM antenna 

KA 92 GPS antenna 

RMMS Section 

97-00-00 

Initial 

Page 6 

Revisiori AD 

05-20-50 


BENDIXIIKING" IFRAVIONICSI KFC goo 


1 1-00-00 

Placards and Markings 

I. General 

Placards and markings for the KFC 900 and IFR Avionics (Categories A and B IFR) for the MD900 

helicopter are shown in Figures 201 and 202. Note that Figure 201 is representative of all instrument 

panel configurations, 2-Tube and 4-Tube. 

2. Decals and Placard 

A. Decal and Placard Application 

Solvent, Cleaning - Methyl Ethyl Ketone (MEK) 

CONSUMABLE MATERIALS 

All decals and placards are self-adhesive type. The placards shown in Figure 201 are part of the MD900 

IFR Placard Sheet, Honeywell part number 057-05805-0001. 

Solvent. Cleanina (MEK) 

1) Apply decals by wiping the surface area with cleaning solvent (MEK) where decal is to be applied. 

Separate backing from decal and apply decal to cleaned wiped surface area, roll out all wrinkles. 

2) Where a decal overlaps or covers drain holes, access doors, etc., the decal must be cut out to 

provide proper draining or ease of opening or removing of doors, plates, etc. 


I 

Page 1 

Revision AD

BENDIXlKIN6" IFR AVIONICS I KFC goo 


3 

NOTE 1 

Figure 201 : Placard Placement 

r- 5 

0 AP/SAS 0 

* MAY BE REDUCED BELOW 

11.000 FT DA AND BELOW -3C. 

REFER TO BASIC AIRCRAFT 

AIRSPEED LIMITATIONS. 

** SAME AS BASIC AIRCRAFT 

AIRSPEED LIMITATIONS 

', 

2. KFC 900 VNE CARD 

3. CO 

Figure 202: Cockpit Placards 

NOTE 1: The "PITCH SYNC" placard is required for both collective heads with all of the 4-Tube Configuration 

installations. Only Pilot's side collective is required to be marked for 2-Tube Configurations. 

Page 2 



1. Electrical System 



A. Aircraft SIN 900-0001 0 thru 900-00051 

96-00-00 

Electrical Power - 


The basic aircraft electrical system has been modified for operation in the IFR environment. The 

External Power Box Assembly, the Essential Bus Circuit Breaker Panel and the Electrical Load Center 

are modified to add additional bussing capabilities. 

The electrical system has been redesigned to provide electrical power to all of the aircraft systems for 

airborne and ground operation. 

A 115126VAC 400Hz inverter is installed to power specific avionics systems required for IFR 

operation. 

Reference Figure 1 and Figure 2 for schematics of the modified electrical system 

B. Aircraft SIN 900-00052 and Subsequent 

(including MD Helicopters Technical Bulletin TB900-018R1) 

The basic aircraft electrical system has been modified for operation in the IFR environment. The 

Essential Bus Circuit Breaker Panel and the Electrical Load Center are modified to add additional 

bussing capabilities. 

The electrical system has been redesigned to provide electrical power to all of the aircraft systems for 

airborne and ground operation. 

A 115126VAC 400Hz inverter is installed to power specific avionics systems required for IFR 

operation. The 11 5VAC 400Hz output is not utilized as part of the installation. 

Reference Figure 3 and Figure 4 for schematics of the modified electrical system. 


I 

Page 1 

Revision AD

BENDIXIKING" IFR AVIONICS I KFC 900 


Figure 1 : Electrical System Schematic 

(SIN 900-00010 thru 900-00051 only) 

Page 2 

Revision AD 


I



Figure 2: Electrical System Schematic (Continued) 

(SIN 900-00010 thru 900-00051 only) 


Page 3 

Revision AD

BENDIXIKING" IFR AVIONICS 1 KFC goo 


Figure 3: Electrical System Schematic 

(SIN 900-00052 and subsequent) 

Page 4 

Revision AD 


I



i i 1 i i i ;I,[ i 

urn 0 LL 0 

5 z 

40 $ 4 

Figure 4: Electrical System Schematic (Continued) 

(SIN 900-00052 and Subsequent) 


96-00-00 

Page 5 

Revision AD

BENDIX/KINGG% IFR AVIONICS 1 KFC goo 


C. External Power Box Assembly (SIN 900-00010 thru 900-00051 only) 

The modification of the External Power Box Assembly was predicated on the box being at the 

900E2750610-113 revision level. 

The modifications included relocation of rectifier CR4, removal of the two 25 amp circuit breakers and 

installation of two 50 amp circuit breakers and one 7.5 amp circuit breaker. 

Reference Figure 1 for the External Power Box Assembly schematics. 

Aircraft SIN 900-00052 and subsequent require no modifications to the External Power Box Assembly. 

D. Essential Bus Circuit Breaker Panel 

The existing Essential Bus Circuit Breaker Panel is removed from the aircraft and replaced with a new 

panel. The new panel has an additional row of circuit breakers. The panel is re-arranged into a Left 

and Right Essential bussing structure for the essential circuit breakers. For aircraft sln 900-00052 

and subsequent, a Left Essential Bus side circuit breaker panel is added to the side of the console. 

The additional IFR avionics circuit breakers are incorporated into the new panel. 

The new panel incorporates Left and Right DC Busses that are powered from the Left and Right 

generator Busses, respectively. Reference Figure 5 and Figure 6 for the new Essential Bus Circuit 

Breaker Panel. 

ESS GCU XMSN ENG FUEL PlTOT 

FlRE FlRE R VLV R HEAT R 

VSCS AP/SAS INSTR 

R TRIM AUDIO ALERT LTG 11 

11 EADl AHRS 1 NAV LDG AIR 

R PRIMARY COM 1 LT DATA CFU 

BUS L L FlRE L VLV L XFD VLV PROBE 

11 BLD AIR STBY EHSI -AP/SAS 

LEAK ATT R CMPTR DISC ACCEL~ II 

r--L DC B U S 1 -R DC B U S 1 

NAV VSCS INSTR XPNDR 

COM 2 L FLOOD ANNUN 1 GPS 

Figure 5: Essential Bus Circuit Breaker Panel 

(SIN 900-00010 thru 900-00051 only) 

Page 6 

Revision AD 


I

BENDIXIKINNG" IFRAVIONICSI KFC goo 


ESS GCU ENG XMSN FUEL PlTOT 

BUS R R FlRE R FlRE VLV R HEAT R 

VSCS WARN INSTR 

llDS R TRIM AUDIO AUDIO LTG 

11 EADI AHRS1 NAV LOG AIR 

R PRIMARY COM 1 LT DATA CFU 

L ESS BUS 

ESS GCU ENG FUEL FUEL PlTOT 

BUS L FIRE L PROBE VLV L HEAT L 

r L ESS BUS i 

GPS 

CMPST 

DlSP 

BLDAIR STBY EHSl 1-AP/SAS-d 11 

LEAK ATT R 'CMPTR DISC ACCEL' 

INVTR 

MODE 

SELECT 

-L DC B U S 1 -R DC B U S 1 

NAV VSCS INSTR XPNDR BLD AIR 

COM 2 L FLOOD ANNUN 1 HEAT 

FLT 

DIR 

FD 

SYNC 

Figure 6: Essential Bus Circuit Breaker Panel 

(SIN 900-00052 and subsequent) 

E. Electrical Load Center 

The Electrical Load Center Modifications include the following: Installation of connector 1 J300 and 

2J300, installation of two 40 amp circuit breakers feeding the Essential Bus Circuit Breaker Panel DC 

Busses, redistribution and/or removal of existing circuit breakers, installation of the IFR avionics circuit 

breakers and wiring, and replacing the existing generator field circuit breakers with remote control 

circuit breakers (RCCB's). 

The generator field RCCB's are controlled via two 112 amp circuit breakers located in the console near 

the key. 

Reference Figure 7 and Figure 8 for the Electrical Load Center circuit breaker layouts. The figures 

may not reflect the installation of all options associated with the IFR Avionics package. 

Page 7 

. Revision AD

BENDXIKINNG" IFR AVIONICS 1 KFC goo 


LEFT GENERATOR BUS 

I 

I 

BATTERY BUS I 

AUDIO CRGO CKPT 

PNL2 HOOK UTlL 

CAB 

UTlL 

I L R I I L R , FUEL 

BST PMP EEC LOW 

EVAP VENT COMP 

EVAP 

0 0 0 @ 

HVR 

LGT 

PITOT 

HEAT2 

CNDSR 

FAN2 

I L R I OFF L R 

DETENT GATE IGNTR 

, CNSL POSN STROBE AREA I 

LIGHTING 

r 

EADl L EHSl L AHRS 1 

AUX 

RIGHT GENERATOR BUS 

llDS TRAK HYDRL AV FAN 

STB 

TEST 

LH DC AHRS 2 RTR FIRE 

BUS FDR BRK HRD 

@ IPS 

0 0 0 @ 

LAND 

LGT 

9 

BUS FDR 

"?LAP 

RIGHT AVIONICS BUS 

RDR RDR MKR RAD 

R/T IND BCN ALT 

ADF 1 FM FM 1 

CTRL 

RT 

0 0 0 0 0 DME 0 0 0 0 

0 0 0 0 0 0 0 0 0 0 

Figure 7: Electrical Load Center Circuit Breaker Panel 

(SIN 900-00010 thru 900-00051 only) 

Page 8 

, . Revision AD 




LEFT GENERATOR BUS 

- 

BATTERY BUS 

AUDIO CRGO CKPT CAB 

PNL2 HOOK UTlL UTlL 

I L R , L R I FUEL 

BST PMP EEC LOW 

EVAP VENT COMP PITOT 

NAP 

HEAT2 

L R I OFF L R 

DETENT GATE IGNTR 

0 0 0 0 @ CNSL 0 POSN @ STROBE @ AREA , @ 

LIGHTING 

All CPLT CNDSR 

GYRO 2 CLOCK FAN2 

0 0 0AHRS 2 FIRE 0SMOKE 

EADl L EHSl L AHRS 1 LH DC 

AUX 

BUS FOR 

RIGHT GENERATOR BUS 

1 :# 

0 0 0 0 @ 

HOIST HOIST ATT PILOT CNDSR 

CUT PWR GYRO 2 CLOCK FAN1 

AHRS 2 ELI BLD AIR RH DC 

AUX HEAT BUS FOR 

PRI HAD DET 

ENC 

SRCH 

ALT LGT LGT FUEL 

CAKGO 

I%%! N2# HOOK 

0 0 0 L FLD 

R FLD 0 0 

00000000c!)~ 

SAS/AP REF 

LEFT AVIONICS BUS 

ADF 2 RADAR MFD MKR RAD 

RT BCN ALT 

EXClT 

EXClT 

I 2 2 

RIGHT AVIONICS BUS 

VAC BUS 3 

0 @ @ @ ADF 1 @ FM FM 01 FM 20 FM 3 0 0 

CTRL RT RT RT 

0PA COM 03 XPNDR 0 DIR 0 NAV 3 0 DME 0STORM 0CAMERA 0NAV 1 0 RMI 

PWR 2 GYRO 2 

SCOPE 

0 0 0 0 0 0 0 0 0 0 

MVG 

MAP 

Figure 8: Electrical Load Center Circuit Breaker Panel 



Page 9 

Revision AD



2. Battery Power Subsystem 

The battery power subsystem remains unchanged. 

3. External Power Subsystem 

The external power subsystem remains unchanged. 

4. DC Power Generation Subsystem 

The DC power generation system has been modified to incorporate a 10 amp Remote Control Circuit 

Breaker (RCCB) in place of each 10 amp generator field circuit breaker. Each of the RCCB's have a onehalf 

amp control breaker located in the pedestal near the key switch. Reference Figure 2 (aircraft SIN 

900-00010through 900-000051) or Figure 4 (aircraft SIN 900-00520 and Subsequent) for schematics of 

the generator field RCCB's. 

5. DC Power Distribution System 

The DC power Distribution system has been modified to incorporate a Left and Right bus structure in the 

Essential Bus Circuit Breaker Panel. 

A Left DC Bus and a Right DC Bus have been added to the Essential Bus Circuit Breaker Panel. The 

busses are supplied via the respective generator bus through 40 amp circuit breakers located in the 

Electrical Load Center. Each DC bus provides power to the Left and Right Essential busses through 

power rectifiers. The rectifiers isolate the DC busses and generator from the essential busses in the event 

of any malfunctions. 

The Essential Bus Circuit Breaker Panel is still powered by the battery via the essential bus relay in the 

External Power Box Assembly. However, two 50 amp circuit breakers replace the 25 amp circuit breakers 

that supply the Essential Bus Circuit Breaker Panel. The wire gauge for the essential bus feeders is also 

changed to 10 gauge. 

For aircraft SIN 900-00010 through 900-00051 only, a 7.5 amp circuit breaker provides power to the Aux 

Left Essential Bus in the Electrical Load Center. The circuit breaker is supplied from the load side of the 

50 amp Left Essential Bus feeder circuit breaker in the External Power Box Assembly. 

The DC Power Distribution consists of the following busses. 

Battery Bus 

Right Essential Bus 

Left Essential Bus 

Aux Left Essential Bus (SIN 900-00010 thru 900-00051 only) 

Right DC Bus 

Left DC Bus 

Right Generator Bus 

Left Generator Bus 

Right Avionics Bus 

Left Avionics Bus 

Lighting Bus 

Figure 9 and Figure 10 depict a simplified schematic of the power distribution system and the circuit 

breakers on each bus. Note, only the circuit breakers installed or relocated as part of the IFR avionics 

installation are addressed. 

Page 10 

Revision AD 



AP/SAS 

REFERENCE 

LT PWR RLY 

RT START RLY 

RT PWR RLY 

RT GEN BUS 

AVIONICS FANS 

#2 AHRS AUX PWR 

E LT 

LEFT EADl 

LEFT EHSl 

#1 AHRS AUX PWR --- RT AVIONICS RLY 

BATTERY BUS 

ADF 1 

DME 

MARKER BEACON 

RT ESS BUS 

RT DC BUS 

INSTRUMENT FLOOD LGTS 

LH ESS FDR 

LEFT GCU 

LEFT ENGINE FlRE 

LEFT FUEL SHUTOFF VALVE 

FUEL TRANSFER VALVE 

FUEL PROBE 

BLEED AIR LEAK 

STBY ATTITUDE INDICATOR 

AP/SAS 

RlGHT EHSl 

COMPUTER 

& 

AUX LT ESS BUS 

FD SYNC 

FLT DIR 

MODE SEL 

INVERTER 

TRIM 

AUDIO PANEL 

AP/SAS ALERT 

INSTRUMENT LIGHTING 

RlGHT EADl 

#1 AHRS PRIMARY PWR 

RT FUEL SHUTOFF VLV 

RlGHT PlTOT HEAT 

COMM/NAV 1 

LANDING LIGHT 

KAD 480 AIR DATA 

CFU 

llDS 

RlGHT VSCS 

RlGHT GCU 

TRANSMISSION FlRE 

RlGHT ENGINE FlRE 

Figure 9: DC Power Distribution 

(SIN 900-0001 0 thru 900-00051 only) 


I 

Page 11 

Revision AD

LT PWR RLY 

,pi AP/SAS ADF REFERENCE 

BENDIXlKIN6" IFRAVIONICS 1 KFC goo 


LT START 

0 11, 

RT START RLY 

RT PWR RLY 

GENERATOR 

LT GEN BUS 

- 1 RT GEN BUS 

AVIONICS FANS 

- m 

#2 AHRS #2 AHRS AUX PWR 

NORMAL SHIPS LOADS 

EXT PWR RLY 

ELT 

PRIMARY PWR 

LEFT EADl 

LEFT EHSl 

#I AHRS AUX PWR - RT AVIONICS RLY 

LH AVIONICS RLY 

' 

ADF 1 

DME 

RH ESS FDR 

ANNUNCIATORS 

TRANSPONDER 

BLEED AIR HEAT 

RT ESS BUS 

WARN AUDIO 

KAD 480 AIR DATA 

LEFT PlTOT HEAT AP/SAS KRG 333 #I FD SYNC INSTRUMENT LIGHTING CFU 

FUEL PROBE AP/SAS KRG 333 #2 FLT DIR RIGHT EADl llDS 

BLEED AIR LEAK MODE SEL #I AHRS PRIMARY PWR RIGHT VSCS 

STBY ATTITUDE INDICATOR 

INVERTER 

RT FUEL SHUTOFF VLV RlGHT GCU 

GPS 

RIGHT PlTOT HEAT 

TRANSMISSION FIRE 

CMPS DlSP 

RlGHT ENGINE FlRE 

Figure 10: DC Power Distribution 


A. Essential Busses 

The essential busses provide power to the systems essential to the aircraft operation as well as those 

systems essential for IFR operation. In the event of a dual generator failure, the essential busses will 

remain powered via the battery. The systems powered by the essential busses can be powered for a 

minimum of 30 minutes after dual generator failure. The power switch must be placed into the ESS 

position in the event of this failure. The use of the left hand pitot heat and the landing light is restricted 

and the landing light can not be turned on until absolutely necessary. The aircraft power switch 

controls power to the essential busses. 

B. Battery Bus 

The No. 2 Attitude and Heading Reference System Primary (AHRS 2 PRI) circuit breaker is added in 

a four tube EFS 40 configured aircraft. The avionics master circuit breaker (AV MSTR) is replaced by 

the AHRS 2 circuit breaker in a four tube EFS 40 configured aircraft. 

Page 12 

Revision AD 


I



C. Lighting Bus 

The instrument lighting (INSTR) circuit breaker has been relocated to the Right Essential Bus. 

D. Left Generator Bus 

The No. 1 Attitude and Heading Reference System Auxiliary (AHRS 1 AUX) and the Left DC Bus (LH 

DC BUS FDR) circuit breakers have been added. Four tube EFS 40 configured aircraft add the left 

side Electronic Attitude and Direction Indictor (EADI L) and Electronic Horizontal Situation Indicator 

(EHSI L) circuit breakers onto the bus. 

E. Right Generator Bus 

The Right DC Bus (RH DC BUS FDR) circuit breaker has been added. 

The avionics fan circuit breaker (AV FAN) is replaced with a 3 amp circuit breaker 

The Collective Friction Unit (CFU) circuit breaker is re-labeled HYD TEST. The CFU is now powered 

from the Right Essential Bus, however, the hydraulic test function is still powered by this bus. 

The Bleed Air Heat (BLD AIR HEAT) circuit breaker has been relocated from the Essential Bus Circuit 

Breaker panel to the Right Generator Bus. 

The No. 2 Attitude and Heading Reference System Auxiliary (AHRS 2 AUX) circuit breaker is added in 

a four tube EFS 40 configured aircraft. 

The Emergency Locator Transmitter (ELT) circuit breaker is added if the ELT option is installed. 

F. Left Avionics Bus 

The Radar Altimeter (RAD ALT) and Marker Receiver (MARKER) circuit breakers have been added. 

The Multi-Function Display (MFD) and Radar Transceiver (RADAR RIT) circuit breakers are added if 

the weather radar1MFD option is installed. For weather radar installations that use the IN 182A Radar 

Indicator, the Radar Indicator (RADAR IND) circuit breaker uses the same position as the MFD circuit 

breaker. 

G. Right Avionics Bus 

The Automatic Direction Finder (ADF 1) and Distance Measuring Equipment (DME) circuit breakers 

are added to this bus. 

H. 26VAC 400 HZ Bus 

This bus has been added to the aircraft. The inverter (located in the RH Avionics Bay) supplies the 

bus. 

The APISAS Reference (APISAS REF) and ADF Reference (ADF REF) circuit breakers are on this 

bus. 


I 

Page 13 

Revision AD

BENDIXIKING" IFR AVIONICS 1 KFC 900 



Page 14 

Revision AD 

I EFFECTNITY: MD900 

I



96-30-00 

DC Power Systems - 

Fault Isolation 

1. Power Busses System Troubleshooting 

This section supplements the existing maintenance manual. 

Table 101: Left Essential Bus Troubleshooting 

Fault Probable Cause Corrective Action Ref. Section 

No power to left Faulty power diode. Replace power diode. 96-30-00 

essential bus (On 

ELECTRICAL 

MASTER panel, 

POWER switch is set 

to BATIEXT position. 

WITHOUT 

EXTERNAL power 

applied to the aircraft.) 

Faulty battery relay. Replace battery relay (Kl) located in 96-30-00 

external power box assembly. 

Faulty battery warm relay. Replace Battery warm disable relay 96-30-00 

(K4-2) located in external Power box 

assembly. 

Faulty POWER switch. Replace POWER switch. 96-30-00 

Faulty battery. Ref. Battery Troubleshooting. 96-30-00 

Faulty wiring Test and repair wiring. 96-30-00 

Faulty 50 amp circuit breaker. Replace circuit breaker (CB 1) located in 96-30-00 

external power box. 

Faulty 30 amp circuit breaker. Replace circuit breaker CB 19 located in 96-30-00 

essential circuit breaker panel. 

Page 4 01 

Revision AD

BENDlX/KlNe;° IFR AVIONICS I KFC goo 


Table 102: Right Essential Bus Troubleshooting 


No power to right Faulty power diode. Replace power diode. 96-30-00 

essential bus (On 

ELECTRICAL 

MASTER panel, 


to BATlEXT position. 

WITHOUT 



Faulty battery relay. Replace battery relay (KI) located in 96-30-00 


Faulty battery warm relay. Replace Battery warm disable relay (K4- 96-30-00 

2) located in external Power box 

assembly. 


Faulty battery. Ref. Battery Troubleshooting. 96-1 0-00 


Faulty 50 amp circuit breaker. Replace circuit breaker (CB2) located in 96-30-00 




Page 102 

Revision AD 


I



Table 103: Aux Left Essential Bus Troubleshooting 

(sln 900-00010 thru 900-00051 only) 


No power to auxiliary Faulty power diode. Replace power diode. 96-30-00 

left essential bus (On 

ELECTRICAL 

MASTER panel, 



WITHOUT 



Faulty battery relay. Replace battery relay (Kl) located in 96-30-00 


Faulty battery warm relay. Replace Battery warm disable relay (K4- 96-30-00 

2) located in external Power box 

assembly. 


Faulty battery. Ref. Battery Troubleshooting. 96-1 0-00 


Faulty 50 amp circuit breaker. Replace circuit breaker (CB 1) located in 96-30-00 




Table 104: Left DC Bus Troubleshooting 


No power to left DC Faulty battery relay. Replace battery relay (Kl) located in 96-30-00 

bus (On ELECTRICAL 


MASTER panel, 



WITH EXTERNAL 

power applied to the 

aircraft.) 





Faulty 40 amp circuit breaker Replace circuit breaker CB36 located in 96-30-00 

electrical load center. 

I 

Page '1 03 

Revision AD

BENDIXlKIN6" IFRAVIONICS I KFC 900 


Table 105: Right DC Bus Troubleshooting 


No power to right DC Faulty battery relay. Replace battery relay (Kl) located in 96-30-00 

bus (On ELECTRICAL 


MASTER panel, 



WITH EXTERNAL 

power applied to the 

aircraft.) 




Faulty 40 amp circuit breaker Replace circuit breaker CB66 located in 96-30-00 

electrical load center. 

2. Verification of Rectifiers, Essential Bus Circuit Breaker Panel 

The Essential Bus Circuit Breaker Panel has two isolation rectifiers that isolate the essential busses from 

the DC busses. The operation of the rectifiers are checked during the pre-flight start sequence by the 

pilot. In the event a failure of either of the rectifiers, the following procedure should be used to verify the 

failure. The faulty rectifier must be replaced. The rectifier designators for aircraft serial numbers 900- 

00010 through 900-00051 are PCRI and PCR2. The designators for aircraft serial numbers 900-00052 

and Subsequent are CR1 and CR2. 

A. PCRI Failure Verification Procedure 

1) Apply ground power to the aircraft and place the POWER switch in the BATIEXT position. 

2) Pull the 30 amp R ESS circuit breaker in the Essential Bus Circuit Breaker Panel. 

3) Verify that the following units andlor systems are powered: the transponder, the GPS (for aircraft 

sln 900-00010 thru 900-00051), the bleed air heat (for aircraft sln 900-00052 and subsequent), all 

annunciators press-to-test. If all of the units and/or systems are in-op, verify the 40 amp RH DC 

BUS FDR circuit breaker is set. 

4) Verify that the equipment on the right essential bus is in-op, with the exception of the llDS and the 

No. 1 AHRS, which have redundant power inputs. 

5) Replace the PCRIICRI rectifier if the above checks are verified. 

Page 104 

Revision AD 

I EFFECTIVITY: MD900



B. PCR2 Failure Verification Procedure 

1) Apply ground power to the aircraft and place the POWER switch in the BATIEXT position. 

2) Pull the 30 amp L ESS circuit breaker in the Essential Bus Circuit Breaker Panel. 

3) Verify that the following units and/or systems are powered: the No.2 NAVICOMM, the left VSCS, 

and the instrument flood lights. If all of the units and/or systems are inoperative, verify the 40 amp 

LH DC BUS FDR circuit breaker is set. 

4) Verify that the equipment on the left essential bus is inoperative (except for the equipment 

powered by the side circuit breaker panel for aircraft s/n 900-00052 and subsequent.) 

5) Replace the PCR21CR2 rectifier if the above checks are verified. 


I 

Page 105 

Revision AD




Page 106 

Revision AD 

I 


1. Circuit Breaker Panel 

BENDIXIKING" IFRAVIONICS I KFC goo 


A. Circuit Breaker Panel Removal 

(Reference Figure 401 and Figure 402) 

WARNING: Power Off 

96-30-00 


Removal 1 Installation 

1) Verify that all power is removed from the aircraft and the POWER switch is in the OFF position. 

2) Unlock the captive fasteners (6 places) holding the circuit breaker panel in place. 

3) Lift the panel until the attached connectors and wires are accessible. 

4) Detach connectors P127, PI28 and PI31 from the panel. 

5) Detach wires P31A10 3, P38A10 3, P113H10 3 and P114HlO 3 from the panel. See Figure 403. 

6) Remove the panel from the aircraft. 

B. Circuit Breaker Panel Installation 




2) Attach connectors P127, PI28 and PI31 to the panel. 

3) Attach wires P31A10 3, P38A10 3, P113H10 3 and P114H10 3 from the panel. See Figure 403. 

4) Place the panel in position on the console. 

5) Lock the captive fasteners (6 places) on the circuit breaker panel. 

6) Restore power to the aircraft. 


I 

Page 401 

Revision AD



C. Side Circuit Breaker Panel Removal (sln 900-00052 and subsequent) 

(Reference Figure 402) 



2) Remove the 2 lower screws from the forward and aft sides (4 total) of the side circuit breaker 

panel. 

3) Move the panel until the attached connector is accessible. 

4) Detach connector P9000 from the console. 

5) Remove the side circuit breaker panel from the aircraft. 

D. Side Circuit Breaker Panel Installation (sln 900-00052 and subsequent) 




2) Attach connector P9000 to the side circuit breaker panel. 

3) Place the panel in position on the side of the console. 

4) Reattach the 2 lower screws from the forward and aft sides (4 total) of the side circuit breaker 

panel. 


Page 402 

Revision AD 


I



11 LT EFlS APISAS RT EFlS 1 I 

TEST 

SYS 1 

HEAT 

OVRD 

@ON 

II 

SYS 2 

OFF 

PlTOT 

H FAT IPS L VSCS R 

1-1 OFF OFF TEST 

I 

ESS GCU XMSN ENG FUEL PlTOT 

FlRE FlRE R VLV R HEAT R 

VSCS AP/SAS INSTR 

I llDS R TRIM AUDIO ALERT LTG I 

11 EADI AHRS 1 NAY LDG 

R PRIMARY COM 1 LT AIR DATA CFU 11 

L ESS BUS - 

ESS GCU ENG 7 FUEL -i 

BUS L FIRE L 'VLV L XFD VLV PROBE' 

BLD AIR STBY EHSl l-AP/SAS-i 

LEAK ATT R CMPTR DISC ACCEL 

@@@@@@ 

-L DC B U S - 1 -R DC B U S 1 

NAV VSCS INSTR XPNDR 

COM 2 L FLOOD ANNUN 1 GPS 

Figure 401: Console Mounted Breakers and Switches 

(SIN 900-00010 thru 900-00051 only) 


Page 403 

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BENDIXIKINNG" IFR AVIONICS 1 KFC goo 


LT EFlS APISAS RT EFlS 

7 gq 6 

HEAT 

SYS 2 

PlTOT 

HEAT 

OFF 

IPS 

ON 

0 OFF 0 

R 

ESS BUS 

ESS GCU ENG XMSN FUEL PlTOT 

BUS R FIRE R FIRE VLV R HEAT R 

VSCS WARN INSTR 

llDS R TRIM AUDIO AUDIO LTG I I 

o ~ s o 

EADl AHRS 1 NAV LDG 11 

PRIMARY COM 1 LT AIR DATA CFU 

I- L ESS BUS --------1 

Jl- 

r L ESS BUS -I 

CMPST 

ESS ~ c u ENG FUEL FUEL PlTOT 

BUS L FIRE L PROBE VLV L HEAT L GPS DlSP 

w 

BLD AIR STBY EHSl -AP/SAS-~ MODE 

LEAK ATT R CMPTR DISC ACCEL 11 lNVTR SELECT 

-L DC B U S 7 -R DC B U S 1 

NAV VSCS INSTR XPNDR BLD AIR 

COM 2 L FLOOD ANNUN 1 HEAT 

Figure 402: Console Mounted Breakers and Switches 


Page 404 

Revision AD 




REFERENCE P38A10 3 

(FROM EXTERNAL POWER 

BOX ASSEMBLY) 

REFERENCE P31AlO 3 

(FROM EXTERNAL POWER 

BOX ASSEMBLY) 

\\ SEEDETAILA /// \, SEE DETAIL B 

. 

\ , \ 

, 

-_-_-. '----__- . 

, 

TYPICAL 

MS27039.8-32 SCREW 

REFERENCE Pll4HlO 3 

(FROM ELECTRICAL 

LOAD CENTER1 

MS21042.8-32 LOCKNUT 

w 

REFERENCE P113H10 3 

(FROM ELECTRICAL 

LOAD CENTER) 

DETAIL A 

DETAIL B 

Figure 403: PCRllCRl and PCR2lCR2 Rectifiers 


. > 

96-30-00 

Page 405 

Revision AD

2. Rectifier PCRIICRI 

A. Rectifier PCRIICRI Removal 



BENDIXIKINNG" IFRAVIONICSI KFC 900 


1 Verify that all power is removed from the aircraft and the POWER switch is in the OFF position. 

2) Remove the Essential Bus Circuit Breaker Panel from the aircraft. 

3) Remove the screw that holds the braided lead of the rectifier to the bus bar. 

4) Remove the nut holding the rectifier base to the bus bar. 

5) Remove the rectifier from the panel. 

B. Rectifier PCRIICRI Installation 




2) Place a 3 inch piece of 150-00028-0000 shrink tubing over the braided lead of the rectifier. 

DO NOT SHRINK THE TUBING. 

3) Secure the braided lead to the bus bar. 

4) Secure the rectifier base to the bus bar 

5) Apply heat to the shrink tubing. 

6) Install the Essential Bus Circuit Breaker Panel into the aircraft. 


C. Rectifier PCR2lCR2 Removal 



1) Verify that all power is removed from the aircraft arid the POWER switch is in the OFF position. 

2) Remove the Essential Bus Circuit Breaker Panel from the aircraft. 

3) Remove the screw that holds the braided lead of the rectifier to the bus bar. 

4) Remove the nut holding the rectifier base to the bus bar. 

5) Remove the rectifier from the panel. 

Page 406 

Revision AD



D. Rectifier PCR2lCR2 Installation 



1) Verify that all power is removed from the aircraft and the POWER switch is in the OFF position 

2) Place a 3 inch piece of 150-00028-0000 shrink tubing over the braided lead of the rectifier. 

DO NOT SHRINK THE TUBING. 

3) Secure the braided lead to the bus bar. 

4) Secure the rectifier base to the bus bar. 

5) Apply heat to the shrink tubing 

6) Install the Essential Bus Circuit Breaker Panel into the aircraft 

7) Restore power to the aircraft 

3. Master Switch Panel 

A. Master Switch Panel Removal 




2) Unscrew the captive fasteners (2 places) holding the master switch panel in place. 

3) Lift the panel until the attached connectors and wires are accessible. 

4) Detach connector PMSTRI from the panel. 

5) Detach connector PMSTR2 from the panel (Four tube EFS 40 configured aircraft only) 

6) Remove the panel .from the aircraft. 

9. Master Switch Panel Installation 




2) Attach connector PMSTRI to the panel. 

3) Attach connector PMSTRZ to the panel (Four tube EFS 40 configured aircraft only). 

4) Place the panel in position on the console. 

Page 407 

Revision AD

BENDIXlKIN6" IFR AVIONICS I KFC 900 


5) Screw the captive fasteners (2 places) on the master switch panel. 


d 

(OVERLAY NOT SHOWN) 

\ 

I 

- KEYWAY (REF) 

I 

i 

WASHER 

WASHER 

SUPPLIED WlTH SWlTCH 

(TYPICAL 3 PLACES) 

Figure 404: Master Switch Panel 

I 

C. RT EFS Master Switch Removal 




2) Remove the master switch panel from the aircraft. 

3) Remove the overlay from the panel. 

4) Remove the RT EFS master switch from panel. 

5) Tag and remove the wiring from the switch. 

Page 408 

Revision AD 




D. RT EFS Master Switch Installation 



1) Terminate the wiring to the RT EFS master switch 

2) Install the RT EFS master switch onto the panel. 

3) Install the overlay onto the panel. 

4) Place the master switch panel in position on the console. 



E. AP Master Switch Removal 






4) Remove the AP master switch from panel. 


F. AP Master Switch Installation 



1) Terminate the wiring to the AP master switch 

2) Install the AP master switch onto the panel. 





G. LT EFS Master Switch Removal (Four Tube configured aircraft only) 



Page 409 

Revision AD

4. Generator Field RCCB's 

A EXISTING HARDWARE 







4) Remove the RT EFS master switch from panel. 


H. LT EFS Master Switch Installation (Four Tube Configured Aircraft Only) 



1) Terminate the wiring to the LT EFS master switch 

2) Install LT EFS master switch onto the panel. 





I 

I LH GEN FIELD I 

Figure 405: Generator Field RCCB's 

I 

A. Left Generator Field RCCB Removal 


Page 410 

Revision AD 


I





2) Tag and remove the wiring from the left generator field RCCB. 

3) Remove the hardware mounting the left generator field RCCB to the Electrical Load Center. 

4) Remove the left generator field RCCB from the aircraft. 

B. Left Generator Field RCCB Installation 




2) Mount the left generator field RCCB to the Electrical Load Center. 

3) Terminate the wiring to left generator field RCCB. 


C. Right Generator Field RCCB Removal 




2) Tag and remove the wiring from the right generator field RCCB. 

3) Remove the hardware mounting the right generator field RCCB to the Electrical Load Center. 

4) Remove the right generator field RCCB from the aircraft. 

D. Right Generator Field RCCB Installation 




2) Mount the right generator field RCCB to the Electrical Load Center. 

3) Terminate the wiring to right generator field RCCB. 


Page 41 1 

Revision AD




5. Generator Field Control Circuit Breakers 

6/32 CAPTURED 

SCREW (2 PLCS) 

(REF) 

GENERATOR 

CONTROL 

CIRCUIT BREAKER 

J 

Figure 406: Generator Field Control Circuit Breakers 

A. Left Generator Field Control Circuit Breaker Removal 




2) Tag and remove the wiring from the left generator field control circuit breaker. 

3) Remove the left generator field control circuit breaker. 

B. Left Generator Field Control Circuit Breaker Installation 




2) Mount the left generator field control circuit breaker to the console. 

3) Terminate the wiring to left generator field control circuit breaker. 


Page 41 2 

Revision AD



C. Right Generator Field Control Circuit Breaker Removal 




2) Tag and remove the wiring from the right generator filed control circuit breaker. 

3) Remove the right generator filed control circuit breaker. 

D. Right Generator Field Control Circuit Breaker Installation 




2) Mount the right generator field control circuit breaker to the console. 

3) Terminate the wiring to right generator field control circuit breaker. 



I 

Page 413 

Revision AD




Page 414 

Revision AD



1. DC Power Systems Inspections 

A. Essential Bus Circuit Breaker Panel 

96-30-00 


Inspection I Test 

1) Visually inspect the panels for any broken or damaged circuit breakers and switches. Visually 

inspect for any missing hardware. No damage or missing hardware allowed. 

2) Visually inspect panel markings for legibility and discoloration. No damage allowed. 

3) Verify panel is properly fastened to the console. 

B. Master Switch Panel 

1) Visually inspect the panels for any broken or damaged circuit breakers and switches. Visually 

inspect for any missing hardware. No damage or missing hardware allowed. 

2) Visually inspect panel markings for legibility and discoloration. No damage allowed. 

3) Verify panel is properly fastened to the console. 


I 

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BPNDIXIKING" IFR AVIONICS I KFC 900 



Page 602 

Revision AD 


I



Avionics - 


General 

This manual is intended to be a supplement to the rotorcraft maintenance manual(s) provided by 

MD Helicopters, Inc. (MDHI) for the Model MD900 (MD Explorer). The information provided here is for the 

items that have been added by the Honeywell International Inc. certification for IFR avionics and KFC 900 

AFCS. This manual will supersede information from MD Helicopters, Inc. only for the specific items 

addressed. 

A list of Honeywell International Inc. Approved Sales and Service Centers can be obtained from Honeywell 

International Inc. Product Support, (USA) 913-782-0400 or by accessing the BendixJKing website 

www. bendixking.com. 

Avionics Systems 

The avionics systems installed as part of the STC enable the aircraft to be operated in the Helicopter 

Instrument Flight environment. The basic IFR avionics package meets Category B IFR requirements. 

Additional avionics systems are required to meet Category A IFR requirements. 

The basic IFR avionics package includes the following systems: Dual VHF NAVICOMM transceivers, a 

single DME transceiver, a single marker receiver, a single ADF receiver, a radar altimeter, a Two-Tube 

EFS 40 with EADIIEHSI, a single AHRS attitude and heading reference system, a GPS long range NAV 

sensor, a single digital air data system, a standby attitude indicator, a standby altimeter and an inverter 

powering the AC power system. 

The following existing aircraft systems are also part of the basic IFR avionics package: a single nondiversity 

Mode S transponder or a ATCRBS transponder (Modes A and C), an audio system with ICS 

capability and a dual vertical stabilizer control system (VSCS). 

The basic IFR avionics package also includes the installation of the KFC 900 Automatic Flight Control 

System (AFCS) that includes the following: flight control computer, mode select panel, rate sensor, linear 

actuators, trim actuator, position resolvers, cable transducers, directional spring cartridge, trim switch and 

annunciator panel. 

The following systems are considered optional: a second EFS 40 system with a second AHRS or a 

mechanical gyro system for the copilot (AD1 and HSI), a weather radar system, a Multi-Function Display 

System and an emergency locator transmitter (ELT). 

The Category A IFR avionics package includes these additional systems: a standby altimeter, an aural 

warning tone generator (and an electronic standby instrument system for 2-Tube configurations.) 

Figure 1 shows the location of the avionics systems components. Figure 2, Figure 3 and Figure 4 show 

the instrument panel layouts for the 2-Tube L-panel, the 2-Tube T-panel and the 4-Tube T-panel basic IFR 

avionics package. Figure 5, Figure 6 and Figure 7 show the instrument panel layouts for the 2-Tube L- 

panel, the 2-Tube T-panel and the 4-Tube T-panel Category A IFR avionics package. Figure 8 shows the 

location of console mounted equipment for aircraft sln 900-00010 thru 900-00051. Figure 9 shows the 

location of console mounted equipment for aircraft sln 900-00052 and subsequent. Figure 10 shows the 

location of console mounted equipment for 2-Tube Category A packages. 


I 

Page I 

.. Revision AD

KSM 575 LINEAR ACTUATORS { 

LATERAL RESOLVER 

COLLECTIVE RESOLVER 

PEDAL RESOLVER 

TRANSPONDER ANTENNA 

EXISTING 

'-RIGHT HAND AVIONICS BAY 

KN 63 DME 

LCR-92s AHRS #I 

CI 1125 QUADRAPLEXER 

SPCS(B) INVERTER 

KA 33 COOLING FAN - 

G 333 RATEIACCELERATION UNITS 

SEE FOLLOWNG FlGU 

CI-120 NAVILOCIGS ANT 

KMR 675 MARKER BEACON 

KN 40 NAV CONVERTER 

KG 102A SLAVED COMPASS 

ART 2000 WX RADAR Rll 

AA2012V ANTENNA PLATE 

CM 2000 CONFIG MODULE 

RADOME 

MODEL 630 AURAL WARN GEN 

ADC-3000 AIR DATA COMP



Figure 2: 2-Tube L-Panel Equipment 


I 

Page 3 

Revision AD



Figure 3: 2-Tube T- Panel Equipment 

Page 4 

Revision AD 


I

BENDIXIKINNG" IFRAVIONICS I KFC goo 


Figure 4: 4-Tube T- Panel Equipment 


Page 5 

Revision AD



Figure 5: 2-Tube L- Panel Equipment - Category A 

Page 6 

Revision AD 


I



Figure 6: 2-Tube T- Panel Equipment - Category A 


I 

Page 7 

Revision AD



Figure 7: 4-Tube T- Panel Equipment - Category A 

Page 8 

Revision AD



- KT 70 

4---- KR 87 

SWI AVIONICS 

TCH PANEL 

KX 165A #2 

AMS 43 

(EXISTING) 

FIRE L MV L XFD YLV PROBE 

CUPTR DISC ACCEL 

Figure 8: Console Mounted Equipment 

(sln 900-00010 thru 900-00051) 


Page 9 

\ , Revision AD



AVIONICS 

SWITCH PANEL 

AMS 43 

(EXISTING) 

7 ENGINE CONTROL 

OYSP TEST 

I 

GENERATOR 

- 7 FUEL SYSTEM 

L BOOST CROSS FEED R BOOST 

TEST HEAT cw OW MNI 

SYS 1 OVRD 

1 1 

7 FUEL SHUTOFF --, 

515 2 OFF 

PlTOT 

HE1 IPS L VSCS R 

ON 

OFF OFF TEST 

-ELECTRICAL MASTER1 

4 4 

AVIONICS L GEN R GEN POWER 

MI ON ocl BAT/EXT 

WF 0 

RWl RESET ESNTL 

@ OFF @ Off 9 

TRlU AUDIO AUDIO 

@@a@@@ 

r L ESS 

nooo ANNUN I 

L 

I L- I1 

i r 


(SIN 900-00052 and Subsequent 

except 2-Tube Category A) 

b - 

Page 10 

Revision AD



AVIONICS 

SWITCH PANEL 

AMS 43 

(EXISTING) 

KMS 540 

GENERATOR 

I ]pJ - 

STROBE 

WSN 

COY 2 L nw0 ANNUN I 

L - - --- - 


(SIN 960-00052 and Subsequent 2-Tube Category A) 

All instrument panel equipment uses 28 volts DC instrument lighting controlled by the INSTR lighting pot 

on the center console control panel. All console/pedestal equipmentlpanels use 28 volts DC lighting 

controlled by the CNSL pot on the center console control panel. The instrument lighting power has been 

relocated from the lighting bus to the right essential bus. Console lighting power remains on the lighting 

bus. 

Page 11 

.Revision AD

BENDIXlKlN6" IFRAVIONICS I KFC goo 


3. VHF Navigation And Communications (NAVICOMM) 

The VHF navigation and communications systems consists of dual KX 1651165A NAVICOMM 

transceivers, a KI 206 navigation indicator, a KN 40 NAV converter, a CI-120 VORILOCIGS antenna 

system, a CI-1125 VORILOCIGS quadraplexer, and two CI-291 VHF COMM antennas. Reference 

Figure 11 and Figure 12 for a system block diagram. 

E 

? s 

8 P 

3 

Figure l"i NAVICCBMM System Bloclc Diagram 

Page 9 2 

Revision AD



Figure 12: NAVICOMM System Block Diagram (Continued) 


97-00-00 

Page 13 

Revision AD



A. KX 16511 65A VHF NAVICOMM Transceiver 

The KX 1651165A VHF NAVICOMM is a console mounted transceiver which provides the following 

functions. 

Two-way voice communication within the frequency range of 118.00 MHz to 136.975 MHz (720 

channels) in 25 kHz increments. 

Reception of navigation signals within the frequency range of 108.00 MHz to 117.95 MHz in 150 

kHz increments (200 channels). 

Reception of glideslope signals within the frequency range of 329.15 MHz to 335.00 MHz in 150 

kHz increments (40 channels). 

VORILOC converter. 

Table 1 : KX 1651165A Leading Particulars 

PART NUMBER 

KX 165 069-1025-25 

Required Mods: 15, 16, 18 

Minimum Software Level: 01 

KX 165A 069-01033-0101 

Required Mods: 

None 

Minimum Software Level: 01/06 

KX 165A (8.33kHz channel spacing) 069-01033-0201 


None 


PHYSICAL DIMENSIONS (With rack): 

Height: 2.050 in. ( 5.207 cm) 

Width: 6.250 in. (15.875 cm) 

Length: 11.631 in. (29.543 cm) 

WEIGHT: (With rack): 5.65 Ibs. (2.31 kg) 

TEMPERATURE RANGE: 

-20°C to +55"C with short time operation at +70°C 

ALTITUDE: 

-15,000 ft. to 50,000 ft. 

POWER REQUIREMENTS: Receive: 0.40 A max 

Transmit: 

6.00 max 

COMM TRANSCEIVER OPERATION: 

1) FREQUENCY DISPLAY WINDOW - The left portion of the digital display read out is allocated to 

for COMM , USE and STANDBY frequencies with a "T" between them to indicate the transmit 

mode of operation. 

2) ON/OFF/VOLUME/TEST KNOB - Rotates clockwise to power the transceiver and adjust COMM 

audio volume. Clockwise rotation increases the volume and counter-clockwise rotation decreases 

volume. Pulling the knob out allows adjustment of desired audio level. Pushing the knob back in 

enables the automatic squelch. 

3) FREQUENCY SELECTION KNOBS - The larger (or outer) knob will change the MHz portion of 

the standby display. At one band-edge (118 or 136 MHz) the following 1 MHz change will wrap 

around to the other band-edge. The smaller (or inner) knob will change the KHz portion of the 

standby display. It will change in steps of 50 KHz when the knob is pushed in, and in 25 KHz 

steps when the knob is pulled out. The wrap around band-edge is also utilized when incrementing 

or decrementing the KHz portion of the standby display. Rotating either knob clockwise 

increments the previous frequency while counter-clockwise rotation decrements the previous 

frequency. 

4) COMM FREQUENCY TRANSFER BUTTON - Pressing the COMM frequency transfer button will 

swap the STBY and USE frequencies Pressing the collective mounted transfer button will also 

accomplish this function. 

Page 14 

Revision AD 


NAV RECEIVER OPERATION: 



5) FREQUENCY DISPLAY WINDOW - The right portion of the digital display read out is allocated to 

for NAV , USE and STANDBYIRAD information. 

6) ONIOFFNOLUMEITEXT KNOB - Rotates clockwise to power the transceiver and adjust COMM 

audio volume. Pulling the knob out allows adjustment of desired audio level. Pushing the knob 

back in enables the automatic squelch. 

7) FREQUENCY SELECTION KNOBS - The frequency channeling is the same as the COMM when 

operating in the frequency mode. The larger (or outer) knob operates in 1MHz steps and 

incrementsldecrements the STANDBYIRAD frequency display. The smaller (or inner) knob 

operates in 50 KHz steps. The wrap around band-edge is also utilized when incrementing or 

decrementing the NAV frequency. When the smaller (or inner) is pulled out, the VOR bearing is 

digitally displayed in the STANDBYIRAD window. When in the bearing mode, the 

incremenudecrement knobs channel the USE frequency window. 

In the radial mode of operation, the right hand window of the NAV display shows the bearing 

FROM the station. When, due to a weak signal, the warning flag is activated, a digital flag, - - -, is 

displayed in the radial window. This flag will also be present whenever an ILS frequency is 

selected. 

8) NAV FREQUENCY TRANSFER BUTTON - When the smaller (or inner) incremenudecrement 

knob is pushed in, pressing the NAV frequency transfer button will swap the STBY and USE 

frequencies 

9) NAV IDENT KNOB - The NAV IDENT knob is active in the pulled out position so that both voice 

and ident can be heard. When the knob is pushed in, the ident tone is attenuated. The volume of 

the voicelident can be adjusted by turning this knob. Clockwise rotation increases the volume, 

and counter-clockwise rotation decreases volume. 

6. KN 40 NAV Converter 

The KN 40 NAV converter is a remote mounted dual NAV converter that also simulates a master DME 

indicator. Omni-bearing, localizer deviation and glideslope deviation outputs are converted and output 

in an ARlNC 429 format for display on the EFS 40 system. 

Table 2: KN 40 Leading Particulars 

PART NUMBER 066-01130-0801 

Required Mods: 1,2,3 



Height: 

5.30 in. 

Width: 

2.80 in. 

Length: 

12.90 in. 

WEIGHT: (With rack): 

4.40 Ibs. 


-55°C to +70°C 

ALTITUDE: 

+55,000 ft. 

POWER REQUIREMENTS: 

+28VDC @ 1 .OA max 

(1 3.46 cm) 

( 7.11 cm) 

(32.77 cm) 

(2.00 Kg) 

C. KI 206 Navigation Indicator 

The KI 206 navigation indicator displays VORILOC, glideslope, TOIFROM, and VORILOC and 

glideslope flag information from the No. 1 KX 1651165A NAVICOMM. The OBS knob allows the pilot 

to select the desired radial from the navigation station. 


Page 15 

Revision AD



Table 3: KI 206 Leading Particulars 

PART NUMBER 066-3034-04 


None 

Minimum Software Level: 

None 


Height: 3.26 in. ( 8.28 cm) 

Width: 3.26 in. ( 8.28 cm) 

Length: 8.06 in. (20.46 cm) 

WEIGHT: (With rack): 1.30 Ibs. (0.59 Kg) 

TEMPERATURE RANGE: -15°C to +55"C, short time to +71 "C 


None 

LIGHTING: 

28vdc 1 OOmA 

D. Navigation Antennas 

The CI-120 VORILOCIGS antenna consists of two CI-120-1 antenna blades, a CI-120-3 power 

combiner and two 513-Cl-120-2 coax assemblies. The antenna system is mounted on the bottom aft 

end of the NOTAR tail boom. 

The CI-1125 quadraplexer (located in the RH avionics bay) converts the VORILOCIGS antenna output 

into two VORILOC outputs and two GS antenna outputs that connect each NAVICOMM. 

The CI-291 VHF COMM antennas (one of the antennas is existing on the aircraft) are mounted on the 

horizontal tail on NOTAR tail boom. Each antenna is connected to a NAVICOMM. 

4. Distance Measuring Equipment (DME) 

The DME system consists of a KN 63 DME transceiver, the KN 40 NAV converter, and a CI-105-6 

DME antenna. Reference Figure 6 for a system block diagram. 

The DME is a remote mounted unit supplying distance, ground speed and time to station to the tuned 

VORIILS station. The DME is only interfaced to (channeled by) the No. 1 KX 1651165A NAVICOMM. 

The DME distance, ground speed and time to station are displayed on the EFS 40 system. DME hold 

is selected (and deselected) via the console mounted avionics switch panel DME HOLD 

SELECTIRELEASE switch. The KN 40 NAV converter acts a master indicator in lieu of a KDI 5721574 

panel mounted indicator. 

Table 4: KN 63 Leading Particulars 


Required Mods: 1, 2, 3,4, 5, 6 


None 


Height: 6.500 in. (16.51 cm) 

Width: 1.180 in. ( 3.00 cm) 

Length (Including connector): 11.55 in. (29.34 cm) 


MAXIMUM ALTITUDE: 

+50,000 ft. 


11 - 33VDC at 17 Watts maximum 

5. Marker Beacon Receiver 

The marker beacon system consists of a KMR 675 marker beacon receiver, the KN 40 NAV 

converter, and a CI-118-9 (or KA 26) marker beacon antenna. 

The KMR 675 is a remote mounted unit that provides glide path marker beacon information. The 

marker beacon audio is interfaced to the existing aircraft audio system. The marker beacon receiver 

Page I 6 

Revision AD 


BENDIX/KINGGO IFRAVIONICSI KFC goo 


is tested by pressing the momentary MARKER TEST switch on the console mounted avionics switch 

panel. The KN 40 NAV converter converts the marker beacon receiver outputs and outputs them in 

an ARlNC 429 format for display on the EFS 40 system. 

Table 5: KMR 675 Leading Particulars 



None 


None 


Height: 2.975 in. (6.750 cm) 

Width: 1.162 in. (2.950 cm) 


WEIGHT: (With rack and connector): 0.75 Ibs. (0.340 kg) 

TEMPERATURE RANGE: -54°C to +55"C Short Time +71 "C 

MAXIMUM ALTITUDE: 

+55,000 ft. 


+27.5 VDC &20% 85mA standby, 1.2A test function 

maximum 

6. Automatic Direction Finder (ADF) 

The ADF system consists of a KR 87 ADF receiver and a KA 448 ADF antenna. Reference Figure 13 

for a system block diagram. 

REFERENCE 

EFS 40 ANALOG OUTPUT 

INDIVIDUAL 

SYSTEM 

BLOCK 

DIAGRAMS 28VDC R AV BUS ADF PWR ADF AUDIO 

A. KR 87 ADF Receiver 

Figure 13: ADF System Block Diagram 

The KR 87 ADF is a console mounted unit that provides bearing information to stations in the 200khz 

to 1799khz band. The ADF also provides audio reception in the AM broadcast range. The ADF Audio 

is interfaced to the existing aircraft audio system. The ADF outputs a DC SINICOS signal and 

superflag to EFS 40 system for display. 

It is recommended that the KR 87 unit be turned off when the aircraft engines are started in order to 

prevent possible voltage transient damage to the radio. The unit is turned on by rotating the volume 

control clockwise past the detent. The volume control is used to adjust the audio output to a 

comfortable listening level. 

Table 6: KR 87 Leading Particulars 

PART NUMBER 066-1072-04 or 066-1072-14 


None 


None 


Height: 

1.38 in. 

Width: 

6.31 in. 

Length (Including connector): 

12.19 in. 


3.20 Ibs. 


-20°C to +55"C 

ALTITUDE: 

50, 000 ft. 


11 to 33VDC, 12W typical 

( 3.51 cm) 

(16.03 cm) 

(30.95 cm) 

(1.47 Kg) 


Page 17 

Revision AD

NOTE: 

Page 18 

Revision AD 

BENDIX/KING@' IFR AVIONICS I KFC goo 


The audio muting feature of the KR 87 will cause the audio output to be muted unless the receiver is 

locked onto a valid station. This reduces inter-station noise and aids the pilot in identifying usable 

stations. 

KR 87 ADF RECEIVER OPERATION: 

1) ADF BUTTON - The KR 87 Automatic Direction Finder has two operational modes. In the ANT 

(Antenna) mode (ADF button out) the loop antenna is disabled, and the unit simply acts as a 

receiver allowing audio reception through the speaker or headphones. The indicator needle will 

remain parked at the 90" relative position, and the ANT message on the left side of the display will 

be lighted. This mode provides slightly clearer audio reception and is used for station 

identification. In various parts of the world, some LIMF stations use an interrupted carrier for 

identification purposes. With the ADF button depressed, the unit is placed into the ADF mode and 

the loop antenna is enabled. The ADF message on the left side of the display will be lighted and 

the indicator needle will point to the relative bearing of the selected station. 

2) BFO BUTTON - A Beat Frequency Oscillator (BFO) function is provided to permit these stations 

to be more easily identified. Pushing the BFO switch will cause a 1000Hz tone to be heard 

whenever there is a radio carrier signal present at the selected frequency. It will also light the BFO 

message in the center of the display. 

3) ACTIVE FREQUENCY WINDOW - The active frequency is displayed in the left hand window. 

This frequency may be changed with the concentric knobs when either timer mode (FLT or ET) is 

being displayed in the right hand window. The exception to this is when the ET message is 

flashing (see below). To set the 10's digit push the small (or inner) knob in and rotate it. Clockwise 

rotation will increment the digit. The digit will roll over at 9 to 0 and roll under (when turning the 

knob counterclockwise) at 0 to 9. With the small knob pulled out the 1's digit may be set. Its 

operation is the same as for the 10's digit. 

4) Turning the large (or outer) knob changes the 100's digit and the 1000's digit. The 100's digit 

carries to the 1000's digit from 9 to 10 and borrows from 10 to 9. The two digits roll over from 17 

to 02 and under from 02 to 17 thus limiting the frequencies to the range of 200KHz to 1799Hz. 

5) STANDBY FREQUENCY WINDOW - The standby frequency is displayed in the right window 

when the FRQ message is lighted. When this is the case, this frequency may be changed with the 

knobs in a manner similar to that explained above for the active frequency. 

6) FREQUENCY BUTTON - If the standby frequency is not being displayed, it may be called to the 

window by pressing the FRQ button. Pressing this button when the standby frequency is displayed 

causes the current standby and active frequencies to be exchanged. 

7) FLTIET BUTTON - If elapsed time (ET) is currently displayed, the FLTIET button will cause the 

flight timer to be displayed. Pressing this button again will exchange the two timers in the display. 

If the standby frequency is displayed, the FLTIET button will cause the timer which was last 

displayed to reappear in the window. (Note: When power is first applied, the flight timer is 

displayed). 

a) FLIGHT TIMER - The flight timer is displayed in the right hand window when the FLT 

message is lit. This timer will count up to 59 hours, 59 minutes, 59 seconds. When the unit is 

first turned on, this timer is automatically started at 0. Minutes and seconds will be displayed 

until a value of 59 minutes and 59 seconds is reached. On the next count, the display will shift 

to hours and minutes. 

b) ELAPSED TIMER - This timer has two modes: Count Up and Count Down. When power is 

applied, it is in the Count Up mode starting at 0. As is true with the flight timer, the elapsed 

timer will count to 59 hours, 59 minutes, 59 seconds, displaying minutes and seconds until 

one hour has elapsed, then displaying hours and minutes. When in the Count Up mode, the 

timer may be reset to 0 by pressing the reset button. (Note: Pressing the reset button will 

reset the elapsed timer regardless of what is currently being displayed) . 

97-00-00 


L

BENDIX/KINGb IFR AVIONICS I KFC goo 


8) RESET BUTTON - To enter the Count Down mode, the Reset (RST) button is held depressed for 

approximately 2 seconds until the ET message begins to flash (this may be done regardless of 

current display). While the ET message is flashing, the timer is in the ET Set mode. In this mode a 

number up to 59 minutes, 59 seconds may be preset into the elapsed timer with the concentric 

knobs. With the small knob pressed in, the 10's of seconds digit may be changed. It will roll over 

from 5 to 0 and under 0 to 5. With the knob pulled out, the 1's of seconds digit may be changed. It 

rolls over from 9 to 0 and under from 0 to 9. The larger knob modifies the minutes. It rolls over 

from 59 to 0 and under from 0 to 59. The timer will remain in the ET Set mode (ET message 

flashing) for 15 seconds after a number is set in or until the RST, FLTIET or FRQ button is 

pressed. The number preset will remain unchanged until the RST button is pressed. When the 

RST button is pressed after a number is preset, the elapsed timer will start counting down. (Note: 

The timer will start when RST is pressed regardless of the current displays.) When the timer 

reaches 0, it changes to the Count Up mode and continues up from 0. Also, the right hand display 

will flash for 15 seconds and the timer alarm line will be pulled low for 1 second. While the 

elapsed timer is counting down, pressing the RST button will have no effect unless it is held for 

approximately 2 seconds. This will cause the timer to stop and enter the Set mode (ET message 

flashing). 

6. KA 446 ADF Antenna 

The KA 448 ADF antenna is an externally mounted loop and sense antenna. The antenna combines 

the loop and sense signals into a single RF signal which is output to the ADF receiver. 

Table 7: KA 44B Leading Particulars 

Part Number 071 -1234-00 

Required Mods: 1,2 

VERTCAL HEIGHT (From aircraft fuselage): 1.80 in ( 4.57 cm) 

WEIGHT: 2.80 Ibs. (1.27 Kg) 


-20°C to +55"C 

ALTITUDE: 

50, 000 ft. 

POWER REQUIREMENTS: 9VDC AT 80mA max (supplied by KR 87) 

7. Global Positioning System (GPS) 

The GPS system consists of a KLN 90B GPS receiver, a KLN 90190B data base, a KA 92 antenna, a 

message and waypoint annunciator, a GPS approach armlactive annunciator switch, and a GPS 

course OBSILEG annunciator switch. Reference Figure 14 for a 2-Tube EFS 40 system block 

diagram and Figure 15 for a 4-Tube EFS 40 system block diagram. 


97-00-00 

Page 19 

Revision AD

BENDIX/KINGG% IFRAVIONICSI KFC goo 


-1 < MESSAGE 8 WAYPOINT ANNUNCIATE 

rnl 

GPS 

&ACTIVE 

iwl 

COURSE OBS 

ANNUNCIATE 

BENDlXlfflNG 

KLN 908 

REFERENCE INDllVUAL 

SYSTEM BLOCK DIAGRAMS 

1 GPSANTENNA 

KA 92 

1 

- 

1 

EFS 40 LNAV DIGITAL OUTPUT 

EFS 40 DIGITAL OUTPUT 

1 

28VDC GPS POWER (L ESS BUS OR R DC BU 

I 

TRIP 

SUP1 

-1 < MESSAGE & WAYPOINT ANNUNCIATE 

mI 1 

GPS COURSE OBS SELECT 

Figure 14: GPS System Block Diagram (2-Tube EFIS) 

I/ 

ARM 8 ACTIVE ANNUNCIATE 

BENDlXlKlNG 

KLN 906 

1 GPSANTENNA 

KA 92 

I 

I 

I 28VDC GPS POWER (L ESS BUS OR R DC BUS) 

Gps ANTENN' 

> 


AIR DATADIGITAL INPUT 



NO. 1 EFS 40 LNAV DIGITAL OUTPUT 

NO 2 EFS40 LNAV DIGITAL OUTPUT 

A. KLN 90B GPS Receiver 

Figure 15: GPS System Block Diagram (4-Tube EFIS) 

The KLN 90B is a panel mounted, long range, GPS based airborne navigation system with a data 

base. The GPS receiver outputs navigation data to the EFS 40 via an ARlNC 429 format. The GPS 

receives altitude and air data information from the KAD 480 air data system as well as heading and 

course information from the EFS 40 system. 

Page 20 

Revision AD 


I



Table 8: KLN 90B Leading Particulars 

PART NUMBER 

KLN 90B 066-04031 -1121 


None 


KLN 90B (European BRNAV compliant) 066-04031 -1122 


None 



Height: 

2.000 in. 

Width: 

6.312 in. 

Length (Including connector): 

14.153 in. 


6.30 Ibs. 

TEMPERATURE RANGE: I to 33 VDC at 2.5 A max 

ALTITUDE: 

50, 000 ft. 

COOLING: 

4CFM minimum required 


11 to 33VDC, 12W typical 

27.5 VDC @ I .O A Nominal 

LIGHTING: 

28 VDC 286 mA max 

KLN 90B GPS RECEIVER OPERATION: 

( 5.080 cm) 

(16.032 cm) 

(35.949 cm) 

(2.86 Kg) 

1) GPS COURSE LEFTIRIGHT SELECT SWITCH - 4-Tube EFS 40 configurations have GPS 

COURSE LEFTIRIGHT select switch located next to the GPS receiver. This switch allows the 

No.1 or the No. 2 EFS 40 system to supply heading and course information to the GPS receiver. 

This switch allows either pilot to control the OBS course during a GPS approach or when 

operating in the OBS mode. 

DATABASEUPDATE: 

The KLN 90B Flight Manual Supplement requires a current data base to be installed in the KLN 90B 

unit for operation in IFR conditions. The data base is updated on a 28 day cycle. It is the 

responsibility of the ownerloperator to verify that the data base is current prior to flight. 

The KLN 90B data base can be updated in one of two ways. A new data base cartridge can be 

installed in place of the existing cartridge. The cartridge is available through the Honeywell 

International Inc. subscription program. 

The existing data base cartridge may also be updated using a laptop computer. The laptop computer 

must be IBM compatible, have an open COM 1 or COM 2 serial port, and have a 3.5" high density 

diskette drive (or the data can be downloaded through the internet.) Connect an IBM compatible 

laptop via the diagnostic connector located in the right hand side of the console. Use the 

200-05647-0022 diagnostic harness to interface the GPS connector to the PC and the diagnostic 

connector. Set the KLN 90B to the Set 0 page. Put the #I diskette into the PC. Cycle the power of the 

PC and follow the menu driven instructions. 

For data base subscriptions, contact Honeywell Navigation Services at 1-800-247-0230 within the 

United States or Canada or 913-712-3145 outside the United States or Canada. 


Page 21 

Revision AD

B. KA 92 GPS Antenna 

BENDIX/KiNGG" IFRAVIONICSI KFC goo 


The KA 92 GPS antenna is mounted on the horizontal tail on the NOTAR tail boom. 

Table 9: KA 92 Leading Particulars 

PART NUMBER 071 -01533-0200 


None 


Height: 2.70 in. ( 6.86 cm) 

Width: 0.70 in. ( 1.78 cm) 


WEIGHT: (With rack): 4.80 oz. (0.14 Kg) 

AIRSPEED RATING: 

600 Kts. TAS 

8. Radar Altimeter 

The radar altimeter system consists of a KRA 405 or KRA 405B radar altimeter transceiver and two 

KA 54A antennas. Reference Figure 16 for a system block diagram. 

28VDC L AVIONICS BUS RAD ALT POWER 

REFERENCE INDIVIDUAL 


AFCS 8 EFS 40 RAD ALT AND VALID ANALOG OUTPUT 

CP 470 CONTROL PANEL RALT TEST INPUT 

KRA 4051405B 

RADAR ALTIMETER 

LEFT HAND KA 54A 


ANTENNA 

RADAR ALTIMETER RECEIVE ANTENNA 

RIGHT HAND KA 54A 


ANTENNA 

RADAR ALTIMETER TRANSMIT ANTENNA 

Figure 16: RDR ALT System Block Diagram 

A. KRA 4051405B Radar Altimeter Transceiver 

The KRA 40514058 is a remote mounted radar altimeter transceiver that provides the pilot with above 

ground level (AGL) altitude data. The radar altimeter outputs altitude data to the EFS 40 and KFC 900 

flight control system. The radar altimeter receives a test input from the CP 470 EFS 40 control 

panel(s). 

Page 22 

Revision AD 


I

BENDIXlKIN6" IFR AVIONICS 1 KFC goo 


Table 10: KRA 4051405B Leading Particulars 

PART NUMBER 

KRA 405 066-1048-02 

Required Mods: 7, 8, 9, 10, 11 

Minimum software Level: 

None 

KRA 405B 066-01153-0101 


None 

Minimum software Level: 01/01 


Height: 5.25 in. (13.34 cm) 

Width: 3.25 in. ( 8.26 cm) 



TEMPERATURE RANGE: -54°C to +71 "C 

ALTITUDE: 

55, 000 ft. 


27.5 VDC + 20% AT 850 mA 

B. KA 54A Radar Altimeter Antenna 

Table 11 : KA 54A Leading Particulars 

PART NUMBER 071 -01501-0000 


None 

PHYSICAL DIMENSIONS: 

Height: 0.90 in. (2.28 cm) 

Width: 3.50 in. (8.90 cm) 

Length: 3.65 in. (9.30 cm) 

WEIGHT: 0.20 Ibs. (0.09 Kg) 


-54°C to +85"C 

The KA 54A radar altimeter antennas interface to the transceiver. One antenna is connected to the 

transmit side of the transceiver and the other antenna is connected to the receive side of the 

transceiver. 

Transponder (XPDR) 

The XPDR system consists of a KT 70 non-diversity Mode S transceiver or KT 71 ATCRBS transceiver, 

an EEPROM board and a CI-105-6 XPDR antenna. Both the transponder and the antenna are existing 

aircraft equipment. 

The XPDR receives Gillham altitude data from the KAD 480 air data system. The XPDR also receives a 

suppression input from the KN 63 DME. The EEPROM board is used to store aircraft specific data, such 

as maximum airspeed and Mode S address (KT 70 only.) 

The EEPROM board is installed as part of the IFR avionics package. The EEPROM board stores the 

aircraft's address and minimum and maximum airspeed values. 


97-00-00 

Page 23 

Revision AD

BENDIX/KlNG@' IFRAVIONICSI KFC goo 


Table 12: KT 70 1 KT 71 Leading Particulars 

PART NUMBER 

KT 70 

066-01141-0101 or 

066-01141-0201 


None 


KT 71 

066-01141-5101 or 

066-01141-5201 


None 



Height: 1.625 in. ( 4.128 cm) 

Width: 6.302 in. (16.007 cm) 

Length: 11.608 in. (29.484 cm) 

WEIGHT: 3.88 Ibs. (1.76 Kg) 


-20°C to +55"C 

ALTITUDE: 

50, 000 ft. 

COOLING: 

No forced-air cooling required, but recommended. 


1.25A @ 27.50VDC 

OPERATION: (Note: The KT 71 transponder does not have Mode S capability) 

1) MODE SELECT KNOB - Rotating the knob from OFF to some other mode will energize the unit. 

The aircraft address and maximum airspeed will be displayed in the following sequence. 

a) The altitude window shall display "AAI" and the ident window shall display the first four (4) 

octal digital of the aircraft address for two (2) seconds. 

b) The altitude window shall display "AA2" and the ident window shall display the last four (4) 

octal digits of the aircraft address for two (2) seconds. 

c) The altitude window shall display the lower limit and the ident window shall display the upper 

limit of the maximum airspeed range for two (2) seconds. 

2) OFF POSITION - The unit is powered off in this position 

3) STANDBY POSITION - The unit is energized but is inhibited from replying to any interrogation. 

"SBY is annunciated on the display and the altitude display is disabled. 

4) TEST POSITION - The unit will illuminate all segments for at least four (4) seconds. At this time 

the EEPROM data is verified. 

5) GROUND POSITION - The unit shall inhibit ATCRBS interrogations and reply to all valid Mode S 

interrogations. The vertical status bit is set in downlink format 0. The ID 4096 code is displayed 

on the right side of the display and the altitude on the left side. "GND" is annunciated on the 

display in this mode. 

6) ON POSITION - The unit is able to reply to all valid Mode A, Mode C and Mode S interrogations, 

however, the altitude information of Mode C replies and altitude fields of MODE S replies are 

suppressed. The altitude display is blank and the ID 4096 code is displayed on the right. "ON" is 

annunciated on the display in this mode. 

7) ALTITUDE POSTION - The unit is able to reply to all valid Mode A, Mode C and Mode S 

interrogations. The altitude information will be sent in Mode C and the altitude field of Mode S 

replies. The ID 4096 code will be displayed on the right and the altitude displayed on the left. 

8) PUSH VFR - Momentarily depressing the mode select knob causes the pre-programmed VFR 

code to supercede whatever code was previously entered. The ID code will immediately be 

accepted for interrogation reply sequence. 

Page 24 

Revision AD 


BENDIXlKIN6" IFRAVIONICSI KFC goo 


9) IDENT PUSHBUTTON - Depressing the "IDT" pushbutton causes the special position 

identification pulse (SPI) to be appended to Mode A replies and sets SPI bit in the Flight Status 

field of Mode S downlink formats 4 and 5 replies for a period of 18 seconds. During this period 

the KT 70 will annunciate the "R". 

10) IDENT CODE SELECTOR KNOBS - The ID 4096 identification code, ID code, for the aircraft is 

displayed in the right hand position of the display, the ident window. There are four (4) ident code 

selector knobs. Each knob selects a separate digit of the 4096 code. 

The ID code may be selected in the Standby, Ground, On and Altitude modes. Five (5) seconds 

after the ID code has been selected or immediately after the "ID7 pushbutton has been pressed 

the new code is written into nonvolatile memory so that the code will not change during power 

interruptions. After the ID code has been saved, the new code can be transmitted. 

10. Attitude and Heading Reference System (pAHRS) 

The pAHRS system consists of a LlTEF GmbH LCR-92s attitude and heading reference unit (AHRU), 

a KMT 112 flux valve (magnetic sensor unit or MSU) and a MSU calibration PROM (CAL PROM). 

A. LCR-92s AHRU 

The LCR-92s AHRU is a remote mounted unit. The AHRU is a strapdown inertial measurement 

system using fiber-optic rate gyros which are "strapped down" to the principal aircraft axes. A digital 

computer mathematically integrates the rate data to obtain heading, pitch and roll. A dual axis internal 

level sensor and the KMT 112 flux valve provide long term references to the system. Reference 

Figure 17 for a single AHRS system block diagram. 

The 4-Tube EFS 40 configuration incorporates a second LCR-92S, KMT 112, CAL PROM, and 

installation tray. An AHRS 112 switch is also provided for each pilot to enable the selection of the 

cross-side AHRS system for display on the EFS 40. Reference Figure 18 for a dual AHRS system 

block diagram. 


Page 25 

Revision AD


EFS 40, AFCS AND WEATHER RADAR DIGITAL OUTPUTS 



AlRlGROUND LOGIC INPUT 

28VDC R ESS BUS AHRS PRIMARY POWER 

28VDC L GEN BUS AHRS AUXILIARY POWER 

NO. 1 LCR-92s 

ATTITUDE & HEADING 

REFERENCE UNIT 

NO. 1 KMT 112 

FLUX VALVE 

FLUX VALVE EXCITATION 

FLUX VALVE INPUT 

DGISLAVED MODE SELECT & CCWICW SLAVING SELECT 

RELE*SE Ww7 

AHRS2 TEST AHRS l 

Figure 17: Single AHRS System Block Diagram 

Page 26 







U 

AIWGROUND LOGIC INPUT 1 

28VDC R ESS BUSAHRS PRIMARY POWER 

28VDC L GEN BUS AHRS AUXILIARY POWER 

11 FLUX VALVE INPUT 1 

NO. 1 KMT 112 

FLUX VALVE 

I 


NO. 1 LCR-92s 

ATTITUDE 8 HEADING 

REFERENCE UNlT 

1 

I 

DGISLAVED MODE SELECT 8 CCWICW SLAVING SELECT 

DGISLAVED MODE SELECT 8 CCWICW SLAVING SELECT 



U 

AlRlGROUND LOGIC INPUT 1 

28VDC BAmERY BUS AHRS PRIMARY POWER 

NO. 2 LCR-92s 

ATTITUDE 8 HEADING 

REFERENCE UNlT 

28VDC R GEN BUS AHRS AUXILIARY POWER 

NO. 2 KMT 112 

FLUX VALVE 


FLUX VALVE INPUT 

, 

Figure 18: Dual AHRS System Block Diagram 

The CAL PROM stores the MSU calibration coefficients after the successful completion of the MSU 

calibration procedure. 

The AHRU outputs aircraft attitude, heading, and flight dynamic information to the EFS 40, KFC 900 

and RDR 2000 systems. The flux valve provides heading information to the AHRU. The CAL PROM 

stores the magnetic heading correction data. 

The AHRS heading modes can be selected via the console mounted avionics switch panel. The 

switch panel has the directional gyrolslaved mode (DGISLVD) switch as well as the slew 

clockwise1counter-clockwise (CWICCW) switch. 


Page 27 

Revision AD



Table 13: LCR 92s Leading Particulars 

PART NUMBER 

LCR-92s 141852-1011 or 141852-1022 

(may be either unit for dual systems) 

Calibration Prom 124282 

Mounting Tray wIFan 140691 

PHYSICAL DIMENSIONS (With Mounting Tray): 

Height: 

14.05 cm max 

Width: 

10.60 cm max 

Length: 

34.35 cm max 

WEIGHT: 

2.8 Kg 


UNKNOWN 

ALTITUDE: 

UNKNOWN 

COOLING: 

No forced-air cooling required, but recommended. 


28VDC, 25W max 

B. KMT 11 2 Flux Valve 

The KMT 112 flux valve is a remote mounted unit that senses the direction of the earth's magnetic 

field and transmits this data to the AHRU. 

Table 14: KMT 112 Leading Particulars 

PART NUMBER 071 -1052-00 

Required Mods: 1 


Height: 2.30 in. (8.55 cm) 

Diameter: 3.37 in. 10.60 cm max 

WEIGHT: 0.30 Ibs. (0.15 Kg) 


-55°C to +55"C 

ALTITUDE: 

-1000 to 40,000 ft. 


12 - 23VRMS, 400Hz from LCR-92s 

Page 28 





I 1 

Digital Air Data System 

The KAD 480 digital air data system consists of a KDC 481T digital air data computer, a KDC 481T 

adapter module, a KAV 485 altimeterNSI and altitude preselector and a temperature probe. 

Reference Figure 19 for a system block diagram. 



'. 

AFCS DIGITAL INPUT 

,,, \ \ 1 28VDC R ESS BUS ADC POWER I I 28VDC R ESS BUS ADC POWER > 

L/ 

- 

DIGITAL BAR0 CORRECTION AND VERTICAL SPEED SELECT 

DIGITAL ALTITUDE & VERTICAL SPEED 

500 OHM ALTITUDE ALERT AUDIO \ 

KDC 481T 

AIR DATA COMPUTER 

1 TEMPERATURE PROBE 

I > 

1 TEMPE-RE PRO- INPU; 

EXISTING IDDS 

GILLHAM ALTITUDE 

Figure 19: Air Data System Block Diagram 

A. KAV 485 AltimeterNertical Speed Indicator 

The KAV 485 altimeterlvertical speed indicator contains a round dial and pointer type display for 1000 

foot altitude, a round dial and pointer display for vertical speed indicator, a selection window for 

barometric corrections, a selection window for altitude preselect and a window for digital altitude 

readout. The unit also houses two concentric knobs for crew input of selected altitude, barometric 

correction, and selected vertical speed, and buttons for selection of altitude hold and vertical speed 

flight director modes. The leading particulars are given in Table 15. 

Page 29 

Revision AD



Table 15: KAV 485 Leading Particulars 



None 


PHYSICAL DIMENSIONS (Without connector): 

Height: 5.975 in. (15.18 cm) 

Width: 3.175 in. (8.065 cm) 

Length: 10.20 in (25.91 cm) 

WEIGHT (Without connector): 3.8 Ibs. (1.72 kg) 


-35°C to +70°C 

ALTITUDE: 

-1000 to +55,000 ft. 

VERTICAL SPEED RANGE: 

+ 3500 ft per minute 

ALTITUDE SELECT RANGE: 

0 to 55,000 ft in 100 ft increments 

BAR0 CORRECT RANGE: 

22 to 32 in Hg or 745 to 1084 HPa 

VERTICAL SPEED SELECT RANGE: 

0 to + 3500 ft per minute in 100 or 1000 ft per min increments 


28 VDC @ 0.6 amps 

LIGHTING: 

28 VDC @ 0.30 amps 

1) PHOTOCELL - Dims digital readout displays automatically. 

2) DIGITAL ALTITUDE DISPLAY - Displays present altitude up to 65,000 feet in 20 foot increments 

when the vertical speed is below 1000 fpm and in 100 foot increments when the vertical speed is 

above 1000 fpm. When the altitude is invalid, a FAIL message appears in this display along with 

the appearance of the ALT flag. 

3) ALTITUDE ALERT (ALERT) ANNUNCIATOR - The ALERT annunciator is illuminated 1000 feet 

prior to the selected altitude, goes out 300 feet prior to the selected altitude and illuminates 

momentarily when the selected altitude is reached. Once the selected altitude is reached, light 

illumination signifies that the 300 foot "safe band" has been exceeded and will remain on until 

1000 feet from the selected altitude. The ALERT light is accompanied by a second aural tone 

anytime the light initially comes on when the selected altitude is reached. 

4) ALTITUDE SELECTIDENSITY ALTITUDE DISPLAY - Displays selected altitude for the altitude 

alert function. Display may be changed by the altitude select knob in 100 foot increments. 

Density altitude is displayed for 5 seconds at the end of the Push-To-Test sequence. (The 5 

second display may be obtained anytime simply by pressing the PUSH BARO TEST button twice; 

once to initiate the test sequence and the second to terminate it.) 

5) DENSITY ALTITUDE (DEN) ANNUNCIATOR - The DEN annunciator is illuminated anytime the 

associated altitude display is density altitude. Density altitude is displayed for 5 seconds at the 

end of the Push-To-Test sequence. (The 5 second display may be obtained anytime simply by 

pressing the PUSH BARO TEST button twice; once to initiate the test sequence and the second 

to terminate it.) 

6) VERTICAL SPEEDIALTITUDE SELECT KNOB - Dual concentric knobs with the inner knob 

having an in (altitude select) and an out (vertical speed) position. In the out position, a bright 

orange band around the knob is visible to identify the knob position. Rotating the inner knob 

changes the display in 100 foot increments with roll over into the 1000 digits. Rotating the outer 

knob changes the display in 1000 foot increments with roll over in the 10,000 digits. 

7) REMOTE ALTITUDE SELECT (ALT SEL) FLIGHT DIRECTOR MODE SELECTOR BUTTON - 

Duplicate button for selecting altitude (same as on the KMS 540 mode selector panel). 

8) VERTICAL SPEED BUG - Indicates the vertical speed selected for a reference. The bug 

(normally stowed behind the shroud at the 3 o'clock position on the VS display) will come into view 

when the inner concentric vertical speed select knob is pulled out or when the VS flight director 

mode is engaged. 

Page 30 

Revision AD 




9) REMOTE VERTICAL SPEED (VS ENG) FLIGHT DIRECTOR MODE SELECTOR BUTTON - 

Duplicate button for selecting vertical speed (same as on the KMS 540 mode selector panel). 

10) VERTICAL SPEED INDICATOR NEEDLE - Indicates instantaneous vertical speed. 

11) ALTIMETER (BARO) SETTING KNOBIPUSH-TO-TEST (PUSH TEST) BUTTON - Dual 

concentric knobs. A Push-To-Test button located at the center of the inner knob will activate a 

system self test procedure. 

12) VERTICAL SPEED (VS) FLAG -Will be in view when vertical speed information is invalid. 

13) ALTIMETER SETTING DISPLAY - Display altimeter setting in either inches of mercury (IN HG) or 

in hectal Pascal's (HPa). The range of settings are from 22.00 to 32.00 IN HG or from 745 to 

1084 HPa. 

14) 100 FOOT ALTITUDE INDICATOR NEEDLE - lndicates altitude in 100 foot increments with 

resolution to the nearest 10 feet. 

15) ALTIMETER (ALT) FLAG -Will be in view when altitude information is invalid. 

16) INCHES OF MERCURYIHECTAL PASCAL SELECT PUSHBUTTON - Selects either inches of 

mercury (IN HG) or hectal Pascal's (HPa) for the altimeter setting display. 

B. KDC 481T Air Data Computer 

The remote mounted KDC 481T takes in pitot and static pressures from the right side of the pitot 

static system and the outside air temperature from the temperature probe, processes the data and 

supplies the KAV 485 AltitudeNertical Speed Indicator (ALTNSI) with altitude, vertical speed, density 

altitude, and altitude alerter information. The KDC 481T has an adapter module that tailors its 

operation for a specific aircraft. The KDC 481T also supplies air data information to the GPS, the 

IIDS, the transponder and the KFC 900 system. The leading particulars are shown in Table 16. 

Table 16: KDC 481T Leading Particulars 

PART NUMBER 

KDC 481T 065-0082-12 


None 


KDC 481T Adapter Module 065-05041 -0025 

PHYSICAL DIMENSIONS (With rack and connector): 

Height: 3.25 in. (8.26 cm) 

Width: 5.43 in. (13.8 cm) 

Length: 13.63 in. (34.62 cm) 

WEIGHT (Without connector): 4.8 Ibs. (2.18 kg) 


-55°C to +70°C 

ALTITUDE: 

-1000 to +55,000 ft. 


28 VDC @ 0.5 amps 

The KDC 481T Adapter Module must be removed from the KDC 481T whenever the KDC 481T is sent 

in for repair, servicing or is replaced. The KDC 481T Adapter Module must be installed into the new or 

loaner KDC 481T prior to installation into the aircraft. Reference the Avionics Removal/lnstallation 

section of this manual for instructions on the removal and installation of the Adapter Module. 

12. Electronic Flight Information System (EFIS or EFS) 

The EFS 40 electronic flight information system consists of an SG 465 symbol generator (SG), an ED 

461 electronic horizontal situation indicator (EHSI), an ED 462 electronic attitude direction indicator 

(EADI), a CP 470 control panel (CP), a panel mounted composite display select (CMPST) switch and 

a collective mounted pitch attitude synchronization (PITCH SYNC) switch. Reference Figure 20 for a 

system block diagram of a 2-Tube EFS 40 system. An option for a second EFS 40 is available and 

consists of the same components as a single EFS 40 system. Reference Figure 21 for a system 

block diagram of a 4-Tube EFS 40 system. 

Page 31 

Revision AD

BENDIX/KINGd IFR AVIONICS I KFC goo 


EADl VIDEOlMODEIDEFLECTIONlFAULTlPOWER 20 ---- 20 

COMPOSITE MODE SELCT 

NO 1 SG 465 

SYMBOL GENERATOR 

CONTROL PANEL MODEIHEADINGICDURSE 

fn 

f2 

+ 

EHSl VIDEOIMODE/DEFLECTIDNlFAULT/POWER I? 

6 

", 

DECISION HEIGHT SELECTION 

RADAR ALTIMETER TEST 

C 

ADF. 

AFCS. AHRS, GPS, MARKER, VHF NAV. 8 WEATHER RADAR DIGITAL INPUTS 

DME. 8 RADAR ALTIMETER ANALOG INPUTS REFERENCE INDIVIDUAL 


AFCS, GPS. WEATHER RADAR DIGITAL OUTPUTS 

DH DISCRETE OUTPUT 

>J 

28VDC RT EADl POWER RT EFlS APISAS LT EFlS 28VDC R ESS BUS EADl POWER 

28VDC RT EHSl POWER 

28VDC LESS BUS EHSl POWER 

26VAC 400HZ REF 1 HIC 

CONFIGURATION MODULE DATA 

CONFIGURATION MODULE 

FAN POWERIGROUND 

COOLING FAN 

Page 32 

Revision AD 

Figure 20: 2-Tube EFlS System Block Diagram 

97-00-00, 


BENDIXIKlNNGe IFRAVIONICSI KFC 900 


EADl VlOEOIMODEIOEFLECTIONlFAULTlPOWER 

NO 2 SG 465 

SYMBOLGENERATOR 

I I 

COMPOSITE MODE SELCT 

CONTROL PANEL MODEMEADlNGlCOURSE 

Ic 

EHSl VlDEOMODElDEFLECTlONlFAULTlPOWER 

IC 

DECISION HEIGHT SELECTION 

PITCH ATTITUDE SYNC SELECT 

Ic 

ADF. 

IC 

AFCS. AHRS. GPS, MARKER, VHF NAV, &WEATHER RADAR DIGITAL INPUTS 

DME, 8 RADAR ALTIMETER ANALOG INPUTS REFERENCE INDIVIDUAL 


MCS. GPS. WEATHER RADAR DIGITAL OUTPUTS 

DH DISCRETE OUTPUT 

I 

28VDC LT EADl POWER RT EFlS APlSAS LT EFlS 28VDC L GEN BUS EADl POWER 

26VCC LT EHSl POWER 

26VCC L GEN BUS EHSl POWER 

26VAC 400HZ REF 1 WC 

NO 1 AHRS SELECT 

1 < ' CONFIGURATION MODULE DATA 

>I C O N F I ~ ~ ~ ~ ~ ~ oI 

o U L E 

FAN POWEWGROUND > 1 

c"&iggN 

CROSSTALK BUS 

FLT DIR LEFTIRIGHTSELECT 

v 

NO. 1 SG 465 

SYMBOLGENERATOR 

NO 2 AHRS SELECT 

Figure 21: 4-Tube EF18 Systern Block Diagram 

Page 33 

Revision AD

A. SG 465 Symbol Generator 



The SG 465 Symbol Generator is a microprocessor driven, remote mounted central control unit which 

receives information from aircraft attitude, navigation, guidance and weather radar system sources. 

This information is then processed for display on CRT display units in the form of X/Y deflection drive 

signals and red-green-blue video signals. It also outputs data to radar, flight directorlautopilot, RNAV, 

LNAV and other navigation systems. A built-in test system continuously monitors system operation 

and assures that valid data is displayed on the display units. The SG 465 is an ARlNC 318 ATR short 

case located in the aft cabin cargo area. A configuration module is installed in the SG rack containing 

all the configuration information for the SG. This module is programmable but is not accessible. The 

SG 465 requires forced air cooling provided by a rack mounted cooling fan. The leading particulars 

are shown in Table 17. 

Table 17: SG 465 Leading Particulars 

PART NUMBERS 066-04021 -1113 


None 

Minimum Software Level 13/01 


Height: 

8.210 in. 

Width: 

3.821 in. 

Length: 

18.29 in. 

WEIGHT (With fan and rack): 

11.13 Ibs. 


-55°C to +70°C 

ALTITUDE: 

55,000 ft. 


+27.5 + 0.5 VDC 

EHSI: 3.0 Amps, EADI: 2.6 Amps 

26 VAC, 400Hz, AT lOmA maximum 

(20.850 cm) 

( 9.705 cm) 

(46.457 cm) 

(5.05 kg) 

B. ED 461 EHSI Display 

The ED 461 is a panel mounted unit used to display flight information. It uses a four inch color CRT 

and converts XN axis deflection signals and red-green-blue video signals from the SG(s) to a video 

display. The ED 461 is used as a Horizontal Situation Indicator (HSI) and has front panel pushbutton 

controls, course and heading controls and a brightness control. The leading particulars are shown in 

Table 18. 

Table 18: ED 461 Leading Particulars 

PART NUMBER 066-03123-1600 


None 


None 


Height: 

4.175 in. 

Width: 

4.240 in. 

Length: 

12.875 in. 

WEIGHT: 

5.4 Ibs. 


-40°C to +55"C 

ALTITUDE: 

55,000 ft. 

POWER REQUIREMENTS: Supplied By SG 465 

LIGHTING: 

28VDC at 0.15 Amps maximum 

(1 0.604 cm) 

( 10.770 cm) 

(32.703 cm) 

(2.45 kg) 

Page 34 

Revision AD 




Displays: 

1) COLOR KEYING - Symbology is color coded to indicate the source of data on the EHSI. Data 

which is coded includes the distance, ground speed, time-to-station, digital course readout, NAV 

source select annunciator, course pointer, course deviation, glideslope pointer, inbound course 

line and VORTAC symbol. The following colors are used: 

GREEN 

ON-SIDE DATA. 

YELLOW 

CROSS SIDE DATA. 

CYAN 

LNAV data (Green when approach approved data is displayed). 

2) NAVIGATION SOURCE ANNUNCIATION - A vertical three or four letter alphanumeric readout 

which indicates the type of navigation system selected. 

3) WIND VECTOR - When the aircraft is equipped with the appropriate LNAV equipment (LORAN 

and/or GPS), an optional full time wind vector indicating approximate wind direction and speed 

may be displayed in white in the upper left corner below the selected course. Wind vector 

information will only be available when valid data is provided by the LNAV. The information 

provided by this vector is advisory only. It is NOT intended for use during approach as critical 

flight data because it will become inaccurate during altitude changes. 

4) DIGITAL COURSE DISPLAY - An alphanumeric readout annunciates the letters CRS and 

indicates the selected navigation course in degrees. When in a MAP display mode, the course 

pointer is not displayed and the digital portion of this display is the only reference for selected 

course. A Desired Track (DTK) readout replaces CRS in the LNAV mode. 

5) COMPASS CARD - Rotating 360" white compass scale referenced to white triangular heading 

index (lubber line). 

6) HEADING INDEX - lndicates current aircraft heading. 

7) HEADING SELECT "BUG" - A notched orange symbol that is normally rotated around the 

compass scale by the heading select knob on the control panel. In the 360" compass mode, a full 

time digital readout of the selected heading is displayed below the vertical deviation scale position. 

In the ARC mode, a digital heading readout is displayed when the heading bug is not completely 

in view. The digital readout will be positioned just inside the compass scale on the side nearest 

the heading bug. Once set, the heading bug rotates the compass card. 

8) DME DISPLAY - The DME readout for the primary NAV source. lndicates distance to stationlwaypoint, 

ground speed and time to station/waypoint. If an LNAV (LORAN and/or GPS) is 

selected as primary NAV sensor, display will be LNAV distance. 

9) BEARING POINTER 1 - Rotating light blue single bar pointer. Points in the direction of the VOR 

1, LNAV waypoint, or ADF (NDB) ground station. 

10) GLIDESLOPE DISPLAY - Stationary white vertical dotted scale. Provides scale reference for 

green GLIDESLOPE DEVIATION POINTER. lndicates glideslope beam center to which aircraft is 

to be flown. Active when NAV receiver is tuned to a localizer frequency. 

11) LATERAL NAVIGATION DISPLAY - Consists of Course Pointer, Course Deviation Indicator, 

Lateral Course Deviation Scale and TO-FROM Indicator. 

12) BEARING POINTER 2 ANNUNCIATION - Color keyed bearing pointer sensor annunciation. DME 

distance also provided if applicable. 

13) BEARING POINTER 2 - Rotating magenta double bar pointer. Points in the direction of VOR 2, 

LNAV waypoint, or ADF (NDB) ground station. 

14) BEARING POINTER 1 ANNUNCIATION - Color keyed bearing pointer sensor annunciation. DME 

distance also provided if applicable. 

15) SYMBOLIC AIRCRAFT - An orange symbolic aircraft provides a visual reference of the aircraft 

present position in relationship to the deviation bar. 


Page 35 

Revision AD



16) HEADING SELECT DISPLAY - Digital readout of the selected heading. 

17) EHSl CONTROL 

Control Functions: 

18) NAVIGATION (NAV) SENSOR SELECT BUTTON - When pressed sequentially, selects VOR (or 

LOC), LNAV (if installed) or ADF for display on the EHSI. 

19) NAVIGATION (112) SYSTEM SELECT BUTTON - When pressed will alternately select navigation 

receiver No. 1 or No. 2 for presentation. 

20) SELF TEST (TSTIREF) BUTTON - When pressed and held for ten seconds, activates an internal 

self test and displays all fault presentations. Upon completion, PASS or FAlL will be annunciated 

on both tubes. To clear the PASS or FAlL annunciations, the TSTIREF button must be pressed 

again. (The EADl will clear automatically in 5 seconds). 

If a map presentation (ARC or HSI) button has already been selected and the LNAV is the 

selected source for presentation on the course pointer, if the TSTIREF is pressed (for less then 

three seconds) it will sequentially select available MAP formats in the following manner: 

a) First push - displays the MAP annunciator (i.e. FPL, AIRPORTS or NAVAIDS) for five 

seconds. 

b) FPL - Flight plan waypoints with ICAO identifiers. 

c) AIRPORTS - Flight plan waypoints and the nearest airports as defined by the LNAV. ICAO 

identifiers will be assigned to the TO WPT only and the airports. 

d) NAVAIDS - Flight plan waypoints and the nearest VOR's and VORTAC's. ICAO identifiers will 

be assigned to the TO WPT only and the NAVAIDs. 

Second (or subsequent) push (within 5 seconds) - selects for display the next sequential MAP 

display mode in the sequence listed under a. above. 

21) RANGE UP BUTTON - Selects the next longer distance range to be displayed when in the NAV 

MAP mode of operation. 

22) RANGE DOWN BUTTON - Selects the next shorter distance range to be displayed when in the 

NAV MAP mode of operation. 

23) ARC MODE SELECTOR BUTTON - When pushed, converts the standard 360" compass rose 

presentation (if displayed) to a large scale, 85" sector presentation for expanded viewing of the 

compass roselmoving map display in the vicinity directly ahead of the aircraft. Sequential button 

pushes provide the following format changes: (1) compass arc, (2) compass arc with moving map 

and (3) back to compass arc. If pushed when the EHSl is in the 360" HSI mode, the initial arc will 

duplicate the existing 360" HSI format. 

24) HEADING SELECT (SYNC) KNOB - Rotated to position the heading bug. Pushing in on the 

center of the knob will sync the bug to the aircraft's present heading under the lubber line. 

25) NO. 2 BEARING POINTER SELECT BUTTON - Sequentially selects navigation sensors for 

waypoint bearing presentation in the manner of an ADF or RMI. The pointer is magenta and 

double barred. The sequence of presentation includes: (1) declutter, (2) VOR 2, (3) LNAV, (4) 

ADF, and (5) back to declutter. Upon successful signal acquisition the pointer will appear, along 

with a pointer assignment annunciation in the lower right hand side of the display. Should a 

flagged condition exist, the pointer will declutter and the pointer assignment annunciation will be 

flagged. If VOR 2 is selected and a LOC frequency is tuned , both the pointer and the assignment 

annunciation will declutter. If VOR 2 is selected along with a MAP presentation, the pointer will 

declutter and a diamond shape symbol will appear on the map field (if in range). If not in range, 

the pointer will remain. 

Page 36 

Revision AD 




26) DISPLAY BRIGHTNESS (BRT) KNOB - Rotates to control display brightness. (Bezel lighting is 

controlled through an airframe brightness control). 

27) NO. 1 BEARING POINTER SELECT BUTTON - Sequentially selects navigation sensors for 

waypoint bearing presentation in the manner of an ADF or RMI. The pointer is light blue and 

single barred. The sequence of presentation includes: (1) declutter, (2) VOR 1, (3) LNAV, (4) 

ADF, and (5) back to declutter. Upon successful signal acquisition the pointer will appear, along 

with a pointer assignment annunciation in the lower left hand side of the display. Should a flagged 

condition exist, the pointer will declutter and the pointer assignment annunciation will be flagged. 

If VOR 1 is selected and a LOC frequency is tuned , both the pointer and the assignment 

annunciation will declutter. If VOR 1 is selected along with a MAP presentation, the pointer will 

declutter and a diamond shape symbol will appear on the map field (if in range). If not in range, 

the pointer will remain. 

28) COURSE SELECT (DIR) KNOB - Rotated to position the course pointer. Pushing in on the center 

of the knob will slew the course pointer on a direct-to course to the selected navigation facility. 

CRS pointer is not active with an LNAV presentation unless the LNAV is in manual OBS mode. 

29) 360" HSI MODE SELECTOR BUTTON - When pushed converts the sector presentation (if being 

displayed) to a standard 360" compass rose. If pushed when already in the 360" HSI mode, will 

select the compass rose with moving map display. Repeated button pushes will continuously 

sequence through the available 360" HSI formats. 

30) COMPOSITE DISPLAY - A reversionary attitudelnavigation display presented on both display 

tubes whenever the composite mode is selected. The following paragraphs describe the various 

displays that composite mode presents. 

31) COMPOSITE DISPLAY HEADING BUG - Moves horizontally along the heading tape. 

32) DIGITAL HEADING BUG - Present in the composite mode. 

33) DIGITAL COURSE DISPLAY - An alphanumeric readout annunciates the letters CRS and DTK 

and indicates the selected navigation courseltrack in degrees. Display is color keyed to the 

selected navigation sensor. 

34) DME DISPLAY - The DME readout for the primary NAV source or WPT distance for GPS. 

35) LATERAL NAVIGATION DISPLAY - Consists of Course Deviation Indicator, Lateral Course 

Deviation Scale and either a white TO or FR annunciation when in non-ILS modes. 

36) NAVIGATION SOURCE ANNUNCIATOR - A vertical three or four letter alphanumeric readout 

which indicates the type of navigation system selected (Green = on-side, Yellow = cross-side). 

37) SELECTED COURSE POINTER - Indicates the selected course. Display is color keyed to the 

selected navigation sensor. 

C. ED 462 EADl Display 

The ED 462 is a panel mounted unit used to display flight information. It uses a four inch color CRT 

and converts X/Y axis deflection signals and red-green-blue video signals from the SG(s) to a video 

display. The ED 462 has no front panel controls and has an inclinometer mounted on the front panel. 

The leading particulars are shown in Table 19. 


97-00-00 

Page 37 

Revision AD



Table 19: ED 462 Leading Particulars 

Part Number 066-03125-2600 


None 


None 


Height: 4.175 in. (10.604 cm) 

Width: 4.240 in. ( 10.770 cm) 

Length: 12.875 in. (32.703 cm) 

WEIGHT: 5.4 Ibs. (2.45 kg) 


-40°C to +55"C 

ALTITUDE: 

55,000 ft. 

POWER REQUIREMENTS: Supplied By SG 465 

LIGHTING: 

28VDC at 0.15 Amps maximum 

Displays: 

1) AIRCRAFT SYMBOL - Fixed orange aircraft reference symbol. 

2) ATTITUDE DISPLAY - Upper blue section represents the sky and the lower brown section 

represents the ground. A white horizontal line represents the horizon. These move with respect to 

the aircraft symbol to display actual pitch and roll attitude. 

3) ROLL ATTITUDE (BANK ANGLE) - Aircraft roll attitude is displayed by means of a bank angle 

pointer moving in relation to a stationary scale with a zero bank index. The scale is graduated at 

0, 10,20,30,45 and 60 degrees. 

4) RADAR ALTIMETER READOUT - White alpha-numeric readout in upper right corner of EADI. 

Annunciates the letters RA and displays altitude in feet if valid radar altimeter data is available. 

Radar altitude readout above 100 feet is indicated in 10 foot increments. Below 100 foot, 5 foot 

increments are displayed. Declutters above 2,500 feet AGL. 

5) PITCH ATTITUDE - Pitch attitude is displayed in white 5 degree increments above and below the 

horizontal line in the blue and brown sections which are referenced to fixed aircraft symbol. 

6) HEADING SCALE - Moving white compass scale. Moves on simulated horizon with reference to 

fixed aircraft symbol. 

7) GLIDESLOPE DISPLAY - Stationary white vertical dotted scale. Provides scale reference for 

green GLIDESLOPE DEVIATION POINTER. Indicates glideslope beam center to which aircraft is 

to be flown. Active when NAV receiver is tuned to a localizer frequency. 

8) RISING RUNWAY - The symbolic Rising runway will be displayed in the lower center of the 

display just above the LOC lateral deviation scale. The center line of the symbolic rising runway 

represents ILS fly-to command. If the radar altimeter provides height above the ground 

information to the EFS 40, the rising runway symbol will start increasing in size at 200 feet AGL 

and will continue to increase in size to 0 feet AGL. When the on-side ILS is selected as the 

primary NAV sensor, the rising runway will be green in color. If the off-side NAV sensor is 

selected, the rising runway will be yellow in color. 

The rising runway will be displayed unless one of the following conditions exists, in which case the 

deviation bar will be displayed: 

a) No radar altimeter 

b) Radar altimeter is not being displayed, above 2,500 feet AGL or not providing computed data 

c) Radar altimeter is below minimum altitude, white dashes are displayed 

d) Radar altimeter is flagged; red dashes displayed 

Page 38 

Revision AD 


BENDIX/KINGG" IFRAVIONICS! KFC goo 


In the event the lateral deviation information becomes invalid or failed, the rising runway or D-bar 

and lateral deviation scale are removed and the lateral deviation scale is replaced with a red "X. 

9) EXPANDED LATERAL DEVIATION SCALE - Located at the bottom center of the EADI, displayed 

in white, with 4 hollow circles and a center diamond is the expanded lateral deviation scale. This 

scale also provides a reference for ILS lateral deviation as displayed on the EHSI. When the 

selected course and aircraft heading differ by more than 105 degrees, the leftlright sensitivity is 

reversed and a green (on-side) or yellow (off-side) BC is displayed left of the center diamond to 

alert the pilot that back course information is being displayed. 

10) SKID INDICATOR - Lighted spirit level to indicate the aircraft's yaw trim condition. 

11) RATE OF TURN DISPLAY - The rate of turn scale is composed of three evenly spaced unfilled 

white rectangles. The rate of turn pointer is an equally sized white filled rectangle balanced atop a 

smaller white filled rectangle. The rate of turn indicator will not be displayed when the composite 

reversionary mode is selected for display. If rate of turn data becomes invalid, the pointer and 

scale will be removed and replaced with a red "X". 

12) MARKER BEACON, ANNUNCIATOR - Alpha readout. Annunciates the letters OM in blue when 

the aircraft is over outer marker beacon; MM in orange when the aircraft is over middle marker 

beacon; and IM in white when aircraft is over inner marker beacon. 


I 

Page 39 

Revision AD

BENDIX/KINGe IFRAVIONICS I KFC goo 


D. CP 470 Control Panel 

The CP 470 control panel is a panel mounted unit that gives the pilot control of the EADl brightness, 

the radar altimeter decision height (DH) setting and the radar altimeter test function. 

Table 20: CP 470 Leading Particulars 

PART NUMBER 071 -01517-0200 


None 


None 


Height (Front panel): 1.000 in. (2.540 cm) 

Width (Front panel): 3.250 in. (8.260 cm) 

Length (With connector): 2.650 in. (6.740 cm) 

WEIGHT (Without fan and rack): 0.2 Ibs. (0.090 kg) 


-40°C to +55"C 

ALTITUDE: 

55,000 ft. 


NO POWER REQUIRED 

LIGHTING: 

28VDC at 0.08 + 0.16 Amps 

1) EADl DISPLAY BRIGHTNESS (AD1 BRT) KNOB - Rotates to control display brightness. (Bezel 

lighting is controlled through an airframe brightness control). 

2) RADAR ALTIMETER TEST (RALT TST) PUSHBUTTON - When pressed, the radar altimeter is 

put into the test mode. The radar altimeter field on the EADl should display 50 + 5 feet of radar 

altitude. 

3) DECISION HEIGHT ADJUSTMENT (DH PULL SET) KNOB - Pulling the knob out and rotating the 

sets the decision height. 

E. Composite Switch 

The CMPST switch is a panel mounted annunciator switch that allows the pilot to select the composite 

mode on the EFS 40. The bottom of the switch illuminates a yellowlamber cross-hatch when the 

composite mode has been selected. 

F. Pitch Sync Switch 

The PITCH SYNC is collective mounted switch that allows the pilot to "synch" the current pitch attitude 

to the horizon. This mode will reset upon power interruption or composite mode selectionldeselection. 

13. Automatic Flight Control System (AFCS) 

The KFC 900 automatic flight control system consists of a KCP 520 flight control computer (FCC), a 

KMS 540 mode select panel (MSP), two KSM 575 linear actuators, a KSA 572 trim motor, two spring 

cartridge cable transducer assemblies, a yaw spring cartridge with a detent switch, four position 

resolvers, a trim switching relay, a VSCS switching relay, two KRG 333 triaxial rate and acceleration 

sensors, a KCM 100 configuration module and an AFCS annunciator panel. The existing aircraft roll 

and pitch trim motors and the right hand vertical stabilizer control system (VSCS) are also integrated 

into the AFCS. 

Reference Figure 22 and Figure 23 for a system block diagram of an AFCS interface to a 2-Tube EFS 

40 system. Reference Figure 24 and Figure 25 for a system block diagram of an AFCS interface to a 

4-Tube EFS 40 system. 

Page 40 

Revision AD 


LT EFlS APISAS RT EFlS 

28VDC L ESS BUS APISAS POWER 

28VDC APISAS POWER 

2BVDC R ESS BUSAPISASALERTPOWER 

2WDC L ESS BUS FLTDlRlMAlNT POWER 


CONFIGUWTION MODULE DATA 

500 OHM AFCS ALERT AUDIO OUTPUT 

I I 

RADAR 



EFS 40 &AIR DATA DIGITAL OUTPUTS 

AHRS AIR DATA 6 EFS40 DIGITAL INPUTS 

ALTIMETER ANALOG INPUTS 

28VDC L ESS BUS APISAS ACCEL POWER 

GO AROUND SELECT > 

28VDC L ESS BUS MODE SEL POWER 

AVIONICS SWITCH PANELAFCS TEST INPUT 

> 1 ACCLEMTION 

NO 1 KRG 333 

ACCLED'I'".' CC.'F"D 

-,,-,. -,.-.,. 

NO. 2 KRG 333 

TRlYlAL RATE 

SENSOR 1 

p-3 

RATE 6 ACCELEROMETER TEST 

- 

CMSF 

DIGITAL INPUT 

- 

HWpQJM 

MSP DIGITAL OUTPUT 

I 1 

I 

MSP DISCRETE OUTPUTS 

I 

KCP 520 

AFCS COMPUTER 

28VDC L ESS BUS FD SYNC POWER 

I 

FDSYNCSELECT 

' 

ll 

FDSYNCSELECT 

APISAS DISCONNECT



Page 42 

Revision AD 

Figure 23: AFCSI2-Tube EFlS System Block Diagram (Continued) 

EFFECTIVITY: MI3900 

I

2BVDC L ESS BUS APISAS POWER 

ZBVDCAPISAS POWER 

AROUND 

28WC R ESSBUSAPISASALERT WWER 

2BVDC L ESS BUS FLT DIR/MAINT WWER 

CONFlGURAllON MODULE DATA 

500OHMAFCS ALERT AUDIO OUTPUT 

REFERENCE INDllWAL 


I1 

EFS40 &AIR DATA DIGITAL OUTPLITS 

0 I ZBVDC L ESS BUS FD SYNC POWER ACCLEPATION SENSOR 

f 

2 I 

ZBVDC L ESS BUS APISAS DISC POWER 

(P ACCLEFATON SENSOR 

m 

1 

cn 

AHRS AIR DATA S EFS 40 DIGITAL INPUTS 

- 

RADAR ALTIMETER ANAL00 INPUTS 

GO AROUND SELECT 

r 

KCP 520 

AFCS COMPUTER 

MSP DIGITAL INPUT 

28M)C L ESS BUS MODE SEL POWER 

MSP DlGlTAL OUTPUT 

AVIONICS SWITCH PANEL AFCS TESTINPUT 

MSP DISCRETE OUTPUTS 

I 

LEFTOR RIGHT FD SYNC SELECT 

ZBVDC L ESS BUS FD SYNC POWER 

em4 

v 

LEFTOR 

- FLT DIR LEFTlRIGHT SELECT 

RIGHT FD SYNC SELECT 

Ul 

I 

FLT DlR LEFTlRlGHT SELECT 

FLT OIR LEFTRIGHT SELECT 

A P M DISCONNECT

FAN FAIL 6 INVERTER FAILANNUNCWTE 

AP AND SAS ENGAGEANNUNCWTE 

AP. SAS. PlTCH AXIS. ROLL AXIS, APISASVSCS 6 YAW AXIS FAIL ANNUNCIATE 

I i 

PlTCH 6 ROLL BEEP TRlM 

PITCH 6 ROLL MANUAL ELECTRIC TRIM DRIVE 

MANUAL ELECTRIC TRlM DRNE 

AP OR SAS TRlM DRIVE 

:Elz 

T-@AR TRIM 

SWlTCWlNG RELAY 

LEDEX TRlM SWITCH 

PlTCH 6 ROLLMANUAL ELECTRIC TRlM SENSE 

AP OR SAS PITCH 6 ROLL TRIM DRIVE 

AP OR SAS TRlM RELAY ENABLE 

PlTCH 6 ROLL METBEEP TRlM 

RIGHT CYCLIC TRlM POWER 

LINEAR ACNATORS 

DIRECTIONAL 

PlTCH 6 ROLL DRIVEIBRAKEILVDT EXClTlATlON 

< TRIM mwmB~A-rnn 

28VDC R ESS BUS TRlM POWER 

ZWDC FD RTTRIM POWER IAP ENGAGED) 

PITCH 6 ROLL LVDT POSITION 

I 

KCP 520 

AFCS COMPUTER 

ZWDC FO LT TRlM POWER (AP ENGAGED) 

2WDC R ESS BUS TRlM POWER 

I 

i 

RVSCS FIN 

SWlTCHlNG REL4Y 

R VERTICAL STABILIZER CONTROL SYSTEM DRNE 

R VSCS FAIL ANNUNCIATE 

EXISTING 

RIGHTVERTICAL 

STABILIZER CONTROL 

SYSTEM COMPUTER 

R VSCSACTUATOR POSITION 

I 

R VSCS ACTUATOR POSITION 

POSITION SYNCHROS 

PITCH. ROLL. PEDAL 6 COLLECTNE POSITION 

26VAClOOHZ EXCITATION 

I



For complete operation information for the KFC 900 AFCS, see the 006-00845-0000 

or 006-00845-0004 Rotorcraft Flight Manual Supplement. 

A. KCP 520 Flight Control Computer 

The KCP 520 FCC is a remote mounted unit that receives inputs from the AHRS, air data, EFS 40, 

both of the KRG 333 triaxial rate and acceleration sensors, the position resolvers, the KMS 540 MSP 

and various cockpit switches. The FCC computes the required commands for the stability 

augmentations system (SAS), the autopilot (AP) and the flight director (FD). The FCC drives the KSM 

575 linear actuators, KSA 572 trim servo, the existing roll and pitch trim servos, and the existing right 

hand VSCS actuator to control the aircraft. The FCC also provides digital outputs to the EFS 40 for 

SAS, AP, and FD mode display, and the air data system for vertical guidance cues. 

The FCC also drives the right hand vertical stabilizer in lieu of the aircraft system when the SAS or AP 

mode engaged. The FCC switches the drive signal to the VSCS actuator via the VSCS switching 

relay, and also switches the R VSCS valid output of the VSCS computer to the IIDS. The FCC 

receives position feedback from the actuator at all times to allow smooth transition into the AP or SAS 

coupled mode. 

Table 21: KCP 520 Leading Particulars 

PART NUMBER 065-00158-0502 


None 



Height: 8.24 in. (20.930 cm) 

Width: 3.821 in. ( 9.705 cm) 

Length: 17.66 in. (44.844 cm) 

WEIGHT: 10.90 Ibs. (4.90 kg) 


-55°C to +70°C 

ALTITUDE: 

55,000 ft. 


+28VDC APISAS 

+27.5 + 0.5 VDC @ 10 amps max 

+28VDC FD 

+27.5 k 0.5 VDC @ 2 amps max 

+28VDC MA1 

+27.5 0.5 VDC @ 2 amps max 

+28VDC Audio 

+27.5 + 0.5 VDC @ 0.2 amps max 

B. KCM 100 Configuration Module 

The KCM 100 configuration module is mounted to the KCP 520 FCC mounting rack and stores the 

KFC 900 installation data. The installation data is stored during the PC installation phase of the KFC 

900 system installation. 

KCM 100 PART NUMBER: 071 -00073-5000 

C. KMS 540 Mode Select Panel 

The KMS 540 MSP is a panel mounted unit that allows selection of AP or SAS, as well as the FD and 

all modes associated with the system. The MSP provides a digital output to the FCC for selected 

modes as well as analog outputs for AP and SAS engagement (in the event of a power failure to the 

MSP). The MSP also receives a digital input from the FCC to light the various mode buttons on the 

face of the MSP. The MSP also receives several discrete switch inputs. The switches include the 

cyclic mounted trim/FD sync switch and the collective mounted yaw trim and go around (GA) switches. 


I 

Page 45 

Revision AD

BENDIX/KINGe IFRAVIONICS I KFC goo 


Table 22: KMS 540 Leading Particulars 

PART NUMBER 065-00159-0701 


None 



Height: 3.375 in. (8.752 cm) 

Width: 3.375 in. (8.752 cm) 

Length: 8.966 in. (22.85 cm) 

WEIGHT: 1.85 Ibs.. (0.84kg) 


-55°C to +70°C 

ALTITUDE: 

55,000 ft. 


+27.5 + 0.5 VDC @ 2 amps max 

LIGHTING: 

+5 + 0.5 VDC @ 10 mA max 

OPERATION: 

1) HEADING SELECT (HDG) MODE - When pushed, will select the heading select (HDG) mode. 

Pushing the button with HDG engaged will disengage HDG and revert to heading hold. 

2) NAVIGATION (NAV) MODE -When pushed, arms the Navigation (NAV) mode. Pushing the NAV 

button with NAV ARM or NAV engaged will disengage NAV, and, in the absence of heading, 

revert to heading hold. 

3) APPROACH (APR) MODE - When pushed, arms the Approach (APR) mode. Pushing the APR 

button with APR ARM or APR engaged will disengage APR and, in the absence of HDG, revert to 

heading hold. 

4) BANK ANGLE LIMIT (BL) MODE - Used to select the maximum bank angle limit for non-approach 

flight director operation. The default bank angle is 200. 15n, Ion, and 250 may also be 

selected with successive pushes of the BL button. 

5) ALTITUDE HOLD (ALT) MODE - When pushed will select Altitude Hold (ALT) mode. Pushing the 

ALT button again with ALT hold engaged will disengage ALT hold and revert to pitch attitude hold. 

6) VERTICAL SPEED HOLD (VS) MODE - When pushed will select Vertical Speed Hold (VS) mode. 

Pushing the VS button with VS engaged will disengage VS and revert to pitch attitude hold. 

7) INDICATED AIRSPEED HOLD (IAS) MODE - When pushed will select Indicated Airspeed Hold 

(IAS) mode. Pushing the IAS button with IAS engaged will disengage IAS and revert to pitch 

attitude hold. 

8) AUTOPILOT (AP) ENGAGE - Engages pitch, roll and yaw axes of the autopilot. Pressing the AP 

button with AP engaged will disengage all axes (pitch and roll axes only). 

9) FLIGHT DIRECTOR (FD) MODE - Selects the flight director basic mode and brings command 

bars into view. Pushing the FD button with flight director engaged will disengage FD. 

10) MODE ANNUNCIATORS - Green mode annunciators are located above each mode select 

button. 

D. KSM 575 Linear Actuator 

The KSM 575 linear actuators are the primary pitch (longitudinal) and roll (lateral) servos for the SAS 

and AP systems. The actuators receive a drive signal from the FCC. The actuators output their 

position to FCC for fault detection. 

The actuators are located in the roof structure between FS 155 and FS 169. They are in series with 

the primary control system in the longitudinal and lateral axes. 

Page 46 

Revision AD 




Table 23: KSM 575 Leading Particulars 

PART NUMBERS 

KSM 575 Lateral 065-00167-0800 


None 

KSM 575 Longitudinal 065-00167-0900 


None 


Height: 2.3 in. (5.06 cm) 

Width: 2.3 in. (5.06 cm) 

Length: 15.8 in. (34.76 cm) 



-55°C to +70°C 

ALTITUDE: 

55,000 ft. 

E. Trim Actuators 

The KSA 572 yaw (thruster) trim actuator and the existing roll (lateral) and pitch (longitudinal) trim 

actuators are controlled by the FCC when the SAS or AP system is engaged. Control of the existing 

roll and pitch trim actuators between the cyclic trim switches and the FCC is done via the trim 

switching relay. This relay is energized during SAS and AP operation only. 

The KSA 572 trim actuator is located forward of the existing roll and pitch trim actuators. The KSA 

572 controls the directional thruster by attaching in parallel to the pedal control system. 

Table 24: KSA 572 Leading Particulars 

PART NUMBER 065-00162-0300 


None 


Height: 3.61 in. (7.942 cm) 

Width: 3.71 in. (8.162 cm) 

Length: 7.655 in. (16.841 cm) 



-55°C to +70°C 

F. Cable Transducer And KSC 573 Yaw Spring Cartridge 

The two spring cartridge cable transducer (string pot) assemblies for the roll (lateral) and pitch 

(longitudinal) axes and the KSC 573 yaw spring cartridge detent switch provide inputs to the FCC 

when the pilot wishes to "FLY through" the AP. This mode is explained in detail in the 

006-00845-0000 or 006-00845-0004 Rotorcraft Flight Manual Supplement. 

The spring cartridges and cable transducers are located under the floor below the pilot's seat. 

G. Position Resolvers 

The four position resolvers provide stick, pedal and collective position to the FCC. The resolvers are 

powered by the inverter and provide AC SINICOS position of the four aircraft axes. 

The longitudinal resolver is located under the floor below the copilot's seat. The lateral resolver is 

located at the top of the "broom closet" (the area just aft of the pilot.) The collective resolver is located 

under the floor at the base of the "broom closet". The directional resolver is attached to the pilot's 

directional pedal assembly. 


Page 47 

Revision AD



Table 25: Position Resolver Leading Particulars 

PART NUMBER 148-00091 -0000 


Diameter: 1.025 in. (8.162 cm) 

Length: 3.25 in. (16.841 cm) 

WEIGHT: 0.75 Ibs. (1.36 kg) 


Input Voltage: 

26 VAC, 400 Hz 

Input Current: 

0.0428 & 10% Amps 

Input Power: 

0.683 + 20% Watts 

TRANSFORMATION RATIO: 0.454 

ACCURACY: 

+7 Minutes 

STATOR OUTPUT VOLTAGE: 11.8+ 0.4V 

NULL VOLTAGE: 

30 mV 

PHASE SHIFT: 

29 degrees leading 

DC ROTOR RESISTANCE: 

96 ohms 

DC STATOR RESISTANCE: 

IMPEDANCES: 

110 ohms 

= 170 + j227 

Zero = 373 + j480 

H. KRG 333 Triaxial Rate And Acceleration Sensor 

The two KRG 333 triaxial rate and acceleration sensors provide three axis data. The FCC receives 

data for all three axes from the No. 1 KRG 333. The No. 2 KRG 333 supplies only roll and pitch rate 

data to the FCC. The FCC provides a test output to both units during the preflight test sequence. The 

gyros are interchangeable with one another. 

Both KRG 333s are located in the center of the roof assembly in the main cabin. The #I is at F.S. 21 5 

and the #2 is at F.S. 200. 

Table 26: KRG 333 Leading Particulars 

PART NUMBER 060-00040-0200 

Required Mods: 1 

Minimum Software Level 

None 


Height: 2.46. ( 6.24 cm) 

Width: 4.61 in. (11.71 cm) 


WEIGHT: 2.60 Ibs.. (1.17 Kg) 


-55°C to +70°C 

ALTITUDE: 

-15,000 to 55,000 ft. 


28VDC @ 0.550 amps nominal 

I. APISAS Annunciator Panel 

The APISAS annunciator panel is a panel mounted unit that annunciates the engagement of the AP or 

the SAS (in green), the failure of the roll and pitch axes (in red), the failure of the FCC VSCS output 

and the yaw trim axes (in amberlyellow) as well as the failures of the inverter and any one of the 

avionics cooling fans (in amberlyellow). The Category A installed aircraft have an additional "LOW 

AIS" annunciation, which requires modifying the panel to remove the existing lens and install the new 

lens. 

Page 48 

Revision AD 




The APISAS annunciator panel is located in the lower right hand center instrument panel. 

APISAS Annunciator Panel Part Number: 037-00228-0001 

APISAS Annunciator Panel CAT A lens Part Number: 037-00228-0102 

J. Flight Director LeWRight Switch 

A 4-tube EFS 40 configuration includes a flight director IeWright (FLT DIR LIR) switch that allows 

either EFS 40 system to display FD information, depending upon the selection annunciated on the 

switch. This switch is located just left of the KLN 90B at the top of the instrument panel. The FLT DIR 

LIR switch also steers the cyclic trim switch1FD SYNC functions appropriately when the AP is engaged 

and coupled to the FD. The FLT DIR LIR switch also supplies a discrete input to the left and right SG 

and the FCC. 

K. Diagnostic Plug 

A diagnostic plug is located in the right hand side of the console. This connector allows interfaces to 

the KLN 90B for database updates, interface to the KFC 900 for installation and maintenance, and 

monitoring of various avionics systems in the aircraft. A Honeywell pln 200-05647-0022 diagnostic 

harness is needed to interface to the diagnostic plug. An equivalent diagnostic harness can be built 

using the schematics in Figure 26 and the parts shown. 

CONNECTOR, 030-03308-0006 (D38999126WD35PN), QTY 1 

STRAIN RELIEF, 030-01475-0002 (MS85049138-15W), QTY 1 

P900D 

n 

CONNECTOR, 030-01 171-0000, QTY 1 

CONTACTS, 030-01 157-001 1, QTY 3 

HOOD WIJACKSCREWS, 030-01464-0000, QTY 1 

AFCS 

/--I 

CONNECTOR, 030-01 171-0000, QTY 1 

CONTACTS, 030-01 157-001 1, QTY 3 

HOOD WIJACKSCREWS. 030-01464-0000. QTY 1 

GPS 

n 

Figure 26: Diagnostic Plug Harness Schematic 

14. Weather Radar System 

The RDR 2000 weather radar system consists of an ART 2000 weather radar receiverltransmitter 

(RIT) with a twelve inch vertically polarized antenna plate, a radome, a CM 2000 configuration module 

and a display (the KMD 850 Multi-Function Display or the IN-182A weather radar indicator.) 

Reference Figure 27 and Figure 28 for a system block diagram of the weather radar system. 


97-00-00 

Page 49 

Revision AD



28VDC L AVIONICS BUS RDR Rfr POWER 

REFERENCE INDIIVUAL 



LC 

EFS 40 DIGITAL CONTROL INPUT 

PROFILE 

LIE 

+20 

ART 2000 

WEATHER RADAR R/T 

L 0 

w 

I' 

5 

-20 

' '"pa 

A I I 

'l i. 

1 '28VDC L AVIONICS BUS RDR IND POWER 1 

DN 

PULL STABOFF 

DlGlATAL 8 ANALOG WEATHER RADAR CONlROL OUTPU 



Figure 27: Weather Radar System Block Diagram (IN-182A shown) 

Page 50 

Revision AD 

1 EFFECTIVITY: MD900 I



I ZBVDC L AVIONICS BUS RDR RIT POWER ) 

NO, I AHRS DIGITAL INPUT 



EFS 40 DIGITAL CONTROL INPUT 

ART ZOO0 

WEATHER RADAR W 

I 

VIEW 

DIGITAL WEATHER RADAR INPUT 

L 1 

DlGlATAL 8 ANALOG WEATHER RADAR CONTROL OUTPU 

I 

ARlNC 429 GPS POSITION INPUT 

I 

ZBVDC LAVIONICS BUS MFD POWER 



A. ART 2000 Transceiver 

Figure 28: KMD 850 MFD Block Diagram 

The ART 2000 is a remote mounted R/T that uses a twelve inch vertically polarized flat plate antenna. 

The R/T outputs weather to the MFDIradar indicator and to the EFS 40 system(s). The R/T receives 

digital control input from the MFDIradar indicator and the EFS system(s). 

Table 27: ART 2000 Leading Particulars 

PART NUMBER 071-01519-0101 

Required Mods: 1,2, 3,4, 5, 6 



Base: 

10.00 in. 

WEIGHT: 

9.90 Ibs. 


-55°C to +70°C 

ALTITUDE: 

55,000 ft. unpressurized 


28VDC at 2.0 amps 

(25.40 cm) 

(4.49 Kg) 

When removing the ART 2000 R/T from the aircraft for service, repair or replacement, the flat plate 

antenna must be removed from the R/T. The flat plate antenna should be installed on the R/T prior to 

installing it on the aircraft. 


Page 51 

Revision AD

B. Flat Plate Antenna 



Table 28: AA2012V Antenna Plate Leading Particulars 

PART NUMBER 071 -01549-0200 

PHYSICAL DIMENSIONS 

HEIGHT 11.88 in. (30.18 cm) 

WEIGHT: 0.95 Ibs. (0.43 Kg) 

ALTITUDE: 


When removing the ART 2000 RIT from the aircraft for service, repair or replacement, the flat plate 

antenna must be removed from the RIT. The flat plate antenna should be installed on the RIT prior to 

installing it on the aircraft. 

C. CM 2000 Configuration Module 

The CM 2000 configuration module stores the operating and configuration data for the RDR 2000 

system. The CM 2000 is mounted to the brackets for the ART 2000. 

Table 29: CM 2000 Leading Particulars 

PART NUMBER 071 -00097-0100 


Height: 2.10 in. (5.33 cm) 

Width: 1.60 in. (4.05 cm) 


WEIGHT: 0.10 Ibs. (0.046 Kg) 


-55°C to +70°C 

ALTITUDE: 

-1000 to 55,000 ft. 

POWER REQUIREMENTS: Supplied by ART 2000 

D. KMD 540 MFD 

The KMD 5501850 systems are based on the KMD 540 base unit. The KMD 540 with the KAC 501 

weather radar module installed makes the KMD 850 system which can display weather radar 

information in a horizontal and vertical format as well as control the weather radar modes and display 

formats. The KAC 504 traffic module is also installed to allow the ARlNC 429 interface between the 

KLN 90B GPS receiver and the KMD 540. 

Table 30: KMD 540 Leading Particulars 

PART NUMBER 066-04035-0101 


None 



Height: 3.98 in. (10.10 cm) 

Width: 6.30 in. (16.01 cm) 

Length: 11.05 in. (28.07 cm) 

WEIGHT: 6.40 Ibs. (2.91 kg) 


-20°C to +70°C 

ALTITUDE: 

35,000 ft. 


28VDC @, 0.71A continuous 

Page 52 

Revision AD

BENDIX/KING" IFRAVIONICSI KFC 900 


E. IN-182A Indicator 

The IN-182A indicator displays weather radar information in a horizontal and vertical format as well as 

controlling the weather radar modes and display formats. 

Table 31: IN-182A Leading Particulars 



None 


None 


Height: 4.11 in. (10.439 cm) 

Width: 6.41 in. (16.281 cm) 


WEIGHT: 9.60 Ibs. (4.36 kg) 


-20°C to +55"C 

ALTITUDE: 



28VDC @ 2.OA continuous 

LIGHTING: 

28VDC @ 264mA 

15. Avionics Cooling Fans 

The 2-Tube EFS 40 configured aircraft have two KA 33 cooling fans with KA 12 fan monitors, one 

cooling fan under the right hand instrument panel (blowing air up into the RH EHSI) and one 

monitored avionics cooling fan mounted on the forward instrument panel (blowing air into the EADl 

bay of the RH instrument panel). Reference Figure 29 for a system block diagram of the 2-Tube EFS 

40 configuration cooling fans and Figure 30 for a system block diagram of the 4-Tube EFS 40 

configuration cooling fans. 

I EFFECTIVITY: MI3900 

I 

Page 53 

Revision AD

1.- 

NO. 2 INSTRUMENT PANEL 

FAN FAIL RELAY 



n 

FAN MONITOR OUTPUT (OPEN =FAIL) 

28VDC R DC BUS ANNUN POWER 

RIGHT HAND FORWARD 

INSTRUMENTPANEL 

COOLING FAN 

WIMONITOR 

U 

28VDC R DC BUS ANNUN POMR 

28VOC R GEN BUSAV FAN POWER 

'FAN MONITOR OUTPUT (2WDC = FAIL) 

I I < -. 

4K500 



1 1 CFAN 

WTOR OUTPUT (28VDC = FAIL) 

28VW R GEN BUSAV FAN POWER 

2WDC R OC BUS ANNUN POWER 

>u 

NO.1 KA33 

KLN 908 COOLING FAN 

WlKA 12 FAN MONITOR 

N0.2KA33 

CNI COOLING FAN 

WlKA 12 FAN MONITOR 

Figure 29: Cooling Fan System Block Diagram (2-Tube EFIS) 

Page 54 

Revision AD 

I EFFECTIVIN: MD900 

I

BENDIXIKlNNGe IFR AVIONICS I KFC goo 


7K508 



MONITOR OUTPUT (OPEN = FAIL) 

LEFT HAND FORWARD 

INSTRUMENT PANEL 

COOLING FAN 

W/MONI TOR 

FAN MONITOR OUTPUT (OPEN = FAIL) 

ZBMC R GEN BUS AV FAN POWER 

1 

, - 

WfiONITOR 

1 

RIGHT HAND FORWARD 

INSTRUMENT PANEL 

COOLING FAN 

ROLL PITCH ROLL PITCH 

VSCS YAW VSCS YAW 

INV FAN INV FAN 

- - 

LOW A/S - 

FAN MONITOR OUTPUT (2BMC = FAIL) 

FAN MONITOR OUTPUT (28MC = FAIL) 

28MC R GEN BUS AV FAN POWER 

ZBMC R E N BUS AV FAN POWER 

28MC R DC BUS ANNUN POWER 

>u 

NO. 1 KA 33 

KLN 9B COOLlNG FAN 

W/KA 12 FAN MONITOR 

IU 

I 

NO. 2 KA 33 

CNI COOLING FAN 

W/KA 12 FAN MONITOR 

Figure 30: Cooling Fan System Block Diagram (4-Tube EFIS) 

The No. 1 KA 33 cooling fan with KA 12 fan monitor cools the KLN 906 GPS receiver. The No. 2 KA 

33 cooling fan with KA 12 fan monitor cools the console mounted avionics (the No. 1 and No. 2 

NAVICOMM and the transponder). 

The 4-Tube EFS 40 configured aircraft have a additional bottom mounted cooling fan under the left 

hand instrument panel (blowing air up into the LH EHSI) and an additional monitored avionics cooling 

fan mounted on the forward instrument panel (blowing air into the EADl bay of the LH instrument 

panel). 

The monitored fans will annunciate a fan failure on the APISAS annunciator panel in the event one or 

more of the fans fails. 

KA 33 Cooling Fan Part Number: 071 -4037-03 


Page 55 

Revision AD



16. Stand by Attitude Indicator and Stand by Altimeter 

The installation incorporates a standby attitude indicator and standby altimeter. The standby attitude 

indicator is located in the lower center instrument panel. The location of the standby altimeter varies 

with the instrument panel configuration. A 2-Tube EFS 40 configuration puts the standby altimeter 

below the KAV 485 altimeterNSI. In a 2-Tube EFS 40 with the mechanical gyro option and the 4- 

Tube EFS 40 configuration, the standby altimeter is located in the left hand instrument panel in the 

standard altimeter location. 

A. STANDBY ATTITUDE INDICATOR 

The attitude gyro is a Goodrich AI-360 panel mounted, self-contained attitude gyro with an 

inclinometer. The gyro does not interface to any other avionics systems. 

Table 32: AI-360 Leading Particulars 



Height: 

3.260 in. maximum 

Width: 


Length: 


WEIGHT: 

3.20 Ibs. maximum 


Operating: 

-45°C to +70°C 

Exposure: 

-55°C to +85"C 

ALTITUDE: 

50,000 ft. 


Starting: 

30 Watts maximum @ 28VDC 

Running: (after 5 minutes minimum) 


LIGHTING: 

2.5 watts @ 28VDC 

B. STANDBY ALTIMETER 

The standby altimeter is the existing standard encoding altimeter that was installed in the aircraft into 

the pilot's static system. The altimeter no longer provides the encoding to the transponder and it is 

now connected to the copilot's static system. 

17. Mechanical Gyro System 

* 

The mechanical gyro system is an option to the 2-Tube EFS 40 configuration. The system consists of 

a panel mounted electric attitude indicator (this is the same attitude gyro as the standby attitude gyro) 

with an inclinometer and a KCS 55A compass system. The KCS 55A compass system consists of a 

remote mounted KG 102A directional gyro (DG), a KI 525A pictorial navigation indicator (HSI), a KMT 

112 flux valve and a KA 51 B slaving accessory. Reference Figure 31 for a system block diagram of 

the mechanical gyro system. 

Page 56 

Revision AD



I 2BVDC L GEN BUS LH ATT POWER ) 

NO. 2 NAV VORlLOClGS INPUT 

28VDC L GEN BUS LH COMP POWER 

KG 102A 

DIRECTIONAL GYRO 

1l 

POWER. SIGNAL GROUND, VALID, DRIVE MOTOR 

SLAVE CWAND CCW SWlTCHES 

I 

I 

SLAVING METER, POWER AND SIGNAL GROUND 

I 

KMT 112 

FLUX VALVE 

SLAVING CONTROL XFORMER 

3 J 

SLAVE 

CCW 

SLAVING CONTROL XFORMER 

A. Attitude Gyro 

Figure 31: Mechanical Gyro System Block Diagram 

The attitude gyro is a Goodrich AI-360 panel mounted, self-contained attitude gyro with an 

inclinometer. This is the same gyro as the Standby Attitude Indicator. The gyro does not interface to 

any other avionics systems. 

Page 57 

Revision AD



Table 33: AI-360 Leading Particulars 



Height: 


Width: 


Length: 


WEIGHT: 

3.20 Ibs. maximum 


Operating: 

-45°C to +70°C 

Exposure: 

-55°C to +85"C 

ALTITUDE: 

50,000 ft. 


Starting: 


Running: (after 5 minutes minimum) 


LIGHTING: 

2.5 watts @ 28VDC 

B. Directional Gyro 

The KG 102A directional gyro is a remote mounted unit that, in conjunction with the KMT 112 flux 

valve, provides a gyro-stabilized magnetic heading to the KI 525A indicator. The unit is mounted in 

the left avionics bay. 

Table 34: KG 102A Leading Particulars 

PART NUMBER: 060-0015-00 

Required Modifications: 

None 

PHYSICAL DIMENSIONS (Including rack wlshock mounts): 

Height: 6.637 in. (16.86 cm) 

Width: 4.844 in. (12.30 cm) 


WEIGHT: 4.70 Ibs.. (2.13 Kg) 


-55°C to +55"C 

ALTITUDE: 

-1000 to 40,000 ft. 

POWER REQUIREMENTS: 28VDC at 1.50A 

C. KI 525A Pictorial Navigation Indicator (or HSI) 

The KI 525A is panel mounted unit that displays gyro-stabilized magnetic heading, selected course 

and selected heading information. The KI 525A indicator receives VORILOC, glideslope, and 

TOIFROM navigation data from the No. 2 VHF NAVICOMM. 

Table 35: KI 525A Leading Particulars 

PART NUMBER: 066-3046-07 


None 


Height: 3.375 in. ( 8.57 cm) 

Width: 3.550 in. ( 9.02 cm) 


WEIGHT: 3.9 Ibs.. (1.786 Kg) 


-30°C to +55"C 

ALTITUDE: 

-1000 to 40,000 ft. 

POWER REQUIREMENTS: +5VDC and +I 5VDC supplied by KG 102A 

LIGHTING: 28VDC at 0.27A 

Page 58 

Revision AD 


D. Slaving Accessory 


006-00757-0000 MAINTENANCE MANUAL.SUPPLEMENT 

The KA 51 B slaving accessory is panel mounted unit that displays slaving error and allows the pilot to 

select the slaved heading or the free gyro mode. Manual clockwise and counter-clockwise slewing of 

the of the indicator can also be performed when in the free gyro mode. 

Table 36: KA 51B Leading Particulars 

PART NUMBER: 071 -1242-06 


None 


Height: 1.20 in. ( 3.05 cm) 

Width: 2.12 in. ( 5.38 cm) 


WEIGHT: 0.2 Ibs.. (0.091 Kg) 


-30°C to +55"C 

ALTITUDE: 

-1000 to 40,000 ft. 


+5VDC and 7.2VAC 400Hz from KG 102A 

E. KMT 11 2 Flux Valve 

The KMT 112 flux valve is a remote mounted unit that senses the direction of the earth's magnetic 

field and transmits this data to the AHRU. The flux valves are mounted at F.S. 276, near the NOTAR 

fan structure. 

Table 37: KMT 112 Leading Particulars 

PART NUMBER: 071 -1052-00 

Required Modifications: 1 


Height: 2.30 in. (5.88 cm) 

Diameter: 3.37 in. (8.55 cm) 

WEIGHT: 0.30 Ibs. (0.15 Kg) 


-55°C to +55"C 

ALTITUDE: 

-1000 to 40,000 ft. 


7.2VRMS, 400Hz from KG 102A 

18. AC Power System 

The AC power System consists of a KGS Electronics SPC-5(B) 50VA static inverter and an inverter 

fail relay and annunciator. Reference Figure 32 for a system block diagram of the AC power system. 


97-00-00 

Page 59 

Revision AD



AP 

AP 

PITCH 

YAW 

I NV 

SAS 

SAS 

ROLL 

VSCS 

FAN 

SAS AP 

SAS AP 

ROLL PITCH 

VSCS YAW 

I NV FAN 

- 

LOW AIS 

INVERTER FAlL OUT (GND = FAIL) 

3K500 

INVERTER FAlL RELAY 

1 INVERTER FAIL OUT (OPEN = FAIL) 

28VDC L ESS BUS INVERTER POWER 

SPC-5(B) 

STATIC INVERTER 

26VAC 400 HZ OUT 

26VAC 400HZ BUS 

Figure 32: AC Power System Block Diagram 

A. SPC-5(B) Static Inverter 

The inverter is a remote mounted, solid state static inverter that supplies 115VAC and 26VAC 400Hz 

single phase sine wave power to the aircraft avionics systems. The 115VAC 400Hz out is not utilized. 

The inverter has internal fault detection that will cause the inverter fail relay to open if power is 

removed or a fault is detected. The failure of the relay will annunciate a yellowlamber "INV on the 

APISAS annunciator panel located center instrument panel. The inverter is mounted in the right 

avionics bay. 

Table 38: SPC6(B) Leading Particulars 

PART NUMBER: 

KGS Electronics SPCd(B) 


Height: 2.75 in. ( 7.00 cm) 

Width: 4.12 in. (10.40 cm) 

Length: 6.50 in. (16.50 cm) 

WEIGHT: 

3.10 Ibs. 

TEMPERATURE RANGE: -55°C to +71 "C 

ALTITUDE: 

55,000 ft. 

INPUT POWER 

20 to 36 VDC 

OUTPUT POWER TOTAL (115VACl26VAC): 

50VA (5OVAl3OVA) 

EFFICIENCY: 67% TO 72% 


Page 60 

Revision AD 

I

19. Category A Equipment 



Category A aircraft incorporate additional features and equipment for operation dependent on the 

configuration of the IFR installation. The Category A configuration requires a pilot's standby altimeter, 

an aural warning generator and both aural and visual VNE warnings. 

The 2-Tube Category A configured aircraft require an additional altimeter, airspeed indicator and 

attitude indicator. This is accomplished by using the Goodrich Avionics GH-3000 Electronic Standby 

Instrument System (ESIS.) This system consists of the GH-3000 indicator, the DCM-3000 detachable 

configuration module, the ADC-3000 air data computer and the MAG-3000 magnetometer. 

A. Aural Warning Generator 

The dB systems, Inc. Model 630 Aural Warning Generator creates the DH Alert tone, the overspeed 

(VNE) warning tone and the altitude alert tone. The APISAS disconnect tone is generated by KCP 520 

AFCS computer but is routed through the Model 630. All tones are output to the aircraft audio system 

via an unswitched and unmuted input. 

Table 39: Model 630 Leading Padiculars 

PART NUMBER: dB Systems, Inc. 630-002 


Height: 

4.900 in. 

Width: 

1.500 in. 

Length: 

7.800 in. 

WEIGHT: 

0.90 Ibs. 


-55°C to +70°C 

ALTITUDE: 

to 70,000 ft. 


+28.0 VDC, 100 mA maximum 

B. GH-3000 Indicator 

The GH-3000 indicator unit is a self-contained three inch AT1 sized instrument, requiring + 28.0 VDC 

input power to provide pitch and roll attitude with slip 1 skip information. This unit contains no moving 

parts for the determination of attitude. Information is displayed on a color Active Matrix Liquid Crystal 

Display (AMLCD). A bezel mounted light sensor provides automatic display dimming capability, with 

manual control achieved through the menu mode. 

Table 40: GH-3000 Leading Particulars 

PART NUMBER: Goodrich 501 -1741-2803 or 501 -1741-0803 

Minimum Software Level: 3.2 


Height and Width: 3.30 in. max (8.38 cm) 

Length: 10.64 in. max with module (27.03 cm) 

WEIGHT: 3.5 Ibs. (1.59 Kg) 


-40°C to +70°C 

ALTITUDE: 

-2,000 to 60,000 ft. 


+28.0 VDC, 50W max, 20W nominal 

LIGHTING: 

28VDC 

C. DCM-3000 Configuration Module 

The DCM-3000 detachable configuration module contains information specific to the aircraft in which it 

is installed and is attached to the back of the GH-3000 indicator. If the GH-3000 indicator is removed, 

the DCM-3000 configuration module is detached and remains with the aircraft. 


Page 61 

.. Revision AD



Table 41 : DCM-3000 Leading Particulars 

PART NUMBER: Goodrich 501 -1803-113 or 501 -1803-41 



Length: 1.50 in. (3.81 cm) 

WEIGHT: 0.05 Ibs. (0.023 Kg) 


-55°C to +55"C 

ALTITUDE: 

-2,000 to 60,000 ft. 


+5.0 VDC from the GH-3000 

D. ADC-3000 Air Data Computer 

The remote-mounted ADC-3000 air data computer takes in left pitot and co-pilot static pressures, 

processes the data and supplies the GH-3000 indicator with airspeed and altitude information. 

Table 42: DCM-3000 Leading Particulars 

PART NUMBER: Goodrich 504-1895-03 


Height: 2.13 in. (5.41 cm) 

Width: 3.25 in (8.26 cm) 

Length. 6.50 in. (16.51 cm) 

WEIGHT: 1.50 Ibs.. (0.675 Kg) 


-55°C to +70°C 

ALTITUDE. 

-2,000 to 60,000 ft. 


+28.0 VDC, 3.0 W max 

E. MAG-3000 Magnetometer 

The MAG-3000 magnetometer uses a three-axis magnetic sensor that senses magnetic fields and 

converts these signals into a digital format that is then transmitted via a RS-422 bus to the GH-3000 

indicator. The three signals are then used with the pitch and roll attitude of the GH-3000 indicator to 

compute the magnetic heading of the aircraft. 

Table 43: MAG-3000 Leading Particulars 

PART NUMBER: Goodrich 501 -1826-01 



Height: 1 90 in. (4.83 cm) 

WEIGHT: 0.50 Ibs.. (0.227 Kg) 


-55°C to +70°C 

ALTITUDE: 

-2,000 to 60,000 ft. 


+28 VDC, 2.5 W max 

Page 62 

Revision AD 


I



20. Emergency Locator Transmitter (ELT) 

The ELT 100HM is a remote-mounted, Type AF (Automatic Fixed) emergency locator transmitter 

(ELT) which transmits on 121.5 and 243.0 MHz. The unit has six G-switches that allow it to be 

activated in any of six axes. 

Table 44: ELT HMIOO Leading Particulars 

PART NUMBER: 

Artex 100HM 


Height: 3.10 in. ( 7.87 cm) 

Width: 3.10 in. ( 7.87 cm) 

Length: 10.4 in. (26.42 cm) 

WEIGHT: 

3.5 Ibs. 


-20°C to +55"C 

ALTITUDE: 

55,000 ft. 

PEAK EFFECTIVE RADIATED POWER: 50mW (min) for 50 hrs 

MODULATION DUTY CYCLE: 

33% min, 55% max 

TRANSMITTER DUTY CYCLE: 

continuous 


I 

Page 63 

Revision AD




Page 64 

Revision AD 


1. General 



97-00-00 

Avionics - 

Fault Isolation I Troubleshooting 

This section provides recommended maintenance practices for the IFR avionics system. This section 

also gives troubleshooting or fault isolation information in the event of any component and/or system 

level problems. 

All maintenance for the IFR avionics systems is "On Condition". Further confirmation of satisfactory 

operation of all systems, visual displays and aural annunciations can be determined by periodic 

operation and testing. 

2. Attitude and Heading Reference System (IVAHRS) 

A. TROUBLESHOOTING 

This section provides fault isolation and flow charts as an aid in troubleshooting the LCR-92s system 

should any failure occur. Figure 101 is a trouble-shooting flow chart designed for Line Replaceable 

Unit (LRU) trouble shooting for the LCR-92s system. If a unit is found to be defective, it should be 

removed and sent to a qualified service center. 


I 

Page 101 

Revision AD



PERFORM INITIAL TURN ON 

SEQUENCE 

VERIFY THE MSU CAL MODE 

SWlTCH IS OFF (DOWN) 

SELECT THE DG MODE 

ON THE AVIONICS SWlTCH 

PANEL 

USING THE SLEW SWITCH. 

SLEW THE COMPASS CARD 

CW AND CCW 

REPLACE THE SG 465 

SWITCH IN THE AVIONICS 

SWlTCH PANEL 

REPLACE THE LCR-92s 

CONTINUE TESTING 

Figure 101 : Troubleshooting LCR-92s System 

Page 102 

Revision AD 


3. Digital Air Data System 



The KAV 485 has two test sequences that can be used for trouble shooting purposes, a power-up test 

sequence and a self test sequence. In addition, a loop-back test can be performed. The loop-back 

test consists of removing the connector on the KDC 481T and installing a connector (KPN 030-02527- 

0019) on the wiring harness that jumpers the 429 transmitter outputs from the KAV 485 to its 

respective inputs where they normally receive information from the KDC 481T. The connector and 

wiring to make this loopback test is shown in Figure 102. This tests the integrity of the 429 transmitter 

and receiver ports of the KAV 485 as well as the wiring to the KDC 481T. 

A. KAV 485 POWER UP TEST SEQUENCE 

Upon initial power up of the KAD 480 system the KAV 485 unit will display the selected altitude and 

the bar0 correction that were selected before power was removed last. Both the ALT and the VS flags 

will pull out of view and the altitude display will display the present bar0 corrected altitude of the 

aircraft. 

If the KAV 485 is receiving invalid altitude data the ALT flag will drop into view and FAIL will be 

displayed in the altitude display window. If it is receiving invalid vertical speed data the VS bug will 

stow and the VS flag will drop into view. 

If the KAV 485 is not receiving any 429 data the altitude select display and the bar0 correct display will 

flash. Both the VS flag and the ALT flag will drop into view. 

B. SELF TEST SEQUENCE (Push-to-Test) 

When the airspeed is above 50 Kts the test consists of lighting all the segments in the gas discharge 

displays and dropping the flags into view. When the airspeed is below 50 Kts and the Push-to-Test 

button on the KAV 485 is pressed, a series of events take place that test most of the operation of the 

KAD 4801480T Air Data System. The test can be terminated at any time by pushing the Push-to Test 

button a second time. Each indicator should be observed to see that the proper sequence of events 

takes place during the test mode. Failure of one of the units to properly sequence through the test 

mode can indicate a defective unit or units. If any of the units fail this test, a second phase of tests 

should be done to determine if the problem is in the actual instrument and/or wiring or in the remote 

KDC 481T (See Loop-back Test). These tests are to prevent unnecessary removal of the KDC 481T 

that would require a re-certification of the aircraft's static system. 

KAV 485 Test Sequence (Below 50 Kts): 

1) Upon pressing the Push-to-Test button the system will illuminate all the display segments for 3 

seconds and drop the flags into view. The illumination of the display segments can be extended 

to 13 seconds by holding the Press-to-Test button in. 

2) The KDC 481T will then engage the Vertical Speed function of the KAV 485. This will cause the 

vertical speed bug to come into view and follow the VS pointer. 

3) When the display segment test has been completed, the KDC 481T will set the Altitude Select 

display at 28,000 ft and will set the displayed aircraft altitude at 26,800 ft. The KDC 481T will then 

start ramping from the aircraft's displayed altitude of 26,800 ft to the selected altitude of 28,000 ft 

at a 3,500 ft per minute rate of climb. 

4) As the displayed aircraft altitude increases, the altitude alerter gives an audio alert (3 beeps) and 

a steady visual alert at 27,000 ft. The visual alert goes out at 27,700 ft (300 ft before reaching the 

selected altitude.) 

5) When the aircraft's displayed altitude reaches the selected altitude of 28,000 ft, the visual alert 

momentarily flashes. There will be a 3 second pause, after which the displayed aircraft altitude 

will ramp down to 27,000 ft at a 3,500 ft per minute rate of descent. At 27,700 ft, the altitude 

alerter gives an audio alert (3 beeps) and a continuously flashing visual alert. The flashing visual 

alert extinguishes at 27,000 ft. 


Page 103 

Revision AD



6) At 27,000 ft, the flags will drop into view and FAIL will also be displayed in the digital altitude 

display window. This is due to a series of invalid signals sent by the KDC 481T. 

7) At the end of the test, all information displayed before the test will be displayed again with the 

exception of the altitude select window. The altitude select window will display the aircraft's 

density altitude for five seconds before reverting back to displaying the selected altitude. 

C. LOOPBACK TEST 

With the loop-back plug installed in place of the KDC 48lT and when the system is powered, each 

piece of equipment sends out its own identification code on its 429 transmitter output to the KDC 

481T. When the equipment receives its own identification label back, it will cause the unit to send out 

predetermined loop-back information on the 429-transmitter bus. ' The units will then receive the 

information back, read it and display it. 

The KAV 485, during the loop-back test, will pull the ALT flag out of view, the digital altitude display will 

read 38,000 feet and the altitude pointer will be at zero. The VS pointer and the VS bug will change 

their respective values as they are displayed by the gas discharge display. The Push-To-Test switch, 

when depressed, will result in the illumination of all segments of the gas discharge display and will 

cause all flags to come into view. If the display unit passes loop-back test, check for power and 

ground at the KDC 481T. If they are present, remove the KAD 481T for service. 

LOOPBACK PLUG, 030-02527-001 9 

(ARRAY PIN PW2E24-61 ZK066) 

* INDICATES LOWER CASE LETTER 

D. PlTOT - STATIC SYSTEM CHECKS 

Figure 102: Loop-back Plug 

Pitot static system checks must be performed, as in the standard ship, according to FAR 91.41 1 and 

FAR 43 Appendix E. The schematics shown in the maintenance manual are correct except that the 

KDC 481T air data computer is plumbed to the right pitot tube and the pilot's static system, and the 

pilot's altimeter (4-Tube and 2-Tube T-Panels only) and VSI are plugged. 

For 2-Tube Category A installations, the ADC-3000 air data computer is plumbed to the left pitot tube 

and the copilot's static system. All Category A installations require the pilot's altimeter to be installed. 

Page 104 



-



4. Electronic Flight Instrumentation System (EFIS or EFS) 

A. EFS 40 SYSTEM FAILURES 

1) DU-DISPLAY UNIT LOSS OF COOLING - A yellow "DU" enclosed in a yellow box is annunciated 

at the bottom left center of the EHSl or bottom left of the EADl when insufficient airflow is detected 

in the display unit. Once annunciated, the faulty display unit will continue to operate for at least 30 

minutes if rated ambient temperature is not exceeded. To extend the operating time, reduce 

display information and brightness to a minimum. 

2) SG-SYMBOL GENERATOR LOSS OF COOLING - A yellow SG enclosed by a yellow box is 

annunciated at the bottom right center of the EHSl and bottom left of the EADl if insufficient 

airflow is detected in the SG. Once annunciated, the SG continues to operate for at least 30 

minutes if the rated ambient temperature is not exceeded. To extend the operating time reduce 

display information and brightness to a minimum. 

3) CP-CONTROL PANEL (ED 461) - A red "CP" enclosed by a red box is annunciated left center of 

the EHSl and lower left of the EADl if a control panel switch is stuck for greater than 10 seconds. 

If a switch fails, the display maintains all currently selected conditions. If the switch should 

become functional, the fault annunciation is removed and normal operation is restored. 

4) HEADING SELECT BUG - A red X is drawn through the heading bug if there is a heading select 

knob failure on the ED 461 control panel. 

5) COURSE SELECT - A red X is drawn through the course pointer head and tail if there is a course 

select knob failure on the ED 461 control panel. 

6) SG-SYMBOL GENERATOR - A red "SG" enclosed in a red box is annunciated at the upper left 

center of the EHSl or lower left of the EADl if certain monitored functions are detected as invalid. 

If the red SG annunciation is encountered, extreme caution should be used on the display for 

navigation. Even after validation and revalidation, the data should only be used as supplementary 

information. A large red "SG" appearing on a black background annunciates an SG failure which 

would result in processed data that is unusable for navigation. 

7) RAW DATA DEVIATION ANNUNCIATIONS - Pointerlscale malfunctions are annunciated by 

removal of the associated pointerlscale and placing a red X drawn in their place. A flag presented 

on the vertical deviation scale results in the deviation pointer being removed. On the EHSI, the 

pointerlscale annunciations include LIR deviation and GS. On the EADI, the scale annunciations 

include LIR deviation and GS. 

8) BEARING POINTER ANNUNCIATIONS - Bearing pointer source failure or invalid data reception 

caused a red X to be drawn through the source annunciator. The bearing pointer or NAVAID 

symbol is also removed. 

9) ALPHANUMERIC READOUT ANNUNCIATIONS - Failures affecting alphanumeric readouts are 

annunciated by a red X drawn through the readout. On the EHSI, the alphanumeric readouts 

include NAV bearing pointer source and CRS or DTK. Failures affecting distance information are 

annunciated by red dashes in the data field. When the distance source is operational but not 

providing valid distance data, dashes of the same color of the sensor are placed in the data field. 

Speed (KT) and time (MN) annunciations are removed if valid distance, speed and time-to-station 

information is not provided by the primary NAV sensor system. 

10) Failures affecting radar altimeter information are annunciated in red dashes in the data field on 

the EADI. When the radar altimeter source is operational but not providing valid data, white 

dashes are placed in the data field. 

11) CHECK CONFIG - A yellow "CHECK CONFIG" message will display in the upper right corner of 

the EHSl and EADl whenever the system configuration memory in the symbol generator and 

rotorcraft rack mounted configuration module do not match. 


Page 105 

Revision AD



B. TROUBLESHOOTING 

This section provides fault isolation flow charts as an aid in troubleshooting the EFS 40 system should 

any failure occur. Figure 103, Figure 104 and Figure 105 are troubleshooting flow charts designed for 

Line Replaceable Unit (LRU) troubleshooting for the EFS 40 system. If a unit is found to be defective, 

it should be removed and sent to a qualified service center. 


SEQUENCE 

ON THE EHSl SEVERAL 

TIMES WHILE OBSERVING 

NOTES: 

1. SYSTEM DISPLAYS AND MODES ARE DETERMINED BY THE 

CONFIGURATION OF THE SYSTEM ATTHE TlME OF INSTALLATION 

REFER TO THE ROTORCRAFT FLIGHT MANUAL SUPPLEMENT 

FOR FURTHER INFORMATION. 

2. THE ORDER IN WHICH THE DISPLAYS ARE CYCLED IS 

DETERMINED BY THE LAST DISPLAY USED WHEN THE UNIT WAS 

POWERED DOWN AND THE CONFIGURATION AT THE TlME OF 

INSTALLATION. REFER TO THE ROTORCRAFT FLIGHT MANUAL 

SUPPLEMENT FOR FURTHER INFORMATION. 

APPROPRIATE REPLACE THE ED 461 CONDITION STILL 


DEPRESS THE ARC BUTON 

ON THE EHSl SEVERAL 

TIMES WHILE OBSERVING 

THE DISPLAY 

J L 


Figure 103: Troubleshooting EFS 40 System 

Page 106 

Revision AD 

97-00-00 


BENDIXlKlN6" IFR AVIONICS I KFC goo 


VERIFY ALL CIRCUIT 

BREAKERSARESET 

I TOBAT/EXT 

SET POWER SWlTCH 

I 

SET THE EFS MASTER 

SWlTCH(ES) TO ON 

REPLACE THE SG4S5 

DEALER FOR CONFlGURATlOh 

REPLACE THE LCR-92s REPLACE THE SG 465 

I KNOBjBRTJONEHSI 

TURN EHSl BRIGHTNESS 

I 

REPLACE THE ED 461 REPLACE THE SG 465 

1 KNO8ONTHECP470 

TURN EADl BRIGHTNESS 

1 

- 

REPLACE THE ED 482 REPLACE THE CP 470 REPLACE THE SG 485 


Figure 104: Troubleshooting EFS 40 System (Continued) 

Page 107 

Revision AD




SEQUENCE 

FLAG IN VIEW ON 


CONDITION STILL 

REFER TO THE AHRS 

TROUBLESHOOTING GUIDE 

SELECT THE DG MODE 

ON THE AVIONICS SWITCH 

PANEL 

USING THE SLEW SWITCH, 

SLEW THE COMPASS CARD 

CWAND CCW 


STILL EXIST? 

REFER TO THE AHRS 

TROUBLESHOOTING GUIDE 

ON THE EHSI. ROTATE IT 

UNlTL THE HDG BUG IS 

TRACK WITH THE 

REPLACE THE ED 461 REPLACE THE SG 465 

STILL EXIST? 

I 

PUSHTHEHDGBUGKNOB 

ON THE EHSI 

CENTER ON THE REPLACE THE ED 461 

- REPLACE THE SG 465 

STILL EXIST? 

Page 108 

Revision AD 


Figure 105: Troubleshooting EFS 40 System (Continued) 


I


C. MAINTENANCE PAGES 

Information displayed in the maintenance pages of EFS 40 can aid in determining internal or external 

(sensor) problems. The maintenance pages shown an the following pages are formatted in three 

columns. The first column detailing what is available for display on the EHSI, the second for the EADl 

and the third showing what is available on the composite display. 

EFS4O HSI MAINTENANCE PAGES 

I 

1 EFS 40 MAINTENANCE 

2 

3 ALLIED-SIGNAL INC. 

4 

5 COPYRIGHT SEPT., 1988 

6 

7 IP 125-00601-0000 

8 NP1 125-00602-0000 

9 DP1 125-00603-0000 

10 RP 125-00604-0000 

EFS4O AD1 MAINTENANCE PAGES EFS4O REVERSION MAINTENANCE PAGES 

I ------_____---_-__---------------- 

I .................................. 


2 


4 

5 COPYRIGHT JAN., 1990 

6 

7 NP2 125-00656-0000 

8 DP2 125-00657-0000 

9 

10 


2 


4 

5 COPYRIGHT JAN., 1990 

6 

7 I P 125-00601-0000 

8 NP3 125-00711-0000 

9 DP3 125-00712-0000 

10 

I 

1 EFIS MAINTENANCE FUNCTIONS PG 01 1 EFIS 

2 

2 

3 --> LRU STATUS 3 --> 

4 SYSTEM CONFIGURATION 4 

5 TEST PATTERNS 5 

6 RECORDED MISC. ERRORS 6 

7 PROCESSOR ITEMS 7 

8 BIT HISTORY STACK 8 

9 WATCHDOG TIMER TEST 9 

10 SUBSYSTEM MENU 10 

11 ASCII TEXT PAGE 11 

MAINTENANCE FUNCTIONS PG 01 1 EFIS MAINTENANCE FUNCTIONS PG 01 

LRU STATUS 

2 

3 --> LRU STATUS 

SYSTEM CONFIGURATION 

4 SYSTEM CONFIGURATION 

TEST PATTERNS 

5 TEST PATTERNS 

RECORDED MISC ERRORS 

6 RECORDED MISC. ERRORS 

PROCESSOR ITEMS 

7 PROCESSOR ITEMS 

BIT HISTORY STACK 

8 BIT HISTORY STACK 

WATCHDOG TIMER TEST 

9 WATCHDOG TIMER TEST 

SUBSYSTEM MENU 

10 SUBSYSTEM MENU 

ASCII TEXT PAGE 11 ASCII TEXT PAGE 

------------------_II-I----IIIIII- 

_-_-___--_______--_----_---_-_----I _____--_____---__-_IIIIIII-I-II-I-I 

I 

1 LRU STATUS/MENU PG 02 1 LRU STATUS/MENU PG 02 1 LRU STATUS/MENU PG 02 

2 2 2 

3 --> SG 

PASS 3 --> SG 

PASS 3 --> SG 

PASS 

4 ECP 

N/A 4 ****NOT USED**** 

4 ECP 

N/A 

5 RCP 

N/A 5 ****NOT USED**** 

5 RCP 

N /A 

6 DU 

PASS 6 DU 

PASS 6 DU 

PASS 

7 CROSS SG 

PASS 7 CROSS SG 

N/A 

_________--_I _-----____-------_------ _________-I 

7 CROSS SG 

.......................... 

PASS 

PG 03 1 SG STATUS/MENU PG 03 1 SG STATUS/MENU 

2 2 

PASS 3 --> 1/0 STATUS FA1 L 3 --> IP 

PASS 4 NP2 PASS 4 NP3 

PASS 5 DP2 PASS 5 DP3 

PASS 6 ****NOT USED**** 6 RP 

PASS 

PASS 

PASS 

N/A 

IP STATUS PG 04 1 

2 

--> COMPUTER STATUS PASS 3 

429 1/0 STATUS PASS 4 

429 ACTIVITY N/A 5 

ANALOG STATUS PASS 6 

SERIAL DME STATUS PASS 7 

EXECUTIVE STATUS N/A 8 

1/0 STATUS PG 04 1 

2 

****NOT USED**** 3 

429 1/0 STATUS FAIL 4 

429 ACTIVITY N /A 5 

ANALOG STATUS PASS 6 

****NOT USED**** 7 

****NOT USED**** 8 

IP STATUS 

--> COMPUTER STATUS 

429 1/0 STATUS 

429 ACTIVITY 

ANALOG STATUS 

SERIAL DME STATUS 

EXECUTIVE STATUS 

PASS 

PASS 

N/A 

PASS 

PASS 

N/A 

COMPUTER STATUS PG 05 1 IP COMPUTER STATUS PG 

2 

CPU TEST 

PASS 3 THIS PAGE NOT AVAILABLE 

RAM TEST 

PASS 4 ON AD1 DISPLAY 

ROM TEST 

PASS 5 

NP RESPONSE PASS 6 

NPIP 12 BIT WORDS PASS 7 

NPIP BOOLEANS PASS 8 

IP CONFIG STATUS PASS 9 

05 1 IP COMPUTER STATUS 

2 

3 CPU TEST 

4 RAM TEST 

5 ROM TEST 

6 NP RESPONSE 

7 NPIP 12 BIT WORDS 

8 NPIP BOOLEANS 

9 IP CONFIG STATUS 

PASS 

PASS 

PASS 

PASS 

PASS 

PASS 

PASS 

EFFECTIVITY: MID908 

I 

Page 109 

.Revision AD

.......................... 

I 

1 IP 429 1/0 STATUS 

2 

LSI 1 

LSI 2 

LSI 3 

LSI 4 

LSI 5 

429 DECODE 

429 INTERRUPT 

NON CONFIGURED 



PG 06 1 429 1/0 STATUS 

2 

PASS 3 LSI 1 

PASS 4 429 DECODE 

PASS 5 CPU INTERRUPT 

PASS 6 NON CONFIGURED 

PASS 7 

PASS ' 8 

PASS 9 

PASS 10 

PG 06 1 IP' 429 1/0 STATUS 

2 

PASS 3 LSI 1 

PASS 4 LSI 2 

PASS 5 LSI 3 

PASS 6 

7 

8 

9 

10 

LSI 4 

LSI 5 

429 DECODE 

429 INTERRUPT 

NON CONFIGURED 

______-_-_--_---__------------___-I 

___________________IIIIIII_IIIIIIII -------------------11111111-111--- 

I 

1 IP 429 ACTIVITY - 1 PG 07 1 429 ACTIVITY PG 07 1 IP 429 ACTIVITY - 1 PG 07 

2 2 2 

3 DME 1 FAIL 3 AHRS 1 FAIL 3 DME 1 FA1 L 

4 DME 2 135 4 AHRS 2 135 4 DME 2 135 

5 NAV 1 033 5 HSI 033 5 NAV 1 033 

6 NAV 2 032 6 6 NAV 2 032 

7 7 7 

8 

9 

10 

11 

12 PRESS NEXT ITEM FOR MORE 12 

12 PRESS NEXT ITEM FOR MORE 

-_-------____--------------------- 

I 

I 

1 IP ANALOG STATUS PG 08 

2 

3 A/D COMPLETE PASS 

4 VREF +5.0 

5 GROUND -1.0 

6 t 5v t4.5 

7 t15V t15.3 

8 -15V -15.0 

9 t28V t27.8 

10 400Hz REF 1 PASS 

11 400Hz REF 2 FAIL 

.................................. 

I 

1 IP SERIAL DME STATUS PG 09 

I 

2 

3 DME INTERRUPT PASS 

4 DME 1 ACTIVE PASS 

5 DME 1 BCD PASS 

6 DME 2 ACTIVE PASS 

7 DME 2 BCD PASS 

8 RNV INTERRUPT PASS 

9 RNV 1 ACTIVE PASS 

10 RNV 2 ACTIVE PASS 

1 ANALOG STATUS 

2 

3 A/D COMPLETE 

4 VREF 

5 GROUND 

6 t5V 

7 t15V 

8 -15V 

9 +28V 

10 400Hz REF 1 

11 400Hz REF 2 

PG 08 1 IP ANALOG STATUS 

2 

PASS 3 A/D COMPLETE 

t10.0 4 VREF 

-1.0 5 GROUND 

t4.5 6 t 5v 

t15.3 7 t15V 

-15.0 8 -15V 

t27.8 9 t28V 

PASS 10 400Hz REF 1 

FA1 L 

_ _ _ _ _ _ _ _ I 

11 400Hz REF 2 

...................... 

SERIAL DME STATUS PG 09 1 IP SERIAL DME STATUS 

2 

3 DME INTERRUPT 

4 DME 1 ACTIVE 

5 DME 1 BCD 

(not available on ADI) 6 DME 2 ACTIVE 

7 DME 2 BCD 

8 RNV INTERRUPT 

9 RNV 1 ACTIVE 

10 RNV 2 ACTIVE 

................................... ----------------------I--I 

-___-______---_____---_-----------I 

I 

1 IP EXECUTIVE STATUS PG 10 1 IP EXECUTIVE STATUS PG 10 1 IP EXECUTIVE STATUS 

2 2 2 

3 75Hz OVERRUN 0 3 3 75Hz OVERRUN 



6 9Hz OVERRUN 255 6 (not available on ADI) 6 9Hz OVERRUN 




PASS 

PASS 

PASS 

PASS 

PASS 

PASS 

PASS 

PASS 

PASS 

t5.0 

-1.0 

t4.5 

+15.3 

-15.0 

t27.8 

PASS 

FAIL 

------------ 

-------------------111111111111 

___________________--------------_I ______---_---_-_-_-_IIIIIIIII_I_III 

I 

1 NP1 STATUS PG 11 1 NP2 STATUS PG 11 1 NP3 STATUS PG 

2 2 2 

3 --> COMPUTER STATUS PASS 3 --> COMPUTER STATUS PASS 3 --> COMPUTER STATUS PASS 

4 EXECUTIVE STATUS N/A 4 EXECUTIVE STATUS N/A 4 EXECUTIVE STATUS N/A 

5 MISC STATUS N/A 5 MISC STATUS N/A 5 MISC STATUS N/A 

PASS 

PASS 

PASS 

PASS 

PASS 

PASS 

PASS 

PASS 

Page 110 

Revision AD 


I

_---------_--______I 

-----_________ 



I 

1 NP1 COMPUTER PG 12 1 NP2 COMPUTER PG 12 1 NP3 COMPUTER PG 12 

2 2 2 

3 CPU TEST PASS 3 CPU TEST PASS 3 CPU TEST PASS 

4 RAM TEST PASS 4 RAM TEST PASS 4 RAM TEST PASS 

5 ROM TEST PASS 5 ROM TEST PASS 5 ROM TEST PASS 

6 IP RESPONSE PASS 6 HSI RESPONSE PASS 6 IP RESPONSE PASS 

7 DP1 RESPONSE PASS 7 DP2 RESPONSE PASS 7 DP3 RESPONSE PASS 

EXECUTIVE 

150HZ OVERRUN 

75HZ OVERRUN 

37HZ OVERRUN 

19HZ OVERRUN 

9HZ OVERRUN 

2HZ OVERRUN 

1HZ OVERRUN 

EXECUTIVE 

75HZ OVERRUN 

37HZ OVERRUN 

19HZ OVERRUN 

9HZ OVERRUN 

4HZ OVERRUN 

2HZ OVERRUN 

1HZ OVERRUN 

PG 13 1 NP3 EXECUTIVE 

2 

0 3 150HZ OVERRUN 







I 

1 NP1 MISC PG 14 1 NP2 MISC PG 14 1 NP3 MISC PG 14 

2 2 2 

3 EEPROM WRT FLTS OOOOH 3 EEPROM WRITE FLTS 000 3 EEPROM WRT FLTS OOOOH 

4 EEPROM READ FLTS OOOOH 4 EEPROM READ FLTS 000 4 EEPROM READ FLTS OOOOH 

I 

1 DP1 STATUS PG 15 1 DP2 STATUS PG 15 1 DP3 STATUS PG 15 

2 

3 --> COMPUTER STATUS PASS 

2 


2 


4 DISPLAY STATUS N/A 4 DISPLAY STATUS N/A 4 DISPLAY STATUS N/A 

--_______________-_---------_-___-I 

_-_-_-_____________IIIIIIIIIIII-III 

I 

1 DP1 COMPUTER STATUS PG 16 1 DP2 COMPUTER STATUS PG 16 1 DP3 COMPUTER STATUS PG 16 

CPU TEST 

RAM TEST 

ROM TEST 

NP1 RESPONSE 

RP RESPONSE 

75HZ OVERRUN 

37HZ OVERRUN 

9HZ OVERRUN 

2HZ OVERRUN 

EXECUTIVE RESETS 

PASS 

PASS 

PASS 

PASS 

PASS 

0 

0 

0 

0 

0 

CPU TEST 

PASS 

RAM TEST 

PASS 

ROM TEST 

PASS 

NP2 RESPONSE PASS 

ATTITUDE CONFIG PASS 

EXECUTIVE RESETS 0 

75HZ OVERRUN 

0 

37HZ OVERRUN 

0 

9HZ OVERRUN 

0 

2HZ OVERRUN 

0 

.--------- I 

. _ - _ - - - - - - - - - - - - - - - 

CPU TEST 

RAM TEST 

ROM TEST 

NP1 RESPONSE 

RP RESPONSE 

75HZ OVERRUN 

37HZ OVERRUN 

9HZ OVERRUN 

2HZ OVERRUN 

EXECUTIVE RESETS 

PASS 

PASS 

PASS 

PASS 

N /A 

0 

0 

0 

0 

0 

DP1 DISPLAY STATUS PG 17 1 DP2 DISPLAY STATUS PG 17 1 DP3 DISPLAY STATUS 

2 

2 

FRAME OVER RUNS 10 3 FRAME OVERRUNS 10 3 FRAME OVER RUNS 10 

END OF FILE ERROR 234DH 4 END OF FILE ERROR 234DH 4 END OF FILE ERROR 234DH 

WAITON75TOBUILD 0 5 WAIT ON 75 TO BUILD 0 5 WAIT ON 75 TO BUILD 0 

75 NOT READY 0 6 75 NOT READY 0 6 75 NOT READY 0 



75 MAX LENGTH 190 9 75 MAX LENGTH 190 9 75 MAX LENGTH 190 



BK MAX LENGTH 190 12 BK MAX LENGTH 190 12 BK MAX LENGTH 190 

__-_-____________-_---_-----__----I 

-__________________IIIIIIIIII-III_I 

I 

1 RP STATUS PG 18 1 PG 18 1 PG 18 

2 2 2 

3 --> COMPUTER STATUS PASS 3 3 THIS PAGE NOT AVAILABLE 

4 1/0 STATUS PASS 4 (not available on ADI) 4 ON REVERSION DISPLAY 


Page 11 1 

. Revision AD



I 

1 RP COMPUTER STATUS 

2 

3 CPU TEST 

4 RAM TEST 

5 ROM TEST 

6 DP1 RESPONSE 

7 lOHZ OVERRUN 

8 9HZ OVERRUN 

9 2HZ OVERRUN 

PG 19 1 

2 

PASS 3 

PASS 4 

PASS 5 

PASS 6 (not 

0 7 

0 8 

0 9 

PG 19 1 PG 19 

2 

3 THIS PAGE NOT AVAILABLE 

4 ON REVERSION DISPLAY 

5 

available on ADI) 6 

7 

___________________--------------_I ----------------------------------- .................................. 

I 

1 RP 1/0 STATUS PG 20 1 

PG 20 1 PG 20 

2 2 

2 

3 429 INPUT PASS 3 

3 THIS PAGE NOT AVAILABLE 

4 429 OUTPUT PASS 4 

4 ON REVERSION DISPLAY 

5 429 LAST RCV LABEL 271 5 

5 

6 453 INPUT PASS 6 (not available on ADI) 6 

7 453 LAST FAIL CODE OOH 7 

7 

8 LTNG LAST FAIL CODE OOH 8 

8 

9 LTNG LAST RCV LABEL 271 9 

9 

RCP STATUS PG 21 1 

2 

CPU VALIDATION PASS 3 

FLAGS PASS 4 

BIT VALIDITY PASS 5 

FLAG VALIDITY PASS 6 

CPU VALIDIATION VAL PASS 7 

EPROM SUM FLAG PASS 8 

ADC CAL FLAG PASS 9 

ALU TEST FLAG PASS 10 

EXECUTION FLAG PASS 11 

WARM START FLAG PASS 12 

KEYBOARD DATA FLAG PASS 13 

PG 21 1 

2 

3 

4 

5 

(not available on ADI) 6 

7 

8 

9 

10 

11 

THIS PAGE NOT AVAILABLE 

ON REVERSION DISPLAY 

I 

1 DU STATUS PG 22 1 DU STATUS PG 22 1 DU STATUS PG 22 

2 2 2 

3 COOLING PASS 3 

_________________-_-_-------------I 

____-_--___________IIIIIIIIIIIIIIII 

COOLING PASS 3 COOLING PASS 

.................................. 

I 

1 CROSS SG STATUS PG 23 1 CROSS SG STATUS PG 23 1 CROSS SG STATUS PG 23 

2 2 

PASS 3 3 IP 

PASS 4 4 NP1 

PASS 5 5 DP1 

PASS 6 (not available on ADI) 6 RP 

PASS 7 7 NP2 

PASS 8 8 DP2 

PASS 

PASS 

PASS 

PASS 

PASS 

PASS 

I 

1 TEST PATTERNS MENU 

2 

3 --> STROKE PATTERNS 

4 RASTER PATTERNS 

5 CLIPPER PATTERNS 

I 

1 STROKE PATTERNS MENU 

2 

3 --> X-Y PATTERN 

4 CONVERGENCE PATTERN 

5 DAMPING PATTERN 

6 STROKE COLORS 

PG 24 1 TEST PATTERNS MENU PG 24 1 TEST PATTERNS MENU PG 24 

2 2 

3 --> STROKE PATTERNS 3 --> STROKE PATTERNS 

4 RASTER PATTERNS 4 RASTER PATTERNS 

5 CLIPPER PATTERNS 5 CLIPPER PATTERNS 

___________________---------------I 

................................ 

PG 25 1 STROKE PATTERNS MENU PG 25 1 

2 2 

3 --> X-Y PATTERN 3 

4 CONVERGENCE PATTERN 4 

5 DAMPING PATTERN 5 

6 STROKE COLORS 6 

STROKE PATTERNS MENU PG 25 

--> X-Y PATTERN 

CONVERGENCE PATTERN 

DAMPING PATTERN 

STROKE COLORS 

Page 11 2 

Revision AD 




_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ I ___------------___________________~ 

_________-___--------------------- 

I 

1 PG 26 1 PG 26 1 PG 26 

2 2 2 

3 3 3 

4 x - y pattern 4 x -y pattern 4 x - y pattern 

__-_________--__-_-__-__-_________I __________________---_-III________~ __________________--------------- 

I 

1 PG 27 1 PG 27 1 PG 27 

2 2 2 

3 3 3 

4 convergence pattern 4 convergence pattern 4 convergence pattern 

___________-__-_____-_____________I 

................................... _________________---------------- 

I 

1 PG 28 1 PG 28 1 PG 28 

2 2 2 

3 3 3 

4 damping pattern 4 damping pattern 4 damping pattern 

~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ ~ 

I 

1 STROKE COLOR MENU PG 29 1 STROKE COLOR MENU 

STROKE COLOR MENU 

2 

2 

3 --> RED 

3 --> RED 

--> RED 

4 GREEN 

4 GREEN 

GREEN 

5 BLUE 

5 BLUE 

BLUE 

6 CYAN 

6 CYAN 

CYAN 

7 MAGENTA 

7 MAGENTA 

MAGENTA 

8 YELLOW 

8 YELLOW 

YELLOW 

9 ORANGE 

9 ORANGE 

ORANGE 

10 WHITE 

10 WHITE 

WHITE 

11 GRAY 

11 GRAY 

GRAY 

I 

1 RASTER PATTERNS MENU PG 30 1 RASTER PATTERNS MENU PG 30 1 RASTER PATTERNS MENU PG 30 

2 2 2 

3 --> ALIGNMENT PATTERN 3 --> ALIGNMENT PATTERN 3 --> ALIGNMENT PATTERN 

4 RASTER COLORS 4 RASTER COLORS 4 RASTER COLORS 

I 

1 PG 31 1 PG 31 1 PG 31 

2 2 2 

3 3 3 

4 4 4 

5 raster pattern 5 raster pattern 5 raster pattern 

I 

1 RASTER COLOR MENU 

2 

3 --> RED 

4 GREEN 

5 BLUE 

6 CYAN 

7 MAGENTA 

8 YELLOW 

9 ORANGE 

10 WHITE 

PG 32 1 RASTER COLOR MENU 

2 

3 --> RED 

4 GREEN 

5 BLUE 

6 CYAN 

7 MAGENTA 

8 YELLOW 

9 ORANGE 

. _ _ _ _ _ I 

10 WHITE 

___________________-------- 

PG 32 1 RASTER COLOR MENU PG 32 

L 

3 --> RED 

4 GREEN 

5 BLUE 

6 CYAN 

7 MAGENTA 

8 YELLOW 

9 ORANGE 

10 WHITE 

___________________--- 

I 

1 CLIPPER ALIGNMENT MENU PG 33 1 CLIPPER ALIGNMENT MENU PG 33 1 CLIPPER ALIGNMENT MENU PG 33 

2 2 2 

3 --> HSI CLIPPERS 3 --> HSI CLIPPERS 3 --> HSI CLIPPERS 

4 AD1 CLIPPERS 4 AD1 CLIPPERS 4 AD1 CLIPPERS 

I 

1 HSI CLIPPER ALIGN PG 34 1 HSI CLIPPER ALIGN PG 34 1 HSI CLIPPER ALIGN PG 34 

2 2 2 

3 3 3 


Page 113 

Revision AD



I 

1 AD1 CLIPPER ALIGN PG 35 1 AD1 CLIPPER ALIGN PG 35 1 AD1 CLIPPER ALIGN PG 35 

2 2 2 

3 3 3 

----I--------------------- 

RECORDED MISC ERRORS - 1 

NOT IMPLEMENTED 

RECORDED MISC ERRORS - 1 PG 36 

NP2 PITCH CMP FLT 00000 

NP2 ROLL CMP FLT 00000 

RECNST PITCH FLT 00000 

RECNST ROLL FLT 00000 

NP2 ATT VALID FLT 00000 

NP2 ATT REFRESH FLT 00000 

DP2 PITCH COMP FLT 00000 

DP2 ROLL COMP FLT 00000 

PRESS NEXT MENU TO CLEAR 

.................................. 

1 RECORDED MISC ERRORS - 1 PG 36 

2 

3 NP3 PITCH CMP FLT 00000 

4 NP3 ROLL CMP FLT 00000 

5 RECNST PITCH FLT 00000 

6 RECNST ROLL FLT 00000 

7 NP3 ATT VALID FLT 00000 

8 NP3 ATT REFRESH FLT 00000 

9 

10 PRESS NEXT MENU TO CLEAR 

11 

I 

1 RECORDED MISC ERRORS - 2 PG 37 1 RECORDED MISC ERRORS - 2 PG 37 1 RECORDED MISC ERRORS - 2 PG 37 

2 2 2 

3 3 3 

4 4 4 

__-_-______________IIII-IIIIIIIIIII --------------------111111111111-- 

___________________---------------I 

I 

1 PROCESSOR ITEMS MENU PG 38 1 PROCESSOR ITEMS MENU PG 38 1 PROCESSOR ITEMS MENU PG 38 

2 2 2 

3 --> RESET COUNTS 3 --> RESET COUNTS 3 --> RESET COUNTS 

4 SW IDENT 4 SW IDENT 4 SW IDENT 

5 MEMORY DUMP 5 MEMORY DUMP 5 MEMORY DUMP 

.................................. I 

I 

1 WATCHDOG RESET COUNTS PG 39 

2 

3 IP CAUSED 3 

4 NP CAUSED 2 

5 DP CAUSED 2 

6 RP CAUSED 0 

7 MAINT CAUSED 0 

8 


1 PROCESSOR RESETS PG 39 

2 

3 NP2 CAUSED 3 

4 DP2 CAUSED 2 

5 MAINT CAUSED 2 

6 HWTST CAUSED 0 

7 

8 


WATCHDOG RESET COUNTS PG 39 

IP CAUSED 3 

NP CAUSED 2 

DP CAUSED 2 

RP CAUSED 

N/A 

MAINT CAUSED 0 


___________________---------------I _-______________-_--I-IIIIIIIIIIII~ .................................. 

I 

1 PROCESSOR SW ID PG 40 1 PROCESSOR SW ID PG 40 1 PROCESSOR SW ID PG 40 

2 2 2 

3 IP 125-00601-0000 3 NP2 125-00656-0000 3 IP 125-00601-0000 

4 NP1 125-00602-0000 4 DP2 125-00657-0000 4 NP3 125-00711-0000 

5 DP1 125-00603-0000 5 5 DP3 125-00712-0000 

6 RP 125-00604-0000 6 6 

I 

1 PROCESSOR RAM 

2 

3 --> IP 3COOH = 004FH 

4 0013H = 03448 

5 NP1 800FH = OOOOH 

6 0013H = 03448 

7 DP1 800FH = OOOOH 

8 0013H = 03448 

9 RP 800FH = OOOOH 

10 0013H = 03448 

PG 41 1 PROCESSOR RAM 

PG 

L 

3 ****NOT USED**** 

4 

5 --> NP2 800FH = OOOOH 

6 0013H = 03448 

7 DP2 800FH = OOOOH 

8 0013H = 03448 

9 ****NOT USED**** 

10 

PROCESSOR RAM PG 41 

--> IP 3COOH - 004FH 

0013H - 03448 

NP3 800FH = OOOOH 

0013H = 03448 

DP3 800FH = OOOOH 

RP 

0013H - 03448 

N/A 

N/A 

Page 114 

Revision AD 


----------------_-_ 



I 

1 BIT HISTORY - 1 PG 42 1 BIT HISTORY - 1 PG 42 1 

2 EVENT DATA 2 EVENT DATA 2 

3 000 0000 1111 1111 0000 3 002 0000 0000 1101 1001 3 

4 000 0000 1111 1111 0000 4 006 0000 0000 0001 1001 4 

5 000 0000 1111 1111 0000 5 002 0000 0000 1101 1001 5 

6 000 0000 1111 1111 0000 6 002 0000 0000 1101 1001 6 

7 000 0000 1111 1111 0000 7 006 0000 0000 0001 1001 7 

8 000 0000 1111 1111 0000 8 002 0000 0000 1101 1001 8 

9 000 0000 1111 1111 0000 9 002 0000 0000 1101 1001 9 

10 000 0000 1111 1111 0000 10 006 0000 0000 0001 1001 10 

11 11 11 

12 PRESS NEXT MENU TO CLEAR ST 12 PRESS NEXT MENU TO CLEAR STACK 12 

STACK 

___________________--__-_-----_--_I 

___________________IIIIIIIIIIIIIIII --- 

I 

1 WATCHDOG TIMER TEST PG 43 1 WATCHDOG TIMER TEST PG 43 1 

2 2 2 

3 THIS TEST WILL RESET 3 THIS TEST WILL RESET 3 

4 THE WATCHDOG TIMER. 4 THE WATCHDOG TIMER. 4 

5 5 5 

6 PRESS NEXT MENU TO CONTINUE 6 PRESS NEXT MENU TO CONTINUE 6 

CONTINUE 

BIT HISTORY - 1 PG 42 

EVENT DATA 

000 0000 1111 1111 0000 

000 0000 1111 1111 0000 

000 0000 1111 1111 0000 

000 0000 1111 1111 0000 

000 0000 1111 1111 0000 

000 0000 1111 1111 0000 

000 0000 1111 1111 0000 

000 0000 1111 1111 0000 


WATCHDOG TIMER TEST PG 43 

THIS TEST WILL RESET 

THE WATCHDOG TIMER. 

PRESS NEXT MENU TO 

I 

1 SUBSYSTEM MENU PG 44 1 SUBSYSTEM MENU PG 44 1 SUBSYSTEM MENU PG 44 

2 2 2 

3 --> RADAR ALIGMENT 3 **** NOT USED ******* 3 --> RADAR ALIGMENT 

***A 

4 AUTOPILOT ALIGMENT 4 NOT USED ******* 4 AUTOPILOT ALIGMENT 

5 AHRS DIAGNOSTICS 5 AHRS DIAGNOSTICS 5 AHRS DIAGNOSTICS 

6 TCAS DIAGNOSTICS 6 **** NOT USED ******* 6 TCAS DIAGNOSTICS 

I 

1 R-T CALIBRATION DATA 

2 SW REV: A 

3 GAIN POT /2: 0.0t 

4 PITCH ANGLE: 0.0t 

5 TILT SETTING: O.OU 

6 ROLL ANGLE: 0.0- 

7 ROLL TRIM: 0.0- 

8 400 HZ REF: 0.0- 

9 AZIMUTH COUNT: 45 

10 ANTENNA ELEVATION: 

11 L = 0.ot 

12 C = 0.0- 

13 R= 0.0t 

FAULTS 

ELV 

AFC 

400HZ 

GYRO 

H.V. 

AGC 

XMITTER 

PG 45 1 PG 45 

2 

3 

4 

5 

(not available on ADI) 6 (not available on reversion) 

7 

--> KCP420 BOARDS 

PREFLT TEST 

AIR DATA/AHRS 

ENGAGE CLUTCH 

SERVO MTR/TACH 

RATE FEEDBACK 

SERVO AMP 

PASS 

PASS 

PASS 

PASS 

PASS 

PASS 

PASS 

EXTERNAL DISCRETES N/A 

429 LABEL STATUS PASS 

1 KFC400 STATUS/MENU PG 46 1 KFC400 STATUS/MENU PG 46 

2 2 

3 3 --> KCP420 BOARDS PASS 

4 4 PREFLT TEST PASS 

5 5 AIR DATA/AHRS PASS 

6 (not available on ADI) 6 ENGAGE CLUTCH PASS 

7 7 SERVO MTR/TACH PASS 

8 8 RATE FEEDBACK PASS 

9 9 SERVO AMP PASS 

10 10 EXTERNAL DISCRETES N/A 

11 11 429 LABEL STATUS PASS 

_____-_______-_--_-IIIII-I_IIIIIIII 

_____________-_____---_-_----_----I 

I 

1 KCP420 BOARDS PG 47 1 KCP420 BOARDS PG 47 1 KCP420 BOARDS PG 47 

2 2 2 

3 POWER SUPPLY PASS 3 3 POWER SUPPLY PASS 

4 1/0 PROCESSOR PASS 4 4 1/0 PROCESSOR PASS 

5 CHANNEL 1 PASS 5 5 CHANNEL 1 PASS 

6 CHANNEL 2 PASS 6 (not available on ADI) 6 CHANNEL 2 PASS 


Page 115 

Revision AD

_________________-_III_IIIIIIIIII_~ _______________--- 

___________________IIIIIII-I------ 



I 

1 KFC400 PREFLIGHT TEST PG 48 1 KFC400 PREFLIGHT TEST PG 48 1 KFC400 PREFLIGHT TEST PG 48 

2 2 2 

3 --> KAM432 TEST PASS 3 3 --> KAM432 TEST PASS 

4 KTA436 TEST PASS 4 4 KTA436 TEST PASS 

5 CONFIGURATION PASS 5 5 CONFIGURATION PASS 

6 CLUTCH TESTS PASS 6 (not available on ADI) 6 CLUTCH TESTS PASS 

__________________________--------I 

I 

1 KAM432 PREFLIGHT TEST PG 49 1 KAM432 PREFLIGHT TEST PG 49 1 KAM432 PREFLIGHT TEST PG 49 

2 2 2 

3 KAM432 VALID PASS 3 3 KAM432 VALID PASS 

4 PREFLIGHT PASS 4 (not available on ADI) 4 PREFLIGHT PASS 

I 

1 KTA436 PREFLIGHT TEST PG 50 1 KTA436 PREFLIGHT TEST PG 50 1 KTA436 PREFLIGHT TEST PG 50 

2 2 2 

3 . KTA436VALID PASS 3 3 KTA436 VALID PASS 

4 UP DRIVE TEST PASS 4 4 UP DRIVE TEST PASS 

5 DOWN DRIVE TEST PASS 5 (not available on ADI) 5 DOWN DRIVE TEST PASS 

I 

1 CONFIGURATION CHECK PG 51 1 CONFIGURATION CHECK PG 51 1 CONFIGURATION CHECK PG 51 

2 2 2 

3 J4202 PIN SY PASS 3 3 J4202 PIN SY PASS 

4 54202 PIN SF PASS 4 4 54202 PIN SF PASS 

5 J4202 PIN D PASS 5 5 54202 PIN D PASS 

6 J4202 PIN SV PASS 6 (not available on ADI) 6 J4202 PIN SV PASS 

7 J4202 PIN ST PASS 7 7 54202 PIN ST PASS 

_______---_________________-------I 

____________________IIIIIIIIIIII_II 

I 

1 CLUTCH PREFLIGHT TEST PG 52 1 CLUTCH PREFLIGHT TEST PG 52 1 CLUTCH PREFLIGHT TEST PG 52 

2 2 2 

3 KCP420 DISENGAGE PASS 3 3 KCP420 DISENGAGE PASS 

4 ENGAGE TEST PASS 4 4 ENGAGE TEST PASS 

5 COMPUTER VALID PASS 5 5 COMPUTER VALID PASS 

6 KMC440 DISENGAGE PASS 6 (not available on ADI) 6 KMC440 DISENGAGE PASS 

I 

1 AIR 

2 

3 

4 

5 

6 

7 

8 

9 

ALT 

IAS 

AP 

FD 

YAW 

HDG 

PG 53 1 AIR 

2 

PASS 3 

PASS 4 

5 

PASS 6 

PASS 7 

PASS 8 

PASS 9 

DATA / AHRS 

PG 53 1 AIR DATA/AHRS 

2 

3 ALT 

4 IAS 

5 

(not available on ADI) 6 AP 

7 FD 

8 YAW 

9 HDG 

PASS 

PASS 

PASS 

PASS 

PASS 

PASS 

I 

1 ENGAGE CLUTCH 

2 

3 AIL 

4 ELE 

5 RUD 

6 PTRM 

7 LTRM 

PG 54 1 ENGAGE CLUTCH PG 54 1 ENGAGE CLUTCH PG 54 

2 2 

PASS 3 3 AIL PASS 

PASS 4 4 ELE PASS 

PASS 5 5 RUD PASS 

PASS 6 (not available on ADI) 6 PTRM PASS 

PASS 7 7 LTRM PASS 

I 

1 SERVO MTR/TACH PG 55 1 SERVO MTR/TACH PG 55 1 SERVO MTR/TACH PG 55 

2 2 2 

3 AIL PASS 3 3 A1 L PASS 

4 ELE PASS 4 4 ELE PASS 

5 RU D PASS 5 5 RUD PASS 

6 PTRM PASS 6 (not available on ADI) 6 PTRM PASS 

7 LTRM PASS 7 7 LTRM PASS 

Page 116 





I 

1 RATE FEEDBACK 

2 

3 ROLL 

4 PITCH 

5 YAW 

PG 56 1 RATE FEEDBACK 

PG 56 1 RATE FEEDBACK 

2 2 

PASS 3 3 ROLL 

PASS 4 4 PITCH 

PASS 5 (not available on ADI) 5 YAW 

PASS 

PASS 

PASS 

I 

1 SERVO AMP 

2 

3 AIL 

4 ELE 

5 RUD 

6 PTRM 

7 LTRM 

PG 57 1 SERVO AMP 

PG 57 1 SERVO AMP 

2 2 

PASS 3 3 AIL 

PASS 4 4 ELE 

PASS 5 5 RUD 

PASS 6 (not available on ADI) 6 PTRM 

PASS 7 7 LTRM 

PASS 

PASS 

PASS 

PASS 

PASS 

I 

1 KFC4OO EXTERNAL DISCRETES PG 58 1 KFC400 EXTERNAL DISCRETES PG 58 1 KFC400 EXTERNAL DISCRETES PG 58 

2 2 2 

3 A/P DUMP (l=OPEN) 0 3 3 A/P DUMP (l=OPEN) 0 

4 CNI (l=SERIII) 1 4 4 CNI (l=SERIII) 1 

5 ROLL STEERING 1 5 5 ROLL STEERING 1 

6 AIR DATA (l=ALTRN) 1 6 (not available on ADI) 6 AIR DATA (l=ALTRN) 1 

7 A/P SYS (l=SINGLE) 0 7 7 A/P SYS (l=SINGLE) 0 

I 

1 BIT HISTORY 

EVENT 

000 

000 

000 

000 

000 

000 

000 

000 

- 2 PG 59 1 

DATA 2 

0000 1111 1111 0000 3 

0000 1111 1111 0000 4 

0000 1111 1111 0000 5 

0000 1111 1111 0000 6 

0000 1111 1111 0000 7 

0000 1111 1111 0000 8 

0000 1111 1111 0000 9 

0000 1111 1111 0000 10 

BIT HISTORY - 

EVENT DATA 

002 0000 

006 0000 

002 0000 

002 0000 

006 0000 

002 0000 

002 0000 

006 0000 

PG 59 1 BIT HISTORY - 2 PG 59 

2 EVENT DATA 

1101 1001 3 000 0000 1111 1111 0000 

0001 1001 4 000 0000 1111 1111 0000 

1101 1001 5 000 0000 1111 1111 0000 

1101 1001 6 000 0000 1111 1111 0000 

0001 1001 7 000 0000 1111 1111 0000 

1101 1001 8 000 0000 1111 1111 0000 

1101 1001 9 000 0000 1111 1111 0000 

0001 1001 10 000 0000 1111 1111 0000 

11 11 11 

12 PRESS NEXT MENU TO CLEAR ST 12 PRESS NEXT MENU TO CLEAR STACK 12 PRESS NEXT MENU TO CLEAR STACK 

___________---_____---------------I ----------------- 

I 

1 BIT HISTORY - 3 PG 60 1 BIT HISTORY - 

2 EVENT DATA 2 EVENT DATA 

3 000 0000 1111 1111 0000 3 002 0000 

4 000 0000 1111 1111 0000 4 006 0000 

5 000 0000 1111 1111 0000 5 002 0000 

6 000 0000 1111 1111 0000 6 002 0000 

7 000 0000 1111 1111 0000 7 006 0000 

8 000 0000 1111 1111 0000 8 002 0000 

9 000 0000 1111 1111 0000 9 002 0000 

10 000 0000 1111 1111 0000 10 006 0000 

_____-__-___-_-------------------- 

PG 60 1 BIT HISTORY - 3 PG 60 

2 EVENT DATA 

1101 1001 3 000 0000 1111 1111 0000 

0001 1001 4 000 0000 1111 1111 0000 

1101 1001 5 000 0000 1111 1111 0000 

1101 1001 6 000 0000 1111 1111 0000 

0001 1001 7 000 0000 1111 1111 0000 

1101 1001 8 000 0000 1111 1111 0000 

1101 1001 9 000 0000 1111 1111 0000 

0001 1001 10 000 0000 1111 1111 0000 

11 11 11 

12 PRESS NEXT MENU TO CLEAR ST 12 PRESS NEXT MENU TO CLEAR STACK 12 PRESS NEXT MENU TO CLEAR STACK 

I 

1 IP 429 ACTIVITY - 2 PG 61 1 429 ACTIVITY - 2 PG 61 1 IP 429 ACTIVITY - 2 PG 61 

2 2 2 

3 DME 1 FA1 L 3 3 DME 1 FAIL 

4 DME 2 135 4 not available 4 DME 2 135 

5 NAV 1 033 5 5 NAV 1 033 

6 NAV 2 032 6 

7 7 

6 

7 

NAV 2 032 

11 11 


11 



Page 11 7 

Revision AD



I 

1 AHRS MAIN MENU PG 62 1 AHRS MAIN MENU PG 62 1 AHRS MAIN MENU PG 62 

2 #1 #2 2 #1 #2 2 #1 #2 

3 --> STATUS PASS PASS 3 --> STATUS PASS PASS 3 --> STATUS PASS PASS 

4 MODES N/A N/A 4 MODES N/A N/A 4 MODES N/A N/A 

5 429 STATUS PASS FAIL 5 429 STATUS PASS FAIL 5 429 STATUS PASS FAIL 

I 

1 AHRS STATUS 

2 

3 AHRU 

4 ATTITUDE 

5 RMCU VALID 

6 MSU EXCITATION 

7 FAN WARNING 

PG 63 1 AHRS STATUS 

#1 #2 2 

PASS PASS 3 AHRU 

PASS PASS 4 ATTITUDE 

FAIL FAIL 5 RMCU VALID 

PASS PASS 6 MSU EXCITATION 

PASS PASS 7 FAN WARNING 

PG 63 1 AHRS STATUS 

#1 #2 2 

PASS PASS 3 AHRU 

PASS PASS 4 ATTITUDE 

FA1 L FA1 L 5 RMCU VALID 

PASS PASS 6 MSU EXCITATION 

PASS PASS 7 FAN WARNING 

PG 63 

#1 #2 

PASS PASS 

PASS PASS 

FAIL FAIL 

PASS PASS 

PASS PASS 

I 

1 AHRS MODES 

2 

3 ALIGN (O=READY) 

4 NORMAL (O=BASIC) 

5 HDG DG/SLVD(O=DG) 

6 GAIN SEL (O=HI) 

7 REVSN ATT (O=NORM) 

8 TAS 

9 VOR/DME INPUT #1 

10 VOR/DME INPUT #2 

0 

1 

0 

0 

PASS 

PASS 

FAIL 

1 

1 

PASS 

PASS 

PASS 

AHRS MODES PG 64 1 AHRS MODES PG 64 

#2 2 #1 #2 

1 3 ALIGN (O=READY) 1 1 

1 4 NORMAL (O=BASIC) 0 1 

1 5 HDG DG/SLVD(O=DG) 1 1 

1 6 GAIN SEL (O=HI) 0 1 

1 7 REVSN ATT (O=NORM) 0 1 

PASS 8 TAS PASS PASS 

ALIGN (O=READY) 

NORMAL (O=BASIC) 

HDG DG/SLVD(O=DG) 

GAIN SEL (O=HI) 

REVSN ATT(O=NORM) 

TAS 

VOR/DME INPUT #1 

VOR/DME INPUT #2 

1 

0 

0 

PASS 

PASS 

FAIL 

PASS 9 VOR/DME INPUT #1 PASS PASS 

PASS 10 VOR/DME INPUT #2 FAIL PASS 

1 TCAS MAIN MENU PG 65 1 TCAS MAIN MENU PG 65 1 TCAS MAIN MENU PG 65 

2 2 2 

3 --> TCAS COMPUTER FAULTS 3 **** NOT USED ******* 3 --> TCAS COMPUTER FAULTS 

4 EFIS TCAS STATUS 4 **** NOT USED ******* 4 EFIS TCAS STATUS 

___________________-_-------------I 

__-__-___-_________-_-------------I -------------------111111111111111 

I 

1 TCAS FAULTS MENU PG 66 1 TCAS FAULTS MENU PG 66 1 TCAS FAULTS MENU PG 66 

2 2 2 

3 --> TCAS FAULTS PAGE 1 3 **** NOT USED ******* 3 --> TCAS FAULTS PAGE 1 

4 TCAS FAULTS PAGE 2 4 **** NOT USED ******* 4 TCAS FAULTS PAGE 2 

5 TCAS FAULTS PAGE 3 5 **** NOT USED ******* 5 TCAS FAULTS PAGE 3 

6 429 STATUS PASS 6 6 429 STATUS N/A 

-------- 

I 

1 TCAS FAULTS - 1 PG 67 1 TCAS FAULTS - 1 PG 67 1 TCAS FAULTS - 1 PG 67 

2 

2 2 

3 PROCESSOR 

PASS 3 THIS PAGE NOT AVAILABLE 3 THIS PAGE NOT AVAILABLE 

4 UPPER ANTENNA PASS 4 ON AD1 DISPLAY 4 ON REVERSION DISPLAY 

5 LOWER ANTENNA PASS 5 5 

6 RADIO ALT 1 PASS 6 6 

RADIO ALT 2 PASS. 7 7 

XPDR 1 

PASS 8 8 

XPDR 2 

PASS 9 9 

ATTITUDE 

PASS 10 10 

HEADING 

PASS 11 11 

I 

1 TCAS FAULTS - 2 TCAS FAULTS - 2 PG 68 1 TCAS FAULTS - 2 PG 68 

RA DISPLAY 1 

RA DISPLAY 2 

XPDR UPPER ANT 

XPDR LOWER ANT 

TCAS TO XPDR 

CP TO XPDR 

ALT 1 TO XPDR 

ALT 2 TO XPDR 

PASS 

PASS 

PASS 

PASS 

PASS 

PASS 

PASS 

PASS 

2 

THIS PAGE NOT AVAILABLE 3 THIS PAGE NOT AVAILABLE 

ON AD1 DISPLAY 4 ON REVERSION DISPLAY 

5 

6 

7 

8 

9 

10 

Page 118 



_______________-__-IIIIIIIIIIIIIII 

BENDIX/KINGG" IFRAVIONICSI KFC 900 


______________-_-----__-----------I 

___________________IIII---I_II--III 

I 

1 TCAS FAULTS - 3 PG 69 1 TCAS FAULTS - 3 PG 69 1 TCAS FAULTS - 3 PG 69 

2 2 

3 THIS PAGE NOT AVAILABLE 3 THIS PAGE NOT AVAILABLE 

4 ON AD1 DISPLAY 4 ON REVERSION DISPLAY 

.................................. I 

I 

1 EFIS TCAS STATUS PG 70 

2 

3 IFILE BAD WORD CNT 12345 

4 IFILE BAD SSM CNT 12345 

5 IFILE DELTA TIME 12345 

.................................. I 

I 

1 ASCII TEXT PAGE MENU PG 71 

2 

3 --> AUTOPILOT BUS (LOW SPEED) 

4 CHECKLIST BUS (HIGH SPEED) 

5 RADAR BUS (ARINC 453) 

EFIS TCAS STATUS PG 70 1 

2 

THIS PAGE NOT AVAILABLE 3 

ON AD1 DISPLAY 4 

5 

__---______________----_-----__-I 

ASCII TEXT PAGE MENU PG 71 1 

2 

**** NOT USED * **A*** 

3 

**** NOT USED * *A**** 

4 

**** NOT USED * ***A** 

5 

EFIS TCAS STATUS PG 70 

THIS PAGE NOT AVAILABLE 

ON REVERSION DISPLAY 

ASCII TEXT PAGE MENU PG 71 

--> AUTOPILOT BUS (LOW SPEED) 

CHECKLIST BUS (HIGH SPEED) 

**** NOT USED * *****A 

______________-____------------_--I ___________________II-IIIIII_IIIII~ 

I 

1 ECP DISCRETE INPUTS PG 72 1 ECP DISCRETE INPUTS PG 72 1 ECP DISCRETE INPUTS PG 72 

2 MODE LINE# 4321 2 2 MODE LINE# 4321 

3 KBD CODE 1011 3 THIS PAGE NOT AVAILABLE 3 KBD CODE 1011 

4 4 ON AD1 DISPLAY 4 

5 KNOB LINE# 12 5 5 KNOB LINE# 12 

6 CRS KNOB 10 6 6 CRS KNOB 10 

7 HDG KNOB 00 7 7 HDG KNOB 00 

8 DH KNOB 11 8 8 DH KNOB 11 

9 DH IN/OUT OUT 9 9 DH IN/OUT OUT 

10 10 10 

11 SWITCH LINE RLUDE 11 11 SWITCH LINE RLUDE 

12 JOYSTICK 11111 12 12 JOYSTICK 11111 

________-_-________-----_-_-__----I 

____________------_II_IIIIIIIIIIIII .................................. 

I 

1 LOW SPEED ASCII TEXT PG 73 1 LOW SPEED ASCII TEXT PG 73 1 LOW SPEED ASCII TEXT PG 73 

2 2 2 

3 3 THIS PAGE NOT AVAILABLE 3 


I 

1 HIGH SPEED ASCII TEXT PG 74 1 HIGH SPEED ASCII TEXT PG 74 1 HIGH SPEED ASCII TEXT PG 74 

2 2 2 

3 3 THIS PAGE NOT AVAILABLE 3 


I 

1 RADAR 453 ASCII TEXT PG 75 1 RADAR 453 ASCII TEXT PG 75 1 RADAR 453 ASCII TEXT PG 75 

2 2 2 

3 3 THIS PAGE NOT AVAILABLE 3 THIS PAGE NOT AVAILABLE 

4 4 ON AD1 DISPLAY 4 ON REVERSION DISPLAY 


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BENDIXlKlN6" IFRAVIONICSI KFC 900 



A. TROUBLESHOOTING 

This section contains detailed checkout and troubleshooting information for the KFC 900 system. This 

section also describes the use of the diagnostic capabilities of the KCP 520 to make a detailed 

checkout of the system harness. The diagnostic information is accessed via the RTI. The following 

information is available using the manual tests area of the diagnostic section. 

NOTE During diagnostic operation, AP FAlL and SAS FAlL will be illuminated on the annunciator 

panel. A red FD will also be illuminated on the EADI. These are normal indications. 

The following flow charts are provided to facilitate troubleshooting of the KFC 900 system. 

BRWiEREUlESET 

TOBLTT 

SETTHE IPS WTER 

SYITMW,Nmr"E*P 

fHEUETW\T,LLLnS 

~"SC(LSIRIm- 

I I 

Figure 106: Troubleshooting KFC 900 System 

Page I20 

Revision AD



/ PREVIOUS 

CONTINUED FROM 

PAGE I 

PERFORM AFCS 

CONFIGURATION 

CONDITION STILL REPLACE THE KCP 520 

PERFORMAFCS 

CONFIGURATION 

CONDITION STILL REPLACE THE KCP 520 

PRESS THEVS BUTTON 

ON THE KMS 540 

REPLACE THE KCP 520 REPLACE THE SG 465 

PRESS THE FD SYNC 

BUTTON 

I I 

CENTER? 

REPLACED? 

REPLACE THE TRlh 

SYNC SWTCH 

REPLACE THE KMS 540 

I 

ANNUNCIATE ON 

THE EADI? 

BEENPEPLACEO? 

REPLACE THE GA SWTCH 

YES 

YES 

CONTINUED ON NEXT PAGE 

Figure 107: Troubleshooting KFC 900 System (Continued) 

Page 121 

, Revision AD



I SIMJLATE 

I 

PREVIOUS PAGE 

&hAIRSPEED 

ABOVE SOKIAS US NO A 

PITOTISTATIC TESTER 

I 

PRESS THE SAS BUTON 


REPLACE THE KMS 540 REPLACE THE KCP 520 

REPLACE ANNUNCIATOR 

I M l 

ILLUMINATE? 

PERFORM LAMP TEST 

PRESS THE DISCONNECT 

ON EITHER CYCUC GRIP 

A 

HEADSETS7 

BEEN 

REPLACE THE AUDIO PANEL 

PRESS THE AP BUTTON 


I I 

REPLACE THE KCP 520 

C 

REPLACE ANNUNCIATOR 

lAMPS 

PERFORM LAMP TEST 

CONTINUED ON NEXl PAGE 

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CONTINUED FROM 


I I 

REPLACETHE KCP 520 

REPLACE YAWSPRING 

CARTRIDGE OR PITCH OR 

ROLL STRING POTS 

I 

COLLECTNE 

8 

REPLACE THE KCP520 

REPLACE YAWSPRING 

CARTRIDGE 

LEFTOR RIGHT I 1 

DIRECTION? 

M"" 

PRESS THE VS BUnDN 

ON THE KMS M 0 

CYCLIC TRlMlFD 

REPLACED? 

YES 

REPLACE THE TRlhUFD 

SYNCH SWTCH 

I I 

REPLACE THE KMS M 0 

EADI? 

REPLACED? "u 

I r 

PRESSTHE PITCHTRIM 

n H ON THE CYCLIC 

UP OR DOWN 

FOR EACH 

PRESS? 

REPLACED? 

SYNCH SWTCH 

REPLACE THE KMS 510 



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B. FCC ANNUNCIATIONS 



The FCC provides mode annunciation information to the MSP to illuminate the mode indicators above 

the appropriate mode pushbutton. It also provides the annunciations described in the following 

sections. These annunciations are also summarized in the following tables. Annunciations in Table 

101 assume that AP was engaged when the condition occurred. Table 102 assumes only SAS was 

engaged when a failure occurred. 

Table 101: AP Failure Annunciations 

Page 124 





Table 102: SAS Failure Annunciations 

AHRSl333 Yaw Rate or 

Miscompare Failure 

FD Sync 

ON 

ON 

OFF 

OFF 

OFF 

OFF 

OFF 

OFF 

ON 

OFF 

YAW 

SAS 

SAS 

SAS 

SAS 

ON 

OFF 

1) POWER FAILURE ANNUNCIATION - The KCP 520 FCC shall monitor the 28 Vdc AP and FD 

power inputs and provide an appropriate annunciation when these inputs fall below the threshold 

for proper operation, as described in the following paragraphs. 

a) APISASIFD POWER FAILURE ANNUNCIATION - The power failure annunciations are 

accomplished by the SAS FAlL and AP FAlL annunciations and by a red FD annunciator 

displayed on the EADI. When a power failure occurs, the SAS FAlL output will be open, 

which is the active state. The harness forces an AP FAlL annunciation whenever SAS FAlL is 

active. The red FD annunciator will be displayed on the EADI whenever the flight director data 

becomes unavailable or invalid. If this flag is annunciated, related autopilotlflight director 

annunciators and command bars are decluttered or flagged, as appropriate. Table 104 

defines the required operation for the AP FAlL and SAS FAlL annunciations. The FD failure 

annunciation is provided for reference, but no action is required by the FCC, since the correct 

annunciation is provided automatically by the EFIS. 


97-00-00 

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BENDIX/KINGGe IFR AVIONICS I KFC goo 


Table 103: AFCS Power Failure Annunciations 

b) MECHANIZATION OF POWER FAILURE ANNUNCIATION - The FCC shall force a FD 

disconnect upon reaching the minimum designed power level for FD operation and force a FD 

processor reset and hold this reset until the power returns above this level. However, AP 

default modes and SAS shall not be affected by a power interrupt to the FD. This action 

causes loss of ARlNC transmission from the FCC to the EADl upon which the EADl will 

display the red FD annunciator. The FD disconnect shall result in a reversion to the AP 

default modes if the AP was engaged prior to the FD power interrupt. Mode annunciation on 

the EADl and MSP will be lost, however, the AP mode will be annunciated by the AFCS 

annunciator panel. 

The FCC shall disconnect coupled flight when the input voltage falls below the minimum level 

designed for APISAS operation, generate a SAS FAIL, and force AP processor resets and hold 

those resets until the power returns to above designed start up level. This action causes mode 

annunciation changes and coupled flight disconnect visual and aural warnings. It also provides for a 

controlled onloff operation of the AP processors and, subsequently, a controlled onloff operation of 

the power warnings. After power has exceeded the designed start up level again, successful 

preflight test shall be required before coupled flight is allowed. 

All power failure annunciations shall cease when the power has reached an acceptable level for 

normal operation. This is achieved by normal FCC processor operation and normal validity 

checking by the EADl on the FCC data being transmitted. 

2) NAVIGATION REFERENCE ANNUNCIATION - The FCC shall provide annunciation on the EFlS 

display indicating when it is coupled to the navigation source selected. The absence of an AP 

annunciation in the AP mode field of the EFlS display shall indicate to the pilot that the autopilot is 

not engaged to the airborne navigation reference. 

3) APISAS MODE ANNUNCIATION - Discrete green annunciations are provided for AP and SAS 

engagement on the AFCS annunciator panel. The FCC shall provide openlground discrete 

outputs for these annunciations, where ground is the active state. These annunciations are 

mutually exclusive - AP shall be annunciated whenever the autopilot function is engaged and the 

cyclic or yaw detent switches are not active; SAS shall be annunciated whenever the SAS function 

is engaged, including momentary interruption of autopilot function with "fly-thru" operation by pitch, 

roll or yaw detent switches. In addition to these discrete annunciations, AP engagement shall also 

be annunciated on the EADI, MSP and AFCS annunciator panel. 

4) SAS FAlL AND AP FAlL ANNUNCIATIONS - The FCC shall provide openlground discrete outputs 

for red SAS and AP failure annunciations, where open is the active state for SAS failure and 

ground is the active state for AP failure. Successful completion of pre-flight test in at least one 

applicable control axis shall clear the applicable failure annunciation. 

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a) SAS FAlL LOGIC - The SAS failure annunciator output shall be active for power failures, 

processor failures, and failures detected by the processors. The latter shall include invalid 

rate signals and failures detected by the monitors. The rate signal will be considered invalid 

for the following conditions. 1) Rate source is invalid. 2) One of the three rate sources 

disagree with the other two rate sources for more than 0.3 seconds and more than 2 degrees 

per second in pitch and more than 2.5 degrees per second in roll will give an appropriate axis 

failure without master SAS fail annunciation. The annunciation of a SAS failure is 

accomplished by an open to the failure annunciator panel. Any failure including preflight test 

that prevents proper SAS operation in all three axes shall generate a SAS failure 

annunciation. Failures which prevent SAS operation in only one or two axes shall be 

annunciated by an axis failure indication. Rate failures as described above will give the 

following system responses. If the failure is either KRG 333 Primary or Secondary roll or pitch 

failure then the system will revert to Hardover Recovery Mode (HOR) in the appropriate axis. 

If the failure is an AHRS roll or pitch failure then system will disconnect the appropriate 

axislaxes. If rate failures exist before engagement it will inhibit the appropriate axis or axes 

from engagement. Rate failures will not require passing preflight test to clear the failure 

annunciation. Trim failures in the roll and pitch axes will result in respective axis failure 

annunciation and will inhibit axis engagement due to the requirement to have trim available for 

HOR in case of a primary servo displacement caused by failure. 

b) AP FAlL LOGIC - The red AP failure annunciation shall be active for all failures that generate 

a red SAS failure annunciation. In addition, with AP engaged an AP single axis failure 

annunciation shall indicate failures in the yaw trim (thruster) control paths detected by the 

thruster servo amplifier and thruster servo actuator monitors. These failures shall be 

annunciated for the failed axis on the AFCS annunciator panel. NOTE: A harness relay 

automatically forces the red AP failure annunciator on for any red SAS failure. 

5) TRIM FAILURE ANNUNCIATIONS - Pitch and roll trim failures shall be annunciated on the EADl 

for any failures in the trim control path of any axis detected by the servo amplifier and servo 

actuator monitors. The pitch and roll single axis appropriate failure annunciation shall be 

activated when AP or SAS is engaged. These failures will be annunciated on the EADl as PTCH 

and ROLL respectively. Thruster failures will be annunciated via a red YAW on the AFCS 

annunciator panel and with a red YAW annunciation on the EADI. 

6) AXIS FAILURE ANNUNCIATIONS - The AFCS annunciator panel in the cockpit annunciates 

failures of the pitch, roll, yaw (thruster), and VSCS (right vertical fin) control axes. The FCC shall 

provide openlground discrete outputs for these annunciations, where ground is the active state. 

These annunciations shall indicate any failures in the indicated control axis, as detected by the 

servo amplifier and servo actuator monitors. In addition to the primary axis annunciations the 

pitch and roll annunciator shall indicate failure of the trim in that respective axis. 

C. AFCS DISCONNECT AURAL ALERT 

The normal duration of the AFCS disconnect aural alert shall be 2.0 +I- 0.5 seconds. Loss of power 

resulting in an AFCS disconnect shall generate an AFCS disconnect aural alert. 

D. MANUAL TESTS 

This section can be accessed from the main menu by entering the Manual Tests ("M") at the 

diagnostic mode screen: 

The FCC provides an RS 232 interface for diagnostic and installation capabilities. The FCC 

installation and diagnostic software is described later in this section. A step by step instruction for an 

initial configuration is also presented later in this section. 

The RS 232 interface to the flight control computer is through a Remote Terminal Interface (RTI) 

connector located on the right hand side of the cockpit center pedestal. Connect the 


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200-05647-0022 diagnostic harness to the pedestal mounted diagnostic connector. Connect the 

AFCS connector to the desired COM port on an IBM compatible computer. 

The RTI will be made using the terminal emulator in the "ACCESSORIES" group of Microsoft 

Windows (version 3.1 or later). Use of other interface mediums is acceptable. The screens do not 

change when using an alternate RTI. 

Double click on the "TERMINAL" icon. Upon entering the terminal emulator, select the "Settings" 

menu item, then select "Communications" menu option. Configure the communications for a 9600 

baud rate, 8 data bits, 1 stop bit, no parity (none), XonlXoff flow control, and the desired COMM port 

(typically COMA). Click on the "OK. 

Select the "Settings" menu item again, and select "Terminal Preferences ..." menu option. Deselect 

the "Use Function, Arrow, and Ctrl Keys for Windows" option at the bottom of the dialogue box. Click 

the "OK. 

It is recommended that the settings that have been entered be saved for future interface to the AFCS. 

The RTI main menu provides the selections for entering diagnostic mode or displaying stored error 

codes. The following paragraphs provide specific instructions on using these capabilities to perform 

the required installation and ground checkout procedures. 

The main menu for the configuration software provides two selections: 1) Enter Diagnostic Mode and 

2) Logged Data. The Diagnostic Mode contains the test and configuration commands for the AFCS. 

The Logged Data contains error codes for the FCC since the last time the error memory was cleared. 

The Diagnostic Mode has six selections: 1) Automated tests, 2) Manual tests, 3) Setup installation, 4) 

Logged data, 5) Software identification and 6) Primitive interface. Automated tests verify operation of 

internal processors and buses in the FCC. Manual tests can be used to verify operation of processors 

internal buses as well as entering various values to the system. Setup installation is used to configure 

the AFCS equipment. Logged data provides access to logged error messages. Software 

identification lists the appropriate software part numbers for the FCC and the MSP. Primitive interface 

is for computer controlled testing. 

- 

System mode: Diagnostic 

Selected processors: AP A, AP B, ED A, MA1 

Diagnostic mode 

A - Automated tests 

M - Manual Tests 

I - Setup installation 

S - Software identification 

Press key for desired option ( to exit) : 

After pressing "M", the following screen should appear: 


Selected processors: AP A, AP B, ED A, MA1 


D - Discrete 1/0 

4 - ARINC 429 1/0 

A - Analog 1/0 


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Select Manual Tests by pressing the m key on the computer. At this point, the screen shows the 

selection of processors available: 


Selected processors: AP A, AP B 

Select processor 

A - Autopilots 

1 - Autopilot A 

2 - Autopilot B 

F - Flight directors 

M - Maintenance 

Press key to select processor, ( to continue) : 

The discrete ilo data for the autopilot processors should look something like the following: 



>: selected output; a, b: no response; *: stale data 

Discrete outputs 

Discrete inputs 

---------------- ................................... 

>Port 0: OOOH AP A Port 0: 08C9H 0000100011001001 

Port 1: OOOH 

AP B Port 0: 08C9H OOOOlOOO11OO1OO1 

Port 2: OOOH AP A Port 1: 4001H 0100000000000001 

Port A: 1H AP B Port 1: 4001H 0100000000000001 

AP A Port 2: 908CH 1001000010001100 

AP B Port 2: 908CH 1001000010001100 

AP A Port 3: 0018H 0000000000011000 

AP B Port 3: 0018H 0000000000011000 

AP A Port A: 6 H 0110 

AP B Port A: 5H 0100 

Discrete output commands: 

S : Select Output 

C : Cycle output patterns (0000, 5555, AAAA, FFFF) 

W : Walking ones and zeros output patterns 

V : Enter user-defined output value in hex 

: Exit 

NOTE : Port A output bit is used by the analog input software; 

It cannot be controlled by the user. 

This is a typical discrete ilo screen. Other screens may vary. 

The ARlNC 429 selection should display a similar screen for processor selection. Once a processor 

has been selected, a screen similar to the following should appear: 


I 

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BENDIXIKINNG" IFR AVIONICS I KFC 900 




>: selected output/input; a, b: no response: *: stale data; m: label match 

ARINC 429 outputs AP A ARINC 429 inputs AP B ARINC 429 inputs 

----------------- ....................... ....................... 

ASIC 0: OOOOOOOOH ASIC 0 ch 0: *7FFFFFFFH ASIC 0 ch 0: *7FFFFFFFH 

ASIC 0 ch 1: *7FFFFFFFH ASIC 0 ch 1: *7FFFFFFFH 

ASIC 0 ch'2: 200000DDH ASIC 0 ch 2: 200000DDH 

ASIC 0 ch 3: *--------H ASIC 0 ch 3: *--------H 

Internal wrap-around 

.................... 

ASIC 0: Disabled 

ARINC 429 commands: 


C : Cycle output patterns (0000, 5555, AAAA, FFFF) 

W : Walking ones and zeros output patterns 

V : Enter user-defined output value in hex 

E : Enable/disable internal wrap-around 

I : Select Input 

M : Toggle label match on and off 

L : Specify label match in hex 

: Exit 

This is a typical ARINC 429 i/o screen. Other screens may vary. 

The analog selection should display a similar screen. Once an analog I10 has been selected, a 

screen similar to the following should appear: 



>: selected output/input; a, b: no response: *: stale data; 

Analog outputs 

AP A Mux 0 Analog inputs 

------------------ .............................................................. 

--- 

8 : 0.0000 0: 7FEH -0.0389 volts 8: ---H ----------- 

9 : 0.0000 1: 7FDH -0.0045 amps 9: ---H ----------- 

10: 0.0000 2: 7FEH -0.0141 in/sec 10: ---H ----------- 

11: 0.0000 3: 7FFH -0.8281 degrees 11: ---H ----------- 

12 : 0.0000 4: 7FDH -0.0146 volts 12: ---H ----------- 

13: 0.0000 5: 7FEH -0.0392 volts 13: ---H ----------- 

14 : 0.0000 6: 802H -0.0030 amps 14: ---H ----------- 

15 : 0.0000 7: 7FFH -0.0071 in/sec 15: ---H ----------- 

Analog 1/0 commands: 


P : Select next input processor 

M : Select next input mux 

H : Select next half of input mux 

V : Enter output value (-1.0 to 1.0) 

T : Toggle between converted data and volts 

: Exit 

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EFFECTIVITY: MID900 

I



E. FCC ERROR CODES 

1) PURPOSE - This section describes the error codes generated by the KCP 520 Flight Control 

Computer. This information should be used to troubleshoot system or computer failures. Refer to 

the use of diagnostics in Section D to further diagnose possible problems. 

2) GENERAL INFORMATION - Each error has a unique number and text message that is displayed 

when the logged errors are displayed. This document provides additional information concerning 

the possible reasons for the error. NOTE: The text for some messages is abbreviated to fit into 

30 characters. 

Errors 0 through 342 are fatal. These cause the processor to be reset. Errors 360-363 and 381 

are detected after a reset has occurred for the indicated reason. The rest of the errors will not 

reset the processor, but will affect operation as indicated in the description. 

3) ERROR CODE DESCRIPTIONS - The following lists the error code number, text message, and 

description for each error logged by the KCP 520. 

I EFFECTIVITY: MD900 -1 

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4) ERROR CODE CATEGORIES - The following lists the general categories for the KCP 520 errors. 

It includes a category name, a description of the category, and the range of error code numbers 

contained in that category. 

Category Error range Description 

Exception Vectors 0 - 299 Related to unintended interrupts (exceptions) detected by 

the common kernel interrupt service routine (generic 

interrupt handler which is used in all KCP 520 

processors) 

Interprocessor Bus 

RS232 

Direct Memory Access 

300 - 399 Related to failures in the microprocessor or operating 

system 

400 - 499 Related to failures in the interprocessor (IP) 

communication bus 

500 - 599 Related to failures in the RS232 serial interface to a 

remote terminal or the configuration module 

600 - 699 Related to failures in the direct memory access (DMA) 

data transfer 

ARINC 429 ASIC 700 - 799 Related to failures in the ARINC 429 LSI 

Flight Director 800 - 899 Related to failures detected by the flight director 

1900 - 1999 processor when an improper mode change is requested 

InputIOutput 900 - 999 Related to generic input and output failures 

Embedded Control 1000 - 1099 Related to failures in the embedded control algorithm 

Algorithm Language 

language (ECAL) algorithms 

Analog input 1200 - 1299 Related to failures when inputting analog data 

Floating point 

1300 - 1399 Related to failures detected when performing floating 

point arithmetic operations 

Installation 

1400 - 1499 Related to installation parameters than are invalid upon 

powerup initialization 

Pre Flight Test 

1500 - 1699 Related to failures detected during the automatic powerup 

or pilot initiated system test 

Gains 

1700 - 1799 Related to failures detected when translating gains from 

ROM to RAM for autopilot processor use 

Frame synchronization 1800 - 1899 Related to 10 Hz task frame losing synchronization with 

the 40 Hz task frame 

Autopilot 2000 - 2099 Related to data mismatch between AP processors 

detected by AP mode logic 

Autopilot monitoring 3000 - 3999 Related to failures detected by the system monitors in the 

autopilot processor 

5) ERROR CODE DESCRIPTIONS - The following lists the error code number, text message, 

unit(s) where failure may have occurred and a description for each error logged by the KCP 520 

flight computer. When more than one unit is listed, there is a possibility that the wiring harness 

connections between any of the listed units has failed. 

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Error #(s) 

Text Message@) 

Possible failed unit@) 

SSP VBR 0 1. KCP 520 

PC VBR 1 

A processor reset occurred due to an unknown cause. 

BUS ERROR 1. KCP 520 

A system bus fault was detected. Either there has been a failure in the hardware bus structure in the KCP 520 or the 

software processing the bus has failed. 

ADDRESS ERROR 1. KCP 520 

The processor attempted to fetch an instruction or multi-byte data packet from an odd (byte) address, instead of fiom 

an even (word) address. 

ILLEGAL INSTRUCTION 1. KCP 520 

An illegal or unimplemented instruction code was fetched by the processor. 

ZERO DIVIDE 1. KCP 520 

The processor attempted an integer division by zero. There will probably also be floating point errors logged when 

this failure occurs. 

CHK, CHK2 INSTRUCTIONS 1. KCP 520 

TRAPcc, TRAPV INSTRUCTIONS 

The processor trapped an instruction. Traps are normally used for debugging purposes. The processor has tried to 

trap an instruction (to stop the processor) when operating normally. 

PRIVILEGE VIOLATION 1. KCP 520 

An attempt was made to execute a privileged instruction when not in supervisor mode (i.e., changing the value of the 

stack pointer when in user mode). 

TRACE 1. KCP 520 

The processor encountered a trace (used for debugging purposes) during normal operation. 

LINE 1010 EMULATION 

LINE 1111 EMULATION 

1. KCP 520 

The processor encountered an exception (interrupt) that is reserved for an emulator. 

HARDWARE BREAKPOINT 1. KCP 520 

The hardware in the KCP 520 incorrectly requested a breakpoint in software to occur. 

COPROCESSOR PROTOCOL VIOLATION 1. KCP 520 

The math coprocessor improperly communicated with the processor. Since there is no math coprocessor, this error 

should not occur. 

FORMAT ERROR 

UNINITIALIZED INTERRUPT 

1. KCP 520 

The processor found an invalid format code in the stack control operations or an interrupt vector that was not 

initialized. 

EXCEPTION RESERVED x 1. KPC 520 

where x is the error number 

Reserved exceptions (interrupts) that are unimplemented in the processor. 

SPURIOUS INTERRUPT 1. KCP 520 

A spurious interrupt occurred in the processor. This can indicate a software problem or the KCP 520 hardware 

incorrectly requested an interrupt. 


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Error #(s) 

2 5 

2 6 

27 

2 8 

2 9 

30 

31 



Text Message(s) 

Possible failed unit(s) 

AUTO-VECTOR LEVEL 1 1. KCP 520 

AUTO-VECTOR LEVEL 2 





AUTO-VECTOR LEVEL 7 NMI 

An exception (interrupt) occurred at the indicated priority level (1 - 7) that could not be properly identified or 

serviced. This can indicate a missing interrupt service routine or other software problem or the KCP 520 hardware 

incorrectly requested an interrupt. 

TRAP 0 1. KCP 520 

TRAP 1 

TRAP 2 

TRAP 3 

TRAP 4 

TRAP 5 

TRAP 6 

TRAP 7 

TRAP 8 

TRAP 9 

TRAP A 

TRAP B 

TRAP C 

TRAP D 

TRAP E 

TRAP F 

An unexpected trap instruction occurred to switch from user mode to supervisor mode. 

COPROC UNORDERED CONDITION 1. KCP 520 

COPROC INEXACT RESULT 

COPROC DIVIDE BY ZERO 

COPROC UNDERFLOW 

COPROC OPERAND ERROR 

COPROC OVERFLOW 

COPROC NAN 

COPROC RESERVED 55 




The math coprocessor detected an arithmetic error during operation. Since there is no math coprocessor, this error 

should not occur. 

EXCEPTION RESERVED x 1. KCP 520 


Reserved exceptions (interrupts) that are unirnplemented in the processor. 

HW INTERRUPT x 


1. KCP 520 

Hardware exceptions (interrupts) that are unirnplemented in the processor. This can indicate a software problem or 

the KCP 520 hardware incorrectly requested an interrupt. 

RAM test failure 1. KCP 520 

Powerup routines detected a failure in the RAM memory. 

301 ROM test failure 1. KCP 520 

Powerup routines detected a failure in the EPROM memory during the CRC checksum test of the ROM. 

302 CPU32 test failure 1. KCP 520 

Powerup routines detected a failure when testing performance of operations in the processor instruction set. 

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Error #(s) 

302 



CPU32 test failure 1. KCP 520 

Powerup routines detected a failure when testing performance of operations in the processor instruction set. 

Timer test failure 1. KCP 520 

Powerup routines detected a failure when testing the processor interval timer. 

Task number out of range 1. KCP 520 

The task number passed to CK-save-async 

asynchronous tasks defined. 

Watchdog test failure 1. KCP 520 

routine as a parameter exceeds the total number of synchronous and 

Powerup routines detected a failure with the software watchdog. The software watchdog failed to interrupt the 

processor within a given time period. 

Kernel frame overrun 1. KCP 520 

Reserved error number, used as a base for following frame overrun errors. 

Kernel task x frame overrun 1. KCP 520 

where x is the error number - 3 10 

The frame time was exceeded while executing task x (task number in error task). The processor ran out of time to 

complete all required tasks during a frame time. 

Watchdog reset 1. KCP 520 

The watchdog circuitry caused a reset that was not expected. 

Double bus fault reset 1. KCP 520 

A second bus exception occurred while still processing a previous bus exception (interrupt). This indicates a failure 

with the interprocessor communication bus. 

Loss of clock reset 1. KCP 520 

Processor system clock has lost its crystal input signal, indicating a possible malfunction in the crystal oscillator. 

CPU fail 1. KCP 520 

The processor was reset due to a RESET instruction or other undiscriminated cause. 

No processor ID 1. KCP 520 

The processor ID discrete input has not been set properly. 

Software watchdog reset 1. KCP 520 

The watchdog circuitry was not reset within the watchdog time-out period, so the watchdog reset the processor. 

NVRAM error queue checksum 1. KCP 520 

The error logging routines detected a checksum error in the non-volatile RAM. 

IP powerup fail 1. KCP 520 

Powerup routines detected a generic fault in the serial inputloutput capability of the processor which affects all 

interprocessor communications. 

NCIP powerup test2 

CIP powerup test3 

1. KCP 520 

Powerup routines detected a failure in indicated channel of the serial interprocessor bus (channel A for CIP, channel 

B for NCIP). 

1. KCP 520 

The status of a received communication packet was invalid. If the error occurred once, probably noise on the bus 

caused a packet to get corrupted.4 


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Error #(s) 

405 

4 0 6 



NCIP RX countL 1. KCP 520 

CIP RX count3 

The count byte in a received packet was improper for the data type (i.e., ARINC 429 data type should have 4 bytes, 

but count byte says there are 5 bytes in the packet). If the error occurred once, probably noise on the bus caused a 

packet to get corrupted! 

NCIP RX invalid type2 

1. KCP 520 

CIP RX invalid type3 

An unsupported data type was received during normal mode operation (i.e., text). If the error occurred once, 

probably noise on the bus caused a packet to get corrupted or a diagnostic mode packet was being transmitted when 

entering normal mode! 

NCIP RX checksum2 

1. KCP 520 

CIP RX checksum3 

The checksum for a received data packet was incorrect. If the error occurred once, probably noise on the bus caused 

a packet to get corrupted? 

NCIP RX ARINC queue full2 1. KCP 520 

CIP RX ARINC queue full3 

The buffer used to store received data from the interprocessor bus has been filled before it could be serviced. The 

communication bus is overloaded with transmitted data, the processor cannot process the data as rapidly as it is being 

re~eived.~.' 

NCIP RX text queue full2 1. KCP 520 

CIP RX text queue full3 

The buffer used to store received text from the interprocessor bus has been filled before it could be serviced. The 


NCIP RX CTS active3 

CIP RX CTS active3 

1. KCP 520 

Data was received on the interprocessor bus while bus status indicated the bus should be available! 

NCIP RX and TX conflict2 1. KCP 520 

CIP RX and TX conflict3 

Data was received on the interprocessor bus while the processor reporting the error had control of the bus.4 

NCIP TX bus conflict2 

CIP TX bus conflict3 

1. KCP 520 

Another processor tried to take bus control while the reporting processor had bus control! 

NCIP detect break2 

CIP detect break3 

1. KCP 520 

A start of end of serial break was detected on the interprocessor bus. If the error occurred once, probably noise on the 

bus caused a packet to get corrupted.4 

NCIP RX wrong char. typ$ 1. KCP 520 

CIP RX wrong char. type 

An unsupported character type was received on the interprocessor bus. If the error occurred once, probably noise on 

the bus caused a packet to get corrupted.4 

IP change of state 1. KCP 520 

The interprocessor bus changed state (fkom inactive to active, etc.) unexpectedly.4 

Page 136 

Revision AD 


I



Error #(s) 

426 

427 



CIP TX IP queue full3 1. KCP 520 

NCIP TX IP queue full2 

The buffer used to store data to be transmitted on the interprocessor bus has been filled before it could be serviced. 

Possibly another processor is "babbling" (transmitting data on the bus almost constantly, not allowing another 

processor to gain control of the bus). 

CIP IP send txt queue full3 1. KCP 520 

NCIP IP send txt queue full2 

The buffer used to store text data to be transmitted on the interprocessor bus during diagnostic mode has been filled 

before it could be serviced. Possibly another processor is "babbling" (transmitting data on the bus almost constantly, 

not allowing another processor to gain control of the bus). 

Unknown text lbl rxd on CIP~ 1. KCP 520 

Unknown text lbl rxd on NCIP~ 

An unrecognized text label was received on the interprocessor bus. If the error occurred once, probably noise on the 

bus caused a packet to get corrupted.4 

NCIP bus ISR exceed max. count 1. KCP 520 

CIP bus 'ISR exceed max. count 3 

During the interrupt service routine for the interprocessor bus, the size of a data packet exceeded the maximum size 

(count in byte^).^ 

IP bus ISR switch error 1. KCP 520 

An error occurred when trying to execute the switch statement on packet type in the interrupt service routine for the 

interprocessor bus. This is a software failure that should not occur. 

NCIP RX break2 1. KCP 520 

CIP RX break3 

A break character was received on the interprocessor communication bus. If the error occurred once, probably 

noise on the bus caused a packet to get 

NCIP RX framing error2 

1. KCP 520 

CIP RX framing error 3 

The receipt of a data packet was incomplete, the processor expected to receive more data packets, but did not. If the 

error occurred once, probably noise on the bus caused a packet to get corr~~ted.~'~ 

2 

NCIP RX overrun error 1. KCP 520 

CIP RX overrun errorJ 

The interprocessor bus receiver received another data byte before the processor could read the previous data byte 

received. If the error occurred once, probably noise on the bus caused a packet to get c~rru~ted.~'~ 

RS232 status register 1. KCP 520 

2. Unit connected to RS 232 port (i.e., PC for interface) 

An error occurred in the RS 232 serial communications transceiver that placed the status into an invalid state. 

RS232 receive queue full 1. KCP 520 

The receive buffer for RS 232 serial information received has filled before it could be serviced. Possibly the RS 232 

bus became overloaded with incoming data and the processor could not keep up.5 

RS232 unknown interrupt source 1. KCP 520 

An interrupt was requested for RS 232 interface, but it was not caused by the transmitter or the receiver. 


I 

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Revision AD



Error #(s) 

503 



RS232 Receive time out 1. KCP 520 

Powerup routines detected a failure to receive a transmitted byte within the allowed time period by the RS 232 

receiver. There may be nothing connected to the RS 232 receive port. 

RS232 Transmit time out 1. KCP 520 

Powerup routines detected that the RS 232 transmitter was unavailable within the allowed time period. 

RS232 test data mismatch 1. KCP 520 

Powerup routines detected a failure in the RS 232 data wraparound test. The processor did not receive back what 

was transmitted. 

DMA 1 queue full 

DMA 2 queue full 

1. KCP 520 

The buffer used for receiving ARINC 429 data from the ASIC has filled before it could be serviced. Possibly the 

processor cannot keep up with data received from the ARINC 429 

DMA 1 transfer not complete 1. KCP 520 

DMA 2 transfer not complete 

Powerup routines detected that the indicated DMA channel failed to transfer all of its requested data.6 

DMA 1 bus source 

DMA 2 bus source 

1. KCP 520 

There was a bus error while attempting to read from the indicated DMA 

DMA 1 bus dest 

DMA 2 bus dest 

1. KCP 520 

There was a bus error while attempting to write data input fi-om the ARINC 429 ASIC into the RAM 

DMA 1 configuration 

DMA 2 configuration 

1. KCP 520 

The port size specified for the source or destination address does not match the address used (e.g. odd address used 

with 16-bit port).6 

DMA 1 transfer 

DMA 2 transfer 

1. KCP 520 

The DMA transfer had not completed when the DMA controller interrupted the 

ARINC 

ARINC 

ARINC 

ARINC 

ARINC 

ARINC 

ARINC 

ARINC 

ARINC 

ARINC 

ARINC 

ARINC 

ARINC 

ARINC 

ARINC 

ARINC 

429 #1 CH 0 label 

429 #1 CH 0 data 

429 #1 CH 1 label 

429 #1 CH 1 data 

429 #1 CH 2 label 

429 #1 CH 2 data 

429 #1 CH 3 label 

429 #1 CH 3 data 

429 #2 CH 0 label 

429 #2 CH 0 data 

429 #2 CH 1 label 

429 #2 CH 1 data 

429 #2 CH 2 label 

429 #2 CH 2 data 

429 #2 CH 3 label 

429 #2 CH 3 data 

1. KCP 520 

Powerup routines detected an invalid label or data received on the indicated ARINC 429 chip and channel (i.e., 

invalid data on 429 chip number 1, channel 1 for error 703). 

Page 138 

Revision AD 




Error #(s) 

716 

717 

718 

7 19 

720 

721 

722 

723 



ARINC 429 #1 CH 0 receive 1. KCP 520 

ARINC 429 #1 CH 1 receive 







Powerup routines detected no received data on the indicated ARINC 429 chip and channel. 

ARINC 429 #1 TX error 1. KCP 520 

ARINC 429 #2 TX error 

Powerup routines detected that transmitted data for the indicated ARINC 429 chip was not received on any channel 

during loopback testing. 

ARINC 429 #1 TX timeout 1. KCP 520 

ARINC 429 #2 TX timeout 

Powerup routines detected that the transmitter for the indicated ARMC 429 chip did not become available in the 

allotted time. 

NAVTRK input-LCPLD Default mde 1. KCP 520 

APRTRK input-LCPLD Default mde 2. ~ ~ ~ 5 4 0 

NAVTRK input-LCPLD HDGSEL mode 

APRTRK input-LCPLD HDGSEL mode 

NAVCAP input-LCPLD NAVCAP mode 

APRCAP input-LCPLD NAVCAP mode 

APRTRK input-LCPLD NAVCAP mode 

NAVTRK input-LCPLD NAVTRK mode 

APRCAP input-LCPLD NAVTRK mode 

APRTRK input-LCPLD NAVTRK mode 

NAVCAP input-LCPLD APRCAP mode 

NAVTRK input-LCPLD APRCAP mode 

APRCAP input-LCPLD APRCAP mode 

NAVCAP input-LCPLD APRTRK mode 

NAVTRK input-LCPLD APRTRK mode 

APRTRK input-LCPLD APRTRK mode 

NAVTRK input-LCPLD GA mode 

APRTRK input-LCPLD GA mode 

There was an invalid lateral mode requested based on the current lateral mode (i.e., for error 800, NAVTRK mode 

was requested, but cannot be engaged when in lateral default mode). 

Illegal Lateral Coupled mode 1. KCP 520 

The requested roll (lateral) coupled mode is not allowed in the current configuration. 

NTA Req input-LARM NOARM mode 1. KCP 520 

ATA input-LARM NOARM mode 2. KMS 540 

ATA Req input-LARM NAVCapArm 

NTA Req input-LARM NAVTrkArm 

ATA Req input-LARM NAVTrkArm 

NTA Req input-LARM AprCapArm 

NTA Req input-LARM AprTrkArm 

ATA Req input-LARM AprTrkArm 

There was an invalid lateral track or approach mode requested based on the current lateral mode (i.e., for error 820, 

. NAV track or approach was requested, but cannot be engaged when in a no arm mode condition). 

Illegal Lateral Arm mode 1. KCP 520 

The requested roll (lateral) arm mode is not allowed in the current configuration. 

r 


Page 139 

Revision AD



Error #(s) 

830 

831 

832 

833 

834 

835 

836 

837 

838 

839 

8 4 0 

841 

8 4 2 

843 

844 

8 4 5 

846 

8 4 7 

848 

84 9 



VNVC Req input-VCPLD VNAVCap 1. KCP 520 

VNVT Req input-VCPLD PAH mode 2. KMS 540 

VNVT Req input-VCPLD AltC mode 

VNVT Req input-VCPLD AltH mode 

VNVT Req input-VCPLD VS mode 

VNVT Req input-VCPLD IAS mode 

VNVT Req input-VCPLD VNAVTrk 

VNVT Req input-VCPLD GSCap mde 

VNVT Req input-VCPLD GSTrk mde 

VNVT Req input-VCPLD GA mode 

GST Req input-VCPLD PAH mode 

GST Req input-VCPLD AltC mode 

GST Req input-VCPLD AltH mode 

GST Req input-VCPLD VS mode 

GST Req input-VCPLD IAS mode 

GST Req input-VCPLD VNAV Cap 

GST Req input-VCPLD VNAV Trk 

GST Req input-VCPLD GS Trk mde 

GST Req input-VCPLD GA mode 

GSC Req input-VCPLD GS Trk mde 

There was an invalid vertical mode requested based on the current vertical mode (i.e., for error 830, VNAV coupled 

was requested, but cannot be engaged when in VNAV capture). 

Illegal Vertical Coupled mode 1. KCP 520 

The requested pitch (vertical) mode is not allowed in the current configuration. 

VNVTA Req input-VARM2 NOARM 1. KCP 520 

VNVTA Req input-VARM2 GSCapArm 2. KMS 540 

VNVTA Req input-VARM2 GSTrkArm 

GSTA Req input-VARM2 NOARM mde 

GSTA Req input-VARM2 VNVCapArm 

GSTA Req input-VARM2 VNVTrkArm 

There was an invalid vertical track or approach mode requested based on the current vertical mode (i.e., for error 

851, VNAV track or approach was requested, but cannot be engaged when in a no arm mode condition). 

Illegal Vertical Arm #2 mode 1. KCP 520 

Illegal Vertical Arm #1 mode 

Illegal Vertical Cpld #2 mode 

The requested pitch (vertical) mode is not allowed in the current configuration. 

EFIS AD1 invalid 1. EFIS AD1 

2. EFIS symbol generator 

The EFIS symbol generator indicated that the EFIS AD1 is invalid or unavailable. 

EFIS HSI invalid 1. EFIS HSI 


The EFIS symbol generator indicated that the EFIS HSI is invalid or unavailable. 

862 EFIS ATT miscompare 1. EFIS symbol generator 

2. One of the attitude sources for the EFIS 

The EFIS symbol generator detected a significant difference between its two attitude sources. 

863 EFIS invalid 1. KCP 520 


The EFIS symbol generator valid output is not being received by the flight computer via the ARINC 429 input. 

864 MSP invalid 1. KCP 520 

2. KMS 540 

Page 140 

Revision AD 

Mode Select Panel information is not being received by the flight computer via the ARINC 429 input. 

EFFECTIVITY: MD9OQ 

I

Error #(s) 

8 65 

BENDXIKING" IFRAVIONICSI KFC goo 




MSP LABEL350 PRGMMEM 1. KMS 540 

The mode select panel detected a ROM memory checksum failure during testing of its EPROM memory. 

MSP LABEL350 RAMMEM 1. KMS 540 

The mode select panel has detected a RAM memory failure during testing of its RAM memory. 

MSP LABEL350 CPUTMNG 1. KMS 540 

The mode select panel detected a CPU timing failure during testing of its CPU. 

MSP LABEL350 CPUINSTR 1. KMS 540 

The mode select panel detected a CPU instruction execution problem when performing its internal instruction test. 

MSP LABEL350 BUSSSM 1. KCP 520 

2. KMS 540 

The mode select panel received ARINC 429 data from the flight computer that had invalid sigdstatus matrix (SSM). 

MSP LABEL350 BUSSDI 1. KCP 520 

2. KMS 540 

The mode select panel received ARINC 429 data from the flight computer that had an invalid source/destination 

identifier (SDI). The received SDI did not match the expected SDI. 

MSP LABEL350 BUSACT 1. KCP 520 

2. KMS 540 

The mode select panel did not receive ARMC 429 data from the flight computer. 

MSP LABEL350 POS5V 


1. KMS 540 

MSP LABEL350 NEG12V 


The indicated power supply (+5 VDC, +12 VDC, -12 VDC, or +28 VDC) in the mode select panel is out of 

tolerance. 

MSP LABEL350 STUCKSW 1. KMS 540 

The mode select panel detected that one of its front panel switches is stuck. 

MSP LABEL350 PWRUP 1. KMS 540 

Power up testing in the mode select panel failed. 

878 MSP LABEL350 CKPTSW 1. KMS 540 

2. aircraft switch panel 

The mode select panel detected that one of the cockpit mounted switches is stuck. 

879 HDG Mode Disallowed 1. AHRS System Components 

2. KCP 520 

The sensors associated with the flight computer Heading Select mode are not valid (i.e., directional gyro inputs). 

880 NAV Mode Disallowed 

881 APR Mode Disallowed 

1. AHRS System Components 


3. KCP 520 

The sensors associated with the flight computer NAV or Approach mode are not valid (i.e., directional gyro inputs or 

NAV information from EFIS). 

882 ALT-SEL Mode Disallowed 1. IUD 480 system components 

2. KCP 520 

The sensors associated with the flight computer Altitude Arm mode are not valid (i.e., altitude input). This could also 

indicate that altitude capture was requested when in glideslope coupled mode 


Page 141 

.Revision AD



Error #(s) 

883 

8 8 4 

885 



VNAV Mode Disallowed 1. KCP 520 

The sensors associated with the flight computer Vertical NAV mode are not valid. This error should not occur, since 

VNAV is not available as a mode. 

ALT Mode Disallowed 1. KAD 480 system components 

2. KCP 520 

The sensors associated with the flight computer Altitude Hold mode are not valid (i.e., altitude input 

IAS Mode Disallowed 1. KAD 480 system components 

2. KCP 520 

The sensors associated with the flight computer Indicated Airspeed Hold mode are not valid (i.e., pressure altitude 

input or airspeed input). 

VS Mode Disallowed 1. KAD 480 system components 

2. KCP 520 

The sensors associated with the flight computer Vertical Speed Hold mode are not valid (i.e., altitude input or 

vertical speed input). 

GA Mode Disallowed 1. KAD480 

2. AHRS system components 

3. KCP 520 

The sensors associated with the flight computer Go Around mode are not valid (i.e., altitude input or pitch attitude 

input). 

Attitude Invalid 1. AHRS system components 

2. KCP 520 

The sensors for inputting attitude information for the flight computer are not valid (i.e., vertical gyro inputs). 

FD Disabled, Strap 1. KCP 520 

The flight director disable discrete input indicates that the flight director should be disabled. 

PITCH Mode Sensor Invalid 1. KCP 520 

The flight director pitch mode was aborted due to an invalid sensor. If this error is logged individually, it indicates an 

internal failure in the flight computer. Otherwise, the accompanying error should identify the sensor input that failed. 

ROLL Mode Sensor Invalid 1. KCP 520 

The flight director roll mode was aborted due to an invalid sensor. If this error is logged individually, it indicates an 

internal failure in the flight computer. Otherwise, the accompanying error should identify the sensor input that failed. 

ALT ARM Sensor Invalid 1. KAD480 

2. KCP 520 

The sensors associated with the flight computer Altitude Arm or Altitude Capture mode are not valid (i.e., altitude 

input). 

ROLL ARM Sensor Invalid 1. AHRS system components 

2. KCP 520 

The sensors associated with the flight computer Roll Arm mode are not valid (i.e., directional gyro inputs, roll 

attitude input). 

VNAV/GS ARM Sensor Invalid 1. EFIS symbol generator 

2. KCP 520 

The sensor associated with the flight computer Vertical NAV mode or Glideslope Arm mode are not valid (i.e., 

glideslopeNNAV deviation input from EFIS). 

Page 142 

Revision AD 


BENDIX/KING" IFR AVIONICS I KFC 900 


- 

1. KAD 480 

The sensor associated with maximum operating velocity limiting are not valid (i.e., indicated airspeed input or mach 

input). 

896 FF last 1. KCP 520 

This is a dummy error code marking the end of the FF error code section. This error should not occur. 

900 CI parity 1. KCP 520 

A data byte was received on the interprocessor bus that had an invalid parity. If the error occurred once, probably 

noise on the bus caused a packet to get corrupted.5 

901 CI recv queue overflow 1. KCP 520 

The buffer used to store received data from the interprocessor bus has been filled before it could be serviced. The 


received.' 

902 CI send queue overflow 1. KCP 520 

The buffer used to store data to be transmitted on the interprocessor bus has been filled before it could be serviced. 

Possibly another processor is "babbling" (transmitting data on the bus almost constantly, not allowing another 

processor to gain control of the bus). 

903 CI unused source 1. KCP 520 

A source identifier was received on the interprocessor bus that was invalid. If the error occurred once, probably noise 

on the bus caused a packet to get corrupted.5 

910 No ASIC XMIT 1. KCP 520 

The common inputloutput routines received a request to transmit ARTNC 429 information of the maintenance 

processor, which does not have an ARMC 429 ASIC available for use. 

911 Unwanted label 1. KCP 520 

An unexpected label was received on one of the ARTNC 429 input channels, this label should have been masked by 

the ARINC 429 ASIC. 

920 CI update timing 1. KCP 520 

A label (interprocessor or ARMC 429) was not received within its update period. This is a generic error that should 

not occur. 

921 Update timing 429-ADC 1. KCP 520 

2. KAD 480 system components 

The ARINC 429 channel receiving information kern the air data computer did not receive data within its update 

period. 

922 Update timing 429-AHRS 1. KCP 520 


The ARINC 429 channel receiving information from the attitudelheading reference system did not receive data 

within its update period. 

923 Update timing CIP-ALLPR 1. KCP 520 

924 Update timing CIP-APALL 

925 Update timing CIP-APOUT 

926 Update timing CIP-FDALL 

927 Update timing CI P-FDOUT 

928 Update timing CIP-MAIOUT 

These errors should not occur. 

Page 143 

Revision AD



Error #(s) 

92 9 



Update timing CIP-APIN I. KCP 520 

Update timing CIP-FDIN 

Update timing CIP-MAIIN 

The specified channel did not receive data on the interprocessor bus within its update period. 

Update timing NCIP-APALL I. KCP 520 

Update timing NCIP-APOUT 


Update timing NCIP-APIN 1. KCP 520 


Update timing A429-XMIT 1. KCP 520 

This error should not occur. 

Update timing A429-ADC 1. KCP 520 

2. KAD 480 system components 

The ARMC 429 channel receiving information from the air data computer did not receive data within its update 

period. 

Update timing A429-AHRS 1. KCP 520 


The ARMC 429 channel receiving information.from the attitudeheading reference system did not receive data 

within its update period. 

Update timing A429-EFIS 1. KCP 520 


The ARINC 429 channel receiving information from EFIS did not receive data within its update period. 

Update timing A429-EMS 1. KCP 520 

2. Flight Management System computer 

The ARMC 429 channel receiving information l?om the flight management system did not receive data within its 

update period. 

Update timing A429MSP 1. KCP 520 

2. KMS 540 

The ARTNC 429 channel receiving information f?om the mode select panel did not receive data within its update 

y:i:~e timing CIP-ALLPR 

Update timing CIP-APALL 

1. KCP 520 

Update timing CIP-APOUT 

Update timing CIP-FDALL 

Update timing CIP-FDOUT 

Update timing CIP-MAIALL 


947 

948 Update timing CIP-APIN 

Update timing CIP-EDIN 

1. KCP 520 

949 Update timing CIP-MAIIN 


950 

951 

Update timing NCIP-FDALL 

Update timing NCIP-FDOUT 

1. KCP 520 

952 Update timlng NCIP-MAIOUT 


Page 144 

Revision AD 

. , 


I

Error #(s) 

953 





Update timing NCIP-FDIN 1. KCP 520 

Update timing NCIP-MAIIN 


Update timing A429-XMIT 

Update timing CIP-ALLPR 

Update timing CIP-APALL 

Update timing CIP-APOUT 

Update timing CIP-FDALL 

Update timing CIP-FDOUT 


Update timing CIP-APIN 

Update timing CIP-FDIN 

1. KCP 520 

1. KCP 520 


Update timing NCIP-FDALL 1. KCP 520 

Update timing NCIP-FDOUT 


Update timing NCIP-FDIN 1. KCP 520 


ECAL Node error 1. KCP 520 

An error occurred while processing one of the ECAL nodes (i.e., a required input to an ECAL node was undefined). 

ECAL Type error 1. KCP 520 

An ECAL stack or FIFO call was made with an improper data type (boolean or floating point). 

ECAL FIFO error 1. KCP 520 

An error occurred in the processor when trying to access the FIFO buffer used by ECAL (FIFO corrupted). 

ECAL Stack error 1. KCP 520 

An error occurred in the processor when trying to access the ECAL stack (stack corrupted). 

ECAL Initial Condition error 1. KCP 520 

A filter or other function allowing initialization options received an illegal initialization code. 

1005 ECAL Index error 1. KCP 520 

An attempt was made to reference a node outside the ECAL data block (i.e., node pointer not initialized properly). 

1006 ECAL Block error 1. KCP 520 

The ECAL data block being processed does not match the selected mode (i.e., processing Heading Hold block when 

in Roll Attitude Hold mode). 

1007 ECAL Bad sign input to summer 1. KCP 520 

The FE-summer function was called with an illegal input parameter. 

1008 ECAL Not enough node inputs 1. KCP 520 

An ECAL function was called with too few input parameters (i.e., one when function requires at least two). 

1009 ECAL Filtering out of range 1. KCP 520 

An ECAL filter routine generated an arithmetic overflow condition. 

1010 ECAL Default error 1. KCP 520 

A generic error occurred while processing the ECAL node or block data. 


I 

Page 145 

Revision AD



Error #(s) Text Message(s) Possible failed unit(s) 

1011 ECAL Bad Node Record error 1. KCP 520 

One of the node records in an ECAL node block is not valid (i.e., improper number of parameters for block type 

specified). 

1012 ECAL Bad Block Pointer error 1. KCP 520 

The pointer to a block in the ECAL data block is not valid (i.e., ECAL data pointer is corrupt). 

1013 ECAL Mode Index out of range 1. KCP 520 

The ECAL mode index is indicating a mode number that does not exist. 

1200 Analog input MUX address error 1. KCP 520 

The MUX address associated with an analog input was incorrect. This probably indicates that the MUX sequencer 

for the analog inputs failed. All modes will dump when this error occurs and the failure can only be cleared by 

executing preflight test again. 

MUX test inputs out of range I. KCP 520 

The analog inputs used for testing each analog to digital converter were out of tolerance. There is one input on each 

analog to digital converter that is used to check for proper operation of the converter (normally one of the power 

inputs, like + 5 V DC). One of these inputs when read in was out of tolerance (i.e., + 5 V DC was read in at a + 10 V 

level). All modes will dump when this error occurs and the failure can only be cleared by executing preflight test 

again. 

Analog loopback failed 1. KCP 520 

The analog input for loopback did not match the analog loopback output. A test signal is output to a digital to analog 

converter and then input into the analog to digital converter for a wraparound comparison. This test signal is changed 

every 25 milliseconds so that the entire analog input voltage range can be tested. The input signal read in and the 

signal output did not match. All modes will dump when this error occurs and the failure can only be cleared by 

executing preflight test again. 

PTCH srv voltage range err 1. KCP 520 

PTCH srv current range err 

PTCH SNS rate range err 

PTCH SNS position range err 

PTCH CMD range err 

ROL srv voltage range err 

ROL srv current range err 

ROL SNS rate range err 

ROL SNS position range err 

ROL CMD range err 

YAW srv voltage range err 

YAW srv current range err 

YAW SNS rate range err 

YAW SNS position range err 

AD test range err 

PTCH LVDT range err 

The indicated analog input (kom one analog to digital converter) was outside of the normal analog input range. The 

analog input (when converted to the corresponding input voltage) was either less than -9.5 V or greater than + 9.5 V. 

Page 146 

Revision AD 

,, I ' I 

, , 

, . EFFECTIVITY: MD900 

1



Error #(s) 

1220 

1221 

1222 

1223 

1224 

1225 

1226 

1227 

1228 

1229 

1230 

1231 

1232 

1233 

1234 

1235 



YAW CMD range err 1. KCP 520 

PTCH TRM srv voltage range err 

PTCH TRM srv current range err 

PTCH TRM CMD range err 

ROL TRM srv voltage range err 

ROL TRM srv current range err 

ROL TRM CMD range err 

YAW TRM srv voltage range err 

YAW TRM srv current range err 

YAW TRM CMD range err 

COLL srv voltage range err 

COLL srv current range err 

COLL CMD range err 

ROL LVDT range err 

YAW LVDT range err 

Servo BD -15VDC range err 

The indicated analog input (from one analog to digital converter) was outside of the normal analog input range. The 


Servo BD 15VDC range err 1. KCP 520 

AP power range err 

PTCH MIDPOINT range err 

ROL MIDPOINT range err 

YAW MIDPOINT range err 

PTCH TRM MIDPOINT range err 

ROL TRM MIDPOINT range err 

YAW TRM MIDPOINT range err 

COLL MIDPOINT range err 

Servo BD 5VDC range err 

Unused input #43 range err 






The indicated analog input (&om one analog to digital converter) was outside of the normal analog input range. The 


PTCH POS COS range err I. KCP 520 

PTCH POS SIN range err 

ROL POS COS range err 

ROL POS SIN range err 

YAW POS COS range err 

YAW POS SIN range err 

COLL POS COS range err 

COLL POS SIN range err 

VG1 PTCH TAN range err 

SEC PTCH rate range err 

VG1 ROL TAN range err 

SEC ROL rate range err 

DG HDG SIN range err 

DG HDG COS range err 

RADAR ALT 2 range err 

ANALOG BD 5VDC range err 




I 

Page 147 

Revision AD



Error #(s) 

1268 

1269 

1270 

1271 

1272 

1273 

1274 

1275 

127 6 

1277 

1278 

1279 

1280 

1281 

1282 

1283 



VG2 PTCH SIN range err I. KCP 520 

VG2 PTCH COS range err 

VG2 ROL COS range err 

VG2 ROL SIN range err 

LAT ACCEL range err 

LONG ACCEL range err 

NORM ACCEL range err 

RG YAW rate range err 

RADAR ALT 1 range err 

ROTOR TORQUE range err 

PRI PTCH rate range err 

PRI ROL rate range err 

VG1 REF range err 

VG2 REF range err 

INTERNAL TEMP range err 

ANALOG BD 15VDC range err 



Unused input #81 range err 1. KCP 520 , . 








Unused input #89 .range err 










Floating point Not a Number 1. KCP 520 

A floating point math routine was called with a value that does not represent a valid number. 

Floating point overflow 1. KCP 520 

A floating point math routine computation resulted in a number whish exceeds the represented number range. This is 

normally caused by dividing a large number by a very small number. 

LVDT installation error I. KCP 520 

This error has been reserved for use by installation when detecting failures during installation of the primary servos 

(LVDTs). At present, it is not used and should not occur. 

FA cyclic installation error 

LAT cyclic installation error 

1. KCP 520 

pedal installation error 

collective installation error 

These errors have been reserved for use by installation when detecting failures during installation of the trim servos. 

At present, they are not used and should not occur. 

config installation data error 1. KCP 520 

This error has been reserved for use by installation when detecting a failure while attempting to write installation 

data to the configuration module. At present, it is no* used and should not occur. 

Page 148 

Revision AD . . .



Error #(s) 

14 0 6 



AP install checksum error 1. KCP 520 

FD install checksum error 2. installation configuration module 

A checksum error occurred when the maintenance processor attempted to retrieve installation data from the 

configuration module for the indicated processor information. 

MA1 processor not ready 1. KCP 520 

This error has been reserved for use by installation when the maintenance processor was not ready to transmit 

installation data when requested by the reporting processor. At present, it is not used and should not occur. 

no processor request error 1. KCP 520 

This error has been reserved for use by installation when the maintenance processor does not receive any requests for 

installation data during powerup initialization. At present, it is not used and should not occur. 

no install data rx from MA1 1. KCP 520 

Installation configuration data was not received fiom the maintenance processor after being requested. The reporting 

processor requested installation data fiom the maintenance processor, but did not receive any installation data from 

the maintenance processor. 

receiving data checksum error 1. KCP 520 

A checksum error occurred when installation data was received &om the maintenance processor. The calculated 

checksum for the data did not match the checksum byte transmitted for the data. 

AP cross side compare error 1. KCP 520 

The calculated checksum for installation data in both autopilot processors does not match. Each autopilot processor 

computes a checksum for its installation data and these two checksum values were not the same. 

NVM checksum error 1. KCP 520 

An invalid checksum for the installation data being used was detected. The reporting processor did not receive 

installation data from the maintenance processor and the checksum computed for its local installation data did not 

match the stored checksum for that data. 

PFT - 2 AP-As or 2 AP-Bs found 1. KCP 520 

Both autopilot processors believe they have the same processor ID. During preflight test, the autopilot processors 

read their performance strap configuration to determine their AP identification (either AP A or AP B). When they 

compared identifications, they both thought they were the same AP. 

PFT sync err waiting for AP A 1. KCP 520 

PFT sync err waiting for AP B 

The other autopilot processor did not respond to the reporting processor when requesting synchronization of 

processors for preflight test. At the beginning of preflight test, each processor sends out a preflight test 

synchronization request on the interprocessor bus and waits for a reply fiom the other processor to begin preflight 

test. The other processor did not respond within a period of time (PFT-SYNC-TIME), 

AP A output control invalid 1. KCP 520 

AP B output control invalid 2. one of the servos (KLA 570 or KSA 572) 

The indicated processor was unable to turn off power or set the brake for at least one servo when it set its processor 

valid discrete to invalid. The indicated processor was unable to disable power to primary servos (KLA 570) or set the 

brake on trim servos (KSA 572) when it set its valid discrete to invalid. Each processor tests for this capability 

i 

individually. 

PFT perf strap miscompare 1. KCP 520 

2. Harness strap module configuration 

The performance strap inputs do not match stored strap configuration. During preflight test, the performance strap 

configuration is read in and compared with a performance strap configuration value stored in RDM memory. The 

stored value is based upon the system the unit was designed to be placed in (i.e., there is a different performance 

strap value for each certification). The value read in during preflight test did not match the value stored in memory. 


Page 149 

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Error #(s) Text Message@) Possible failed unit(s) 

1520 accelerometer invld during PFT 1. KAB 330 

2. KCP 520 

The accelerometer valid input was incorrect during preflight test. During preflight test, the accelerometer test output 

is set to test to indicate testing of the accelerometer validity. After setting this output to test, the processor waits for a 

period of time (PFT-ACCELTIME) before reading the acceleration validity. At that time, the accelerometer valid 

input could have indicated that the accelerometer was valid. After this check, the accelerometer test output is set to 

nornlal. After setting this output to normal (not in test), the processor waits for a period of time 

(PFT-ACC-NORM-TIME) before reading the acceleration validity. At that time, the accelerometer valid input 

could have indicated that the accelerometer was invalid. 

1520 PFT accel valid norm mode fail 1. KRG 333 

2. KCP 520 

The accelerometer valid input did not return to a normal value during preflight test. During preflight test, the 

accelerometer test output is set to normal after checking for test values. After setting this output to normal (not in 

test), the processor waits for a period of time (PFT-ACC-NORM-TIME) before reading the acceleration validity. 

The accelerometer valid input indicated that the accelerometer was invalid at that time. 

1520 PFT accel valid fail 1. KRG 333 

2. KCP 520 

The accelerorneter valid input did not return to a normal value during preflight test. During preflight test, the 

accelerometer test output is set to normal after checking for test values. After setting this output to normal (not in 

test), the processor waits for a period of time (PFT-ACC-NORM-TIME) before reading the acceleration validity. 

The accelerorneter valid input indicated that the accelerometer was invalid at that time. 

1521 accelerometer lat tst val bad 1. KRG 333KAB 330 

1522 accelerometer long tst val bad 2. ~ ~ ~ 5 2 0 

1523 accelerometer norm tst val bad 

The indicated acceleration value was not at the expected test value during preflight test. During preflight test, the 

accelerometer test output is set to test to indicate testing of the accelerometer values. After setting this output to test, 

the processor waits for a period of time (PFT-ACCEL-TIME) before reading the acceleration values. The indicated 

acceleration value read in at that time was either not above or not below its expected threshold level (lateral 

acceleration should be below PFT-LAT-TST-LIM, longitudinal acceleration should be above 

PFT-LONG-TST-LIM, and normal acceleration should be above PFT-NORM-TST-LIM). 

1521 PFT accel lat tst val bad 1. KRG 333 

1522 PFT accel long tst val bad 2. KCP 520 

1523 PFT accel norm tst val bad 

The indicated acceleration value was not at the expected test value during preflight test. During preflight test, the 

accelerometer test output is set to test to indicate testing of the accelerometer values. After setting this output to test, 

the processor waits for a period of time (PFT-ACCEL-TIME) before reading the acceleration values. The indicated 

acceleration value read in at that time was either not above or not below its expected threshold level (lateral 

acceleration should be below PFT-LAT-TST-LIM, longitudinal acceleration should be above 

PFT-LONG-TST-LIM, and normal acceleration should be above PFT-NORM-TST-LIM). 

1524 accelerometer lat value error 1. KRG 333KAB 330 

1525 accelerometer long value error 2. KCP520 

1526 accelerometer norm value error 

The indicated acceleration value did not return to a value within its normal range of operation during preflight test. 

During preflight test, the accelerometer test output is set to normal after checking for test values. After setting this 

output to normal (not in test), the processor waits for a period of time (PFT-ACC-NORM-TIME) before reading 

the acceleration values. The indicated acceleration value was either below the minimum threshold (PFT-LAT-MIN 

for lateral acceleration, PFT-LONG-MIN for longitudinal acceleration, and PFT-NORNMIN for normal 

acceleration) or above the maximum threshold (PFT-LAT-MAX for lateral acceleration, PFT-LONG-MAX for 

longitudinal acceleration, and PFT-NORM-MAX for normal acceleration) for normal operation. 

Page 150 

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Error #(s) Text Message(s) Possible failed unit@) 

1524 PFT accel lat value error I. KRG 333 

1525 PFT accel long value error 2. KCP 520 

1526 PFT accel norm value error 

The indicated acceleration value did not return to a value within its normal range of operation during preflight test. 

During preflight test, the accelerometer test output is set to normal after checking for test values. After setting this 

output to normal (not in test), the processor waits for a period of time (PFT-ACC-NORM-TIME) before reading 

the acceleration values. The indicated acceleration value was either below the minimum threshold (PFTLAT-MM 

for lateral acceleration, PFT-LONG-MM for longitudinal acceleration, and PFT-NORM-MM for normal 

acceleration) or above the maximum threshold (PFT-LAT-MAX for lateral acceleration, PFT-LONG-MAX for 

longitudinal acceleration, and PFT-NORM-MAX for normal acceleration) for normal operation. 

1527 PFT accel valid test mode fail 1. KRG 333 

2. KCP 520 

The accelerometer valid input was not at the expected test value during preflight test. During preflight test, the 

accelerometer test output is set to test to indicate testing of the accelerometer validity. After setting this output to test, 

the processor waits for a period of time (PFT-ACCEL-TIME) before reading the acceleration validity. The 

accelerometer valid input indicated that the accelerometer was valid at that time. 

1527 PFT accel valid tst fail 1. KRG333 

2. KCP 520 

The accelerometer valid input was not at the expected test value during preflight test. During preflight test, the 

accelerometer test output is set to test to indicate testing of the accelerometer validity. After setting this output to test, 

the processor waits for a period of time (PFT-ACCELTIME) before reading the acceleration validity. The 

accelerometer valid input indicated that the accelerometer was valid at that time. 

1530 PFT pitch cmd DAC or ADC error 1. KCP 520 

1531 PFT roll cmd DAC or ADC error 

1532 PFT yaw cmd DAC or ADC error 

1533 PFT pit trm cmd DAC or ADC err 

1534 PFT rol trm cmd DAC or ADC err 

1535 PFT yaw trm cmd DAC or ADC err 

1536 PFT collect cmd DAC or ADC err 

The value read in on the analog to digital converter for a servo command did not match the value output to the digital 

to analog converter for that servo during preflight test. During preflight test, all servos are fust verified to be 

unpowered. Then, each servo is individually commanded to a minimum test value (PFT-SRV-DAC-MM) and a 

maximum test value (PFT-SRV-DAC-MAX). All other servos are commanded with a 0 command. At each test 

instance, each servo command is input fiom the analog to digital converter (from the hardware wraparound) and 

compared with the value output. The absolute difference between the input and output servo command values for the 

indicated servo was greater than a minimum threshold (PFT-ADC-DAC-LIM) during this test. 

1540 PFT pitch midpoint error 1. KCP 520 

1541 PFT roll midpoint error 2. Indicated servo 

1542 PET yaw midpoint error 

1543 PFT pitch trim midpoint error 

1544 PFT roll trim midpoint error 

1545 PFT yaw trim midpoint error 

1546 PFT collect midpoint error 

The indicated servo amplifier midpoint voltage input failed during preflight test. The absolute difference between the 

expected value for the midpoint voltage and the analog midpoint voltage input exceeded a threshold 

(PFT-MIDPNT-VLT-TOL) for the indicated axis. The expected midpoint voltage varies based on whether the 

indicated servo is powered andlor selected (PFT-MID-VLT-NOPWR when servo is not powered, 

PFT-MID-VLT-SEL when servo is powered and selected, and PFT-MID-VLT-NOSE when servo is powered 

and not selected. All three midpoint voltage conditions are tested for each installed servo at some point during 

preflight test). 


I 

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Error #(s) 

1550 

1551 

1552 



PFT pitch LVDT sense error 1. KCP 520 

PFT roll LVDT sense error 2. Indicated servo 

PFT yaw LVDT sense error 3. LVDT position sensor for indicated servo 

The indicated servo LVDT sense (power) failed during preflight test. Either the LVDT sense voltage was above a 

minimum threshold (PFT-LVDT-VALID-MIN) when the indicated servo was not powered or the LVDT sense 

voltage was below the minimum threshold (PFT-LVDT-VALID-MM) when the indicated servo was powered. 

PFT pitch servo position err 1. KCP 520 

PFT roll servo position err 2. Indicated servo 

PFT yaw servo position err 3. LVDT position sensor for indicated servo 

The indicated servo LVDT position failed during preflight test. The LVDT position input is monitored to be between 

the stored LVDT stop positions, determined during installation, for the indicated axis. This LVDT position was 

outside of the LVDT stop position range by more that a percentage (PFT-LVDT-POS-TOL) of the total LVDT 

position range for that axis. 

PFT pit trm srv position err 1. KCP 520 

PFT rol trm srv position err 

PFT yaw trrn srv position err 

2. Indicated control position resolver 

PFT collect srv position err 

The indicated servo control position failed during preflight test. The control position input is monitored to be 

between the stored control position stop position, determined during installation, for the indicated axis. This control 

position was outside of the control position stop position range be more than a percentage (PFT-TRIM-POS-TOL) 

of the total control position range for that axis. 

PFT pitch LVDT rate too high 1. KCP 520 

PFT roll LVDT rate too high 2. Indicated servo 

PFT yaw LVDT rate too high 3. LVDT position sensor for indicated servo 

The indicated servo LVDT position rate failed during preflight test. The LVDT position rate input is tested when the 

indicated servo is powered with the brake engaged (position rate should be zero at this time, since the servo is not 

moving). The LVDT position rate was above a minimum threshold (PFT-LVDT-RATE-MAX) for that axis. 

PFT pit offset crnt too high 1. Indicated servo 

PET rol offset crnt too high 

PFT yaw offset crnt too high 

2. KCP 520 

PFT pit trrn offset crnt high 

PFT rol trrn offset crnt high 

PET yaw trrn offset crnt high 

PFT collect offset crnt high 

The motor current for the indicated servo failed during preflight test. Each servo is commanded to its present 

position as read in from the analog inputs (a zero command is output for the trim servos). At that time, the motor 

current for the indicated servo is tested (motor offset current should be zero at this time, since there is no servo 

drive). The motor current was above a minimum threshold (PFT-PRI-OFF-CUR for KLA 570 servos, 

PFT-TRM-OFF-CUR for KSA 572 or BFG type servos) for the indicated servo. 

PFT pit offset volt too high 1. Indicated servo 

PFT rol offset volt too high 2. KCP 520 

PET yaw offset volt too high 

PFT pit trrn offset volt high 

PFT rol trrn offset volt high 

PFT yaw trrn offset volt hlgh 

PFT collect offset volt high 

The motor voltage for the indicated servo failed during preflight test. Each servo is commanded to its present 

position as read in from the analog inputs (a zero command is output for the trim servos). At that time, the motor 

voltage for the indicated servo is tested (motor offset voltage should be zero at this time, since there is no servo 

drive). The motor voltage was above a minimum threshold (PFT-OFF-VOLT) for the indicated servo. 

Page 152 

Revision AD 

1 EFFECTIVITY: MD900

BENDIXlKlN6" IFRAVIONICS I KFC goo 


Error #(s) 

1600 

1601 

1602 

1603 

1604 

1605 

1606 



PFT pitch drive err 1. Indicated servo 

PFT roll drive err 2. KCP 520 

PFT yaw drive err 

PFT pitch trrn drive err 

PFT roll trrn drive err 

PFT yaw trrn drive err 

PFT collect drive err 

Motor stall current for the indicated servo failed during preflight test when testing the servo brake. The indicated 

servo was commanded to a position other than its present position as read in from the analog inputs with the servo 

brake engaged. KLA 570 servos are commanded a percentage of full-scale servo travel from their present position 

(PFT-PRIDRV-TOL) and KSA 572 and BFG type servos are commanded a percentage of their full command 

value (PFT-TRM-DRV-TOL) with the servo brake engaged. The motor current for the indicated servo was not 

above a minimum threshold (PFT-PRI-DRV-CUR for KLA 570 servos, PFT-TRM-DRV-CUR for KSA 572 and 

BFG type servos) within a certain period of time (PFT-DRIVE-TIME) after the servo command was applied. 

PFT pitch monitor error 1. Indicated servo 

PFT roll monitor error 2. KCP520 

PFT yaw monitor error 

PFT pitch trrn monitor error 

PFT roll trrn monitor error 

PFT yaw trrn monitor error 

PET collect monitor error 

A servo monitor failure was detected during preflight test. Some of the monitors for the servos are executed 

throughout the preflight test period. One of these monitors detected a failure for the indicated servo. There should be 

an Autopilot Monitor failure (error code 1200 - 1299 or 3000 - 3999) logged in conjunction with this error. 

PFT pitch brake err 

PFT roll brake err 

PFT yaw brake err 

PFT pitch trrn brake err 

PFT roll trrn brake err 

PFT yaw trm brake err 

PFT collect brake err 

1. Indicated servo 

2. KCP 520 

Servo movement was detected for the indicated servo (if KLA 570) when the brake was engaged during preflight test 

or the servo brake was not engaged. The indicated KLA 570 servo moved from its original position (by more than 

the amount indicated by PFT-DRV-POS-TOL) while the brake for that servo was engaged or the brake engaged 

input indicated that the servo brake was not engaged when either the brake release hi or brake release lo output for 

the servo was false. 

PFT rate valid norm mode fail 1. KRG333 

2. KCP 520 

The body rate valid input did not return to a normal value during preflight test. During preflight test, the body rate 

test output is set to normal after checking for test values. After setting this output to normal (not in test), the 

processor waits for a period of time (PFT-RATKNORM-TIME) before reading the body rate validity. The body 

rate valid input indicated that the rate sensor was invalid at that time. 

PFT rate valid fail 1. KRG 333 # 1 

2. KCP 520 

The body rate valid input from KRG 333 # 1 did not return to a normal value during preflight test. During preflight 

test, the body rate test output is set to normal after checking for test values. After setting this output to normal (not in 

test), the processor waits for a period of time (PFT-RATE-NORM-TIME) before reading the body rate validity. 

The body rate valid input indicated that the rate sensor was invalid at that time. 


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Error #(s) 

1631 





PFT pitch rate test value bad I. KRG333 

PFT roll rate test value bad 2. KCP 520 

PFT yaw rate test value bad 

The indicated body rate value was not at the expected test value during preflight test. During preflight test, the body 

rate test output is set to test to indicate testing of the body rate values. After setting this output to test, the processor 

waits for a period of time (PFT-RATE-TIME) before reading the body rate values. The indicated body rate value 

read in at that time was either not above or not below its expected threshold level (pitch body rate should be above 

PFT-PIT-TST-LIM, roll body rate should be above PFT-ROL-TST-LIM, and yaw body rate should be below 

PFT-YAW-TST-LIM). 

PFT pitch rate tst val bad 1. KRG333#1 

PFT roll rate tst val bad 2. KCP 520 

PET yaw rate tst val bad 

The indicated body rate value input from KRG 333 # 1 was not at the expected test value during preflight test. 

During preflight test, the body rate test output is set to test to indicate testing of the body rate values. After setting 

this output to test, the processor waits for a period of time (PFT-RATE-TIME) before reading the body rate values. 

The indicated body rate value read in at that time was either not above or not below its expected threshold level 

(pitch body rate should be above PFT-PIT-TST-LIM, roll body rate should be above PFT-ROL-TST-LIM, and 

yaw body rate should be below PFT-YAW-TST-LIM). 

PFT pitch rate out of range 1. KRG 333 

PET roll rate out of range 2. KCP 520 

PFT yaw rate out of range 

The indicated body rate value did not return to a value within its normal range of operation during preflight test. 

During preflight test, the body rate test output is set to normal after checking for test values. After setting this output 

to normal (not in test), the processor waits for a period of tinle (PFT-RATRNORM-TIME) before reading the body 

rate values. The indicated body rate value was either below the minimum threshold (PFT-PIT-MIN for pitch body 

rate, PFT-ROL-MIN for roll body rate, and PFT-YAW-MM for yaw body rate) or above the maximum threshold 

(PFT-PIT-MAX for pitch body rate, PFTROL-MAX for roll body rate, and PFT-YAW-MAX for yaw body rate) 

for normal operation. 

PFT pitch rate value error 1. KRG333#1 

PFT roll rate value error 2. KCP 520 

PFT yaw rate value error 

The indicated body rate value input from KRG 333 # 1 did not return to a value within its normal range of operation 

during preflight test. During preflight test, the body rate test output is set to normal after checking for test values. 

After setting this output to normal (not in test), the processor waits for a period of time (PFT-RATE-NORM-TIME) 

before reading the body rate values. The indicated body rate value was either below the minimum threshold 

(PFT-PIT-MIN for pitch body rate, PFT-ROL-MIN for roll body rate, and PFT-YAW-MM for yaw body rate) or 

above the maximum threshold (PFT-PIT-MAX for pitch body rate, PFT-ROL-MAX for roll body rate, and 

PFT-YAW-MAX for yaw body rate) for normal operation. 

PFT rate valid test mode fail 1. KRG333 

2. KCP 520 

The body rate valid input was not at the expected test value during preflight test. During preflight test, the body rate 

test output is set to test to indicate testing of the body rate validity. After setting this output to test, the processor 

waits for a period of time (PFT-RA-TIME) before reading the body rate validity. The body rate valid input 

indicated that the rate sensor was valid at that time. 

1637 PFT rate valid tst fail I. KRG333#1 

2. KCP 520 

The body rate valid input from KRG 333 # 1 was not at the expected test value during preflight test. During preflight 

test, the body rate test output is set to test to indicate testing of the body rate validity. After setting this output to test, 

the processor waits for a period of time (PFT-RATE-TIME) before reading the body rate validity. The body rate 

valid input indicated that the rate sensor was valid at that time. 

Page 154 


EFFECTIVITY: MDSQO

Error #(s) 

1640 

1641 

1642 

1643 

164 4 

1645 

1646 





PFT pitch clutch/relay err 1. Indicated servo 

PFT roll clutch/relay err 2. KCP 520 

PFT yaw clutch/relay err 

PFT pitch trrn clutch/relay err 

PFT roll trm clutch/relay err 

PFT yaw trm clutch/relay err 

PFT collect clutch/relay err 

Servo clutch or relay engagement status did not match expected clutch or relay engagement status during preflight 

test. The clutch/relay engaged input indicated that the servo clutch/relay was not engaged when the clutchlrelay 

engage hi and clutchlrelay engage lo output for the servo was true or that the servo clutchlrelay was engaged when 

the clutchlrelay engage hi or clutch/relay engage lo output for the servo was false. 

PET rate valid #2 fail 1. KRG 333 # 2 

2. KCP 520 

The body rate valid input from KRG 333 # 2 did not retum to a normal value during preflight test. During preflight 

test, the body rate test output is set to normal after checking for test values. After setting this output to normal (not in 

test), the processor waits for a period of time (PFT-RATE-NORM-TIME) before reading the body rate validity. 

The body rate valid input indicated that the rate sensor was invalid at that time. 

PFT pitch rate #2 tst val bad 1. KRG333#2 

PFT roll rate #2 tst val bad 2. KCP 520 

The indicated body rate value input from KRG 333 # 2 was not at the expected test value during preflight test. 

During preflight test, the body rate test output is set to test to indicate testing of the body rate values. After setting 

this output to test, the processor waits for a period of time (PFT-RATRTIME) before reading the body rate values. 

The indicated body rate value read in at that time was either not above or not below its expected threshold level 

(pitch body rate should be above PFT-PIT-TST-LIM, roll body rate should be above PFT-ROL-TST-LIM, and 

yaw body rate should be below PFT-YAW-TST-LIM). 

PFT pitch rate #2 value error 1. KRG333#2 

PFT roll rate #2 value error 2. KCP 520 

The indicated body rate value input from KRG 333 # 2 did not return to a value within its normal range of operation 

during preflight test. During preflight test, the body rate test output is set to normal after checking for test values. 

After setting this output to normal (not in test), the processor waits for a period of time (PFT-RATKNORM-TIME) 

before reading the body rate values. The indicated body rate value was either below the minimum threshold 

(PFT-PIT-MIN for pitch body rate, PFT-ROL-MIN for roll body rate, and PFT-YAW-MIN for yaw body rate) or 

above the maximum threshold (PFT-PIT-MAX for pitch body rate, PFT-ROL-MAX for roll body rate, and 

PFT-YAW-MAX for yaw body rate) for normal operation. 

1655 PFT rate valid #2 tst fail 1. KRG333#2 

2. KCP 520 

The body rate valid input from KRG 333 # 2 was not at the expected test value during preflight test. During preflight 

test, the body rate test output is set to test to indicate testing of the body rate validity. After setting this output to test, 

the processor waits for a period of time (PFT-RATE-TIME) before reading the body rate validity. The body rate 

valid input indicated that the rate sensor was valid at that time. 

1656 PFT AHRS pitch rate invalid 1. AHRS system components 

1657 PFT AHRS roll rate invalid 2. KCP 520 

The indicated rate input from the AttitudeMeading Reference system was invalid during preflight test. During 

preflight test, the rate input from the AttitudeMeading Reference system is tested for validity. At that time, the rate 

input was invalid. 

PFT trim test timeout 1. KCP 520 

2. Pilot did not complete manual portion of preflight test 

3. Pitch beep trim switch 

4. Roll beep trim switch 

To complete preflight test, when requested the pilot must exercise the pitch trim and roll trim servos by engaging the 

pitch and roll beep trim switches in all directions for a period of time (PFT-TRIM-ENG-TIME). For some reason, 

the servos were not exercised in all directions within the time allotted for the trim test (PFT-TRIM-TEST-TIME). 


97-00-00 

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Revision AD



Error #(s) Text Message@) Possible failed unit(s) 

1661 PFT trim test no roll current I. Indicated trim servo 

1662 PET trim test no pitch current 2. KCP 520 

To complete preflight test, when requested the pilot must exercise the pitch trim and roll trim servos by engaging the 

pitch and roll beep trim switches in all directions for a period of time (PFTTRIM-ENG-TIME). Either the servo 

current for the indicated servo was greater than a threshold (PFT-TRIM-TEST-MM) or the difference between 

servo current for the indicated servo when stopped and servo current for the indicated servo when moving was not 

greater than a threshold (PFT-TRIM-TEST-THRES) when the indicated servo was exercised by the pilot. 

Monitor gain translation type 1. KCP 520 

Invalid translation gain index 

An error was detected when translating autopilot gains ffom ROM constants to RAM values. Either the gain index 

was out of range (larger than total number of translation gains) or there was an invalid translation type indicated in 

the table (i.e., a filter translation for a monitor gain). 

Pitch Mistrim 

Roll Mistrim 

Yaw Mistrim 

1. KCP 520 

2. Trim servo for indicated axis 

3. LVDT position sensor for indicated primary servo 

The indicated primary servo was detected to be in a mistrim condition. The position for the indicated primary servo 

was more than a percentage (PIT-MIS-TRIM-TOL for pitch, ROL-MIS-TRIM-TOL for roll, and 

YAW-MIS-TRIM-TOL for yaw) of the full-scale primary servo travel from center in the same direction for a 

certain period of time (MIS-TRIM-TIME). 

Powerup lOhz sync error 

lOhz frame sync error 

I. KCP 520 

The 10 Hz task frame in the autopilot processor lost sync with the 40 Hz task frame. 

Autolevel input in PAH mode I. KCP 520 

Autolevel input in ALTC mode 2. KMS 540 

Autolevel input in ALTH mode 

Autolevel input in VS mode 

Autolevel input in 1AS mode 

Autolevel input in GA mode 

Autolevel input in VNAV-Cap 

Autolevel input in VNAV-Track 

GS-Cpt input in Autolevel 

GS-Trt input in Autolevel 

GS-Trk input in Autolevel 

There was an invalid vertical mode requested based on the current vertical mode (i.e., for error 1900, autolevel mode 

was requested, but cannot be engaged when in Pitch Attitude Hold (PAH) mode). 

AP discrete switch mismatch 1. KCP 520 

SCAS discrete switch mismatch 2. KMS 540 

The indicated mode controller switch information did not match. The data received from the mode controller for the 

indicated switch's position (engaged or released) did not match the data input directly from the discrete input for a 

certain period of time (SWITCH-MISMATCH-TIME). This failure will be cleared when the switch position 

received from-the mode controller matches the switch position indicated by the switch discrete input.. 

2002 AP MSP discrete stuck switch 1. KCP 520 

2003 SCAS MSP discrete stuck switch 2. KMS 540 

2004 AP disc discrete stuck switch 3. Indicated switch on cockpit 

2005 AP manual PET stuck switch 

The indicated switch stuck in the engaged position. The discrete data input for the switch indicated that the switch 

remained in the active position for a period of time (STUCK-SWITCH-TIME). The switch is considered to be stuck 

and the input will be ignored until the discrete data input for the switch indicates that the switch has been released 

(no longer stuck). 

3000 First monitoring error 1. KCP 520 

Page 156 

Revision AD - .. 

This is a dummy error code marking the beginning of the autopilot monitoring error code section. This error should 

not occur. 


I



Error #(s) Text Message(s) Possible failed unit(s) 

3001 Pit cntrl pos rsnable mon I. KCP 520 

3002 

3003 

Rol cntrl pos rsnable mon 

Yaw cntrl pos rsnable mon 

2. Indicated control position resolver 

3004 Col cntrl pos rsnable mon 

A control position was detected to be out of the installed control position range. The control position input is 

monitored to be between the stored control position stop positions, determined during installation, for the indicated 

axis. This control position was outside of the control position stop position range by more than a percentage 

(CNTRL-POS-TOL) of the total control position range for that axis for a certain period of time 

(CNTRL-POS-TIME). This failure will be cleared when the control position is within the control position range for 

a certain period of time (RECOVERY-TIME). 

3005 Pit rate comparison mon 1. AHRS system components 

3006 Rol rate comparison mon 2. KRG333 # I 

3. KRG333 # 2 

4. KCP 520 

A pitch or roll body rate discrepancy was detected. Comparison of body rates from the primary, secondary, and 

tertiary rate sources indicated that at least one of the rate sources failed. The absolute difference between primary and 

secondary body rate, primary and tertiary body rate, or secondary and tertiary body rate exceeded a threshold 

(BODY-PIT-RATE-TOL for pitch, BODYROL-RATE-TOL for roll) for a certain period of time 

(BODY-RATE-TIME). This failure will be cleared when the rate difference between all three rate sources is below 

the threshold for a certain period of time (RECOVERY-TIME). 

3007 Yaw rate comparison mon I. AHRS system components 

2. KRG333 # I 

3. KCP 520 

A yaw body rate discrepancy was detected, the difference between body rate from the primary and secondary rate 

sources was excessive. The absolute difference between primary and secondary yaw body rate exceeded a threshold 

(BODY-YAW-RATE-TOL) for a certain period of time (BODY-RATE-TIME). This failure will be cleared when 

the rate difference is below the threshold for a certain period of time (RECOVERY-TIME). 

3009 FD cmd monitor-pitch up 1. KCP 520 . 

3010 ED cmd monitor-pitch down 

The pitch command received from the flight director processor exceeded the indicated direction limit. The pitch axis 

command from the flight director either was greater than a maximum limit (FDCMD-PIT-UP), causing a pitch up 

error, or less than a minimum limit (FDCMD-PIT-DN), causing a pitch down error, for a certain period of time 

(FDCMD-PITTIME). This failure will be cleared when the pitch axis command from the flight director is between 

the maximum and minimum limits for a certain period of time (RECOVERY-TIME). 

3011 FD cmd monitor-roll left 1. KCP 520 

3012 FD cmd monitor-roll right 

The roll command received from the flight director processor exceeded the indicated direction limit. The roll axis 

command from the flight director either was greater than a maximum limit (FDCMD-ROL-RT), causing a roll right 

error, or less than a minimum limit (FDCMD-ROL-LF), causing a roll left error, for a certain period of time 

(FDCMD-ROL-TIME). This failure will be cleared when the roll axis command %om the flight director is between 

the maximum and minimum limits for a certain period of time (RECOVERY-TIME). 

3013 pit pri-DAC comparison mon 1. KCP 520 

3014 rol pri-DAC comparison mon 

3015 yaw pri-DAC comparison mon 

The DAC wraparound value for the indicated servo does not match the value calculated by the reporting processor. 

On AP A, the analog servo command input was outside of the band between the current task frame servo command 

and the previous task frame servo command by a threshold (MULTI-AXIS-DAC-TOL-AP-A). On AP B, the 

absolute difference between the computed command for the servo and the analog servo command input exceeded a 

threshold (DAC-CMP-TOL-B) for a certain period of time (DAC-CMP-TIME-B) while the command difference 

did not change polarity (i.e., computed command was continually greater than analog command ipput) and the 

change in output command in a 25 millisecond interval did not exceed a maximum limit (DAC-CMP-MAX) during 

the failure time. This failure can only be cleared by executing preflight test again. 


, Page 157 

Revision AD



Error #(s) 

3016 

3017 

3018 



pit trm-DAC comparison mon 1. KCP 520 

rol trm-DAC comparison rnon 

yaw trm-DAC comparison rnon 

The DAC wraparound value for the indicated servo does not match the value calculated by the reporting processor. 

The absolute difference between the computed command for the servo and the analog servo command input 

exceeded a threshold (DAC-CMP-TOL-A for AP A or DAC-CMP-TOL-B for AP B) for a certain period of time 

(DAC-CMP-TIME-A for AP A or DAC-CMP-TIME-B for AP B) while the command difference did not change 

polarity (i.e., computed command was continually greater than analog command input). Also, for AP B, the change 

in output command in a 25 millisecond interval did not exceed a maximum limit (DAC-CMP-MAX) during the 

failure time. This failure can only be cleared by executing preflight test again. 

pit pri-servo midpoint volt rnon 1. KCP520 

rol pri-servo midpoint volt rnon 

yaw pri-servo midpoint volt rnon 

2, Indicated 

pit trm-servo midpoint volt rnon 

rol trm-servo midpoint volt rnon 

yaw trm-servo midpoint volt rnon 

The indicated servo amplifier midpoint voltage input failed. The absolute difference between the expected value for 

the midpoint voltage and the analog midpoint voltage input exceeded a threshold (MIDPNT-VLT-NOPWR-TOL 

when servo is not powered or MIDPNT-VLT-TOO when servo is powered) for a certain period of time 

(MIDPNT-VLT-TIME). The expected midpoint voltage varies based on whether the indicated servo is powered 

andfor selected (MIDPNT-VLT-NOPWR when servo is not powered, MIDPNT-VLT-SEL when servo is powered 

and selected, and MIDPNT-VLT-NOSEL when servo is powered and not selected). This failure can only be cleared 

by executing preflight test again. 

pit pri-servo amp model mon 1. KCP 520 

rol pri-servo amp model mon 2. Indicated servo 

yaw pri-servo amp model mon 3. LVDT position sensor for indicated servo (if KLA 570) 

pit trm-servo amp model rnon 

rol trm-servo amp model rnon 

yaw trm-servo amp model rnon 

The indicated servo amplifier failed. The servo amplifier for a KLA 570 is modeled in software using the following 

equation : 

VIn - 

Kf - 

Vcmd - 

Kfb - 

Ptb - 

Poff - 

Kr - 

A, - 

servo motor voltage 

servo forward loop gain (PRI-FWD-LOOP) 

servo command (in volts) 

feedback conversion constant (converts inches to volts) 

LVDT position (in inches) 

LVDT position offset (in inches) 

rate conversion constant (converts incheslsecond to volts) 

LVDT position rate (in inches/second) 

The servo amplifier for a KSA 572 or BFG type servo is modeled in software using the following equation 

VBn - 


Kf - 

servo forward loop gain (TRM-FWD-LOOP) 

Vc!nd - 

servo command (in volts) 

The computed servo motor voltage obtained using this equation is then limited to an absolute maximum value 

(MAX-SRV-VOLT) and compared with input servo motor voltage. The absolute difference between computed 

servo motor voltage and input servo motor voltage exceeded a threshold (AMP-MODEL-TOL) for a certain period 

of time (AMP-MODEL-TIME). This failure can only be cleared by executing preflight test again. 

Page 158 

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BENDIX/KING@ IFRAVIONICS I KFC goo 


Error #(s) 

3031 

3032 

3033 

3034 

3035 

3036 



pit pri-servo current mon I. KCP 520 

rol pri-servo current mon 2. Indicated servo 

yaw pri-servo current rnon 

plt trm-servo current rnon 

rol trm-servo current rnon 

yaw trm-servo current rnon 

The indicated servo motor was drawing excessive current. The absolute input motor current for the indicated servo 

was greater than a maximum limit (MAX-LVDT-CUR for a KLA 570 servo, MAX-TRIM-CUR for a KSA 

572 servo, MAXBFG-CUR for a BFG type servo) for a certain period of time (AMP-SERVO-CUR-TIME). 

This failure can only be cleared by executing preflight test again. 

pit pri-LVDT valid rnon 

rol pri-LVDT valid rnon 

yaw pri-LVDT valid rnon 

1. KCP 520 


3. LVDT position sensor for indicated servo 

The LVDT position validity for the indicated servo failed. The voltage input for LVDT validity for the indicated 

servo was below a minimum threshold (LVDT-VALID-VOLT) for a certain period of time 

(LVDT-VALID-TIME). This failure can only be cleared by executing preflight test again. 

pit pri-LVDT pos rsnable mon 1. KCP 520 

rol pri-LVDT pos rsnable mon 2. Indicated servo 

yaw pri-LVDT pos rsnable mon 3. LVDT position sensor for indicated servo 

An LVDT position was detected to be out of the installed LVDT position range. The LVDT position input is 

monitored to be between the stored LVDT stop positions, determined during installation, for the indicated axis. This 

LVDT position was outside of the LVDT stop position range by more than a percentage (LVDT-RSN-TOL) of the 

total LVDT position range for that axis for a certain period of time (LVDT-RSN-TIME). This failure can only be 

cleared by executing preflight test again. 

pit pri-servo motor model mon 1. KCP 520 

rol pri-servo motor model rnon 2. Indicated servo 

yaw pri-servo motor model mon 3. LVDT position sensor for indicated servo (if KLA 570) 

The indicated servo amplifier failed. The servo motor for a KLA 570 is modeled in software using the following 

equation : 


back emf constant (PRI-BACK-EMF) 

LVDT position rate (in incheslsecond) 

motor resistance (PRI-RESIST) 

11 - servo motor current 

The computed servo motor voltage obtained using this equation is compared with input servo motor voltage. The 

absolute difference between computed servo motor voltage and input servo motor voltage exceeded a threshold 

(MOTOR-MODEL-TOL) for a certain period of time (MOT-MOD-PRI-TIME). This failure can only be cleared 

by executing preflight test again. 

304 6 pit pri-no sol engage mon I. KCP 520 

3050 

3051 

rol pri-no sol engage mon 

yaw pri-no sol engage mon 


3052 pit trm-no sol engage mon 

3053 rol trm-no sol engage mon 

3054 yaw trm-no sol engage mon 

The brake for the indicated servo did not release as requested The brake release input for the servo did not indicate 

the brake was released for a certain period of time (SOL-ENGAGE-TIME) when the brake release hi and brake 

release lo outputs for the servo are both true. This failure can only becleared by executing preflight test again. 


I . . 3 . 

. . 

. . 

Page 459 

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BENDXIKING" IFR AVIONICS I KFC 900 


Error #(s) Text Message(§) Possible failed unit(s) 

3055 pit pri-no sol disengage mon 1. KCP 520 

3056 

3057 

rol pri-no sol disengage mon 

yaw pri-no sol disengage mon 


3058 pit trm-no sol disengage mon 

3059 rol trm-no sol disengage mon 

3060 yaw trm-no sol disengage mon 

The brake for the indicated servo did not engage as requested. The brake release input for the servo did not indicate 

the brake was engaged for a certain period of time (SOL-DISENG-TIME-A for AP A or SOL-DISENG-TIME-B 

for AP B) when either the brake release hi or brake release lo output for the servo was false. This failure can only be 


excess pitch att rnon 

excess roll att rnon 


2. KCP520 

Roll or pitch attitude was detected to be at an unusual value when the autopilot was engaged. Predicted attitude is 

computed in software using the following equation : 

att = att + att . - 

P 

aftp - 

predicted attitude 

all - 

current attitude (in degrees) 

ah - 

attitude rate (in degreeslsecond) 

The predicted attitude obtained from this computation was either greater than a maximum limit (XSATT'PIT-UP 

for pitch, XSATT-ROL-RT for roll) or less than a minimum limit (XSATT-PIT-DN for pitch, XSA7T-ROL-LF 

for roll) for a certain period of time (XSATT-TIME). This failure will be cleared when the predicted attitude is 

between the maximum and minimum limits for a certain period of time (RECOVERY-TIME). 

excess lateral accel mon 1. KRG 333 

excess longitudinal accel mon 2. KCP520 

excess normal accel rnon 

The indicated acceleration value was detected to be at an unusual value when the autopilot was engaged. The servo 

command for an axis must contribute to the excessive acceleration detected (i.e., pitch servo command for lateral 

acceleration driving in direction to cause the excessive acceleration, not prevent it). This condition was met and the 

indicated acceleration was either less than a minimum limit (XSACC-LAT-NEG for lateral, XSACC-LONG-NEG 

for longitudinal, XSACC-NORM-NEG for normal) or greater than a maximum limit (XSACC-LAT-POS for 

lateral, XSACC-LONG-POS for longitudinal, XSACC-NORM-POS for normal) for a certain period of time 

(XSACC-TIME). This failure will be cleared when the indicated acceleration is between the minimum and 

maximum limits for a certain period of time (RECOVERY-TIME). 

collect-DAC comparison mon 1. KCP 520 

collect-servo midpoint volt rnon 

collect-servo amp model rnon 

collect-servo current rnon 

collect-no sol engage rnon 

collect-no sol disengage rnon 

1 

s+l 

These errors should not occur, since there is no collective axis in the KCP 520. 

pit pri-servo stalled mon 1. Indicated servo 

rol pri-servo stalled mon 2. KCP 520 

yaw pri-servo stalled rnon 

A stalled servo was detected, servo stopped at a position other than the mechanical stop. When the servo motor 

current for the servo actuator exceeds a threshold (LVDT-POS-CUR) for a certain period of time 

(STOP-POS-TIME), the input servo LVDT position is compared with the stored stop position, determined during 

installation, for that servo. The difference between these two values was greater than a percentage 

(STOP-POS-TOL) of the full scale travel for that servo (absolute difference between both stop positions as 

determined during installation). This failure can only be cleared by executing preflight test again. 

Page 160 

Revision AD 


1



Error #(s) Text Message(s) Possible failed unit@) 

3080 pit trm-servo stalled mon 1. Indicated servo 

3081 rol trm-servo stalled mon 2. Indicated axis control position resolver 

3082 yaw trm-servo stalled mon 3. KCP 520 

A stalled servo was detected, servo stopped at a position other than the mechanical stop. When the servo motor 

current for the servo actuator exceeds a threshold (TRIM-POS-CUR for a KSA 572 or BFG-POS-CUR for a BFG 

type servo) for a certain period of time (STOP-POS-TIME), the input synchro position from the control position 

resolver for that axis is compared with the stored stop position, determined during installation, for that servo. The 

difference between these two values was greater than a percentage (STOP-POS-TOL) of the full scale travel for that 

servo (absolute difference between both stop positions as determined during installation). This failure can only be 


3083 collect-servo stalled mon 1. KCP 520 

This error should not occur, since there is no collective axis in the KCP 520. 

3084 Pit position synchro exc mon 1. Indicated control position resolver 

3085 Rol position synchro exc mon 2. KCP 520 

3086 Yaw position synchro exc mon 

3087 Col position synchro exc mon 

The excitation voltage for the indicated control position resolver is inadequate for proper operation. The input 

control position excitation voltage was below a threshold (CNTRL-POS-EXC-THRES) for a certain period of 

time (CNTRL-POS-EXC-TIME) or the validity for the indicated axis position was invalid (indicating invalid 

excitation). If the failure was caused by the input control position excitation voltage, the failure can only be cleared 

by executing preflight test again. If the failure was caused by the axis position validity, the failure will be cleared 

when the validity is valid for a certain period of time (RECOVERY-TIME). 

3088 Invalid pitch cmd from FD~ 1. KCP 520 

3089 Invalid roll cmd from FD~ 

The roll or pitch command from the flight director was invalid. The command received on the interprocessor bus 

from the flight director for the indicated axis was invalid (validity indicated invalid) for a certain period of time 

(FDCMD-DATA-TIME). This failure will be cleared when the command is valid for a certain period of time 

(RECOVERY-TIME). 

3090 LVDT detected in wrong axis 1. KCP 520 

Monitoring of an LVDT was attempted in an axis that does not have an LVDT. This error indicates that the ROM 

servo information table in the processor code has been corrupted. This failure can only be cleared by executing 

preflight test again. 

3091 Multi axis DAC compare 1. KCP 520 

The DAC wraparound values for servo commands for at least two axes did not match the values calculated by the 

reporting processor. The analog servo command input was outside of the band between the current task frame servo 

command and the previous task frame servo command by a threshold (MULTI-AXIS-DAC-TOL-m-A for AP A 

or MULTI-AXIS-DAC-TOL-AP-B for AP B). This failure can only be cleared by executing preflight test again. 

3093 Yaw body rate monitor 1. KCP 520 

3094 Pitch body rate monitor 2. KRG 333 # 1 

3095 Roll body rate monitor 

The body rate input for the indicated axis is invalid. Either the body rate input validity indicated the rate was invalid 

or the absolute body rate was above a threshold (MAX-PITCH-RATE for pitch rate, MAX-ROLL-RATE for roll 

rate, or MAX-YAW-RATE for yaw rate) for a certain period of time (BODY-RATLTIME). This failure will be 

cleared when the body rate is valid and absolute body rate is below the threshold for a certain period of time 

(RECOVERY-TIME). 

3096 KRG 333 #2 pit rate valid mon 1. KCP 520 

3097 KRG 333 #2 rol rate valid mon 2. KRG333 # 2 

The body rate input for the indicated axis is invalid. The body rate input validity indicated the rate was invalid for a 

certain period of time (BODY-RATE-TIME). This failure will be cleared when the body rate is valid and absolute 

body rate is below the threshold for a certain period of time (RECOVERY-TIME). 


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Revision AD

BENDIXIKlNNGe IFR AVIONICS I KFC goo 


Error #(s) 

3098 

Page 162 

Revision AD 



Low power system failure I. KCP 520 

A monitor or preflight test failure was detected while input +28 V DC power was considered at a low voltage. This 

error is logged instead of the normal monitoring or preflight test error when input + 28 V DC is below a minimum 

threshold (MIN-28V-THRESHOLD). This error will be logged when +28 V DC is below the threshold and will 

not be logged when + 28 V DC is above the threshold. 

AHRS Pitch attitude valid mon I. AHRS system components 

AHRS Roll attitude valid mon 2. KCP520 

AHRS Heading valid rnon 

AHRS Pitch rate valid rnon 

AHRS Roll rate valid rnon 

AHRS Yaw rate valid rnon 

The indicated input from the Attitudemeading Reference system was invalid. The indicated input was invalid for a 

certain period of time (AHRS-VAL-TIME). This failure will be cleared when the AHRS input is valid for a certain 

period of time (RECOVERY-TIME). 

plt prl-no cltch disengage mon 1. KCP 520 

rol prl-no cltch disengage mon 2. Indicated servo 

yaw prl-no cltch dlsengage rnon 

pit trm-no cltch dlsengage rnon 

rol trm-no cltch dlsengage rnon 

yaw trm-no cltch disengage rnon 

collect-no cltch dlsengage rnon 

The clutch for the indicated servo did not disengage as requested. The clutch engage input for the servo did not 

indicate the clutch was disengaged for a certain period of time (CLUTCHDISENGAGE-TIME) when the clutch 

engage hi or clutch engage lo output for the servo is false. This failure can only be cleared by executing preflight test 

again. 

pit pri-no clutch engage mon 1. KCP 520 

rol prl-no clutch engage mon 2. Indicated servo 

yaw prl-no clutch engage mon 

plt trm-no clutch engage rnon 

rol trm-no clutch engage rnon 

yaw trm-no clutch engage rnon 

collect-no clutch engage rnon 

The clutch for the indicated servo did not engage as requested.'The clutch engage input for the servo did not indicate 

the clutch was engaged for a certain period of time (CLUTCH-ENGAGE-TIME) when the clutch engage hi and 

clutch engage lo outputs for the servo are both true. This failure can only be cleared by executing preflight test again. 

plt pri-VSCS posltlon mon 1. KCP 520 

rol pri-VSCS position mon 2. Indicated servo 

yaw pri-VSCS positlon rnon 

plt trm-VSCS posltion rnon 

rol trm-VSCS positlon mon 

yaw trm-VSCS posltlon rnon 

collect-VSCS position rnon 

The input VSCS position for the indicated servo did not match output position for the servo. The absolute difference 

between input VSCS position and output VSCS command exceeded a percentage (VSCS-COMF-TOL) of the total 

VSCS position range for that axis for a certain period of time (VSCS-COMP-TIME). This failure can only be 


pit pri-no relay engage mon 1. KCP 520 

rol pri-no relay engage mon 2. Indicated servo 

yaw pri-no relay engage rnon 

pit trm-no relay engage non 

rol trm-no relay engage rnon 

yaw trm-no relay engage rnon 

collect-no relay engage mon 

The relay for the indicated servo did not engage as requested. The relay engage input for the servo did not indicate 

the relay was engaged for a certain period of time (RELAY-ENGAGE-TIME) when the relay engage hi and relay 

engage lo outputs for the servo are both true. This failure can only be cleared by executing preflight test again. 

.-. . 

97-00-00 

. EFFECTIVITY: MD900 

. 

I,, , 

.. . . 

. \

Error #(s) 

3150 

3151 

3152 

3153 

3154 

3155 

3156 





pit pri-no relay disengage mon I. KCP 520 

rol pri-no relay disengage mon 2. Indicated servo 

yaw pri-no relay disengage rnon 

pit trm-no relay disengage rnon 

rol trm-no relay disengage rnon 

yaw trm-no relay disengage rnon 

collect-no relay disengage rnon 

The relay for the indicated servo did not disengage as requested. The relay engage input for the servo did not indicate 

the relay was disengaged for a certain period of time (RELAY-DISENGAGE-TIME) when the relay engage hi or 

relay engage lo output for the servo is false. This failure can only be cleared by executing preflight test again. 

3160 pit pri-no SAS pos centering 1. KCP 520 

3161 rol pri-no SAS pos centering 2. Indicated servo 

3162 yaw pri-no SAS pos centering 3. Indicated axis control position resolver 

4. LVDT position sensor for indicated servo 

The indicated servo did not return to its center position within a specified time period in SAS mode. The further the 

servo position is from center, the shorter the time period for the failure. There are following position percentages (of 

full scale servo travel) correspond to the matching failure times : 1) SAS-CENTER-PERCENT-1 has a failure time 

of SAS-CENTER-TIME-I ,2) SAS-CENTER-PERCENT-2 has a failure time of SAS-CENTER-TIME-2,3) 

SAS-CENTER-PERCENT-3 has a failure time of SAS-CENTER-TIME-3,4) SAS-CENTER-PERCENT-4 has 

a failure time of SAS-CENTER-TIME-4, and 5) SAS-CENTER-PERCENT-5 has a failure time of 

SAS-CENTER-TIME-5. This failure will be cleared when SAS mode is disengaged for the axis in which the failure 

occurred. 

3163 A/D bit stuck mon 1. KCP 520 

One of the analog input loopback test values did not match the expected value for that input (indicating that one of 

the data lines on the analog-to-digital converter input has probably stuck to a high or low value). The difference 

between the analog loopback value input and the expected analog loopback value was greater than a threshold 

(STUCK-BIT-THRES). This failure can only be cleared by executing preflight test again. 

3999 Last monitoring error 1. KCP 520 

This is a dummy error code marking the end of the autopilot monitoring error code section. This error should not 

occur. 

' When more than one unit is listed, there is also a possibility that the harness interconnection 

between any of the listed units has failed. 

4 

If this failure is logged by an AP processor, the failure occurred in the AP IP communication bus. If 

this error is logged by an FD or maintenance processor, the failure occurred in the FD IP 

communication bus. 

The failure occurred in the common IP communication bus. 

This failure is detected by the interrupt service routine that processes the communication. Any 

receive error (i.e., RX status) will cause the received communication packet to be ignored by the 

receiving processor. 

5 

When this error occurs, data may have been lost. 

7 

Since the AP processor uses DMA channel 2 for analog input, a DMA 2 failure logged by an AP 

processor could indicate that the analog input service routine or analog input hardware has failed 

instead of the ARlNC 429 ASIC. 

This error will not be logged if both pitch and roll commands are invalid or if the system is configured 

as a SCASIATT (SCAS and attitude hold only) system. 

Only if this monitor was caused by a body rate validity failure and not a body rate out of range 

failure. 


Page 163 

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Page 164 

Revision AD 



When this monitor failure is detected and AP mode is engaged, it will cause loss of AP and SAS 

mode in the affected axis, but the monitor failure will not be detected when SAS mode is engaged. 

10 

Only if indicated airspeed is less than 50 nautical miles per hour. 

6) THRESHOLDS AND CONSTANTS - The following is a list of the thresholds and constants for the 

MD900 (rncluding the 902 confrguration) helicopter certification. This information is used by 

autopilot monrtoring and preflight test modules as necessary to determine failures. 

Constant name Value Units 

AHRS-VAL-TIME 300 milliseconds 

AMP-MODEL-TIME 300 milliseconds 

AMP-MODEL-TOL 8.4 volts 

AMP-SERVO-CUR-TIME 60 seconds 

BFG-POS-CUR 0.25 amp 

BODY-RATE-TIME 1000 milliseconds 

CLUTCH-DISENGAGE-TIME 400 milliseconds 

CLUTCH-ENGAGE-TIME 400 milliseconds 

CNTRL-POS-EXC-THRES 17 volts 

CNTR-OS-EXC-TIME 300 milliseconds 

CNTRL-POS-TIME 400 milliseconds 

CNTRL-POS-TOL 20% NIA 

DAC-CMP-MAX 102 bits ADC in 

DAC-CMP-TIME-A 50 milliseconds 

DAC-CMP-TIME-B 325 milliseconds 

DAC-CMP-TOL-A 205 bits ADC in 

DAC-CMP-TOL-B 820 bits ADC in 

FDCMD-DATA-TIME 300 milliseconds 

FDCMD-PIT-DN -30 degrees 

FDCMD-PIT-TIME 600 milliseconds 

FDCMD-PIT-UP 20 degrees 

FDCMD-ROL-LF -3 1 degrees 

FDCMD-ROL-RT 3 1 degrees 

FDCMD-ROL-TIME 600 milliseconds 

LVDT-POS-CUR 0.6 amp 

LVDT-RSN-TIME 300 milliseconds 

LVDT-RSN-TOL 20% NIA 

LVDT-VALID-TIME 300 milliseconds 

LVDT-VALID-VOLT 0.5 volt 

MAX-BFG-CUR 0.25 amp 

MAX-LVDT-CUR 1 amp 

MAX-PITCH-RATE 10 degreeslsecond 

MAX-ROLL-RATE 15 degreeslsecond 

MAX-SRV-VOLT 26 volts 

MAX-TRIM-CUR 0.25 amp 

MAX-YA W-RATE 15 degreeslsecond 

MIDPNT-VLT-NOPWR 0 volts 

MIDPNT-VLT-NOPWRTOL 6.0 volts 

MIDPNT-VLT-NOSEL 28 volts 

MIDPNT-VLT-SEL 14 volts 

MIDPNT-VLT-TIME 300 milliseconds 

MIDPNT-VLT- TOL 4.2 volts 

MIN-28V-THRESHOLD 17.5 volts 

IMIS-TRIM-TIME 10 seconds 

MOT-MOD-PRI-TIME 300 milliseconds 

MOTOR-MODEL-TOL 8.4 volts 


L



Constant name 

MULTI-AXIS-DAC-TOL-AP-A 

MULTI-AXIS-DAC-TOL-AP-B 

PFT-ACCEL-TIME 

PFT-ADC-DAC-LIM 

PFTDRIVE-TIME 

PFT-DRV-POS-TOL 

PFT-LATMAX 

PFT-LAT-MrN 

PFT-LAT-TST-LIM 

PFT-LONG-MAX 

PFT-LONG-MlN 

PFT-LONG-TST-LIM 

PFT-LVDTPOS-TOL 

PFT-LVDTRATE-MAX 

PFT-LVDT-VALIDMIN 

PFTMID-VLT-NOPWR 

PFT-MID-VLT-NOSEL 

PFT-MID-VLT-SEL 

PFT-MIDPNT-VLTTOL 

PFT-NORNMAX 

PFT-NORM-MIN 

PFT-NORM-TST-LIM 

PFT-OFF-VOLT 

PFT-PIT-MAX 

PFT-PITMIN 

PFT-PITTST-LIM 

PFT-PRI-DRV-CUR 

PFT-PFU-DRV-TOL 

PFT-PRI_OFF-CUR 

PFT-RATE-NORM-TIME 

PFT-RATE-TIME 

PFT-ROL-MAX 

PFT-ROL-MrN 

PFT-ROL-TST-LIM 

PFT-SRV-DAC-MAX 

PFT-SRV-DAC-MIN 

PFT-SYNC-TIME 

PFT-TRIM-ENG-TIME 

PFT-TRIM-POS-TOL 

PFT-TRIM-TEST-MIN 

PFT-TRIM-TEST-THRES 

PFT-TRIM-TEST-TIME 

PFT-TRM-DRV-CUR 

PFTTRM-DRV-TOL 

PFT-TRM_OFF-CUR 

PFT-Y A W-MAX 

PFT-YAW-MIN 

PFT-YAW-TST-LIM 

PIT-MIS-TRIM-TOL 

PRIBACK-EMF 

PRLFWD-LOOP 

PRI-RESIST 

Value 

62 

123 

1 

500 

205 

300 

0.0 1 

16.1 

-16.1 

-25.76 

40.25 

-24.15 

96.6 

20% 

0.175 

0.5 

0 

2 8 

14 

4.2 

64.4 

0.0 

86.94 

2.0 

8 

-8 

30 

500 

25% 

0.1 

1 

500 

12 

-12 

3 0 

1640 

- 1640 

1.5 

1 

20% 

0.0 16 

0.006 

2 

20 

50% 

0.025 

12 

-12 

-3 0 

25% 

-9.34 

-20.5 

-2 1.5 

Units 

bits ADC in 

bits ADC in 

second 

milliseconds 

bits ADC in 

milliseconds 

inch 

feet/second2 

feet/second2 

feet/second2 

feet/second2 

feet/second2 

feet/second2 

NIA 

incheslsecond 

volts 

volts 

volts 

volts 

volts 

feet/second2 

feetlsecond2 

feet/second2 

volts 

degreeslsecond 



milliamps 

NIA 

amp 

second 

milliseconds 




bits DAC out 

bits DAC out 

seconds 

second 

NIA 

amp 

amp 

minutes 

milliamps 

NIA 

amp 




NIA 

volts/inch/second 

NIA 

ohms 


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BENDIX/KINGG" IFRAVlONlCSI KFC 900 


Constant name Value Units 

RECOVERY-TIME 500 milliseconds 

RELAY-DISENGAGE-TIME 400 milliseconds 

RELAY-ENGAGE-TIME 400 milliseconds 

ROL-MISTRIM-TOL 25% N/A 

SAS-CENTER-PERCENT- 1 25% N/A 

SAS-CENTER-PERCENT-2 30% N/A 


SAS-CENTER-PERCENT-4 40% N/ A 


SAS-CENTER-TIME-I 2.5 seconds 

SAS-CENTER-TIME-2 2 seconds 

SAS-CENTER-TIME-3 1.5 seconds 

SAS-CENTER-TIME-4 1 second 

SAS-CENTER-TIME-5 0.5 second 

SOL-DISENG-TIME-A 400 milliseconds 

SOL-DISENG-TIME-B 300 milliseconds 

SOL-ENGAGE-TIME 300 milliseconds 

STOP-POS-TIME 300 milliseconds 

STOP-POS-TOL 20% NIA 

STUCK-BIT-THRES 15 bits ADC in 

STUCK-SWITCH-TIME 5 seconds 

SWITCH-MISMATCH-TIME 500 milliseconds 

TRIM-POS-CUR 0.25 amp 

TRM-FWD-LOOP -5.6 NIA 

VSCS-COMP-TIME 10 seconds 

VSCS-COMP-TOL 20% NIA 

XSACC-LAT-NEG -16.1 feet/second2 

XSACC-LAT-POS 16.1 feet/second2 

XSACC-LONG-NEG -16.1 feet/second2 

XSACC-LONG-POS 16.1 feet/second2 

XSACC-NORM-NEG -19.3 feet/second2 

XSACC-NORM_POS 22.5 feet/second2 

XSACC-TIME 600 milliseconds 

XSATT-PIT-DN -25 degrees 

XSATT-PIT-UP 25 degrees 

XSATT-ROL-LF -45 degrees 

XSATT-ROL-RT 45 degrees 

XSATT-TIME 600 milliseconds 

YAW-MIS-TRIM-TOL 20% NIA 

' This voltage is actually the aircraft power +28 VDC voltage read in (nominally 28 V) less the average servo 

amp drop (set to 2 V in software). 

F. FAILURE ANNUNCIATION 

When a monitoring or preflight test error is logged, the failure is annunciated to the pilot 

Failure to pass preflight test prevents future engagement of AP mode and SAS mode in the axislaxes 

affected by the failure. If a preflight test failure is detected in the roll or pitch axis during each of three 

test attempts, future engagement of AP mode and SAS mode is prevented in both the roll and pitch 

axes. If a preflight test failure is detected in the yaw axis during each of three test attempts, future 

engagement of AP mode and SAS mode is prevented in the yaw axes. When a preflight test failure 

occurs that does not affect all axes, the failure discrete for the failed axislaxes will be set to fail. If a 

preflight test failure affecting all axes is detected during each of three test attempts, future 

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engagement of AP mode and SAS mode is prevented. When this type of failure occurs, the AP fail 

discrete will be set to fail and the SAS fail discrete will be set to fail. 

The following preflight test error codes will result in the loss of AP mode and SAS mode in the pitch 

and roll axes only: 

PFT accel norm tst val bad 

PFT accel norm value error 

PFT pitch cmd DAC or ADC error 

PFT roll cmd DAC or ADC error 

PFT pit trrn cmd DAC or ADC err 

PFT rol trm cmd DAC or ADC err 

PFT pitch midpoint error 

PFT roll midpoint error 

PFT pitch trim midpoint error 

PFT roll trim midpoint error 

PFT pitch LVDT sense error 

PFT roll LVDT sense error 

PFT pitch servo position err 

PFT roll servo position err 

PFT pit trrn srv position err 

PFT rol trrn srv position err 

PFT pitch LVDT rate too high 

PFT roll LVDT rate too high 

PFT pit offset crnt too high 

PFT rol offset crnt too high 

PFT pit trrn offset crnt high 

PFT rol trm offset crnt high 

PFT pit offset volt too high 

PFT rol offset volt too high 

PFT pit trrn offset volt high 

PFT rol trrn offset volt high 

PFT pitch drive err 

PFT roll drive err 

PFT pitch trrn drive err 

PFT roll trm drive err 

PFT pitch monitor error 

PFT roll monitor error 

PFT pitch trm monitor error 


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1614 PFT roll trm monitor error 

1620 PFT pitch brake err 

1621 PFT roll brake err 

1631 PFT pitch rate tst val bad 

1632 PFT roll rate tst val bad 

1634 PFT pitch rate value error 

1635 PFT roll rate value error 

1643 PFT pitch trm clutchlrelay err 

1644 PFT roll trm clutchlrelay err 

1650 PFT rate valid # 2 fail 

1651 PFT pitch rate #2 tst val bad 

1652 PFT roll rate #2 tst val bad 

1653 PFT pitch rate #2 value error 

1654 PFT roll rate #2 value error 

1655 PFT rate valid #2 tst fail 

1656 PFT AHRS pitch rate invalid 

1657 PFT AHRS roll rate invalid 

1660 PFT trim test timeout 

1661 PFT trim test no roll current 

1662 PFT trim test no pitch current 

The following preflight test error codes will result in the loss of AP mode and SAS mode in the yaw 

axis only : 

PFT accel lat tst val bad 

PFT accel lat value error 

PFT yaw trrn cmd DAC or ADC err 

PFT yaw trim midpoint error 

PFT yaw trm srv position err 

PFT yaw trrn offset crnt high 

PFT yaw trm offset volt high 

PFT yaw trm drive err 

PFT yaw monitor error 

PFT yaw trrn monitor error 

PFT yaw trm brake err 

PFT yaw rate tst val bad 

1636 PFT yaw rate value error 

1642 PFT yaw clutchlrelay err 

1645 PFT yaw trm clutchlrelay err 

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5ENDIX/KlNGGe IFRAVIONICS I KFC goo 


1633 PFT yaw rate test value bad 

1636 PFT yaw rate out of range 

1642 PFT yaw clutchlrelay err 

The following preflight test error codes will result in the loss of AP mode and SAS mode in pitch, roll 

and yaw axes: 

PFT - 2 AP-As or 2 AP-Bs found 

PFT sync err waiting for AP A 

PFT sync err waiting for AP B 

AP A output control invalid 

AP B output control invalid 

PFT perf strap miscompare 

PFT accel valid fail 

PFT accel valid tst fail 

PFT rate valid fail 

PFT rate valid tst fail 

When a monitoring error resulting in loss of AP mode occurs in only one axis (i.e., roll trim servo 

failure), the AP mode is dumped for the affected axis, the failure discrete for the failed axis will be set 

to fail, and the disconnect aural alert tone for that mode will sound for approximately 5 seconds. When 

AP mode is disengaged, the axislaxes failure discrete(s) will be cleared. If possible, AP mode will 

revert to SAS mode in the affected axislaxes (i.e., for acceleration failures). This will occur for any 

error code listed here, but not listed for loss of SAS mode for the same axis below. 

The following monitoring error codes will result in the loss of AP mode in the pitch axis only: 

3001 Pit cntrl pos rsnable mon 

3005 Pit rate comparison mon 

3019 pit pri-servo midpoint volt mon 

3022 pit trm-servo midpoint volt mon 

3025 pit pri-servo amp model mon 

3028 pit trm-servo amp model mon 

3031 pit pri-servo current mon 

3034 pit trm-servo current mon 

3037 pit pri-LVDT valid mon 

3040 pit pri-LVDT pos rsnable mon 

3043 pit pri-servo motor model mon 

3046 pit pri-no sol engage mon 

3055 pit pri-no sol disengage mon 

3063 excess pitch att mong 

3067 excess normal accel mong 

3077 pit pri-servo stalled mon 


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BEAIDIX/KINGGQ IFRAVIONICS I KFC goo 


3080 pit trm-servo stalled mon 

3084 Pit position synchro exc mon 

3094 Pitch body rate monitor 

3096 KRG 333 #2 pit rate valid mon 

31 03 AHRS Pitch rate valid mon 

31 13 pit trm-no cltch disengage mon 

31 20 pit trm-no clutch engage mon 

The following monitoring error codes will result in the loss of AP mode in the roll axis only: 

Rol cntrl pos rsnable rnon 

Rol rate comparison rnon 



rol pri-servo amp model rnon 


rol pri-servo current rnon 



rol pri-LVDT pos rsnable rnon 

rol pri-servo motor model rnon 

rol pri-no sol engage rnon 

rol pri-no sol disengage rnon 

excess roll att mong 

rol pri-servo stalled rnon 

rol trm-servo stalled rnon 

Roll position synchro exc rnon 

Roll body rate monitor 

KRG 333 #2 rol rate valid rnon 


rol trm-no cltch disengage rnon 


The following monitoring error codes will result in the loss of AP mode in the yaw axis only: 

3003 Yaw cntrl pos rsnable mon 

3007 Yaw rate comparison mon 

3024 yaw trm-servo midpoint volt mon 

3030 yaw trm-servo amp model mon 

3036 yaw trm-servo current mon 

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.

BENDIX/KlNG@ IFR AVIONICS I KFC 900 



3060 yaw trm-no sol disengage mon 

3065 excess lateral accel mong 

3082 yaw trm-servo stalled mon 


3093 Yaw body rate monitor 

31 02 AHRS Heading valid mon1° 

31 05 AHRS Yaw rate valid mon 

31 15 yaw trm-no cltch disengage mon 

3122 yaw trm-no clutch engage mon 

31 32 yaw pri-VSCS position mon 

3142 yaw pri-no relay engage mon 

3152 yaw pri-no relay disengage mon 

When a monitoring error resulting in loss of SAS mode occurs in only one axis (i.e., roll primary servo 

failure), SAS mode is dumped for the affected axis, the failure discrete for the failed axis will be set to 

fail, and the disconnect aural alert tone for that mode will sound for approximately 5 seconds. When 

SAS mode is disengaged, the axislaxes failure discrete(s) will be cleared. 

The following monitoring error codes will result in the loss of SCAS mode in the pitch axis only: 

3001 Pit cntrl pos rsnable mon 

3005 Pit rate comparison mon 

301 9 pit pri-servo midpoint volt mon 

3022 pit trm-servo midpoint volt mon 

3025 pit pri-servo amp model mon 

3028 pit trm-servo amp model mon 

3031 pit pri-servo current mon 

3034 pit trm-servo current mon 

3037 pit pri-LVDT valid mon 

3040 pit pri-LVDT pos rsnable mon 

pit pri-servo motor model rnon 

pit pri-no sol engage rnon 

pit pri-no sol disengage rnon 

pit pri-servo stalled rnon 

pit trm-servo stalled rnon 

Pit position synchro exc rnon 

Pitch body rate monitor8 

KRG 333 #2 pit rate valid rnon 

AHRS Pitch rate valid rnon 


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BEN6)IX/KINGe IFRAVIONICSI KFC goo 


31 13 pit trm-no cltch disengage mon 

3120 pit trm-no clutch engage mon 

3160. pit pri-no SAS pos centering 

The following monitoring error codes will result in the loss of SAS mode in the roll axis only: 

Rol cntrl pos rsnable rnon 

Rol rate comparison rnon 



rol pri-servo amp model rnon 


rol pri-servo current rnon 



rol pri-LVDT pos rsnable rnon 

rol pri-servo motor model rnon 

rol pri-no sol engage rnon 

rol pri-no sol disengage rnon 

rol pri-servo stalled rnon 

rol trm-servo stalled rnon 

Roll position synchro exc rnon 

Roll body rate monitor8 

KRG 333 #2 rol rate valid rnon 


rol trm-no cltch disengage rnon 


rol pri-no SAS pos centering 

The following monitoring error codes will result in the loss of SAS mode in the yaw axis only: 

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Revision AD 

3003 Yaw cntrl pos rsnable mon 

3007 Yaw rate comparison mon 

3024 yaw trm-servo midpoint volt mon 

3030 yaw trm-servo amp model mon 

3036 yaw trm-servo current mon 


3060 yaw trrn-no sol disengage mon 

3082 yaw trm-se~o stalled mon 



I



3093 Yaw body rate monitor8 

31 05 AHRS Yaw rate valid mon 

3115 yaw trm-no cltch disengage mon 

3122 yaw trm-no clutch engage mon 

31 32 yaw pri-VSCS position mon 

31 42 yaw pri-no relay engage mon 

31 52 yaw pri-no relay disengage mon 

3162 yaw pri-no SAS pos centering 

When a monitoring error resulting in loss of AP mode for all axes occurs (i.e., vertical gyro failure), AP 

mode will dump, AP annunciation will flash for approximately 5 seconds, the AP disconnect aural alert 

tone will sound for approximately 5 seconds, and the AP fail discrete output will be set to fail. If 

possible, AP mode will revert to SAS mode for all available axes (axes that do not have a failure 

affecting SAS operation). This will occur for any error code listed here, but not listed for loss of SAS 

mode for all three axes listed below. 

The following monitoring and preflight test error codes will result in the loss of AP mode in pitch, roll 

and yaw axes: 

3009 FD cmd monitor-pitch up 

301 0 FD cmd monitor-pitch down 

301 1 FD cmd monitor-roll left 

3012 FD cmd monitor-roll right 

3013 pit pri-DAC comparison mon 

rol pri-DAC comparison rnon 

yaw pri-DAC comparison rnon 

pit trm-DAC comparison rnon 

rol trm-DAC comparison rnon 

yaw trm-DAC comparison rnon 

Invalid pitch crnd from FD 

Invalid roll crnd from FD 

LVDT detected in wrong axis 

Multi axis DAC compare 

AHRS Pitch attitude valid rnon 

AHRS Roll attitude valid rnon 

AID bit stuck rnon 

When a monitoring error resulting in loss of SAS mode for all three axes occurs (i.e., DAC command 

comparison), SAS mode will dump, SAS annunciation will flash for approximately 5 seconds, the SAS 

disconnect aural alert tone will sound for approximately 5 seconds, and the SAS fail discrete output 

will be set to fail. 


1 

, 

. 

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The following monitoring and preflight test error codes will result in the loss of SAS mode in pitch, roll 

and yaw axes: 

301 3 pit pri-DAC comparison mon 

3014 rol pri-DAC comparison mon 

301 5 yaw pri-DAC comparison mon 

3016 pit trm-DAC comparison mon 

301 7 rol trm-DAC comparison mon 

301 8 yaw trm-DAC comparison mon 

3090 LVDT detected in wrong axis 

3091 Multi axis DAC compare 

3163 AID bit stuck mon 

When an AP mode failure affecting one axis occurs and it is the only axis engaged in AP mode, AP mode 

will dump, AP annunciation will flash for approximately 5 seconds, the AP disconnect aural alert tone will 

.sound for approximately 5 seconds, and the AP fail discrete output will be set to fail. When AP dumps, 

SAS mode will be engaged for any axis that does not have a failure affecting SAS mode operation and 

failure discretes for any axis that is engaged in SAS mode will be cleared. If SAS mode cannot be 

engaged in any axis, SAS fail discrete output will be set to fail and failure discretes for all axes will be 

cleared. 

When a SAS mode failure affecting one axis occurs and it is the only axis engaged in SAS mode with no 

axes engaged in AP mode, SAS mode will dump, SAS annunciation will flash for approximately 5 

seconds, the SAS disconnect aural alert tone will sound for approximately 5 seconds, the SAS fail discrete 

output will be set to fail, and the failure discretes for all axes will be cleared. 


This section covers the failure of the one or more of the avionics cooling fans. 

The fan fail annunciation on the APISAS annunciator panel can be illuminated by any one of up to four fan 

monitors. The fans include the KA 33lKA 12 fan mounted on the battery box, the KA 33lKA 12 mounted in 

theright hand avionics bay, the forward right hand instrument panel fan, and (4-Tube installations only) the 

forward left hand instrument panel fan. 

If the fan fail annunciator is illuminated, check each fan for operation. Remove and replace the failed 

fan(s) as required. 

7. Annunciators and Bulb Replacement 

This section covers the replacement of annunciators and/or bulbllamps in the annu8nciatorsd and the 

APISAS annunciator panel. 

This section applies to the following annunciatorlswitches. 

AHRS 1/2 Select (pilot) (4-tube option) 

AHRS 1/2 Select (copilot) (4-tube option) 

FLT DIR LIR (4-tube option) 

CMPST (pilot) 

CMPST (copilot) (4-tube option) 

GPS CRS SELECT LIR (4-tube option) 

GPS CRS OBSILEG 

GPS APR ARMIACW 

, , 

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BENDIXlKIN6" IFRAVIONICS I KFC goo 


The bulbs can be replaced by extracting the lamp capsule from the front of the assembly. There are 

four (4) bulbs per lamp capsule. Refer to the parts list in Chapter 98 for replacement bulb part 

number. 

El. Annunciators 

This section applies to the following annunciators. 

MSGIWPT (pilot) 

MSGIWPT (copilot) (4-tube only) 

VNE (pilot) (Cat A only) 

VNE (copilot) (4-tube Cat A only) 

The bulbs for the annunciator lamp capsule cannot be replaced. A new lamp capsule must be 

ordered and installed. The lamp capsule can be removed from the assembly 


I 

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97-00-00 

Avionics - 

Removal 1 Installation 

I. General 

This section provides instructions for removing, installing and adjusting each unit of the KFC 900 AFCS 

and IFR avionics package. 

[ail 


2. VHF Navigation and Communications (NAVICOMM) 

A. KX 165lKX 165A NAVICOMM 

The KX 165lKX 165A transceivers are located in the forward right hand side of the console. The 

No. 1 KX 165lKX 165A is the aft most unit. The No. 2 KX 165lKX 165A is forward of the No. 1 

KX 1651KX 165A. 

1) REMOVAL (either unit) 

a) Remove the decorative bezel around the console mounted avionics units. 

b) Use a 3/32" Allen wrench inserted in the hole in the bottom(aft) center of the NAVICOMM. 

Turn the Allen wrench counter clockwise to loosen the locking screw inside the unit. The unit 

will gradually push itself out of its rack. 

c) Slide the unit out the rack. 

2) INSTALLATION (either unit) 

a) Slide the unit into the rack. 

b) Use a 3/32" Allen wrench inserted in the hole in the bottom(aft) center of the NAVICOMM. 

Turn the Allen wrench clockwise to tighten the locking screw inside the unit. The unit will 

gradually draw itself into its rack. Continue turning until the unit is secure in the rack, being 

careful not to over tighten the locking screw. 

c) Install the decorative bezel around the console mounted avionics units. 


I 

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BENDIXIKINNGQ IFRAVIONICS I KFC goo 


B. KI 206 NAV Indicator 

The KI 206 is located in the pilot's instrument panel below the airspeed indicator. 

1) REMOVAL 

a) Remove the four screws securing the unit to the instrument panel. 

b) Slide the unit out of the instrument panel 

c) Disconnect the harness connector. 

2) INSTALLATION 

a) Connect the harness connector to the unit. 

b) Slide the unit into the instrument panel. 

c) Secure the unit to the instrument panel: 

C. CI-1125 Quadraplexer 

The quadraplexer is located in the right hand avionics bay, mounted to the plough beam. Gain access 

through the right hand avionics bay door. 

1) REMOVAL 

a) Remove the five coaxial cables from the quadraplexer 

b) Remove the screws securing the quadraplexer to the plough beam. 

c) Remove the quadraplexer from the aircraft. 


a) Mount the quadraplexer to the plough beam. 

b) Secure the coaxial cable connectors to the appropriate connectors on the quadraplexer 

D. CI-I 20 VORILOCIGS Antenna 

The CI-120 antenna is located on the aft bottom tail boom. 

1) REMOVAL 

a) Remove the cover of the NAV antenna box. 

b) Disconnect the coaxial cable connector from the antenna blades. 

c) Remove the antenna blades from the NAV antenna box. 

d) Disconnect and remove the coaxial cables that were connected to the NAV antenna blades. 

e) Disconnect the remaining coaxial cable connector. 

f) Remove the antenna combiner from the tail boom. 

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I




a) Install the antenna combiner to the tail boom. 

b) Install the antenna blades to the NAV antenna box. 

c) Connect the coaxial cables to the antenna blades and the antenna combiner 

d) Install the cover on the NAV antenna box. 

E. CI-291 COMM Antenna (either antenna) 

The COMM antennas are located on each side of the horizontal stabilizer. 

1) REMOVAL 

a) Remove the screws securing the antenna to the horizontal stabilizer 

b) Lift the antenna from the aircraft. 

c) Disconnect the coaxial cable connector from the antenna. 

d) Remove and discard the antenna gasket 


a) Apply C232 sealant to a new antenna gasket. 

b) Prepare the surface for electrical bonding 

c) Connect the coaxial cable connector to the antenna. 

d) Place the antenna on the horizontal stabilizer and secure. 

Distance Measuring Equipment (DME) 

The DME transceiver is located in the inboard right hand avionics bay. Gain access through the right 

hand avionics bay door. 

A. KN 63 DME 

1) REMOVAL 

a) Disconnect the harness connector and coaxial cable connector from the unit. 

b) Loosen the hold down screw securing the unit to the rack. 

c) Lift the antenna from the aircraft. 

d) Remove the unit from the rack. 


97-00-00 

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a) Place the unit in its mounting rack. 

b) Secure the hold down screw until the unit is secured. 

c) Connect the coaxial cable connector and the harness connector to the unit. 

B. CI-105-6 DME Antenna 

The DME antenna is located on the forward left-hand side of the fuselage. 

1) REMOVAL 

a) Remove the four screws securing the antenna to the aircraft. 

b) Pull the antenna away from the aircraft. 



a) Connect the coaxial cable connector to the antenna. 

b) Secure the antenna to the aircraft. 


A. KMR 675 Marker Beacon Receiver 

The marker beacon receiver is located in the left-hand avionics bay. Gain access through the left hand 

avionics bay door. 

1) REMOVAL 

a) Disconnect the harness connector from the unit 

b) Loosen the hold down screw securing the unit to its rack. 

c) Remove the unit from its rack. 


a) Install the unit into its mounting rack. 

b) Tighten the hold down screw until the unit is secure in its rack. 

c) Connect the harness connector to the unit. 

B. KA 26 Marker Antenna 

The marker beacon antenna is located on the bottom fuselage. 

1) REMOVAL 

a) Remove the access panel from the bottom of the fuselage. 

b) Disconnect the coaxial cable connector from the antenna. 

c) Remove the two nuts securing the antenna. 

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BENDIX/KING@ IFR AVIONICS I KFC 900 



a) Install the antenna onto the aircraft. 

b) Connect the coaxial cable connector to the antenna. 

c) Replace the access panel. 


A. KR 87 ADF Receiver 

1) REMOVAL 


b) Use a 3/32" Allen wrench inserted in the hole in the top (forward) of the ADF. Turn the Allen 

wrench counter clockwise to loosen the locking screw inside the unit. The unit will gradually 

push itself out of its rack. 

c) Slide the unit out of the rack. 



b) Use a 3/32 Allen wrench inserted in the hole in the top (forward) of the ADF. Turn the Allen 

wrench clockwise to tighten the locking screw inside the unit. The unit will gradually draw 

itself into its rack. Continue turning until the unit is secure in the rack, being careful not to 

over tighten the locking screw. 


B. KA 44B ADF Antenna 

The ADF antenna is located on the bottom fuselage. 

1) REMOVAL 

a) Remove the access panel from the bottom of the fuselage. 

b) Disconnect the harness connector from the antenna. 

c) Remove the four screws securing the antenna to the access plate. 

d) Discard the antenna gasket. 


I 

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a) Install the antenna and antenna gasket onto the access plate. 

b) Connect the harness connector to the antenna. 

c) Replace the access panel. 


A. KLN 90B GPS Receiver 

The GPS receiver is located in the top of the center instrument panel. 

1) REMOVAL 

a) Use a 3/32" Allen wrench inserted in the hole in the top right side of the GPS receiver (to the 

right of the ONIOFFIBRT knob). Turn the Allen wrench counter clockwise to loosen the 

locking screw inside the unit. The unit will gradually push itself out of its rack. 

b) Slide the unit out the rack. 



b) Use a 3/32" Allen wrench inserted in the hole in the top right side of the GPS receiver (to the 

right of the ONIOFFIBRT knob). Turn the Allen wrench clockwise to tighten the locking screw 

inside the unit. The unit will gradually draw itself into its rack. Continue turning until the unit is 

secure in the rack, being careful not to over tighten the locking screw. 

B. KA 92 GPS Antenna 

The GPS antenna is located on the center portion of the horizontal stabilizer. 

1) REMOVAL 

a) Remove the screws securing the antenna to the horizontal stabilizer 

b) Lift the antenna from the aircraft. 




b) Place the antenna on the horizontal stabilizer and secure. 

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7. Radar Altimeter 

A. KRA 4051KRA 405B Radar Altimeter 

The radar altimeter is located in the forward nose area. 

1) REMOVAL 

a) Remove the clear panel (or radome if weather radar is installed) from the aircraft. 

b) Disconnect the harness connector and the coaxial cable connectors on the front of the radar 

altimeter. 

c) Loosen the hold down knob securing the unit into its rack 

d) Remove the unit from the mounting rack 



b) Tighten the hold down knob until the unit is secured into its rack. 

c) Connect the harness connector and the coaxial cable connectors to the unit. 

d) Replace the clear panel (or radome) and secure. 

B. KA 54A Antenna 

The transmit and receive radar altimeter antennas are located on the bottom of the fuselage. 

1) REMOVAL (either antenna) 

a) Remove the screws securing the antenna to the aircraft. 


c) Disconnect the coaxial cable connector from the antenna 

d) Discard the antenna gasket. 

2) INSTALLATION (either antenna) 

a) Slide the new antenna gasket over the coaxial cable. 

b) Connect the coaxial cable to the antenna. 

c) Secure the antenna and a new antenna gasket to aircraft. 


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8. Transponder (XPDR) 

A. KT 70 1 KT 71 Transponder 

1) REMOVAL 


b) Use a 3/32" Allen wrench inserted in the hole in the bottom (aft) center of the transponder. 

Turn the Allen wrench counter clockwise to loosen the locking screw inside the unit. The unit 

will gradually push itself out of its rack. 

c) Slide the unit out the rack. 



b) Use a 3/32" Allen wrench inserted in the hole in the bottom (aft) center of the transponder. 

Turn the Allen wrench clockwise to tighten the locking screw inside the unit. The unit will 

gradually draw itself into its rack. Continue turning until the unit is secure in the rack, being 

careful not to over tighten the locking screw. 


B. CI-105-6 XPDR Antenna 

The transponder antenna is located on the forward right hand side of the fuselage. 

1) REMOVAL 

a) Remove the four screws securing the antenna to the aircraft. 





b) Secure the antenna to the aircraft. 

9. Attitude and Heading Reference System WAHRS) 

A. LCR-92s AHRU 

The No. 1 LCR-92s is located in the outboard right hand avionics bay. Gain access through the right 

hand avionics bay door. The No. 2 LCR-92s is located in the outboard left-hand avionics bay (4-Tube 

installations only). 


a) Remove the harness connectors, the fan connector, and the CAL PROM from the unit. 

b) Loosen the hold down securing the unit in its rack. 

c) Remove the unit from its mounting rack 

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BENDIX/KING" IFR AVIONICS I KFC goo 



a) Install the unit into its mounting rack. 

b) Tighten the hold down securing the unit in its rack 

c) Connect the CAL PROM, fan connector and harness connectors to the unit. 

3) BONDING 

a) Check the bonding between the LCR-92s rack and airframe ground. The resistance should 

be 2.5 milli-ohms or less. 

b) If the resistance is too high, remove the rack and clean the mating surface of the rack and the 

shelf. The bare aluminum should be treated with Alodine 1201 or equivalent anti-corrosive 

treatment. 

B. Calibration Prom (either unit) 

Each LCR-92s has a calibration PROM (CAL PROM) connected to it. 


a) Remove the LCR-92s from the aircraft. 

b) Remove the two screws securing the CAL PROM to the mounting rack. 


a) Secure the CAL PROM to the mounting rack. 

b) Install the LCR-92s in the aircraft. 

C. KMT 11 2 Flux Valve 

The flux valves are located in the aft cabin aft of the left generator control unit. Gain access through 

the aft door. The flux valve for the right side AHRS (pilot's side) is located in the right (inboard) 

position of the bracket. The flux valve for the left side AHRS (co-pilot's side, 4-tube only) is located in 

the left (inboard) position of the bracket. 


a) Remove the harness connector from the unit. 

b) Remove the three brass screws securing the unit to the bracket. 

DO NOT USE MAGNETIC SCREWDRIVERS IN THlS AREA. USE A NON-MAGNETIC SCREWDRIVER TO 

REMOVE THE FLUX VALVE MOUNTED SCREWS. 

c) Remove the unit from the bracket. 


a) Set the unit in the mounting bracket. 

b) Secure the unit to the mounting bracket with three brass screws. 

WARNlNG 




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d) Refer to the Installation Checkout Procedures for instructions on aligning the compass 

system. 

10. Digital Air Data System 

A. KDC 481T Adapter Module 

The adapter module is installed inside the air data computer. It must be removed anytime the air data 

computer is replaced or sent to the service center for repair or calibration. The adapter module must 

be installed before installing the loaner or replacement air data computer into the aircraft. Reference 

Figure 401 for the adapter module removal installation drawing. Always perform the 

removal/installation in a static free environment, using the appropriate antistatic processes and tools. 

1) REMOVAL 

a) Place the KDC 481T on an antistatic surface. 

b) Remove the four pan head screws securing the cover to the chassis of the unit. 

c) Remove the cover from the unit. 

d) Slightly loosen the two screws at the left front bottom and left front top of the unit. 

e) Remove the two screws at the left rear bottom and left rear top of the unit. 

f) Swing the PC card assembly away from the unit. 

g) Remove the adapter module. 

Page 41 0 

Revision AD 


I



Figure 401: KDC 481T Adapter Module lnstallationlRemoval 

INSTALLATION 

a) Place the KDC 481T on an antistatic surface. 

b) Remove the four pan head screws securing the cover to the chassis of the unit. 

c) Remove the cover from the unit. 

d) Slightly loosen the two screws at the left front bottom and left front top of the unit. 

e) Remove the two screws at the left rear bottom and left rear top of the unit. 

f) Swing the PC card assembly away from the unit. 

g) Verify the adapter module part number before installation. 

h) Install the adapter module in the designated location (refer to Figure 401). 

i) Swing the PC card assembly back into position. 

j) Install the two screws removed from the left rear bottom and left rear top of the unit. 

k) Tighten the two screws at the left front bottom and left front top of the unit. 

I) Slide the cover over the unit. 

m) Install the four pan head screws securing the cover to the chassis of the unit. 


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BENDIX/IKINGG" IFRAVIONICSI KFC goo 


B. - KDC 481 T Air Data Computer 

The air data computer is mounted in the inboard left-hand avionics bay. Gain access through the left 

hand avionics bay door. 

1) REMOVAL 

a) Remove the pitot and static lines from the front of the KDC 481T. 

b) Remove the harness connector from the front of the KDC 481T. 

c) Loosen the hold down clamps on the forward part of the KDC 481T computer rack. Remove 

the computer. 

d) lnspect the harness for worn, loose, or frayed wires. lnspect the pitot and static lines for 

security and kinks. 


a) Verify the correct module is installed in the KDC 481T before installation. 

b) Reinstall the KDC 481T computer by inserting it in the rack, attaching the hold down clamps 

and tightening them. 

c) The pitot static system must be rechecked at this point. 

3) BONDING 

a) Check the bonding between the KDC 481T rack and airframe ground. The resistance should 




treatment. 

C. KAV 485 AltimeterNSl 

The AltimeterNSI is located directly to the right of the pilot's EFlS displays. 

1) REMOVAL 

a) Remove the four screws in the faceplate. 

b) Slide the unit out of the instrument panel 

c) Remove the harness connector from the back of the unit. 




c) Secure the unit to the instrument panel. 

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5ENDIX/KlNGG" IFRAVIONICS I KFC goo 


D. Temperature Probe 

The temperature probe is located on the center, lower, forward part of the fuselage. 

1) REMOVAL 

a) Remove the six screws securing the temperature probe to the aircraft. 

b) Pull the temperature probe away from the aircraft. 

c) Disconnect the harness connector from the temperature probe. 


a) Connect the harness connector to the temperature probe. 

b) Reinstall the temperature probe using the six screws. 

11. Electronic Flight Instrumentation System (EFIS or EFS) 

A. SG 465 Symbol Generator 

The symbol generator(s) are mounted in the aft cabin. Gain access through the aft door. The No. 1 

SG is mounted on the right hand side of the cabin. In a 4-Tube installation, the No. 2 SG is mounted 

on the left-hand side of the cabin. 

1) REMOVAL 

a) Turn the hold-downs counter clockwise until the unit is out of the connector. 

b) Unlock the hold-downs. 

c) Slide the unit out of its mounting rack. 


a) Slide the unit into its mounting rack. 

b) Lock the hold-downs. 

c) Turn the hold-downs clockwise until the unit is secure. The hold-downs will slip when the unit 

is secure. 

3) BONDING 

a) Check the bonding between the SG 465 rack and airframe ground. The resistance should be 

2.5 milli-ohms or less. 



treatment. 

B. ED 4611462 EHSIIEADI 

The EADl is located in the pilot's instrument panel. The EHSl is located directly below the EADI. The 

copilot's instrument panel will have an EADl and EHSl in a 4-Tube installation. 



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BENDXIKING" IFR AVIONICS I KFC goo 


CAUTION: 

DO NOT USE MAGNETIC TOOLS ON OR NEAR THE ED 461 OR ED 462 EFlS DISPLAY UNITS 

a) Remove the screw in the upper left hand corner of the display. 

b) Use a 3/32" Allen wrench in the screw in the lower right hand corner of the display to unlock 

the unit from its rack. 

c) Slide the display out of the panel. The connector is built into the rack and disconnects as the 

unit is slid back. 


CAUTION: 

DO NOT USE MAGNETIC TOOLS ON OR NEAR THE ED 461 OR ED 462 EFlS DISPLAY UNITS 

a) Slide the unit into the correct position. 

b) Use a 3/32" Allen wrench in the screw in the lower right hand corner of the display to secure 

the unit into its rack. 

c) Secure the screw in the upper left-hand corner of the display. 


A. KCP 520 Flight Control Computer 

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The flight control computer is located in the bay aft of the left avionics bay. Gain access through the 

panel under the left cockpit seat. The flight computer has a cooling fan installed to increase its service 

life. 

1) REMOVAL OF UNIT 

a) Turn the hold-downs counter clockwise until the unit is out of the connector 

b) Unlock the hold-downs. 

c) Slide the unit out of its mounting rack. 

2) REMOVAL OF RACK 

a) Remove the clamps from the harness. 

b) Remove the four screws attaching the rack to the brackets. 

c) Carefully pull the rack out of the bay to gain access to the connector screws. 

d) Remove the six screws holding the backshell to the rack and remove the backshell. 

e) Remove the two screws holding the configuration module to the rack and remove the module. 

f) Remove the four screws holding the connector on the rack and remove the connector. 

3) INSTALLATION OF RACK 

a) Install the connector, configuration module, and backshell using the screws that were 

removed. 

b) Carefully replace the rack onto the brackets in the bay. Make sure the harness and connector 

are not stressed during this operation to prevent damage to the wires and pins. 




c) Install the rack to the brackets using the four screws that were removed 

d) Install the clamps to hold the harness in place 

4) INSTALLATION OF UNIT 

a) Slide the unit into its mounting rack. 

b) Lock the hold-downs. 

c) Turn the hold-downs clockwise until the unit is secure. The hold-downs will slip when the unit 

IS secure. 

5) BONDING 

a) Check the bonding between the KCP 520 rack and airframe ground. The resistance should 




treatment. 

B. KMS 540 Mode Select Panel 

The mode select panel is located in the lower left side of the pilot's instrument panel or in a panel 

attached to the console for 2-Tube Category A installations. 

1) REMOVAL 

a) Unlock the four captive fasteners on the panel (console installation only.) 

b) Remove the four screws securing the unit to the panel. 

c) Slide the unit out of the panel. 

d) Disconnect the harness connector from the unit. 



b) Slide the unit into the panel 

c) Install the four screws securing the unit to the panel. 

d) Position and lock the four captive fasteners on the panel (console installation only.) 

C. KRG 333 Triaxial Rate And Acceleration Sensor 

The KRG 333 is a remote mounted triaxial rate and acceleration sensor. Both sensors are located in 

the roof area of the cabin (at approximately FS 207). Gain access by removing the interior ceiling 

panel. 

CAUTION 

USE EXTREME CARE WHEN HANDLING THE TRlAXlAL RATE AND ACCELERATION SENSORS. 


a) Remove the screws securing the sensor shelf to the roof structure. 

b) Remove the screw holding the ground wires. 


- 

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c) Disconnect the harness connector from the unit. 

d) Remove the screws securing the sensor to the shelf. 


a) Secure the unit to the shelf. 

b) Secure the ground wires to shelf. 


d) Secure the shelf to the roof structure of the aircraft. 

D. KSM 575 Linear Actuator (Lateral Axis) 

The KSM 575 Linear Actuator is located in the cabin roof area (approx. FS 160, RBL 4.) Gain access 

by removing the interior ceiling panel. When centered, this actuator measures 15.82 + 0.03 inches 

between centers of the rod ends. 

WARNING: TO PREVENT STRUCTURAL DAMAGE TO THE ACTUATOR, DO NOT APPLY TORQUE BETWEEN 

OUTPUT ROD AND HOUSING OF ACTUATOR. 

1) REMOVAL 

a) Disconnect the harness connector. 

b) Remove the cable clamp and attaching hardware. 

c) Remove the lower plate and the 16 attaching screws. 

d) Remove the lower portion of the frame at FS 162.0 (See Figure 402). 

e) Remove the lower portion of the frame at BL 0.0 (See Figure 403). 

f) Remove the hardware at each rod-end. 

g) Remove the actuator. 

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NAS6203-2 BOLT 

AN960-10 WASHER 

MS21042-L3 NUT 

2 PLACES 

3 

I I 




3 PLACES 

PIN 047-1 0971 -0002 

NAS6203-2 BOLT NAS6203-2 BOLT ----/ 

AN960-10 WASHER AN960-10 WASHER 



Figure 402: View Looking Aft - FS 162.0 




6 PLACES 

NAS6203-2 BOLT 2 


MS21042-L3 

/ 

PIN 047-1 101 4-0002 



MS21042-L3 

Figure 403: View Looking Right - BL 0.0 


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Revision AD




a) Route the harness and forward end of the actuator through the forward frames to the 

bellcrank. 

b) Position the aft end of the actuator to the aft bellcrank. 

c) lnstall the hardware at each rod-end. 

d) Connect the harness connector (aft position). 

e) Position the harness and cable clamp to allow full movement of actuator. 

f) lnstall the cable clamp and attaching hardware. 

g) Install the lower portion of the frame at FS 162.0 (See Figure 402). 

h) lnstall the lower portion of the frame at BL 0.0 (See Figure 403). 

i) lnstall the lower plate and the 16 attaching screws. 

E. KSM 575 Linear Actuator (Longitudinal Axis) 

The KSM 575 Linear Actuator is located in the cabin roof area (approx. FS 160, RBL 12.) Gain access 

by removing the interior ceiling panel. When centered, this actuator measures 15.80 f 0.03 inches 

between centers of the rod ends. 

WARNING: TO PREVENT STRUCTURIIL DAMAGE TO THE ACTUATOR, DO NOT APPLY TORQUE BETWEEN 

OUTPUT ROD AND HOUSING OF ACTUATOR. 

1) REMOVAL 

a) Disconnect the harness connector. 

b) Remove the cable clamp and attaching hardware. 

c) Remove the lower portion of the frames at FS 167 (Figure 404). 

d) Remove the lower portion of the frames at FS 169 (See Figure 405). 

e) Remove the hardware at each rod-end. 

f) Remove the actuator 

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Revision AD 


I



I 

-- 

#I_ 

2 




9 PLACES 

PIN 047-1 101 3-0003 


. NAS6203-3 



3 PLACES 

PIN 047-1 101 5-0003 




8 PLACES 

\ 



a) Route the harness and forward end of the actuator through the forward frames to the 

bellcrank. 

b) Position the aft end of the actuator to the aft bellcrank. 


97-00-00 

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Revision AD


006-00757-0000 MA1 NTENANCE MANUAL SUPPLEMENT 

c) Install the hardware at each rod-end 

d) Connect the harness connector (forward position.) 

e) Position the harness and cable clamp to allow full movement of actuator. 

f) Install the cable clamp and attaching hardware. 

g) Install the lower portion of the frames at FS 167 (Figure 404). 

h) Install the lower portion of the frames at FS 169 (See Figure 405). 

F. KSA 572 Trim Actuator 

The KSA 572 Trim Actuator is located in the bay under the pilot's seat. It may be necessary to 

remove the longitudinal and lateral trim actuators in order to gain access to the KSA 572 actuator. 

1) REMOVAL 

a) Disconnect the spring cartridge at the bellcrank (aft end). 

b) Unbolt the trim actuator from the floor. 

c) Disconnect the spring cartridge from the trim actuator. 

d) Disconnect the trim actuator connector. 

e) Remove the actuator. 


a) Connect the spring cartridge to the trim actuator. 

b) Mount the actuator to the shelf. 

c) Connect the trim actuator connector. 

d) Connect the spring cartridge to the bellcrank. 

G. Pitch Position Resolver 

The pitch (longitudinal) position resolver is located in bay aft of the left-hand avionics bay. Gain 

access through the panel under the left cockpit seat. 

1) REMOVAL 

a) Disconnect the position resolver connector. 

b) Loosen the screw that connects the resolver arm to the resolver shaft. 

c) Remove the four screws that attach the resolver to the bracket 

d) Remove the resolver. 


a) Mount the resolver to the bracket and secure the four screws with safety wire. 

b) Attach the resolver arm to the resolver shaft and tighten the screw. 

c) Connect the position resolver connector. 

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H. Roll Position Resolver 

BENDIXKING" IFR AVIONICS I KFC goo 


The roll (lateral) position resolver is located in the "broom closet" behind the pilot's seat (FS 155.5). 

Gain access by removing the interior cover panel behind the right cockpit seat. 

1) REMOVAL 



c) Remove the four screws that attach the resolver to the bracket. 






I. Directional Position Resolver 

The directional (yaw) position resolver is located in the pilot's directional pedal bay. 

1) REMOVAL 


b) Remove the cable clamp. 

c) Loosen the screw that connects the resolver arm to the resolver shaft. 

d) Remove the four screws that attach the resolver to the bracket. 

e) Remove the resolver. 





d) Reinstall cable clamp. 

J. Collective Position Resolver 

The collective position resolver is mounted to the right plough beam, below the floor, at the base of the 

broom closet. Gain access through the panel below the right cockpit seat. 

1) REMOVAL 



c) Remove the four screws that attach the resolver to the bracket. 



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a) Mount the resolver to the bracket and secure the four screws with safety wire 

b) Attach the resolver arm to the resolver shaft and tighten the screw 


K. Cable Transducer 

The Cable Transducers (string pots) are mounted to the lateral and longitudinal spring cartridges 

which are in the bay under the pilot's seat. Gain access through the panel under the right cockpit seat. 


a) Disconnect the spring cartridge at each end. 

b) Remove the spring cartridge from the aircraft. 

c) Disconnect cable from eyelet. 

d) Remove the two screws that mount the transducer to the bracket. 

e) Unpin the harness from the terminal block. 

Remove transducer. 


a) Install the harness to the terminal block (A674 TBI). 

b) Mount the transducer to the bracket using the two screws. 

c) Connect the cable to the eyelet. 

d) Install the spring cartridge in the aircraft. 

e) Adjust cable transducer using system diagnostics so that the cable is at center of travel 

L. Directional Spring Cartridge 

The Directional Spring Cartridge is located in the bay under the pilot's seat. Gain access through the 

panel under the right cockpit seat. 

1) REMOVAL 

a) Remove the hardware attaching the KSA 572 to the shelf. 

b) Remove spring cartridge. 


a) Mount the forward end of the spring cartridge to the KSA 572 trim actuator and the aft end to 

the bell crank. 

b) Install the KSA 572 to the shelf using the hardware that was removed 

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M. T-BAR Trim Switching Relay 

The T-Bar trim switching relay is located under the forward console area (FS 115.0). 

1) REMOVAL 

a) To gain access from below, remove the retractable landing light, if installed,. 

b) To gain access from the front, remove the weather radar radome and RIT or the front cover 

and landing lights, if installed. 

c) Remove the harness connector from the relay. 

d) Remove the relay from the mounting plate. 


a) Mount the relay to the mounting plate. 

b) Connect the harness connector to the relay. 

c) Install the units removed to gain access (landing light, weather radar radome, etc.) 

N. LEDEX Trim Switch 

The LEDEX trim switch is located in under the forward console area (FS 115.0) 

1) REMOVAL 

a) To gain access from below, remove the retractable landing light, if installed,. 

b) To gain access from the front, remove the weather radar radome and RIT or the front cover 

and landing lights, if installed. 

c) Remove the harness connector from the switch. 

d) Remove the two bolts attaching the mounting plate. 

e) Remove the switch from the mounting plate. 


a) Mount the switch to the mounting plate. 

b) Connect the harness connector to the switch 

c) Install the two bolts attaching the mounting plate. 

d) Install the units removed to gain access (landing light, weather radar radome, etc.) 

0. APISAS Annunciator Panel 

The APISAS annunciator panel is located in the center instrument panel to the right of the standby 

attitude indicator. 

1) REMOVAL 

a) Remove the four screws securing the annunciator panel to the instrument panel. 

b) The annunciator panel is a rear mount unit. Remove the unit from behind the instrument 

panel. 


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Revision AD



c) Remove the harness connector from the unit. 



b) Position the unit behind the instrument panel and secure it. 

c) lnstall the four screws that secure the annunciator panel to the instrument panel. 

P. Cyclic Trim Switch Assembly 

The cyclic trim switchlflight director sync switch is installed in place of the original cyclic trim switch on 

the pilot's cyclic stick grip. The 4-Tube installations also incorporate the new trim switchlflight director 

sync switch into the copilot's cyclic stick grip. 

1) REMOVAL (either cyclic grip) 

a) Loosen the setscrew at the base of the cyclic grip. 

b) Loosen the grip by turning the mounting ring counter clockwise. 

c) Remove the grip from the cyclic stick. 

d) Remove the screws securing the trim switch, float switch and hook switch to the grip. 

e) Pull the switch assembly away from the grip 

f) Remove the snap ring at the base of the grip that that holds the connector in place. 

g) Pull the connector away from the grip. 

h) Make any necessary repairs. 

2) INSTALLATION (either cyclic grip) 

a) lnstall the connector into the base of the grip 

b) lnstall the snap ring. 

c) Install the switch assembly onto the grip and secure. 

d) Install the grip onto the cyclic stick. 

e) Tighten the mounting ring to secure the grip to the stick. 

f) Tighten the setscrew at the base of the grip. 

13. Weather Radar System 

A. ART 2000 Transceiver 

The weather radar transceiver is located behind the radome. The flat plate antenna must be removed 

whenever the ART 2000 transceiver is replaced or sent in for repair. The flat plate antenna must be 

installed onto the loaner, repaired or replacement transceiver prior to installation. 

1) REMOVAL 

a) Remove the radome from the aircraft 

b) Disconnect the harness connector from the unit. 

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Revision AD 




c) Remove the four screws securing the transceiver to the aircraft. 


a) lnstall the transceiver on the aircraft and secure. 

b) Connect the harness connector to the unit. 

c) lnstall the radome on the aircraft. 

B. Flat Plate Antenna 

The flat plate antenna is attached to the weather radar transceiver. The flat plate antenna must be 

removed whenever the ART 2000 transceiver is replaced or sent in for repair. The flat plate antenna 

must be installed onto the loaner, repaired or replacement transceiver prior to installation. 

1) REMOVAL 

a) Remove the radome from the aircraft. 

b) Remove the six screws securing the flat plate antenna to the transceiver. 


a) lnstall the flat plate antenna onto the transceiver. 

b) lnstall the radome on the aircraft. 

C. CM 2000 Configuration Module 

The configuration module is located just aft and above the weather radar transceiver 

I) REMOVAL 

a) Remove the radome from the aircraft. 


c) Remove the two bolts and nuts securing the configuration module to the aircraft 


a) lnstall and secure the configuration module to the aircraft. 


c) lnstall the radome on the aircraft. 

D. IN-182A Weather Radar Indicator 

The IN-182A indicator is located in the lower left portion of the center instrument panel. 

1) REMOVAL 

a) Remove the side panel from the left side of the console. 

b) Using a 3/32" Allen wrench in the two holes in the bottom corners of the indicator, turn the 

locking screw counter clockwise until the unit slides freely in its mounting rack. 

c) Slide the unit part of the way out of its mounting rack and disconnect the harness connector 

from the indicator. 

d) Slide the unit the rest of the way out of the instrument panel. 


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Revision AD




a) Slide the unit part way into its mounting rack. 

b) Connect the harness connector to the indicator and slide the unit the rest of the way into its 

mounting rack. 

c) Using a 3/32" Allen wrench in the two holes in the bottom corners of the indicator, turn the 

locking screws clockwise. The unit will draw itself into the mounting rack. 

d) Install the side panel from the left side of the console. 

E. KMD 5501850 Multi-Function Display 

The KMD 5501850 MFD is located in the lower left portion of the center instrument panel. 

1) REMOVAL 

a) Using a 3/32" Allen wrench in the hole in the upper right corner of the unit, turn the locking 

screw counter clockwise until the unit is loose in the mounting rack. 

b) Remove the unit from the mounting rack. 


a) Slide the unit into the mounting rack. 

b) Using a 3/32" Allen wrench in the hole in the upper right corner of the unit, turn the locking 

screw clockwise. The unit will draw itself into the mounting rack. 


A. No. 1 KA 33 Cooling Fan 

The No.1 KA 33 cooling fan is located forward of the instrument panel on top of the battery box. This 

fan cools the KLN 90B GPS receiver. 

1) REMOVAL 

a) Remove the hose attached to the fan. 

b) Remove the hardware securing the fan to the battery box. 


d) Remove the fan from the aircraft. 


a) Connect the harness connector to the fan. 

b) lnstall and secure the fan to the battery box. 

c) Connect the hose to the fan. 

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Revision AD 


I

BENDIXIKINGG" IFRAVIONICSI KFC goo 


B. No. 2 KA 33 Cooling Fan 

The No.2 KA 33 cooling fan is located in the right hand avionics bay. Gain access through the right 

hand avionics bay door. This fan cools the NAVICOMM transceivers and the transponder. 

1) REMOVAL 

a) Remove the hoses attached to the fan. 


c) Remove the hardware securing the fan to the brackets 

d) Remove the unit from the aircraft. 


a) lnstall and secure the fan to the battery box. 

b) Connect the harness connector to the fan 

c) Connect the hoses to the fan. 

C. lnstrument Panel Forward Cooling Fan 

The instrument panel forward cooling fan is mounted on the forward side of the pilot's instrument 

panel. The T-panel installations have a fan on the forward side of the copilot's instrument panel also. 

1) REMOVAL (either fan) 

a) Disconnect the harness connector from the fan harness in the bottom of the instrument panel. 

b) Remove the hardware securing the fan doubler to the forward side of the instrument panel. 

c) Remove the hardware securing the fan to the fan doubler. 

2) INSTALLATION (either fan) 

a) lnstall and secure the fan to the fan doubler. 

b) Install and secure the fan doubler to the forward side of the instrument panel. 

c) Connect the harness connector to the fan harness in the bottom of the instrument panel. 

D. lnstrument Panel Lower Cooling Fan 

The instrument panel lower cooling fan is mounted on the bottom of the pilot's instrument panel. The 

T-panel installations have a fan on the bottom of the copilot's instrument panel also. 

1) REMOVAL (either fan) 

a) Disconnect the harness connector from the fan harness in the bottom of the instrument panel. 

b) Remove the hardware securing the fan to the bottom of the instrument panel. 

2) INSTALLATION (either fan) 

a) lnstall and secure the fan to the bottom of the instrument panel. 

b) Connect the harness connector to the fan harness in the bottom of the instrument panel. 


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Revision AD

E. KCP 520 Cooling Fan 



The KCP 520 cooling fan is mounted on the bottom of the KCP 520 mounting rack. Gain access 

through the panel under the left cockpit seat. 

1) REMOVAL 

a) Remove the KCP 520 from its mounting rack 

b) Disconnect the harness connector from the fan harness. 

c) Remove the hardware securing the fan to the KCP 520 mounting rack. 


a) Install and secure the fan to the KCP 520 mounting rack panel. 

b) Connect the harness connector to the fan harness. 

c) Install the KCP 520 into its mounting rack. 

15. Standby Attitude lndicator and Standby Altimeter 

A. Standby Attitude lndicator 

The standby attitude indicator is located in the bottom center of the center instrument panel. 

1) REMOVAL 

a) Remove the hardware securing the indicator to the instrument panel. 

b) Slide the unit out of the instrument panel. 






B. Standby Altimeter 

The standby altimeter indicator is located in the bottom right hand corner of the pilot's instrument 

panel in a 2-Tube "L" standard installation and in ALL Category A installations. The standby altimeter 

in a 4-Tube or 2-Tube "T" standard installation is located in the copilot's instrument panel in the 

standard altimeter location. 

1) REMOVAL 

a) Remove the hardware securing the altimeter to the instrument panel 


c) Disconnect the wiring at the in-line splice. 


a) Connect the wiring at the in-line splice. 

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Revision AD 






d) Perform a static system check in accordance with FAR 91.41 1. 


A. Attitude Indicator 

The attitude indicator is located in the top center of the copilot's instrument panel. 

1) REMOVAL 








B. KI 525A HSI 

The attitude indicator is located in the center of the copilot's instrument panel. 

1) REMOVAL 



c) Disconnect the harness connectors from the unit. 


a) Connect the harness connectors to the unit. 



C. KA 51 B Slaving Accessory 

The slaving accessory is located in the copilot's instrument panel below the airspeed indicator. 

1) REMOVAL 



c) Disconnect the harness connectors from the unit. 


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Revision AD




a) Connect the harness connectors to the unit. 



D. KG 102A Directional Gyro 

The directional gyro is located in the left-hand avionics bay. Gain access through the left avionics bay 

door. 

1) REMOVAL 

a) Disconnect the harness connector from the gyro 

b) Remove the two screws securing the gyro to its mounting rack. 

c) Slide the gyro out of its mounting rack. 


a) Slide the gyro into its mounting rack. 

b) Secure the gyro to its mounting rack being sure that bonding strap is secured under one of 

the screws. 

c) Connect the harness connector to the gyro. 

E. KMT 112 Flux Valve 

The flux valves are located in the aft cabin aft of the left generator control unit. Gain access through 

the aft door. The flux valve for the right side AHRS (pilot's side) is located in the right (inboard) 

position of the bracket. The flux valve for the left side KI 525A (co-pilot's side, mechanical gyro 

package only) is located in the left (inboard) position of the bracket. 


a) Remove the harness connector from the unit. 


WARNlNG 



c) Remove the unit from the bracket. 


a) Set the unit in the mounting bracket. 

b) Secure the unit to the mounting bracket with three brass screws. 




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Revision AD 

EFFECTIVIN: MD900



d) Refer to the Installation Checkout Procedures for instructions on aligning the compass 

system. 


A. SPC-5(B) Inverter 

The inverter is located in the right hand avionics bay. Gain access through the right avionics bay door. 

1) REMOVAL 

a) Remove the No. 1 LCR-92s AHRU from the right hand avionics bay. 


c) Remove the hardware securing the unit to the avionics shelf. 


a) Secure the unit to the avionics shelf. 


c) Install the No. 1 LCR-92s AHRU into the right hand avionics bay. 

18. Accessories 

A. Annunciator Power Supply 

The KA 172 annunciator power supply is located in the top aft section of the left hand avionics bay. 

Gain access through the left avionics bay door. 

1) REMOVAL 

a) Disconnect the harness connectors from the unit. 

b) Remove the hardware securing the unit to the brackets. 


a) Secure the unit to the mounting bracket. 

b) Connect the harness connectors to the unit. 

B. Avionics Switch Panel 

The avionics switch panel is located in the left forward portion of the console. 

1) REMOVAL 

a) Unscrew the captive fasteners (2 places) holding the avionics switch panel in place. 

b) Lift the avionics switch panel until the attached connector is accessible. 

c) Detach connector from the avionics switch panel. 


A) Attach the connector to the panel. 

b) Attach the connector to the avionics switch panel. 


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c) Place the avionics switch panel in position on the console. 

d) Screw the captive fasteners (2 places) on the avionics switch panel. 

19. Category A 

A. Aural Warning Generator 

The aural warning generator is located in the bay aft of the left-hand side avionics bay. Gain access 

through the panel under the left cockpit seat. 

1) REMOVAL 

a) Disconnect the harness connector from the unit. 

b) Remove the hardware securing the unit to the shelf. 



b) Attach the unit to the shelf. 

B. GH-3000 Standby Indicator 

The standby indicator is located below the airspeed indicator on the pilot's instrument panel. 

1) REMOVAL 

a) Loosen the clamp securing the unit to the instrument panel. 


c) Disconnect the harness connector and configuration module from the unit. 


a) Connect the harness connector and configuration module to the unit. 

b) Slide the unit into the instrument panel 

c) Tighten the clamp securing the unit to the instrument panel 

C. ADC-3000 Air Data Computer 

The air data computer is located in the bay aft of the left side avionics bay. Gain access through the 

panel under the left cockpit seat. 

1) REMOVAL 

a) Disconnect the harness connector from the unit. 

b) Disconnect the pitot and static lines from the unit. 

c) Remove the hardware securing the unit to the shelf. 


a) Attach the unit to the shelf. 

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I



c) Connect the pitot and static lines to the unit. 

d) The pitotktatic system must be rechecked 

D. MAG-3000 Magnetometer 

The magnetometer is located in the aft cabin aft of the left generator control unit in the left (inboard) 

position of the bracket. Gain access through the aft door. 

1) REMOVAL 

a) Disconnect the harness connector 


WARNlNG 

DO NOT USE MAGNETIC SCREWDRIVERS IN THIS AREA. USE A NON-MAGNETIC SCREWDRIVER TO 


c) Remove the triangular spacer. 


a) Set the triangular spacer in place on the unit. 

b) Secure the unit to the lower side of the mounting bracket with three brass screws 

c) Connect the harness connector 

20. ELT 

The ELT is located on top of the engine deck, left side, STA 284. Gain access by removing the aft, 

left side cowling. 

1) REMOVAL 

a) Remove the hardware securing the unit to the brackets 

b) Disconnect the end cap and connector from the unit. 


a) Connect the connector and end cap to the unit. 

b) Secure the unit to the brackets with the hardware. 


I 

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I 


BENDIX/K/NG@ IFR AVIONICS I KFC goo 


97-00-00 

Avionics - 

Inspection I Test 

1. General 

This section provides instructions for inspecting and testing each unit of the KFC 900 AFCS and IFR 

avionics package. 

2. VHF Navigation and Communications (NAVICOMM) 

A. NAVICOMM Inspection 

1) Inspect the KX 1651KX 165A transceivers for damage. No damage allowed. 

2) On the horizontal stabilizer, inspect the COMM antennas for damage. No damage allowed. 

3) On the aft tail boom, inspect the VORILOCIGS antennas, combiner and coaxial cables for 

damage. No damage allowed. 

4) In the right hand avionics bay, inspect the VORILOCIGS quadraplexer for damage. No damage 

allowed. 

5) On the pilot instrument panel, inspect the KI 206 indicator for damage. No damage allowed. 

6) In the left-hand avionics bay, inspect the KN 40 for damage. No damage allowed. 

6. COMM Operational Test 

This procedure applies any time a KX 1651KX 165A, COMM antenna and/or antenna coax is repaired 

or removed and replaced. 

1) On the ELECTRICAL MASTER panel, set POWER to the BATIEXT position. 

2) Plug in pilot headset and select the appropriate COMM 1 or 2, as required, and COMM 1 or 2, as 

required, MIC on the audio panel. 

3) Turn on the transceivers 

4) With the transceivers on and warmed up, pull the PULL TEST transceiver function control knob 

out and verify background noise is audible. Adjust volume controls to comfortable level, then 

depress knob. Verify that the background noise ceases. 

5) Select a desired frequency and verify that desired frequency is displayed in the standby position. 

6) Depress the frequency transfer button, Verify that the active and standby frequencies interchange. 

7) Using the left inner knob (PULL 25K), verify that frequency changes in 25kHz steps while tuning. 

8) With transceiver on and warmed up, key and voice modulate transmitter. Verify satisfactory sidetone 

in headsets and verify that transmit indicator illuminates when transmitter is keyed. 

9) Perform testing to determine if there is satisfactory electromagnetic compatibility (EMC) between 

the KLN 90B and all of the communications radios installed on the aircraft. There should be 

adequate isolation from the harmonic interference of VHF communication transceivers (i.e. the 

No. 1 and No. 2 KX 1651165A VHF NAVICOMM transceivers, andlor any other communications 

transceiver installed on the aircraft). 

10) Display the STA 1 page on the KLN 90B and verify valid satellite vehicle (SV) with elevations of 

25" or areater. While monitoring SV signal-to-noise ratio (SNR) values, tune the VHF transmitters 


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to the frequencies listed in Table 601 and key on each frequency for a period of 20 seconds. 

Observe if any SV with an elevation of 25" or areater flags (a flag is indicated with an asterisk, *, 

by the SV number). If no SV with an elevation of 25" or greater flags during any,given 

transmission, the KLN 90B installation is considered interference free. This test must be 

performed with all VHF COMM transceivers that are a part of the installation. 

11) Turn off transceivers. 

Table 601 : VHF Comm Frequencies 

121.150 MHz 1 121.175 MHz 1 121.200 MHz 

131.250 MHz 1 131.275 MHz 1 131.300 MHz 

12) On the ELECTRICAL MASTER panel, set POWER to the OFF position. 

C. NAV Operational Test 

This procedure applies any time a KX 1651KX 165A, VORILOCIGS antenna and/or antenna combiner, 

KN 40, KI 206, VORILOCIGS quadraplexer and/or antenna coax is repaired or removed and replaced. 


2) Plug in pilot headset and select the appropriate NAV 1 or 2, as required, on the audio panel. 

3) Turn on the transceivers. 

4) Select an ILS frequency and verify that desired frequency is displayed in the standby position. 

Use a VOR/LOC/GS ramp generator to generate a signal. 


6) Configure the pilot (and copilot if applicable) EHSl for an ILS 1 or 2, as required, presentation. 

7) Verify the both localizer and glideslope are valid on the EHSl and KI 206 (ILS 1 only). Verify 

proper deviation indication for the ILS using the ramp generator. 

8) With the transceivers on and warmed up, pull the PULL IDENT transceiver function control knob 

out and verify the ident is audible. Adjust volume controls to comfortable level, then depress 

knobs. Verify that the ident ceases. 

9) Turn off transceivers. 


3. Distance Measuring Equipment (DME) 

A. DME Inspection 

1) Inspect the KN 63 DME transceiver for damage. No damage allowed. 

2) On the bottom left hand fuselage, inspect the DME antenna for damage. No damage allowed. 

3) On the AVIONICS SWITCH panel, inspect the DME HOLDIRELEASE switch for damage. No 

damage allowed. 

B. DME Operational Test 

This procedure applies any time a KN 63, DME antenna, KN 40 and/or antenna coax is repaired or 

removed and replaced. 

1) On the ELECTRICAL MASTER panel, set POWER to the BATIEXT position and set AVIONICS 

to the ON position. 

a) Plua in rsilot headset and select the DME on the audio rsanel. 

- 

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5ENDIX/KlNGG" IFRAVIONICS 1 KFC goo 


2) Use a DME ramp generator to generate a signal. 

3) Verify the DME audio in the headsets 

4) Configure the pilot (and copilot if applicable) EHSl for an VORIILS presentation. 

5) Verify the DME distance displayed on the EHSl(s) is consistent with the ramp generator. 

6) On the ELECTRICAL MASTER panel, set AVIONICS to the OFF position and set POWER to the 

OFF position. 


A. Marker Beacon lnspection 

1) lnspect the KMR 675 receiver for damage. No damage allowed 

2) On the bottom center fuselage, inspect the marker antenna for damage. No damage allowed. 

3) On the AVIONICS SWITCH panel, inspect the MRKR TEST switch for damage. No damage 

allowed. 

B. Marker Operational Test 

This procedure applies any time a KMR 675, marker beacon antenna, KN 40 and/or antenna coax is 

repaired or removed and replaced. 



2) Plug in pilot headset and select the MRKR on the audio panel. 

3) Use a ramp generator to generate a signal. 

4) Verify the marker audio in the headsets. 

5) On the AVIONICS SWITCH panel, press the MRKR TEST switch 

6) Verify the marker annunciations appear on the EADl(s). 

7) Using the ramp generator, verify the inner, middle and outer marker reception of the receiver. 

Verify the correct annunciations on the EADl(s). 


OFF position. 


A. ADF lnspection 

1) Inspect the KR 87 receiver for damage. No damage allowed. 

2) On the bottom center fuselage, inspect the KA 44B ADF antenna for damage. No damage 

allowed. 

B. ADF Operational Test 

This procedure applies any time a KR 87, KA 44B ADF antenna and/or antenna coax is repaired or 

removed and replaced. 




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2) Plug in pilot headset and select the ADF on the audio panel. 

3) Turn on the receiver. 

4) Select a desired frequency and verify that desired frequency is displayed in the standby position. 


6) Adjust volume controls to comfortable level. Verify that the audio is present. 

7) Configure the pilot (and copilot if applicable) EHSI for an ADF presentation. 

8) Verify the ADF is valid on the EHSI. Verify proper deviation indication for ADF bearing. 

NOTE: Ground Power Units (GPU) and other obstructions can interfere with ADF reception. It may be 

necessary to test the reception of the ADF while the aircraft is operating. 

9) Press the FLTIET button and verify that the unit returns to one of the timer modes. The radio will 

return to whichever timer mode was active before the FRQ button was pressed in Step A above. If 

the unit has reentered the ET (Elapsed Timer) mode, press the FLTIET button once more to enter 

the FLT (Flight Timer) mode. Turn the unit off and then back on and verify that the flight timer has 

reset to zero. 

10) Press the FLTIET button to enter the ET mode and note that the timer is in the Count Up mode. 

11) Press the RESET button and verify that the timer resets to zero and then continues counting up. 

12) Enter the Count Down mode by pressing and holding the RESET button for approximately 2 

seconds until the ET annunciator on the display begins to flash and then enter any convenient 

time (up to 59 minutes and 59 seconds) with the tuning knobs. The timer will remain in the ET Set 

mode (as indicated by the flashing ET annunciator) for 15 seconds after the time is entered or 

until the RESET FLTIET or FRQ button is pressed. The preset time will remain unchanged until 

the RESET button is pressed, at which time the Elapsed Timer will begin to count down. Verify the 

following conditions: 

The timer counts down to zero and then begins to count up. 

The display flashes for approximately 15 seconds after the counter reaches zero. 

External alarms (if installed) are activated for approximately 1 second after the 

counter reaches zero. 

13) Verify that pressing the FLTIET button exchanges the two timers in the display. Press the FRQ 

button and verify that the standby frequency is displayed in the right hand window of the display 

and that subsequent FRQ button cycles will cause the active and standby frequencies to be 

exchanged. 

14) Place the KR 87 in the ANT mode and tune in several known stations. Verify that audio reception 

is satisfactory and that volume control operation is normal. Verify that the ADF indicator needle is 

parked at the 90" position relative to the nose of that aircraft. Place the unit in the ADF mode and 

verify that the needle points to the station. 

15) Press the BFO button to enter the BFO mode and verify that the BFO tone is present in the 

receiver audio (if a keyed CW station is used, the tone heard will be the coded identifier). 


OFF position. 

C. ADF Quadrantal Error Adjustment 

This procedure applies any time a KA 448 ADF antenna repaired or replaced. 

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The system has been factory adjusted to compensate for the average amount of quadrantal error 

(QE) that exists due to the shape of the airframe. Therefore, little or no QE compensation adjustment 

should be required. Nonetheless, the following procedure should be followed after the installation is 




complete in order to verify proper pointing. In the event that QE adjustment is required, follow the 

procedure outlined below. 



2) Tune in a NDB station or compass locator that gives a strong, clear signal free of fading. It is 

EXTREMELY important to choose a strong NDB. AM Broadcast station will have a greater depth 

of modulation and may result in an unsteady pointer condition. Position the aircraft on the ramp in 

an area that is clear of surrounding buildings such that the indicator points to 0" to the station (i.e., 

the aircraft is heading directly toward the station). Note the aircraft heading. The ADF Bearing 

should be i: 5" of the magnetic heading to the station based on a sectional chart. 

3) Using the aircraft directional gyro or compass, turn the aircraft to the left 45". Note the indicated 

relative bearing and the amount of error. Continue to turn the aircraft, stopping at each 45" point 

and noting the relative bearing error. The errors at the 0°, 90°, 180°, and 270" points should be 

within i: 5". Average the absolute errors at the quadrantal points (45", 135", 225" and 315") to 

determine the amount of QE compensation required. 

4) The QE compensation potentiometer is located to the side of the antenna connector on the KA 

44B antenna. If the antenna is inaccessible from inside the aircraft the antenna will have to be 

unfastened and pulled away from the aircraft far enough to insert a jeweler's screwdriver into the 

adjustment hole. The adjustment hole is protected by a threaded cap, which must first be 

removed. The QE adjustment pot has a sensitivity of approximately 1" per turn. Refer to Figure 

601 to determine which direction to turn the pot. 

NOTE Take care not to misplace the O-ring seal underneath the threaded cap. After QE adjustments 

have been completed, this seal and the threaded cap must be re-installed in the antenna to 

insure that the electronics compartment is environmentally sealed. 

Figure 601: QE Compensation Adjustment 

If the relative bearings at the quadrantal points 

appear as above, turn the Q.E. adjustment pot 

counter-clockwise 

If the relative bearings at the quadrantal points 

appear as above, turn the Q.E. adjustment pot 

clockwise 


OFF position. 


A. GPS Inspection 

1) Inspect the KLN 90B receiver for damage. No damage allowed. 

2) On the horizontal stabilizer, inspect the KA 92 GPS antenna for damage. No damage allowed. 

3) On the pilot instrument panel, inspect the MSGMlPT annunciator for damage. No damage 

allowed. 


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4) On the KLN 90B "dog house", inspect the GPS CRS switch and the GPS APPR switch for 


5) (Four-Tube EFS installations only) On the KLN 90B "dog house", inspect the GPS CRS SEL 

switch for damage. No damage allowed. 

6) (Four-Tube EFS installations only) On the copilot instrument panel, inspect the MSGNVPT 

annunciator for damage. No damage allowed. 

B. GPS Operational Test 

This procedure applies any time a KLN 90B and or the KA 92 GPS antenna andlor antenna coax is 


1) On the ELECTRICAL MASTER panel, set POWER to the BATlEXT position. 

2) Turn unit on and verify proper remote annunciator operation during unit self test sequence. The 

MSG, WPT, ARM, and ACTV annunciations should be illuminated during this test. Manipulate the 

controls until the KLN 90B'is past the initialization pages. Verify all of the annunciators are 

extinguished. If the MSG light comes on, view the message page to verify that there is a 

message. 

3) Manipulate the KLN 90B controls to display the SET Page 1 on the left half of the screen and the 

NAV Page 2 on the right half of the screen. On the SET Page 1 screen, enter the aircraft's 

present position accurate to within 60 nautical miles. Select SET Page 2. Verify that the date and 

time are accurate too within 10 minutes; update if required. 

4) Move the aircraft to a location of acceptable GPS signal coverage (usually outside and away from 

buildings and tall structures that could mask low elevation satellites). Select the STA Page 1, (left 

half of screen). The GPS status should change to ACQ (acquisition) shortly, and within 7.5 

minutes of unit turn on, the KLN 90B should transition to NAV D or NAV status and provide an 

accurate present position based on latitudellongitude coordinates as well as bearing and distance 

from the nearest NAVAID, reference the NAV 2 page on the right half of the screen. (Typical 

time-to-valid times are from 3 to 4 minutes depending on satellite coverage). If the status comes 

up as SRCH (search the sky), the KLN 90B will take up to 20 minutes to calculate a position. 

5) Perform testing to determine if there is satisfactory electromagnetic compatibility (EMC) between 

the KLN 90B and all of the communications radios installed on the aircraft. There should be 

adequate isolation from the harmonic interference of VHF communication transceivers (i.e. the 

No. 1 and No. 2 KX 1651165A VHF NAVICOMM transceivers, and/or any other communications 

transceiver installed on the aircraft). 

6) Display the STA 1 page on the KLN 90B and verify valid satellite vehicle (SV) with elevations of 

25" or areater. While monitoring SV signal-to-noise ratio (SNR) values, tune the VHF transmitters 

to the frequencies listed in Table 602 and key on each frequency for a period of 20 seconds. 

Observe if any SV with an elevation of 25" or areater flags (a flag is indicated with an asterisk, *, 

by the SV number). If no SV with an elevation of 25" or greater flags during any given 

transmission, the KLN 90B installation is considered interference free. This test must be 

performed with all VHF COMM transceivers that are a part of the installation. 

Table 602: VHF Comm Frequencies 

121.150 MHz 121.175 MHz 121.200 MHz 

131.250 MHz 1 131.275 MHz 1 131.300 MHz 1 


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I



7. Radar Altimeter System (RALT) 

A. RALT lnspection 

1) lnspect the KRA 405IKRA 4058 receiver for damage. No damage allowed 

2) On the bottom center fuselage, inspect both of the KA 54A RALT antennas for damage. No 


B. KRA 405 Operational Test 

This procedure applies any time a KRA 405 and/or the KA 54A antennas and/or antenna coax is 




2) Verify that the radar altimeter read out on the EADl is present with no dashes displayed. 

3) Press the RALT TEST button on the CP 470 EFS control panel below the EHSI. 

4) Verify that the radar altimeter readout on the EADl is 50 k5 feet. 


OFF position. 

C. KRA 405B Operational Test 

This procedure applies any time a KRA 405B and/or the KA 54A antennas and/or antenna coax is 




2) Depress the calibration switch SW1 on the front of the KRA 405B for approximately 10 seconds. 

3) Verify that the radar altimeter read out on the EADl is 0 feet. 

4) Press the RALT TEST button on the CP 470 EFS control panel below the EHSI. 

5) Verify that the radar altimeter readout on the EADl is 50 +5 feet. 


OFF position.. 

8. Transponder (XPDR) 

A. XPDR lnspection 

1) lnspect the KT 70IKT 71 transceiver for damage. No damage allowed. 

2) On the bottom right fuselage, inspect the XPDR antenna for damage. No damage allowed. 

3) lnspect the KDC 481T air data computer for damage. No damage allowed. 

B. XPDR Operational Test 

This procedure applies any time a KT 70IKT 71 and/or the XPDR antennas and/or antenna coax is 


On the ELECTRICAL MASTER panel, set POWER to the BATIEXT position. 


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BENDIXKINGG" IFR AVIONICS I KFC goo 


1) Set the function select switch on the XPDR to the STBY position. Allow 1 minute for warm-up. 

2) Set the function select switch to the TST position. 

3) Verify that all of the segments of the altitude window and the IDENT window illuminate for four 

seconds 

4) Verify that there are no fault codes annunciated. The fault codes are as follows 

F01 Squitter Failure (KT 70 only) 

F02 Internal EEPROM Failure 

F03 External EEPROM Failure 

F04 Critical Hardware Failure 

5) If no faults are detected, set the function select switch to the STBY position. 

6) On the ELECTRICAL MASTER panel, set POWER to the OFF position 

C. XPDR Ramp Test 

This procedure applies any time the KT 70lKT 71 is repaired or replaced. This test requires the use of 

Mode S ramp generator for the KT 70. The KT 71 may be tested with a standard ATCRBS ramp 

generator or a Mode S ramp generator. A pitotlstatic system tester is also required. 

1) On the ELECTRICAL MASTER panel, set POWER to the BATlEXT position. 


3) Set the pilot altimeter (KAV 485 ALTNSI) to 29.92 in Hg (1013 MB). 

4) Using the ramp generator, verify the address and the maximum airspeed (KT 70 only). 

5) Using the ramp generator, verify the reply frequency is 1090 +I MHz. 

6) Using the ramp generator and a pitotlstatic system tester, perform an integration check of the 

XPDR and the air data computer. Verify the altitude reporting and the 4096 code. 


D. EEPROM Test 

This procedure applies any time a KT 70lKT 71 EEPROM is repaired or replaced. This test requires 

the use of Mode S ramp generator for the KT 70. The KT 71 does not require a ramp generator 

check 


2) Perform the display adjust as desired. 

a) Set the function select switch on the XPDR to the TST position. 

b) Press the IDT push-button for 5 seconds until dAl appears in the altitude window. 

c) Select the desired display adjustment by pressing the VFR push-button. 

d) Set the desired value in the IDENT window with the far right knob. The dAl adjustment allows 

the photocell response time to be varied from 1 to 8, where 1 is fast and 8 is slow. The 

factory default is 1. The dA2 adjustment allows the display brightness to be varied from 0 to 

64, where 0 is dim and 64 is bright. The factory default is 20. The dA3 adjustment allows for 

the VendorIAge compensation to be varied from 0 to 255, where 0 is dim and 255 is bright. 

The factory default is 0. 

e) Press the IDT push-button or turn the mode select knob to exit the display adjust mode and 

save the new values. 

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3) Perform the aircraft address and maximum airspeed programming (KT 70 only). Skip to 4) for the 

KT 71. 

a) Set the function select switch on the XPDR to the TST position. 

b) Press the VFR push-button for 5 seconds until 0000 appears in the altitude window. 

c) Enter AAAA with the ident code select knobs and press the IDT push-button. If the code is 

incorrect, the unit will return to the test mode. 

d) AA1 will be displayed in the altitude window and the 4 most - significant octal digits of the 

aircraft address will be displayed in the ident window. If un-programmed, the altitude window 

will have zeros. Turn the ident selector knobs to enter the aircraft address. 

e) Depress the VFR push-button to enter the 4 most - significant digits and continue to the least 

significant digits of the aircraft address. 

f) AA2 will be displayed in the altitude window and the 4 least - significant octal digits of the 

aircraft address will be displayed in the ident window. If un-programmed the altitude window 

will have zeros. Turn the ident selector knobs to enter the aircraft address. 

g) Depress the VFR push-button to enter the 4 least - significant digits and continue to the 

maximum airspeed. 

h) The low end of the maximum airspeed range will be displayed in the altitude window and the 

upper range of the maximum airspeed will be displayed in the ident window. If unprogrammed 

the altitude window will have zeros. Turn the rightmost ident selector knob to 

enter the maximum airspeed range of 75 to 150 knots. 

i) Press the VFR push-button to save the maximum airspeed value 

j) When the program mode is exited, the unit will reset as if it was energized. 

k) Move the mode selector knob to the OFF position then back to TST. The altitude window 

shall display AAI and the ident window will display the first 4 octal digits of the aircraft address 

for 2 seconds. The altitude window shall then display AA2 and the ident window will display 

the last four digits of the aircraft address for 2 seconds. The altitude window will then display 

the lower limit of the maximum airspeed range and the ident window will display the upper 

limit of the maximum airspeed range. 

I) Verify that the displays match the programmed values 

m) Press the IDT push-button or turn the mode select knob to exit the display adjust mode and 

save the new values. 

n) Using the ramp generator, verify the address and the maximum airspeed. 


9. Attitude and Heading Reference System (AHRS) 

A. AHRS Inspection 

1) lnspect the LCR-92s AHRU for damage. No damage allowed. 

2) lnspect the AHRS CAL PROM for damage. No damage allowed. 

3) lnspect the KMT 112 flux valve for damage. No damage allowed. 


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4) (Applicable to Four-Tube EFS' installations only) On the AVIONICS SWITCH panel, inspect the 

AHRS 2 CCWICW switch and the AHRS 2 DGISLVD switch for damage. No damage allowed. 

5) (Applicable to Four-Tube EFS installations only) On the KLN 90B "dog house", inspect the AHRS 

select switches for damage. No damage allowed. 

B. AHRS Operational Test 

This procedure applies any time an LCR-92s is repaired andlor replaced. 

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1) On the ELECTRICAL MASTER panel, set POWER to the BATIEXT position 

2) On the EFlS APISAS SWITCH panel, set the RT EFlS switch to the ON position. 

3) (Applicable to Four-Tube EFlS installations only) On the EFlS APISAS SWITCH panel, set the LT 

EFlS switch to the ON position. 

4) Verify that the AHRS completes its alignment procedures and that all attitude and heading flags 

. are cleared on the EADl and EHSI. 

5) Verify the displayed attitude and heading is reasonable with relationship to the aircraft's current 

position (i.e. roll attitude, pitch attitude are reasonable). 

6) (Applicable to the No. 1 LCR-92s only) Verify that the AFCS can pass its pre-flight test sequence. 

7) (Applicable to the No. 1 LCR-92s only) Verify that the Flight Director can be engaged. 

8) (Applicable to the No. 1 LCR-92s only) If the weather radar option is installed on the aircraft, 

perform the radar stabilization procedure. 


EFlS switch to the OFF position. 

10) On the EFlS APISAS SWITCH panel, set the RT EFlS switch to the OFF position. 


MSU and CAL PROM Operational Test 

This procedure applies any time an MSU or CAL PROM is repaired andlor replaced. The flux valve 

calibration procedure must be performed with the aircraft engines running and all normal systems 

powered. This procedure can be performed from any initial heading. 

When a new flux valve is installed, an initial rough alignment may be made followed by the calibration 

procedure. When the procedure has been completed the aircraft should be aligned with a reference 

direction, the flux valve alignment adjusted until the residual index error is removed, and the correct 

heading is indicated. 

During the procedure the aircraft is turned clocks wise to eight different headings approximately 45" 

apart, a + 5" error in spacing is acceptable. These headings are indicated on the appropriate system's 

primary heading indicator. 

The aircraft can be rotated about its vertical axis or taxied in a circle to align with the required 

headings. 

The operator supervises the procedure via the EHSI display. The displayed heading and the heading 

flag are used to reach the 8 headings used and to determine when the next heading change is to be 

made. See the detailed procedure that follows this general description. 

The calibration mode is selected by the MSU CAL MODE switch on the front panel of the LCR-92s 

AHRU being placed in the up (ON) position. The AHRS NORMITEST (located in the RH avionics bay 

behind the LCR-92s AHRU) switch must be moved to the TEST position to disable the airlground 

logic input to the AHRS. Disabling the airlground logic means the aircraft is assumed on the ground. 

If the airlground discrete indicates that the aircraft is on the ground the flux valve calibration mode is 


I



engaged. If the airlground discrete indicates that the aircraft is in the air the MSU CAL MODE switch 

position is ignored and the normal mode of operation. 

The Attitude Warn Flag is displayed throughout the performance of the procedure. 

NOTE If the electrical system, which can only be switched on in the air, must remain off, the heading 

system may exhibit uncompensated errors during flight. A way should be found to switch 

them on without changing the 'On Ground' indication to AHRU. 

As long as a heading change is less than 5" in the calibration mode initial position the displayed 

heading is the input received from the flux valve. This enables manual checks on the input error for 

different headings. 

When the heading change reaches 5" away from the initial procedure heading, the heading relative to 

the initial procedure heading is displayed (i.e. the compass card on the EHSl will slew to the 0" 

heading despite actual heading). This means that headings do not have to be calculated by the 

ground crew, the next required heading is always the 45" * 5" position on the EHSl (moving the 

aircraft in a clockwise rotation). 

In each of the eight positions, including the initial position, the system accepts heading from the flux 

valve. The time required for data collection depends on aircraft movements, caused for example by 

wind. During data collection and the turns between positions, the Heading Warn Flag is displayed. At 

the end of each data collection period, the flag disappears to indicate that the turn to the next heading 

can be started. 

If the flag does not disappear, it indicates that either the heading is outside the k 5" tolerance or data 

has not been correctly collected because of excessive aircraft motion. When this happens, the 

procedure must be started again. 

After data has been collected for each of the eight headings, the system calculates the compensation 

factors and stores this data in the MSU calibration PROM. The MSU calibration PROM is attached to 

the AHRU mounting tray. AHRU replacement does not require a new flux valve calibration. 

The compass card on the EHSl will slew to a heading after the last compensation factors have been 

calculated. This is an indication of the quality of the compensation available. The value indicated is 

the standard deviation of the residual error multiplied by 100. When the calibration was successful the 

heading warn flag is removed from view on this display. 

If the heading warn flag continues to be displayed, the procedure failed. The indicated results are not 

stored in the MSU calibration PROM and the last valid values are retained. If the heading is greater 

than 100" (residual error I") the calibration should be regarded as invalid even if the heading warn flag 

is not displayed and the procedure must be repeated. 

After a successful calibration, the system is returned to the normal mode of operation by placing the 

AHRU switch MSU CAL MODE down to the OFF position and moving the AHRS NORMITEST switch 

back to the NORM position. All warning flags disappear and normal operation is resumed. 

If the MSU CAL MODE is accidentally left in the "ON" position, the attitude warn flag is displayed 

during a ground run. The display of these flags should prevent flight with the switch in this position. 

However, if the aircraft takes off despite the warning, normal operation will be resumed when the 

GroundIAir discrete input indicates 'in air'. On the ground, incorrect headings will be displayed. 





4) Verify that the AHRS completes its alignment procedures and that all attitude and heading flags 

are cleared on the EADl and EHSI. 


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5) The flux valve should be indexed to eliminate as much error as possible. Rotate the flux valve in 

it's mounting plate until the heading is as accurate as possible. 

6) Place the MSU CAL MODE switch on the front of the LCR-92s in the ON position (up). 

7) Place the AHRS NORMITEST switch in the TEST position (down). The switch is located in the 

left-hand aviodcs bay. 

8) Verify that the EADl displays an invalid condition. This condition will be present during the 

remainder of the calibration procedure. 

9) Verify that the heading warn flag is in view on the EHSl 

10) Use Table 603 as a checklist to perform the MSU calibration. 

11) Upon completion of the MSU Calibration procedure, Verify the validity of the heading by checking 

the North, South, East and West cardinal headings as well as the 45" headings. 



13) On the EFlS APISAS SWITCH panel, set the RT EFlS switch to the OFF position 


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Table 603: MSU Calibration Checklist 

CHECKLIST ITEM 

A/C in location with no external magnetic disturbances 

Engines running 

All electrical equipment switched on 

AHRS alignment completed, all flags out of view 

MSU CAL MODE switch switched to "ON" (up) 

... AHRS . - NORMITEST switch switched to "TEST" (down) 

ATT Flag in view 

HDG Flag in view 

Record initial HDG indication: 

HDG Flag disappears 

ARC to 45" lndicated HDG 


HDG flag disappears 

NC to 90" lndicated HDG 









NC to 225 " lndicated HDG 









Record indication of calibration quality (HDG indication on compass): 

MSU CAL MODE switch to "OFF' (down) 

AHRS NORMITEST switch switched to "NORM" (up) 

HDG Flag out of view 

ATT Flag out of view 

10. Digital Air Data System (DADS) 

A. DADS Inspection 

1) Inspect the KDC 481T air data computer for damage. No damage allowed. 

2) lnspect the KAV 485 altimeterNSl for damage No damage allowed. 

3) On the bottom fuselage, inspect the temperature probe for damage. No damage allowed. 

4) (Category A equipped aircraft only) On the pilot instrument panel, inspect the VNE warning 

annunciator for damage. No damage allowed. 


I 

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B. DADS Operational Test 

This procedure applies any time the KDC 481T air data computer, the adapter module, the KAV 485 

altimeterNSI andlor the temperature probe is repaired andlor replaced. 


2) Verify the following. 

a) Upon pressing the BAR0 (PUSH TEST) button, the system will illuminate all the display 

segments for three seconds and drop the flags into view. The illumination of the display 

segments can be extended to 13 seconds by holding the Press-to-Test button in. 

b) The KDC 481T will then engage the Vertical Speed function of the KAV 485. This will cause 

the vertical speed bug to come into view and follow the VS pointer. 

c) The KDC 481T will set the Altitude Select display at 28,000ft and will set the displayed aircraft 

altitude at 26,800ft. The KDC 481T will then start ramping from the aircraft's displayed 

altitude of 26,800ft to the selected altitude of 28,000ft at a 3,500 feet per minute rate of climb. 

d) As the displayed aircraft altitude increases, the altitude alerter gives an audio alert (3 beeps) 

and a steady visual alert at 27,000 feet. The visual alert goes out at 27,700 ft (300ft before 

reaching the selected altitude.) 

e) When the aircraft's displayed altitude reaches the selected altitude of 28,00Oft, the visual alert 

momentarily flashes. There will be a three-second pause, after which the displayed aircraft 

altitude will ramp down to 27,000ft at 3,500 feet per minute rate of descent. At 27,700 feet, 

the altitude alerter gives an audio alert (3 beeps) and a continuously flashing visual alert. The 

flashing visual alert extinguishes at 27,000 feet. 

f) At 27,00Oft, the flags will drop into view and FAIL will also be displayed in the digital altitude 

display window. This is due to a series of invalid signals sent by the KDC 481T. 

g) At the end of the test, all information displayed before the test will be displayed again with the 

exception of the altitude select window. The altitude select window will display the aircraft's 

density altitude for five seconds before reverting back to displaying the selected altitude. 

h) (Category A equipped aircraft only) At the end of the test sequence the aural VNE warning 

will be heard in the headset. The VNE annunciator will illuminate momentarily and then 

extinguish. 

C. Air Data Computer Operational Test 

This procedure applies any time the KDC 481T air data computer is repaired or replaced. This test 

requires the use of Mode S ramp generator for the KT 70. The KT 71 may be tested with a standard 

ATCRBS ramp generator or a Mode S ramp generator. A pitoffstatic tester is also required. 



3) Set the pilot altimeter (KAV 485 ALTNSI) to 29.92 in Hg (1013 MB). 

4) Using the ramp generator and a pitoffstatic system tester, perform an integration check of the 

XPDR and the air data computer. Verify the altitude reporting and the 4096 code. 


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D. TEMPERATURE PROBE 

Gain access to the temperature probe as required. Remove the connector from the temperature 

probe. Check the resistance of the temperature probe at current ambient temperature according to 

Table 604. Replace temperature probe if resistance values are not within the tolerance shown. 

Table 604: Temperature Sensor Values 

11. Electronic Flight Information System (EFIS) 

A. EFIS Inspection 

1) lnspect the SG 465 symbol generator(s) for damage. No damage allowed. 

2) lnspect the ED 461 display unit(s) for damage. No damage allowed. 

3) lnspect the ED 462 display unit(s) for damage. No damage allowed. 

4) lnspect the EADl level assembly (or inclinometer) on the EADl for damage. No damage allowed. 

5) lnspect the CP 470 control panel(s) for damage. No damage allowed. 

B. EFlS Operational Test 

This procedure applies 2-Tube EFS 40 and 4-Tube EFS 40 installations. This procedure must be 

performed any time a ED 461 and/or a ED 462 display unit is repaired or replaced. 


2) On the EFlS APISAS SWITCH panel, set the RT EFlS switch to the ON position 



4) Upon initial application of power to the EFS 40 system a "TEST IN PROGRESS" message will 

appear on the displays. Upon completion of the self-test, a yellow "SELF TEST PASS" message 

will replace the "TEST IN PROGRESS" message. This indicates the EFS 40 system components 

are functioning normally. Sensor flags may appear on the display until they are valid. 


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6) On the EFlS APISAS SWITCH panel, set the RT EFIS switch to the OFF position. 


C. SG 465 Symbol Generator Configuration 

1) This procedure applies any time a SG 465 symbol generator is repaired or replaced. This 

procedure applies 2-Tube EFS 40 and 4-Tube EFS 40 installations. 

a) On the ELECTRICAL MASTER panel, set POWER to the BATlEXT position. 

b) On the EFlS APISAS SWITCH panel, set the RT EFlS switch to the ON position. 

c) (Applicable to Four-Tube EFlS installations only) On the EFlS APISAS SWITCH panel, set 

the LT EFlS switch to the ON position. 

d) Upon completion of the self-test, a yellow "SELF TEST PASS" message will replace the 

"TEST IN PROGRESS" message. A yellow "CHECK CONFIG" message may also appear. 

e) Press the system testlsystem reference TSTIREF button on the appropriate EHSl bezel and 

hold until the system goes into test mode (approximately three to five seconds). Once the test 

is done the system will display the "SELF TEST PASS" message on the EHSI. 

f) Press the HSI and ARC buttons simultaneously. Within 5 seconds, this will display the EFlS 

maintenance title page on the appropriate EHSl 

g) Press the recessed S1 switch on the front of the SG 465. 

h) At the bottom of all maintenance pages, a legend shows how the buttons on the EHSl 

function to select operations that may be performed from the maintenance pages. The 

buttons are as follows: NEXT MENU V (range down); PREVIOUS MENU A (range up); 

NEXT ITEM (#2 bearing pointer); PREVIOUS ITEM t (#I bearing pointer) 

i) Press the NEXT MENU button (range down V). This will advance to the EFlS Maintenance 

Functions menu. 

j) Select COPY RACK 1 & 2 TO SG. The Copy Configuration page will then be displayed. 

k) Press the next menu V button. This will start the copying process. The system will respond 

with a COPYING then a COPY PASS after a few seconds. Wait about 10 more seconds to 

allow enough time for the EADl information to copy. The symbol generator will now have the 

rack configuration data copied from the configuration module. 

I) Press the previous menu A button to return to the Configuration Menu. 

m) Check and verify that the rack data and the SG data are the same by selecting the 

VIEWIEDIT EQUIPMENT CONFIG menu and checking through it. Next, check the 

VIEWIEDIT OPERATING CONFIG menu for any errors. 

n) If no errors are found return to the Configuration Menu. Press the TSTIREF button to return 

the system to the normal displays. 

o) The "CHECK CONFIG" message should not be displayed. 

p) (Applicable to Four-Tube EFlS installations only) On the EFlS APISAS SWITCH panel, set 

the LT EFlS switch to the OFF position. 

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q) On the EFlS APISAS SWITCH panel, set the RT EFlS switch to the OFF position. 

r) On the ELECTRICAL MASTER panel, set POWER to the OFF position 

This procedure applies any time a SG 465 configuration module is repaired or replaced. This 

procedure applies 2-Tube EFS 40 and 4-Tube EFS 40 installations. 

a) On the ELECTRICAL MASTER panel, set POWER to the BATIEXT position. 

b) On the EFlS APISAS SWITCH panel, set the RT EFlS switch to the ON position 




"TEST IN PROGRESS" message. A "CHECK CONFIG" message may also appear. 

e) Press the system testlsystem reference TSTIREF button on the appropriate EHSl bezel and 

hold until the system goes into test mode (approximately three to five seconds). Once the test 

is done the system will display the "SELF TEST PASS" message on the EHSI. 

f) Press the HSI and ARC buttons simultaneously. Within 5 seconds, this will display the EFlS 

maintenance title page on the appropriate EHSl 

g) Press the recessed S1 switch on the front of the SG 465. 

h) At the bottom of all maintenance pages, a legend shows how the buttons on the EHSl 



NEXT ITEM 3 (#2 bearing pointer); PREVIOUS ITEM t (#I bearing pointer) 

i) Press the NEXT MENU button (range down V). This will advance to the EFlS Maintenance 


j) Select COPY SG TO RACK 1 & 2. The Copy Configuration page will then be displayed. 

k) Press the next menu V button. This will start the copying process. The system will respond 


allow enough time for the EADl information to copy. The rack will now have the symbol 

generator configuration data copied to the configuration module. 

I) Press the previous menu A button to return to the Configuration Menu 

m) Check and verify that the rack data and the SG data are the same by selecting the 



n) If no errors are found return to the Configuration Menu. Press the TSTIREF button to return 


o) The "CHECK CONFIG" message should not be displayed 

p) (Applicable to Four-Tube EFlS installations only) On the EFlS APISAS SWITCH panel, set 


q) On the EFlS APISAS SWITCH panel, set the RT EFlS switch to the OFF position 

r) On the ELECTRICAL MASTER panel, set POWER to the OFF position. 


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D. CP 470 Operational Test 

This procedure applies 2-Tube EFS 40 and 4-Tube EFS 40 installations. This procedure must be 

performed any time a CP 470 control panel is repaired or replaced. 

a) On the ELECTRICAL MASTER panel, set POWER to the BATIEXT position and set 

AVIONICS to the ON position. 


c) (Applicable to Four-Tube EFlS installations only) On the EFIS APISAS SWITCH panel, set 


d) Upon completion of the EFlS self-test, press the RALT TEST button of the CP 470. Verify the 

radar altimeter tests. 

e) Adjust the EADl BRT knob and verify the EADl display brightness changes. Clockwise 

rotation increases the brightness and counter-clockwise rotation decreases the brightness. 

f) Adjust the DH set knob by pulling the knob out. Turn the knob clockwise to increment the DH 

value on the EADl and counterclockwise to decrement the DH value. 

g) Push the DH SET knob in. 

h) (Applicable to Four-Tube EFlS installations only) On the EFlS APISAS SWITCH panel, set 


i) On the EFlS APISAS SWITCH panel, set the RT EFlS switch to the OFF position. 

j) On the ELECTRICAL MASTER panel, and set AVIONICS to the OFF position and set 

POWER to the OFF position. 

E. EFlS Configuration Procedure 

This procedure applies 2-Tube EFS 40 and 4-Tube EFS 40 installations. This procedure can be 

performed anytime the EFlS configuration module and the SG 465 configuration data must be reentered. 

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Make sure the EFlS is not in any reversionary modes before starting this procedure. The AHRS 112 

select switches must show green for pilot and copilot (four tube only) and Composite (CMPST) should 

not be selected on either side. 

To configure the EFS 40, the maintenance pages must be accessed. The following procedure will be 

used on all symbol generators. The procedure will require use of the bezel mounted controls on the 

EHSI (ED 461). 

a) On the ELECTRICAL MASTER panel, set POWER to the BATIEXT position. 





"TEST IN PROGRESS" message. A "CHECK CONFIG" message may also appear. 

e) To enter the maintenance pages press the system testlsystem reference TSTIREF button on 

the pilot's EHSl bezel and hold until the system goes into test mode (approximately three to 

five seconds). Once the test is done the system will display the "SELF TEST PASS" message 

on the EHSI. 

1 EFFECTIVITY: MD900 I



Press the HSI and ARC buttons simultaneously. Within 5 seconds, this will display the EFlS 

maintenance title page on the appropriate EHSI. 

At the bottom of all maintenance pages, a legend shows how the buttons on the EHSl 



NEXT ITEM 3 (#2 bearing pointer); PREVIOUS ITEM t (#I bearing pointer) 

Press the NEXT MENU button (range down V). This will advance to the EFlS Maintenance 


- 

Select the SYSTEM CONFIGURATION line. Do this by pressing the next item button (z) to 

move the pointing hand beside the line. Then press the NEXT MENU button V. 

Press the "SI" switch located on the face of the symbol generator being configured. 

The selected line and pointing hand 

become visible and are always highlighted in yellow. 

The configuration menu should now be displayed on the appropriate EHSl 

The configuration tells the EFS 40 symbol generator(s) what sensors are included in the 

system interface. 

The VIEWIEDIT EQUIPMENT menu identifies the different equipment that can be interfaced 

with the EFS 40. Each line will lead into a sub-menu used to select the type of interface 

defined by the equipment interfaced to the EFS 40. The VIEWIEDIT EQUIPMENT menu also 

contains the present value defining the interface used for the equipment. This information is 

contained in the three columns labeled SG, RKI and RK2. The SG column contains the 

interface configuration information contained within the symbol generator. The RKI and RK2 

columns contain interface configuration information contained within the configuration module; 

located on the symbol generator rack. The columns represent nonvolatile memory so when 

power is removed from the system, the configuration information is retained. The symbol 

generator contains one nonvolatile memory unit and the configuration module contains two 

nonvolatile memory units. If the SG column differs from the two RK columns for a given 

parameter then that configuration parameter will appear in red, thus giving one of the possible 

reasons for the CHECK CONFIG message. 

Use the next item 3 and previous item t buttons to move through the ViewIEdit Equipment 

Menu (it has several pages). Configure the equipment using Table 605. 

When done configuring the ViewIEdit Equipment Menu, press the previous menu o button to 

return to the Configuration Menu. 

Select the VIEWIEDIT OPERATION CONFIG line from the Configuration Menu. The 

ViewIEdit Operation menu will now be displayed. 

Configure the operating parameters using Table 606 using the same technique described 

above. 

When finished with the ViewIEdit Operation menu, press the previous menu o button to exit 

back to the Configuration Menu. The configuration must now be saved to the symbol 

generator and racks. 

Select COPY SG TO RACK 1 & 2. The Copy Configuration page will then be displayed 

"PRESS NEXT MENU BUTTON" 

"TO COPY THE CONFIG DATA IN" 

"THE SG TO RACKS 1 AND 2" 


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u) Press the next menu V button. This will start the copying process. The system will respond 


allow enough time for the EADl information to copy. The rack will now have the symbol 

generator configuration data copied to the configuration module. 

v) Press the previous menu A button to return to the Configuration Menu. 

w) Check and verify that the rack data and the SG data are the same by selecting the 



x) If no errors are found return to the Configuration Menu. Press the TSTIREF button to return 


y) (Applicable to Four-Tube EFlS installations only) On the EFlS APISAS SWITCH panel, set 


z) On the EFlS APISAS SWITCH panel, set the RT EFlS switch to the OFF position. 

aa) On the ELECTRICAL MASTER panel, and set AVIONICS to the OFF position and set 

POWER to the OFF position. 

Table 605: EFS 40 Equipment Configuration 

ITEM RH LH DESCRIPTION 

SG NUMBER 0 1 0 = #I EFIS; 1 = #2 EFlS 

SINGLEIDUAL AR AR SEE NOTE 1 

DU TYPE 0 0 ED 461 ED 462 

ATTlTUDElHDG #I 2 2 429AHRS SYSTEM 

ATTITUDEIHDG #2 AR AR SEE NOTE2 

RATE OF TURN 8 8 429 YAW RATE AHRS SYSTEM 

ADF #I 1 1 DC SlNlCOS 

VORIILS #I 2 2 429ANGLE TOVOR 

VORIILS #2 2 2 429ANGLE TOVOR 

DME #I 2 2 KING SERIAL 

FMS #I 5 5 KLN 90 -GPS 

FMS VNAV 0 0 NONE 

RADAR ALT 1 1 KRA 405 (-IOmVIFT) 

AFCS TYPE 3 3 429AFCS SYSTEM 

AFCS COMMAND BAR SCALING 1 1 429 PITCHIROLL COMMANDS 

AFCS MODE ANNUNCIATORS 1 1 KING 429 AUTOPILOT 

RADAR TYPE AR AR SEE NOTE 3 

RADAR INDICATOR AR AR SEE NOTE3 

VARIABLE LNAV 1 1 LNAV 1 VARIABLE, LNAV 2 IS FIXED SCALE FACTOR 

Table 605 EQUIPMENT CONFIGURATION NOTES: 

1. The No. 2 or left hand EFS 40 system is optional. If the second system is not installed, 

configure the SingleIDual selection for single HSIIADI System (2). If the second system is 

installed, configure the SingleIDual selection for Dual HSIIADI System (3). 

2. The No. 2 AHRS system is optional and only installed with the No. 2 EFS 40. Configure for 

none (0) if the second AHRS is not installed. Configure for 429 AHRS (2) system if the 

second AHRS is installed. 

3. The RDR 2000 weather radar system is optional. If a radar is not installed configure Radar 

Type and Radar lndicator as none (0). If the radar is installed and weather display on the 

EHSl is desired, configure the Radar Type for RDS81182lRDR2000 (1) and configure the 

Radar lndicator for BendixIKing (1). If radar display on the EHSl is not desired, configure 

Radar Type and Radar lndicator as none (0). 

4. Configuration items not listed can be configured at the installer's discretion 

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Table 606: EFS 40 Operating Configuration 

.... "-" . -"........ ......... . .. . .. . . . . "." .. . ... ... . .... . . .- . ... 

.- . .-. -- ................. 

!I 

" _. " "" 

ITEM .... . .............................. .......... RH LH DESCRIPTION 

. .- . "" . ... . - ......... . . ................................................................................ -- " . . .- .. . .......... .-................................... 

. 

VERTICAL SCALE SIDE 0 0 RIGHT SIDE OF EADIJEHSI DISPLAY 

DECLUTTER GS ON BC 1 1 YES 

DISPLAY FMS MAP ON A NON-MAP NAV SOURCE 0 0 NO 1 

DISPLAY WIND VECTOR 1 1 YES 

DISPLAY DRIFT 2 2 YES 

I 

DG ONLY MODE AVAILABLE 0 0 NO 

DME DISTANCE ONLY 0 0 NO 

RADAR ONLY MODE 0 0 NO 

SPARE 0 0 SPARE 

MFD NAV CONTROL 0 0 NORMAL NAV SOURCE SEQUENCE 

DISPLAY HEADING TAPE 1 1 YES 

AD1 PLANEICOMMAND BAR AR AR SEE NOTEA. 

ROLL INDICATOR 1 1 SKYPOINTER 

I 

DECLUlTER UNUSUAL ATTITUDE 1 1 YES 

CAT II AVAILABLE 0 0 NO 

PERSPECTIVE LINES 1 1 YES 

DH SELECT I or 2 1 or 2 YES or YES SYNC FROM OTHER SG 

CONTROL PANEL SYNCH 0 0 NO 

SELECTED HEADING SYNCH 0 0 NO 

SELECTED COURSE SYNCH 0 0 NO 

NORTH UP MAP 0 0 NO 

VERTICAL POINTER TYPE 0 0 SMALL DIAMOND 

DISPLAY FMS MESSAGE 1 1 YES 

SELECTED HEADING COLOR 0 0 ORANGE 

COMMAND BAR COLOR 0 0 GREEN 

REVERSIONARY MODE ANNUN 0 0 NONE 

RISING RUNWAY 2 2 RUNWAY AND DBAR 

AD1 DEVIATION SOURCE 0 0 ON-SIDE ILSIMLS 

COMMAND BAR FILTER 2 2 0.2 SECONDS 

DATUM SCALING 0 0 393mVlDEGREE (KING) 

HEADING FAIL ANNUNCIATOR 0 0 NORMAL HEADING FAILURE 

VNAV APPROACH SCALE 0 0 1000 FEET IS FULL SCALE 

LNAV COURSE CONTROL 0 0 ON-SIDE LNAV COURSE CONTROL ONLY 

SG #I SIDE AR AR SEE NOTE B. 

AIRCRAFT SYMBOL 1 1 HELICOPTER SYMBOL 

RADAR SCAN 1 1 100 DEGREES 

RADAR SDI 2 3 2 = INDICATOR #2; 3 = INDICATOR #3 

PITCH OFFSET SYNC DISCRETE 1 1 YES 

ADF POINTER HOLD DISTANCE 0 0 NO 

tj 

Table 606 OPERATING CONFIGURATION NOTES: 

A. The item "ADIIPLANE COMMAND BAR" may be configured for Wedge Planelsingle Cue 

(0) or Dual CueIDual Cue (1). 

B. Configure the RH SG 465 item "SG#I 

SIDE" to be (0) for a 2-tube configuration or (1) for a 

4-tube configuration. Configure the LH SG 465 item "SG#I 

SIDE" to be (1) for a 4-tube 

configuration. 

C. Configuration items not listed can be configured at the installer's discretion. 


A. AFCS Inspection 

1) lnspect the KCP 520 AFCS computer for damage. No damage allowed. 

2) lnspect the KCM 100 external configuration module for damage. No damage allowed. 

3) lnspect the KMS 540 mode select panel for damage. No damage allowed. 


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4) In lower to middle center instrument panel, inspect the AFCS mode annunciator panel for 


5) lnspect the KSA 572 yaw trim motor for damage. No damage allowed. 

6) lnspect the yaw spring cartridge for damage. No damage allowed 

7) lnspect the roll and pitch spring cartridge transducers (string pots) for damage. No damage 

allowed. 

8) lnspect the KSM 575 linear actuators for damage. If the post that protrudes from the actuator 

housing is bent or touching the side of the slotted hole in the bracket, the actuator must be 

replaced. (This is an indication that torque has been applied to the unit and the output rod may be 

structurally damaged.) No damage allowed. 

9) lnspect the KRG 333 triaxial rate and acceleration sensors for damage. No damage allowed 

10) lnspect the roll, pitch, yaw and collective position synchros for damage. No damage allowed. 

11) lnspect the 1 K500,2K500 and 5K500 relays for damage. No damage allowed. 

12) (Applicable to aircraft with the T-Bar trim switching relay only). lnspect the T-Bar trim switching 

relay for damage. No damage allowed. 

13) (Applicable to aircraft with the LEDEX Trim Switch only). lnspect the LEDEX trim switch and relay 

8K500 for damage. No damage allowed. 

14) lnspect the pilot cyclic trim switch assembly for damage. No damage allowed. 

15) lnspect the pilot cyclic grip and copilot grip (if copilot cyclic is installed) AP disconnect switches 

for damage. No damage allowed. 

16) (Applicable to Four-Tube EFlS installations only) lnspect the copilot cyclic trim switch assembly for 


17) (Applicable to Four-Tube EFlS installations only) lnspect the FLT DIR select switch for damage. 

No damage allowed. 

18) lnspect the pilot collective yaw trim switch for damage. No damage allowed. 

19) (Applicable to Four-Tube EFlS installations only) lnspect the copilot yaw trim switch for damage. 

No damage allowed. 

B. AFCS Operational Test 

This procedure applies all installations. This procedure must be performed any time any of the 

following equipment is repaired or replaced. 

KCP 520 AFCS computer 

Either KRG 333 triaxial rate and acceleration sensor 

KMS 540 mode select panel 

KSA 572 yaw trim motor 

Yaw spring cartridge 

Either of the roll and/or spring cartridge transducers (string pots) 

Either of the existing aircraft roll and/or pitch trim motor 

1 K500,2K500 and 5K500 T-BAR relays and/or the LEDEX switch or 8K500 relay 

The pilot cyclic trim switch or AP disconnect switch and copilot (applicable to 4-tube 

installations only) cyclic trim switch or AP disconnect switch 

The pilot collective yaw trim switch and copilot (applicable to 4-tube installations only) yaw trim 

switch 

No testing of the flight director functions is required. The KFC 500 system self-test verifies proper 

functionality of all flight director functions. 

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4) On the EFlS APISAS SWITCH panel, set the APISAS switch to the ON position. 

5) Plug in the pilot headset. 

6) Upon power-up, the FCC will perform an internal check for about 1 second. After completion of 

this test, the FCC will transition automatically to a pre-flight test. During this test, the following will 

occur: 

a) Each linear actuator shall be tested with a minimum drive signal and the brake engaged. 

b) The right vertical fin shall be tested with a minimum drive signal. 

c) The red PITCH and ROLL fail lights will start flashing on the APISAS annunciator panel. 

d) Using the pilot or copilot cyclic trim switch, drive roll trim to the left for one second. The ROLL 

fail annunciation will stop flashing and stay on. 

e) Drive the roll trim to the right for one second. The ROLL fail annunciation should extinguish. 

f) Drive pitch trim forward for one second. The PITCH fail annunciation will stop flashing and 

stay on. 

g) Drive the pitch trim aft for one second. The PITCH fail annunciation should extinguish 

7) On the MSP, press the SAS button. Verify that the SAS light on the MSP and the green "SAS" on 

the annunciator panel are illuminated and a green "SAS" appears on the EADI. Note, in 4-Tube 

installations the cross-side EADl will annunciate AP and SAS mode engagement in yellow, with an 

arrow pointing to the on side. The FLT DIR switch indicates which position has control of the flight 

director (for 4-tube installations.) 

8) Test the AFCS disconnect aural and visual warning. Press the MSP SAS button again to 

disengage the SAS. 

9) A flashing red "SASH should appear in the upper left of the pilot's EADl and a flashing green "SAS" 

should appear on the annunciator panel and the MSP (cross side if applicable.) 

10) A tone should be heard in the headsets and the green SAS on the pilot's EADI, the green SAS on 

the annunciator panel, and the green lamp above the SAS button on the MSP should extinguish. 

A flashing red "SAS" should appear briefly in the upper left of the pilot's EADl and a red "SAS" 

should appear on the annunciator panel. 

11) On the MSP, press the AP button. Verify that the AP light on the MSP and the green "AP" on the 

annunciator panel are illuminated and a green "AP" appears on the EADI. 

12) Test the AFCS disconnect aural and visual warning. Press the MSP AP button again 

13) A flashing red "AP" should appear briefly in the upper left of the pilot's EADl and a flashing green 

"AP" on the annunciator panel. The system will revert to SAS and a green "SAS" annunciation 

should appear on the EADI, annunciator panel and the MSP. 

14) On the MSP, press the "AP" button. Verify that the AP light on the MSP and the green "AP" on the 


15) Move the cyclic stick to right or left a few inches. The green "AP" should change to "SAS" and a 

yellow "DNT" will be annunciated on the EADl to the right of the "SAS. 


Page 623 

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Page 624 

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Move the cyclic stick aft or forward a few inches. The green "AP" should change to "SAS" 

and a yellow "DNT" will be annunciated on the EADl to the right of the "SAS". 

16) Press in on the left or right yaw pedal. The green "AP" should change to "SAS" and a yellow 

"DNT" will be annunciated on the EADl to the right of the "SAS". 

17) On the EFlS APISAS SWITCH panel, set the APISAS switch to the OFF position. 




20) On the ELECTRICAL MASTER panel, and set AVIONICS to the OFF position and set POWER to 

the OFF position. 

AFCS Configuration 

This procedure applies to all installations. The first time the AFCS is turned on in a new installation, or 

whenever the KCM 100 external configuration module, a control position synchro, cable transducer 

(string pot) and/or linear actuator is replaced, the FCC must be configured through an RS 232 

interface. 

The FCC provides an RS 232 interface for diagnostic and installation capabilities. The FCC 

installation and diagnostic software is described later in this section. A step by step instruction for an 

initial configuration is also presented later in this section. 

The RS 232 interface to the flight control computer is through a Remote Terminal Interface (RTI) 

connector located on the right hand side of the cockpit center pedestal. Connect the 

200-05647-0022 diagnostic harness to the pedestal mounted diagnostic connector. Connect the 

AFCS connector to the desired COM port on an IBM compatible computer. 

The RTI will be made using the terminal emulator in the "ACCESSORIES" group of Microsoft 

Windows (version 3.1 or later). Use of other interface mediums is acceptable. The screens do not 

change when using an alternate RTI. 

Double click on the "TERMINAL" icon. Upon entering the terminal emulator, select the "Settings" 

menu item, then select "Communications" menu option. Configure the communications for a 9600 

baud rate, 8 data bits, 1 stop bit, no parity (none), XonIXoff flow control, and the desired COMM port 

(typically COMI). Click on the "OK. 

Select the "Settings" menu item again, and select "Terminal Preferences ..." menu option. Deselect 

the "Use Function, Arrow, and strl Keys for Windows" option at the bottom of the dialogue box. Click 

the "OK". 

It is recommended that the settings that have been entered be saved for future interface to the AFCS. 

The RTI main menu provides the selections for entering diagnostic mode or displaying stored error 

codes. The following paragraphs provide specific instructions on using these capabilities to perform 

the required installation and ground checkout procedures. 

The main menu for the configuration software provides two selections: 1) Enter Diagnostic Mode and 

2) Logged Data. The Diagnostic Mode contains the test and configuration commands for the AFCS. 

The Logged Data contains error codes for the FCC since the last time the error memory was cleared. 

The Diagnostic Mode has six selections: 1) Automated tests, 2) Manual tests, 3) Setup installation, 4) 

Logged data, 5) Software identification and 6) Primitive interface. Automated tests verify operation of 

internal processors and buses in the FCC. Manual tests can be used to verify operation of processors 

internal buses as well as entering various values to the system. Setup installation is used to configure 

the AFCS equipment. Logged data provides access to logged error messages. Software 

identification lists the appropriate software part numbers for the FCC and the MSP. Primitive interface 

is for computer controlled testing. 




Setup installation has two sub-menus: 1) Installation setup for autopilot and 2) Installation setup for 

flight director. 

The autopilot installation setup has nine (9) selections. For an installation, each of the sections must 

be addressed. The selections are: 1) Audio volume, 2) Audio frequency, 3) 3-axis FDIAP, 4) LVDT 

position, 5) Collective position, 6) Pitch Cyclic position, 7) Roll Cyclic position, 8) Pedal position and 9) 

Cyclic string pot positions. 

Flight director setup has one selection, which is the number of EFlS tubes that are installed. 

The FCC compares its configuration data with data stored in the KCM 100 external configuration 

module. The configuration module is mounted on the KCP 520 rack. At power up the KCP 520 

automatically reads the configuration information from the configuration module. Configuration is not 

required if the system has been previously configured and position synchros and linear actuator 

assemblies have not changed. 




3) (Applicable to Four-Tube EFlS installations only) On the EFlS APlSAS SWITCH panel, set the LT 



5) Connect a PC with terminal emulation software via a serial port on the terminal to the diagnostic 

connector located on the right side of the center pedestal in the cockpit. Use the terminal for 

connection and configuration information. The terminal should be properly configured and 

powered. Pull and set the MODE SEL circuit breaker in the aft circuit breaker panel or forward 

side circuit breaker panel. This causes the MSP to perform power-up self-test. 

6) On the EFlS APlSAS SWITCH panel, set the RT EFlS switch to the ON position. Upon power-up, 

the MSP will illuminate all panel switch lights for approximately one second and the system will go 

through its pre-flight test procedure. The RTI main menu should appear. If it does not, press 

"ctrl" and "w" simultaneously. If communication cannot be established, check the RS-232 

interconnect and setup. 

Communication should be established with the FCC. It should be noted that is the same as 

the key. Pressing enter at any time during this procedure when it is not specified to do so 

may abort the configuration procedure and require the procedure to be repeated. 

KCP 520 Flight Computer 

....................... 

D - Enter Diagnostic mode 

L - Logged data 

Press kev for desired oution: 

Press "DM to enter Diagnostic mode. This is the mode for configuring the flight control 

computer. The system will request confirmation by requesting "KCP520" (no quotations) be 

typed. Before pressing enter, push and hold the AFCS DlSC switch and FD SYNC switch 

simultaneously. Wait 5 seconds and press enter. Release the AFCS DlSC and FD SYNC 

switches. 

I 


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BENDIXIKING" IFRAVlONlCS I KFC 900 


System mode: Normal 

KCP 520 Flight Computer 

....................... 

D - Enter Diagnostic mode 

L - Logged data 

Press key for desired option : 

Please confirm your request to enter diagnostic mode 

by entering 'KCP 520' : 

The system will then respond with the following screen: 

The following processor did not respond: 

FD B 

The system will be allowed to enter diagnostic mode. 

Press any key to continue .... 

This response is normal. The system currently has no FD B processor. The Diagnostic menu 

is then displayed. 


Selected processors: AP A, AP B, FD A 


--------------- 

A - Automated tests 

M - Manual Tests 

I - Setup Installation 

L - Logged Data 

S - Software Identification 

P - Primitive Interface 

Press key for desired option ( to exit): 

Type "I" (for Setup Installation) to enter the setup installation sequence for configuration. The 

installation setup menu is then displayed: 

Page 626 

Revision AD 


I




Selected processors: AP A, AP B, FD A 

Installation Setup 

------------------ 

A - Installation setup for autopilot 

F - Installation setup for flight director 


Type " A to enter the installation setup for autopilot. The configuration setup menu is then 

displayed: 



Data value (1 (min) - 8 (max)) : 0 


------------------ 

> Audio volume 

Audio frequency 

3-axis FDIAP 

LVDT position 

Collective position 

Pitch cyclic position 

Roll cyclic position 

Pedal position 

>:selected item 

upldown arrow: prevlnext item; lefWright arrow: prevlnext screen 

EID: increaseldecrease data one-step or begin installation process 

S: save installation data; : exit 

With the ">" next to AUDIO VOLUME, press "EM until "4" displays on the Data entry line. This 

is the level for the volume. 


I 

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Data value (1 (min) - 8 (max)) : 4 


------------------ 

> Audio volume 


3-axis FDIAP 

LVDT position 


Pitch cyclic position . 



Cyclic string pot positions 


upldown arrow: prevlnext item; lewright arrow: prevlnext screen 



Then press the down arrow "J". This enters the selected volume and advances to the next menu 

item. 



Data value (1 - 4 (max)) : 1 


------------------ 

Audio volume 

> Audio frequency 

3-axis FDIAP 

LVDT position 







upldown arrow: prevlnext item; leftlright arrow: prevlnext screen 



With the ">" now pointing to AUDIO FREQUENCY, press "E" until the Data entry line displays "2" (2 KHz.) 

Page 628 

Revision AD 






Data value (1 (min) - 8 (max)): 2 


------------------ 

Audio volume 

>Audio frequency 

3-axis FDIAP 

LVDT position 


Pitch.cyclic position 




>: selected item 


EID: increaseldecrease data one- step or begin installation process 


Press the down arrow "$". This enters the selected frequency and advances to the next menu item. 



Data value (0: SCASIATT; 1 : 3-axis FDIAP) : 1 


Audio volume 


> 3-axis FDIAP 

LVDT position 







upldown arrow: prevlnext item; lefilright arrow: prevlnext screen 



With the ">" now pointing to 3-axis FDIAP, press "E". This toggles between "0" and "1": Select "I", 

3-axis FDIAP. 


Page 629 

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Data value (0: SCASIATT; 1: 3-axis FDIAP) : 1 


------------------ 

Audio volume 


> 3-axis FDIAP 

LVDT position 







upldown arrow: prevlnext item; lefWright arrow: prevlnext screen 



Press the down arrow "4". This advances to the next menu item. 

NOTE The remaining configuration items require that hydraulics be applied to the aircraft. Also, 

collective position must be set to 80% or greater (with reference to the llDS collective position 

display) prior to moving the cyclic. Press the AP and SAS buttons simultaneously on the MSP 

prior to moving the collective. 

Page 630 

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I





pitch stroke length: actual = O.XXXX, expected = 0.1912 to 0.2587: FAIL 

roll stroke length: actual = O.XXXX, expected = 0.3825 to 0.51.75: FAIL 

right fin stroke length: actual = 0.5174, expected = 0.4000 to 0.6000: FAIL 


------------------ 

Audio volume 


3-axis FDIAP 

> LVDT position 







upldown arrow: prevlnext item; left/right arrow: prevlnext screen 



Note that the actual stroke length values shown will be some value stored during manufacturing. 

These values will change after completing this portion of the installation setup. With the ">" now 

pointing to LVDT POSITION, press "EM. This initiates automatic calibration procedure for the linear 

actuator LVDT's and the right vertical fin. Each linear actuator and the right vertical fin should move 

stop to stop in each direction, then center in the following order: pitch, roll then the right vertical fin. 

This enters the LVDT positions and the system should indicate whether this pass or failed with the 

following screen: 


97-00-00 

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Revision AD





pitch stroke length: actual = O.XXXX, expected = 0.1912 to 0.2587: FAIL 

roll stroke length: actual = O.XXXX, expected = 0.3825 to 0.5 1.75: FAIL 

right fm stroke length: actual = O.????, expected = 0.4000 to 0.6000: PASS 


------------------ 

Audio volume 


3-axis FDIAP 

> LVDT position 










Note that the actual stroke length values must be in the expected range to pass. Press the down 

arrow "J" to advance to next menu item. 



expected range = -46.67 to -70.00 

endpoints = XX.XX, XX.XX; actual range = XX.XX: FAIL 


------------------ 

Audio volume 


3-axis FDIAP 

LVDT position 

> Collective position 









Note that the actual range value and endpoint values shown will be some value stored during 

manufacturing. This value will change after completing this portion of the installation setup. With 

the "z" now pointing to COLLECTIVE POSITION, press "E". This initiates the collective position 

Page 632 





synchro calibration. Next, simultaneously press the AP and SAS buttons on the MSP while pulling 

the collective to the full up position. Wait five seconds and press the space bar on the remote 

terminal keyboard. Push collective to the full down position (CAUTION: Do not use excessive 

force). Wait five seconds and press the space bar on the remote terminal keyboard. The following 

screen should appear: 




endpoints = ??.??, ??.??; actual range = ??.??: PASS 


------------------ 

Audio volume 


3-axis FDIAP 

LVDT position 

> Collective position 






upldown arrow: prevlnext item; IefWright arrow: prevlnext screen 

Em: increaseldecrease data one-step or begin installation process 


Note that the actual range value must be in the expected range to pass. Also, the endpoint values 

will be shown for the collective range. Press the down arrow "&" to advance to next menu item. 

Reset the collective to 80% being sure to press the AP and SAS buttons on the MSP while moving 

the collective up. 


97-00-00 

Page 633 

Revision AD








------------------ 

Audio volume 


3 -axis FDIAP 

LVDT position 


> Pitch cyclic position 










the ">" now pointing to Pitch cyclic position, press "EM. This initiates the pitch cyclic position synchro 

calibration. Push the cyclic to the full forward position. Ensure that that the cyclic stick is at its 

furthest point of travel in its circular motion. Wait five seconds and press the space bar on the 

remote terminal keyboard. Pull the cyclic to the full back (aft) position, again, ensure that that the 

cyclic stick is at its furthest point of travel. Wait five seconds and press the space bar on the remote 

terminal keyboard. The following screen should appear: 


Page 634 

Revision AD 97-00-00.








------------------ 

Audio volume 


3-axis FDIAP 

LVDT position 


> Pitch cyclic position 






ED: increaseldecrease data one step or begin installation process 



will be shown for the pitch cyclic range. Press the down arrow "A" to advance to next menu item. 






------------------ 

Audio volume 


3-axis FDIAP 

LVDT position 



> Roll cyclic position 





EiD: increaseldecrease data one-step or begin installation process 




the ">" now pointing to Roll cyclic position, press "En. This initiates the roll cyclic position synchro 


Page 635 

Revision AD



calibration. Push the cyclic to the full right position while also pulling the stick to furthest most aft 

position. Wait five seconds and press the space bar on the remote terminal keyboard. Push the 

cyclic to the full left position while also pulling the stick to furthest most aft position. Wait five 

seconds and press the space bar on the remote terminal keyboard. The following screen should 

appear: 






------------------ 

Audio volume 


3 -axis FDIAP 

LVDT position 



> Roll cyclic position 




upldown arrow: prevlnext item; lefllright arrow: prevlnext screen 




will be shown for the roll cyclic range. Press the down arrow "$" to advance to next menu item. 

Page 636 










------------------ 

Audio volume 


3 -axis FDIAP 

LVDT position 




> Pedal position 




Em: increaseldecrease data one-step or begin installation process 




the ">" now pointing to Pedal position, press "EN. This initiates the pedal position synchro 

calibration. Push the right yaw pedal all the way forward, making sure to push all of the way through 

the spring cartridge. Wait five seconds and press the space bar on the remote terminal keyboard. 

Push the left yaw pedal all the way forward, making sure to push all of the way through the spring 

cartridge. Wait five seconds and press the space bar on the remote terminal keyboard. The 

following screen should appear: 


97-00-00 

Page 637 

Revision AD








------------------ 

Audio volume 


3 -axis FDIAP 

LVDT position 




> Pedal position 



upldown arrow: prevlnext item; 1efWright arrow: prevlnext screen 

ED: increaseldecrease data one-step or begin installation process 


Note that the actual range value must be in the expected range to pass. Also, the endpoint 

values will be shown for the pedal position range. Press the down arrow "J" to advance to 

next menu item. 



pitch ratio: actual = O.????, expected range = 0.4000 to 0.6000 FAIL 

roll ratio: actual = O.????, expected range = 0.4000 to 0.6000 FAIL 

- 

Page 638 

Revision AD 


------------------ 

Audio volume 


3-axis FDIAP 

LVDT position 





> Cyclic string pot positions 



ED: increaseldecrease data one-step or begin installation process 





I

BENDIXKINNG" IFR AVIONICS I KFC goo 


the ">" now pointing to Cyclic string pot positions, press "E". This initiates the cyclic string pot 

positions calibration. Do not apply any pressure to the cyclic stick. The cyclic should be centered 

and there should not be any forces acting against the spring cartridges. Press the space bar on the 

remote terminal keyboard. The following screen should appear: 



Insure the cyclic is in the free center position 

pitch ratio: actual = O.????, expected range = 0.4000 to 0.6000 FAIL 

roll ratio: actual = O.????, expected range = 0.4000 to 0.6000 FAIL 

Press spacebar when ready, any other key to abort 


------------------ 

Audio volume 


3 -axis FDIAP 

LVDT position 










Press the spacebar on the remote terminal keyboard. The following screen should appear: 



String pots installation successful 

pitch ratio: actual = O.XXXX, expected range = 0.4000 to 0.6000 PASS 

roll ratio: actual = O.XXXX, expected range = 0.4000 to 0.6000 PASS 


------------------ 

Audio volume 


3-axis FDIAP 

LVDT position 











97-00-00 

Page 639 

Revision AD



Adjust the actual range values to be between 0.4500 and 0.5500 (Reference Figure 602). 

LONGITUDINAL SPRING 

CARTRIDGE (REF) 

This completes the installation setup. 

Figure 602: String Pot Adjustment 

If at any time a test did not pass or there is some question as to whether to controls were in the 

correct position, re-run the configuration procedure. Otherwise, press "S" to save the configuration. 

The following screen should appear: 

Page 640, 

Revision AD 


I

BENDIXIKlNG@ IFRAVIONICS I KFC goo 




Saving installation data ... 




------------------ 

Audio volume 


3-axis FDIAP 

LVDT position 







upldown arrow: prevlnext item; leWright arrow: prevlnext screen 



Upon a successful save, the following screen should appear: 



Installation data saved OK 




------------------ 

Audio volume 


3-axis FDIAP 

LVDT position 







upldown arrow: prevlnext item; leftfright arrow: prevlnext screen 



At this point, configuration information can be reviewed. Simply cycle through each section of the 

configuration procedure and verify that each states installation is complete. If a review is complete 

or not needed, press enter to obtain the next screen: 


I 

Page 641 

Revision AD




Selected processors: AP A, AP B, FD A, MIA 


------------------ 

A - Installation setup for autopilot 

F - Installation setup for flight director 


Type "F" for flight director setup. The flight director installation setup menu is then displayed: 


Selected processors: FD A 


------------------ 

> EFIS configuration 





Press " E until either "2" or "4" is shown in Data value, whichever is appropriate for the number of 

tubes installed. Press "S" to save the flight director configuration data. The following screen should 

appear: 

Page 642 

Revision AD 


- 

I





Saving installation data ... 

Data value (0 - 5 Tubes): 2 


------------------ 

> EFIS configuration 





Upon a successful save, the following screen should appear: 



Installation data saved OK 

I 


EFIS configuration 





Press three times to return to the main menu. This completes the configuration 

process. 


Page 643 

Revision AD



Page 644 

Revision AD 

7) Plug in the pilot headset 

8) On the EFlS APlSAS SWITCH panel, set the APISAS switch to the OFF position. 

9) On the EFlS APISAS SWITCH panel, set the APlSAS switch to the ON position 

10) Upon power-up, the FCC will perform an internal check for about 1 second. After completion of 

this test, the FCC will transition automatically to a pre-flight test. During this test, the following will 

occur: 

a) Each linear actuator shall be tested with a minimum drive signal and the brake engaged 

b) The right vertical fin shall be tested with a minimum drive signal. 

c) The red PITCH and ROLL fail lights will start flashing on the APISAS annunciator panel. 

d) Using the pilot or copilot cyclic trim switch, drive roll trim to the left for one second. The ROLL 

fail annunciation will stop flashing and stay on. 

e) Drive the roll trim to the right for one second. The ROLL fail annunciation should extinguish. 

f) Drive pitch trim forward for one second. The PITCH fail annunciation will stop flashing and 

stay on. 

g) Drive the pitch trim aft for one second. The PITCH fail annunciation should extinguish 

11) On the MSP, press the SAS button. Verify that the SAS light on the MSP and the green "SAS" on 

the annunciator panel are illuminated and a green "SAS" appears on the EADI. Note, in 4-Tube 

installations the cross-side EADl will annunciate AP and SAS mode engagement in yellow, with an 

arrow pointing to the on side. The FLT DIR switch indicates which position has control of the flight 

director (for 4-tube installations.) 

12) Test the AFCS disconnect aural and visual warning. Press the MSP SAS button again to 

disengage the SAS. 

13) A flashing red "SAS" should appear in the upper left of the pilot's EADl and a flashing green "SAS" 

should appear on the annunciator panel and the MSP (cross side if applicable.) 

14) A tone should be heard in the headsets and the green SAS on the pilot's EADI, the green SAS on 

the annunciator panel, and the green lamp above the SAS button on the MSP should extinguish. 

A flashing red "SAS" should appear briefly in the upper left of the pilot's EADI and a red "SAS" 

should appear on the annunciator panel. 

15) On the MSP, press the AP button. Verify that the AP light on the MSP and the green "AP" on the 


16) Test the AFCS disconnect aural and visual warning. Press the MSP AP button again. 

17) A flashing red "AP" should appear briefly in the upper left of the pilot's EADI and a flashing green 

"AP" on the annunciator panel. The system will revert to SAS and a green "SAS" annunciation 

should appear on the EADI, annunciator panel and the MSP. 

18) On the MSP, press the "AP" button. Verify that the AP light on the MSP and the green "AP" on the 


19) Move the cyclic stick to right or left a few inches. The green "AP" should change to "SAS" and a 

yellow "DNT" will be annunciated on the EADl to the right of the "SAS". 

20) Move the cyclic stick aft or forward a few inches. The green "AP" should change to "SAS" and a 

yellow "DNT" will be annunciated on the EADl to the right of the "SAS". 

21) Press in on the left or right yaw pedal. The green "AP" should change to "SAS" and a yellow 

"DNT" will be annunciated on the EADl to the right of the "SAS". 


BENDIXIKlNG@ IFR AVIONICS I KFC goo 


22) (Category A equipped aircraft only) With the AP still engaged, press the "FD" button on the MSP 

to engage the flight director. Verify that the green "SR" appears on the EADI. Verify that a red 

"LOW AIS" annunciation appears on the annunciator panel. 







13. Weather Radar System (WX) 

This section applies to aircraft installed with IN-182A radar indicator only. Refer to Section 14 for 

radar installations that are interfaced to the KMD 850 MFD. 

A. WX Inspection 

1) lnspect the radome for damage. No damage allowed. 

2) lnspect the ART 2000 receiverltransmitter (RTT) for damage. No damage allowed. 

3) lnspect the flat plate antenna for damage. No damage allowed. 

4) lnspect the CM 2000 configuration module for damage. No damage allowed. 

5) lnspect the IN-182A radar indicator for damage. No damage allowed. 

B. WX Operational Test 

This procedure must be performed any time the ART 2000 or IN-182A is repaired or replaced 

WARNING 

1) On the ELECTRICAL MASTER panel, set POWER to the ON position and set AVIONICS to the 

ON position. 


3) Wait for the No. 1 (or pilot) AHRS to come valid. 

4) On the IN-182A indicator, select the TST position using the function select knob in the upper right 

hand corner. 

WHENEVER THE FUNCTION SWITCH IS IN THE "ON POSITION, RF ENERGY IS BEING 

RADIATED. DO NOT ALLOW PERSONNEL TO STAND WITHIN 15 FEET OF THE AREA BEING 

SCANNED BY THE ANTENNA. TESTS INVOLVING THE RADIATION OF RF ENERGY MUST 

NOT BE MADE IN THE VICINITY OF REFUELING OPERATIONS. ALWAYS USE THE "TEST OR 

"STANDBY' POSITIONS, AS APPLICABLE. 

5) Select the 80NM range on the indicator 

6) Verify the test pattern appears on the indicator approximately 7 to 8 seconds after select TST. 

The test pattern consists of four colored arcs, with green at the bottom, then yellow, red and 

magenta at the top. The pattern should update left to right and right to left sweeps. Observe the 

top of the magenta arc to verify the sweep. The top of the magenta arc will have a slight ripple 

while the antenna sweeps. This indicates the test data is updating. 

Select the OFF position using the function select knob. 


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BENDIXlKING@ IFR AVIONICS I KFC goo 





C. CM 2000 CONFIGURATION MODULE PROGRAMMING 

This procedure must be performed anytime the CM 2000 configuration module is repaired or 

replaced. 

WARNING 

1) Using a KPA 900 configuration module programmer, the KPA 900, software, and operators guide 

are part of the 050-0331 1-0000 kit that can be ordered from Honeywell. Program the module with 

the information from Table 607. 

Table 607: CM 2000 Configuration Parameters 

PARAMETER 

DESIRED ANTENNA SWEEP 

CONNECTOR POS . 

GYRO SOURCE 

ANALOG GYRO TYPE 

ANALOG GYRO COMPENSATION 

MAP GAIN 

EFlS STRUT SWITCH 

TARGET ALERT 

VALUE 

100 DEG 

TOP 

429 DIGITAL 

UNKNOWN 

DO NOT COMPENSATE 

GAIN CHANGE ACCEPTED 

OVERRIDE DISALLOWED 

ENABLED 

2) The configuration module must be installed in the aircraft and connected to the harness to 

complete the remaining procedures. 


ON position. 



6) The following procedures are performed utilizing the "GAIN" knob, "RANGE" buttons, and the 

mode buttons on the radar indicator. 


8) Enter the maintenance mode by performing the following procedure. 

WHENEVER THE FUNCTION SWITCH IS IN THE "ON" POSITION, RF ENERGY IS BEING 

RADIIITED. DO NOT ALLOW PERSONNEL TO STAND WITHIN 15 FEET OF THE AREA BEING 



"STANDBY" POSITIONS, AS APPLICABLE. 

a) Set the radar function selector to TST. Turn the GAlN knob to the minimum level (counterclockwise). 

b) Set the antenna tilt to full up and select the 240NM range. 

c) Simultaneously press the Wx, WxNVxA and VP buttons to display the maintenance menu. 

Reference Figure 603. 

d) Wait at least 15 seconds and then press the range up button to display the "RT 

CALIBRATION DATA page. Reference Figure 604. 

Page 646 



Wx 

VVxA 

ON, 

PROFILE 

UNITS 

VP 

ON/ 

VERTICAL 

PROFILE 

UNITS 



9) Upon the display of the RT Calibration Data Page, with the system in calibration mode, the fault 

fields will flash briefly. No faults should be displayed when the fields stop flashing. This verifies 

the calibration mode is entered. 

10) Adjust the roll trim for 0". 

/'- 

0 

@ BRT 

- 

1 

El 

,'&El 

' 

BENDIX 3 

SELECT TEST 

(- RETURN R/T CALlB 

NAV DATA 

GATE ARRAY TEST 

SWITCHES 

CROSS HATCH 

/iii 

SBY OFF 

rn 

rn 

M 

TO 

DN 

0 

0 

\ PULL STAB OFF J 

Wx 

VVxA 

ON, 

VERTICAL 

PROFILE 

UNITS 

VP 

ON/ 

VERTICAL 

PROFILE 

UNITS 

Figure 603: RDR Maintenance Page 

/$b 

SBY OFF 

f 

BENDIX 

3 

0 

-1 

,.&El 

RT CALIBRATION DATA 

(PRESS Wx TO RETURN) 

GAIN POT %2: 31 .O- FAULTS: 

PITCH ANGLE: 0.OU 400 REF 

TILT SETTING: 0.OU GYRO 

ROLL ANGLE: O.OR H.V. 

ROLL TRIM: O.OR AFC 

400 HZ REF: O.O+ AGC 

AZIMUTH COUNT: +45 XMITTER 

ANTENNA ELEVATION: 

ELV 

L = 0.OU C = 0.OU R = O.OU 

piFJ 

TO 

DN 

0 

0 

\ PULL STAB OFF / 

Figure 604: RT Calibration Data Page 


97-00-00 

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11) Perform the pitch-offset procedure as follows. 

a) Adjust the GAlN knob for a "GAIN POT %2" setting between -10.5 and -12.5. A 06 should be 

displayed in the "AZIMUTH COUNT field. 

b) Check that the tilt table is set for 0" of pitch attitude. 

c) Adjust the "TILT SETTING" between 5 and 10 UP to increment the "PITCH ANGLE" field to 

0.0" +l.OO (adjusting the "TILT SETTING" between 5 and 10 DOWN will decrement the 

numbers.) Upon reaching 0.0" +I .OO, quickly adjust the "TILT SETTING" to above 10 to lock 

in the setting. Leave the "TILT SETTING" above 10. 

d) Set the tilt table for 10" pitch up attitude. The "PITCH ANGLE" value on the indicator should 

be 10.OU +I .OO. If the value is out of range, repeat the first three steps of this procedure. 

e) Set the tilt table for 10" pitch down attitude. The "PITCH ANGLE" value on the indicator 

should be 10.OD +I .OO. If the value is out of range, repeat the first three steps of this 

procedure: 

f) Set the tilt table to 0.0" of pitch attitude. The "PITCH ANGLE" value on the indicator should 

be 0.0 +I .OO. 

12) Perform the roll-offset procedure as follows. 


displayed in the "AZIMUTH COUNT field. 

b) Check that the tilt table is set for 0" of roll attitude. 

c) Adjust the "TILT SETTING" between 5 and 10 UP to increment the "ROLL ANGLE" field to 

0.0" +I .OO(adjusting the "TILT SETTING" between 5 and 10 DOWN will decrement the 

numbers.) Upon reaching 0.0" +l.OO, quickly adjust the "TILT SETTING" to above 10 to lock 

in the setting. Leave the "TILT SETTING" above 10. 

d) Set the tilt table for 10" roll right attitude. The "ROLL ANGLE" value on the indicator should 

be 10.OR +I .OO. If the value is out of range, repeat the first three steps of this procedure. 

e) Set the tilt table for 10" roll left attitude. The "ROLL ANGLE" value on the indicator should be 

10.OL +I .OO. If the value is out of range, repeat the first three steps of this procedure. 

f) Set the tilt table to 0.0" of roll attitude. The "ROLL ANGLE" value on the indicator should be 

0.0 +I .oO. 

13) Save the offset configuration data as follows. 


displayed in the "AZIMUTH COUNT" field. 

b) Set the "TILT SETTING" to 15.OD. The fault fields will flash indicating that the save procedure 

is beginning. If the save procedure is successful, the "GYRO" fault will disappear and the 

"AZIMUTH COUNT" will step. 

c) If the "GYRO" field remains unchanged, set the "TILT" to 0" and repeat the second step of this 

procedure. 

14) Select the OFF position on the IN-182A using the function select knob. 


OFF position. 

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14. Weather Radar System (WX) 

This section applies to aircraft installed with KMD 850 MFD only. Refer to Section 13 for radar 

installations that are interfaced to the IN-182A radar indicator. 

A. WX Inspection 

1) lnspect the radome for damage. No damage allowed. 

2) lnspect the ART 2000 receiverltransmitter (RIT) for damage. No damage allowed. 

3) lnspect the flat plate antenna for damage. No damage allowed. 

4) lnspect the CM 2000 configuration module for damage. No damage allowed. 

5) lnspect the KMD 540 MFD for damage. No damage allowed. 

B. WX Operational Test 

This procedure must be performed any time the ART 2000 R/T or the KAC 501 weather radar module 

is repaired or replaced. 


ON position. 

Note 



4) On the KMD 850 MFD, select the WX function select button to display the "WX page. 

5) Select the TST position using the function select knob in the lower right hand corner of the MFD. 

Upon application of power to the MFD, the weather radar will always be set to the "SBY" 

(standby) mode. This is done to preclude "accidentallyJJ leaving the weather radar on. The 

weather radar will also be put into the "SBY" mode when GPS ground speed (as received from 

the external GPS receiver) transitions below 30 KTS. 

WARNING 

WHENEVER THE FUNCTION SWITCH IS IN THE "ON" POSITIONl RF ENERGY IS BEING 

RADIATED. DO NOT ALLOW PERSONNEL TO STAND WITHIN 15 FEET OF THE AREA BEING 



"STANDBY' POSITIONS, AS APPLICABLE. 

6) Select the 80NM range on the MFD. 

7) Verify the test pattern appears on the indicator approximately 7 to 8 seconds after select TST. 

The test pattern consists of four colored arcs, with green at the bottom, then yellow, red and 

magenta at the top. The pattern should update left to right and right to left sweeps. Observe the 

top of the magenta arc to verify the sweep. The top of the magenta arc will have a slight ripple 

while the antenna sweeps. This indicates the test data is updating. 

8) Select the OFF position using the function select knob on the MFD. 


10) .On the ELECTRICAL MASTER panel, and set AVIONICS to the OFF position and set POWER 

to the OFF position. 


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C. CM 2000 CONFIGURATION MODULE PROGRAMMING 

This procedure must be performed anytime the CM 2000 configuration module is repaired or 

replaced. 

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Revision AD 

1) Using a KPA 900 configuration module programmer, the KPA 900, software, and operators guide 

are part of the 050-0331 1-0000 kit that can be ordered from Honeywell. Program the module with 

the information from Table 608. 

Table 608: CM 2000 Configuration Parameters 

PARAMETER 

DESIRED ANTENNA SWEEP 

CONNECTOR POS 

GYRO SOURCE 

ANALOG GYRO TYPE 

ANALOG GYRO COMPENSATION 

MAP GAIN 

EFlS STRUT-SWITCH 

TARGET ALERT 

2) The configuration module must be installed in the aircraft and connected to the harness to 

complete the remaining procedures. 


ON position. 



VALUE 

100 DEG 

TOP 

429 DIGITAL 

UNKNOWN 

DO NOT COMPENSATE 

GAIN CHANGE ACCEPTED 

OVERRIDE DISALLOWED 

ENABLED 

6) On the EFlS APlSAS SWITCH panel, set the RT EFlS switch to the OFF position. 

7) Enter the maintenance mode by performing the following procedure. 

a) Press the WX function select key until the weather radar page is displayed. 

b) Rotate the outer knob to place the radar into the test state. 

c) Set the range to 240NM. 

d) Set the tilt to 15 degrees up using the joystick. 

e) Set the gain to minimum using the inner knob. 

f) Press the AUX function select key to enter the "Auxiliary mode cover page". 

g) Press the power key next to the WX SETUP soft label. 

h) Rotate the inner knob counter-clockwise to obtain the minimum gain setting 

i) Press the power key next to the of the WX CALlB soft label to enter the "Radar configuration 

password page". 

j) Press the power key next to the 3 soft label four (4) times to enter the maintenance password 

"3 3 3 3". Upon entering the last "3", the "Wx Configuration Page (Calibration Enabled)" page 

will be displayed 

k) Upon display of the "Wx Configuration Page (Calibration Enabled)" page, the "FAULT" fields 

will illuminate briefly and then extinguish. No faults should be displayed. This verifies that the 

calibration mode is entered. 

I) Rotate the "GAIN" knob to obtain a value of -26.5 to -28 in the "GAIN" field. This will initiate 

the antenna clearance scan. The antenna will move to each of the extreme positions to 




determine that there is no interference with antenna movement and all scan motors are 

working properly. 

m) Do not exit the "Wx Configuration Page (Calibration Enabled)" page 

8) Perform the pitch-offset procedure as follows. 

a) Adjust the GAlN knob for a GAlN setting between -10.5 and -12.5. "06" should be in the 

AZIMUTH ANGLE field. 

b) Check that the tilt table is set for 0" pitch. 

c) Adjust the TlLT SETTING between 5" and 10" UP to increment the PITCH ANGLE field to 

0.0" + 1 .OO (adjusting the TlLT SETTING between 5" and 10" DOWN will decrement the 

numbers). Upon reaching 0" + 1 .OO, quickly adjust the TlLT SETTING to above 10" to lock in 

the setting. 

d) Set the tilt table to 10" pitch up. The PITCH ANGLE field value should be 10.0" UP + 1.0". 

e) Set the tilt table to 10" pitch down. The PITCH ANGLE field value should be 10.0" DOWN + 

1 .oO. 

f) Set the tilt table to 0" pitch. The PITCH ANGLE field value should be 0.0" + 1 .OO 

9) Perform the roll-offset procedure as follows. 

a) Adjust the GAlN knob for a GAlN setting between -7.0 and -9.0. "07" should be displayed in 

the AZIMUTH ANGLE field. 

b) Check that the tilt table is set for 0" roll. 

c) Adjust the TlLT SETTING between 5" and 10" UP to increment the ROLL ANGLE field to 

10.0" k 1 .OO (adjusting the TlLT SETTING between 5" and 10" DOWN will decrement the 

numbers). Upon reaching 0" + l.OO, quickly adjust the TlLT SETTING to above 10" to lock in 

the setting. 

d) Set the tilt table to 10" roll right. The value should be 10.0" R + 1 .OO 

e) Set the tilt table to 10" roll left. The value should be 10.0" L + 1 .OO. 

f) Set the tilt table to 0" roll. The value should be 0.0" + 1 .OO 

10) Save the offset configuration data as follows. 

a) Adjust the GAlN knob for a GAlN setting between -3.5 and -5.5. "08" should be displayed in 

the AZIMUTH ANGLE field. 

b) Set the TlLT SETTING to 15.0" DOWN. The fault fields will flash indicating the save 

procedure is beginning. If the save procedure is successful, the GYRO fault will disappear 

and the azimuth angle will step. 

c) If the GYRO fault remains unchanged, Set the TlLT SETTING to 0" and repeat Step 2. 


OFF position. 

MFD Configuration Operational Test 

These procedures must be performed any time the KMD 540 is repaired or replaced. 

1) KMD 540 Configuration Procedure 


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a) On the ELECTRICAL MASTER panel, set POWER to the ON position and set AVIONICS to 

the ON position. 

b) Turn the MFD on using the OFFION knob in the lower left-hand corner. 

c) Set the BRT knob in upper left-hand corner to maximum 

d) The BENDIXIKlNg logo will appear on the display and the function indicators and power key 

labels will light up briefly. 

e) A self-test page will appear indicating the status of the unit. Acknowledge this page by 

pressing the power key next to the "OK soft label. 

f) A warning page will then be presented. Acknowledge this page in the same manner as noted 

above. 

g) The "TOPO ON MAP" page will appear. If the GPS navigation source is not valid, the "NO 

EXTERNAL GPS" message will appear on the screen. It is.recommended, but not required, 

that the GPS receiver be navigating at this time so that the interface to the MFD can be 

validated. 

h) Press the MAP function select button to select the "TOPO OFF MAP" page. The topographic 

data will be decluttered. 

i) Pressing the AUX function select button displays the "Auxiliary mode cover page" as shown in 

Figure 605. The "Auxiliary mode cover page" allows the user to enter the setup pages for 

configuring the KMD 540 and any installed modules (i.e. the KAC 501 weather radar module 

and the KAC 501 traffic module). 

Note: The figures depicting the KMD 540 Display may not always resemble the actual display. 

Unless otherwise noted, the figures are shown for reference purposes only. 

Figure 605: Auxiliary Mode Cover Page 

Page 652 





Figure 606: System Configuration Password Page 

j) Press the power key next to the "SYSTEM CONFIG." soft label. The system maintenance 

password page is displayed as shown in Figure 605. Press the power key next to the "3" soft 

label to enter the password "3 3 3 3". Upon entering the last "3", the "System Configuration 

Page" will be displayed as shown in Figure 607. 

Figure 607: System Maintenance Page 

k) Press the Power Key next to the "SYSTEM SETUP" Soft Label to display the "System setup 

cover page." As shown in Figure 608. 


I 

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BENDIX/KING" IFRAVIONICS I KFC goo 


Figure 608: System Setup Cover Page 

I) Press the power key next to the "LIGHT CURVE" soft label to setup the display lighting, 

indicator lighting and the back lighting for the MFD. The fist page to appear is the "Display 

Lighting Curve" page, which controls the display brightness, reference Figure 609. This page 

provides three power key options. "PREV PAGE" returns to the "System Configuration Page", 

"RESET CURVE" (reset to default) and "NEXT (go to the next page). If a setting other than 

the default is desired, the joystick control may be used to manually adjust the setting. Moving 

the joystick left and right selects the position on the brightness control axis. Move the joystick 

up and down changes the brightness level for the selected data point. The vertical green line 

on the display represents the current position of the brightness knob. When the display is 

adjusted as desired, select "NEXT to continue or "PREV PAGE" to return. 

Note: The lighting curves shown in Figure 609, Figure 6010 and Figure 611 are examples of the 

curves used for the certification in the MDHl MD900. 

Figure 609: Display Lighting Curve 

m) The "NEXT page will be the "Indicator Lighting Curve" page, reference Figure 6010, which 

controls the brightness of the green "Function Indicator" lighting. All indicators will be lit during 

Page 654 





the adjustment. Functions are the same as with the "Display Lighting Curve" page. Adjust 

the display accordingly and press the "NEXT" power key. 

Figure 6010: Indicator Lighting Curve 

n) The "NEXT" page, reference Figure 61 1, will be the "Backlighting Curve" page, which controls 

the lighting bus level for the keys (buttons) and the front bezel. The functions are the same as 

on the "Display Lighting Curve" page except for the additional "LBUS VOLT." function. 

Pressing the power key next to the "LBUS VOLT." soft label toggles the back lighting option 

between 28VDC, 14VDC, 5VDC and 5VAC. The 28V page is shown in Figure 61 1. Adjust 

the display accordingly. The vertical green line represents the current aircraft panel lighting 

dimmer control position. Pressing "NEXT" will loop back through the lighting options. If all of 

the lighting functions are adjusted as desired, press "PREV PAGE" to return to the "System 

Maintenance page". 

Figure 611: Back Lighting Curve 

o) Pressing "NEXT" will loop back through the lighting options. After setting the lighting curves to 

the desired levels, press "PREV PAGE" to return to the "System Configuration Page". 


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KMD 540 Map Setup 

a) Press the AUX function select button on the unit. This will display the "Auxiliary mode cover 

page". If the "External Video" page appears, press the AUX key a second time. The "Auxiliary 

mode cover page" provides setup pages including the Map. 

b) Press the power key next to the "MAP SETUP" soft label to enter MAP Setup. A page similar 

to Figure 612 will appear. This is "Map Setup page (I)". There are a total of four pages of 

map setup options, reference Figure 612, Figure 613, Figure 614 and Figure 61 5. On any of 

the four pages, use the joystick to change the settings as desired. Use the "RESET VALUES' 

power key to set values to the defaults. Use the "NEXT" power key to cycle between the 

pages. When finished, use the "SAVE & EXIT power key to save changes and return to the 

"Auxiliary mode cover page". 

Figure 612: Map Setup Page 1 


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c) On the ELECTRICAL MASTER panel, set AVIONICS to the OFF position and set POWER to 


3) KMD 540 DATA I10 setup 

a) Press the Power Key next to the "DATA 110" Soft Label to enter the "Data I10 page" shown in 

Figure 616. This page allows the user to enableldisable the Stormscope interface and 

configure the heading input and navigation input. Use the joystick to disable the Stormscope 

input (if it is enabled). Note that the Stormscope interface is not part of this STC. The 

installing agency must approve this interface if it is desired. 


I 

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BENDIXIKINNG" IFRAVIONICS 1 KFC goo 


Figure 616: Data 110 Page 

b) Press the Power Key next to the "HDG SRCS" Soft Label to display the "Heading Monitor 

page.", as shown in Figure 617. 

Figure 617: Heading Monitor Page 

c) Verify that the heading value in the "FMSIHDG:" field display is consistent with the heading on 

the pilot's EHSI. The KLN 90B must be turned on and must have passed self-test prior to 

receiving valid heading to the KMD 540. 

d) Press the Power Key next to the "PREV PAGE" Soft Label to return to the "Data I10 page" 

(Figure 61 8). 

e) Press the Power Key next to the "NAV SOURCE" Soft Label to display the "Nav source setup 

page." as shown in Figure 618. 

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Revision AD 


I

5ENDIX/KlNGG" IFRAVIONICS I KFC goo 


Figure 618: NAV Source Setup Page 

f) Use the joystick to select the "POSITION SOURCE" field. Change the "SETTING" field to 

"ARINC 429. 

g) The "RS232 TYPE" field can be ignored. 

h) Use the joystick to move to the "ARINC 429 BUS SPEED" field. Change the "SETTING" field 

to "LOW. 

i) Press the Power Key next to the "PREV PAGE" Soft Label to return to the "Data I10 page." 

(Figure 607). 


This section applies to all installations. 

A. Inspection 

lnspect the KCP 520 AFCS computer cooling fan for damage. No damage allowed. 

lnspect the No. 1 SG 465 symbol generator cooling fan for damage. No damage allowed. 

(Applicable to Four-Tube EFlS installations only) lnspect the No. 2 SG 465 symbol generator 

cooling fan for damage. No damage allowed. 

lnspect the KA 33 cooling fan in the right-hand avionics bay for damage. No damage allowed. 

lnspect the KA 33 cooling fan forward of the instrument panel for damage. No damage allowed. 

lnspect the cooling fan on the right hand forward instrument panel for damage. No damage 

allowed. 

lnspect the cooling fan on the right hand underside instrument panel for damage. No damage 

allowed. 

(Applicable to Four-Tube EFlS installations only) lnspect the cooling fan on the left hand forward 

instrument panel for damage. No damage allowed. 

(Applicable to Four-Tube EFlS installations only) lnspect the cooling fan on the left hand 

underside instrument panel for damage. No damage allowed. 


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BENDIX/KINGG" IFRAVlONlCSI KFC 900 


10) (Not applicable to all installations, only aircraft with Mod 1 harness assemblies)lnspect relay 

4K500 for damage. No damage allowed. 

11) lnspect relay 6K500 for damage. No damage allowed. 

12) (Applicable to Four-Tube EFlS installations only) lnspect relay 7K500 for damage. No damage 

allowed. 



B. Avionics Cooling Fan Operation 

This procedure must be performed any time a cooling fan is repaired or replaced 


ON position. 




4) lnspect replaced or repaired fan(s) for operation. 

5) On the AVIONICS SWITCH panel, press ANNUN TEST button to test the annunciators. Verify 

the yellow FAN annunciator illuminates on the AFCS mode annunciator panel (all other dead-face 

annunciators will also illuminate). 





OFF position. 

16. Standby Attitude Gyro 


A. Inspection 

1) lnspect the standby attitude gyro for damage. No damage allowed. 

B. Standby Attitude Operation 

This procedure must be performed any time standby attitude gyro is repaired or replaced. 

Page 660 

Revision AD 


ON position. 

2) On the EFlS APlSAS SWITCH panel, set the RT EFlS switch to the ON position. 

3) Allow approximately thirty seconds for the AHRS system to come valid and approximately one to 

three minutes for the standby attitude gyro to "spin up". 

4) Verify the attitude flag on the standby attitude gyro is out of view or "pulled" 

5) Make any necessary adjustment to the pitch attitude reference standby attitude gyro as required 

(symbolic airplane). 

Verify that the standby attitude gyro is in agreement with the AHRS presentation on the 

EADI with respect to pitch and roll attitude. 


I

BENDIXJKING" IFRAVIONICS 1 KFC goo 




OFF position. 


This section only applies to installations that have the copilot attitude gyro and KCS 55A compass 

system installed. 

A. Inspection 

1) lnspect the copilot attitude gyro for damage. No damage allowed 

2) lnspect the KI 525A pictorial navigation indicator (or HIS) for damage. No damage allowed. 

3) lnspect the KA 51 B slaving accessory in for damage. No damage allowed. 

4) lnspect the KG 102A directional gyro located in the left-hand avionics bay for damage. No 


5) lnspect the KMT 112 flux valve for damage. No damage allowed. 

B. Mechanical Gyro System Operation 

1) This procedure only applies to installations that have the copilot attitude gyro and KCS 55A 

compass system installed. This procedure must be performed any time the copilot attitude gyro is 

repaired or replaced. 




c) Allow approximately thirty seconds for the AHRS system to come valid and approximately one 

to three minutes for the copilot attitude gyro to "spin up". 

d) Verify the attitude flag on the copilot attitude gyro is out of view or "pulled". 

e) Make any necessary adjustment to the pitch attitude reference on the copilot attitude gyro as 

required (symbolic airplane). 

f) Verify that the copilot attitude gyro is in agreement with the AHRS presentation on the EADl 

with respect to pitch and roll attitude. 

g) On the EFlS APISAS SWITCH panel, set the RT EFlS switch to the OFF position. 

h) On the ELECTRICAL MASTER panel, set AVIONICS to the OFF position and set POWER to 



compass system installed. This procedure must be performed any time the KI 525A HSI or the 

KG 102A directional gyro is repaired or replaced. 



b) On the EFlS APISAS SWITCH panel, set the RT EFlS switch to the ON position 

c) Allow approximately thirty seconds for the AHRS system to come valid and approximately one 

to three minutes for the copilot compass system to "spin up". 


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d) Verify the heading flag on the KI 525A HSI is out of view or "pulled" 

e) Verify that the heading on the KI 525A HSI is in agreement with the pilot's EHSI. 

f) Tune NAV 2 to a local ILS frequency or use a ramp generator to establish a valid ILS signal 

g) Select the ILS 2 presentation on the pilot's EHSl 

h) Verify that the KI 525A HSI and the pilots EHSl are in agreement with respect to D-Bar 

presentation (not that both course pointers should be set to the same course). 

i) On the EFIS APlSAS SWITCH panel, set the RT EFIS switch to the OFF position. 

j) On the ELECTRICAL MASTER panel, set AVIONICS to the OFF position and set POWER to 



compass system installed. This procedure must be performed any time the KA 518 slaving 

accessory or the KMT 112 flux valve is repaired or replaced. 

a) Perform the KMT 112 alignment procedure as follows. 

i) On the ELECTRICAL MASTER panel, set POWER to the ON position and set 

AVIONICS to the ON position. 

ii) With the complete KCS 55A system operating and synchronized, position the 

aircraft on a compass rose, magnetic North heading. 

iii) Place the KA 51 B in the "Free Gyro" mode and center the slave meter with the + 

toggle switch. For best results, remove the two mounting screws that secure the 

unit to the panel and slide the unit out until the meter test jacks and compensator 

potentiometers are accessible. 

iv) Connect a digital milli-volt meter to the unit test jacks (common connection of the 

milli-volt meter to the black test jack of the KA 51 B and positive connection of the 

milli-volt meter to the red test jack of the KA 51 B. 

v) Record the algebraic error between the compass rose and the heading on the KI 

525A. Repeat procedure on East, South and West magnetic heading. 

vi) Add the algebraic errors and divide by four to obtain the index error 

vii) Loosen the mounting screws on the KMT 112 and rotate the unit an amount 

equal to the index error to cancel out the index error. Re-tighten the mounting 

screws. This procedure may need to be repeated after the NIS and E/W 

compensators have been adjusted (see following paragraphs). 

b) The KMT 112 alignment must be completed prior to starting the KA 51 B alignment procedure. 

c) With the complete KCS 55A compass system operating and the KA 51 B in the "Free Gyro" 

mode, position the aircraft on a compass rose. Adjust the compensation as follows. 

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I



i) Place the aircraft on a magnetic North heading and center the compass card 

North under the lubber line with the CWICCW switch. Place a non-magnetic 

blade screwdriver in the NIS potentiometer in the KA 51 B Slaving Accessory and 

zero the external milli-volt meter (0.OVDC + 50mV). 

ii) Place the aircraft on magnetic East heading and center the compass card East 

under the lubber line with the CWICCW switch. Place a non-magnetic blade 

screwdriver in the E/W potentiometer in the KA 51 B Slaving Accessory and zero 

the external milli-volt meter (0.OVDC + 50mV). 

iii) Place the aircraft on a magnetic South heading and center the compass card 

South under the lubber line with the CWICCW switch. Place a non-magnetic 

blade screwdriver in the NIS potentiometer in the KA 51 B Slaving Accessory and 

adjust the external milli-volt meter for 112 of the existing milli-volt meter readout. 

iv) Place the aircraft on a magnetic West heading and center the compass card 

West under the lubber line with the CWICCW switch. Place a non-magnetic 

blade screwdriver in the E N potentiometer in the KA 51B Slaving Accessory 

and adjust the external milli-volt meter for 112 of the existing milli-volt meter 

readout. 

v) As a final check of the KCS 55A compass system, position the aircraft on the 

compass rose and turn to each of the four cardinal headings while the KCS 55A 

system is in the Slaved Gyro mode. All readings should be within + 2" of those 

on the compass rose. Verify that the compass system matches the whiskey 

compass at 12 points (every 30"). The KA 51B can now be secured back into 

the instrument panel. The alignment is complete. 

d) On the ELECTRICAL MASTER panel, set AVIONICS to the OFF position and set POWER to 




A. Inspection 

1) In the right-hand avionics bay, inspect the SPC-5B inverter for damage. No damage allowed. 

2) In the left-hand avionics bay, inspect relay 3K500 for damage. No damage allowed. 



B. AC Power System Operation 

Perform this procedure any time the SPCdB inverter or the 3K500 relay is repaired or replaced. 

1) On the ELECTRICAL MASTER panel, set POWER to the ON position. 

2) Verify the yellow INV annunciation of the AFCS mode annunciator panel is extinguished. 


Page 663 

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3) On the AVIONICS SWITCH panel, press the ANNUN TEST button to test the annunciators. 

Verify the yellow INV annunciator illuminates on the AFCS mode annunciator panel (all other 

dead-face annunciators will also illuminate). 

4) In the Electrical Load Center, verify (with a voltmeter) that the bus bar on across circuit breakers 

CB71 and CB72 has 26VAC. 

5) On the ELECTRICAL MASTER panel, set POWER to the OFF position 

19. Avionics Accessories 


A. Inspection 

1) In the left-hand avionics bay (located on the left plough beam), inspect the KA 172 annunciator 

power supply for damage. No damage allowed. 

2) Inspect the avionics switch panel for damage. No damage allowed. 

B. Avionics Accessories Operation 

Perform this procedure any time the KA 172 annunciator power supply is repaired replaced. 

1) On the ELECTRICAL MASTER panel, set POWER to the ON position. 


Verify that the AFCS mode annunciator panel and all of the dead-face annunciators in Table 609 

illuminate. Note that the annunciators with visible white legends identified in Table 610 will not 

illuminate in the ANNUN BRIGHT mode. The bright mode is the default when power is initially 

applied to the aircraft systems. 

Table 609: Dead-Face Annunciator Colors 

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3) Replace any bulbs. that do not illuminate. 


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BENDIXIKINNG IFRAVIONICS 1 KFC goo 


4) On the AVIONICS SWITCH panel, select the ANNUN DIM mode. Note that the switch is a threeposition 

toggle switch. The normal position is in the center. Selection of BRIGHT or DIM is 

accomplished by moving the switch to the desired mode, then letting it return to center. 


6) Verify that all of the AFCS mode annunciator panel, the dead-face annunciators listed in Table 

609, and all of the visible annunciator legends listed in Table 610 are illuminated. It may be 

necessary to drape the cockpit with tarps or blankets in order to darken it enough to observe the 

visible white legends. 

7) Replace any bulbs. that do not illuminate. 

Table 610: Visible White Annunciator Legends 

VISIBLE WHITE ANNUNCIATORS 

Pilot CMPST switch 

GPS CRS switch 

GPS APPR switch 

GPS CRS SEL switch 

Pilot AHRS select switch 

Copilot AHRS select switch 

FLT DIR select switch 

Copilot CMPST switch 

APPLICABILTY 

All 

All 

All 

4-Tube .Only 

4-Tube Only 

4-Tube Only 

4-Tube Only 

4-Tube Only 


C. Avionics Switch Panel Operation 

Perform this procedure any time the avionics switch panel is repaired or replaced. 


ON position. 





5) On the pilot's EHSI, select VOR 1 

6) Tune the No. 1 VHF NAV to a desired frequency. Use a VORILOCIGS ramp generator to 

generate a signal. 

7) Use a DME ramp generator to establish a valid distance to station 

8) On the AVIONICS SWITCH panel, select the DME HOLD mode. Note that the switch is a threeposition 

toggle switch. . The normal position is in the center. Selection of HOLD or RELEASE is 

accomplished by moving the switch to the desired mode, then letting it return to center. The 

normal position is in the center. Verify that the DME hold annunciation appears on the pilot's 

EHSI. 

9) Select the DME RELEASE mode. Verify that the DME hold annunciation extinguishes. 

10) On the AVIONICS SWITCH panel, press the MRKR TEST button to test the marker beacon 

receiver. Verify that the marker beacon annunciation on the EADl(s) appear. 

On the AVIONICS SWITCH panel, press the APISAS TEST button initiate the AFCS selftest. 

Verify that the AFCS starts the self-test. 


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Verify that the AFCS mode annunciator panel and all of the dead-face annunciators The bright 

mode is the default when power is initially applied to the aircraft systems. 

12) On the AVIONICS SWITCH panel, select the ANNUN DIM mode. Note that the switch is a threeposition 

toggle switch. The normal position is in the center. Selection of BRIGHT or DIM is 

accomplished by moving the switch to the desired mode, then letting it return to center. Verify that 

all of the annunciators illuminate (in the dimmed state). 

13) On the AVIONICS SWITCH panel, select the AHRS 1 DG mode. Verify that the yellow FHDG 

annunciation appears on the pilot's EHSI. 

14) On the AVIONICS SWITCH panel, select the AHRS 1 SLVD mode. Verify that the yellow FHDG 

annunciation extinguishes on the pilot's EHSI. 

15) On the AVIONICS SWITCH panel, select the AHRS 1 CCW mode. Verify that the compass card 

on the pilot's EHSI moves in the counter clockwise direction. 

16) On the AVIONICS SWITCH panel, select the AHRS 1 CW mode. Verify that the compass card on 

the pilot's EHSI moves in the clockwise direction. 

17) (Applicable to Four-Tube EFlS installations only) On the AVIONICS SWITCH panel, select the 

AHRS 2 DG mode. Verify that the yellow FHDG annunciation appears on the copilot's EHSI. 


AHRS 2 SLVD mode. Verify that the yellow FHDG annunciation extinguishes on the copilot's 

EHSI. 


AHRS 2 CCW mode. Verify that the compass card on the copilot's EHSI moves in the counter 

clockwise direction. 


AHRS 2 CW mode. Verify that the compass card on the copilot's EHSI moves in the clockwise 

direction. 






OFF position. 

20. lnstrument and Console Lighting 


A. lnstrument and Console Lighting Operation 

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ON position. 





5) On the LIGHTING CONTROL panel, set LT MSTER to the ON position. 




6) On the LIGHTING CONTROL panel, adjust the INST lighting knob to the maximum brightness 

position (clockwise rotation). Verify that all of the instrument lighting to the individual units. 

7) On the LIGHTING CONTROL panel, adjust the CONSOLE lighting knob to the maximum 

brightness position (clockwise rotation). Verify that all of the console lighting to the individual 

units. 

8) On the LIGHTING CONTROL panel, set LT MSTER to the OFF position. 



10) On the EFlS APISAS SWITCH panel, set the APISAS switch to the OFF position 



OFF position. 

21. Aural Warning Generator 

This section applies to Category A installations only. 

A. Inspection 

1) Inspect the Model 630 aural warning unit for damage. No damage allowed 

B. Aural Warning Unit Operation 

Perform this procedure any time the Model 630 aural warning unit is repaired or replaced. 


ON position. 


3) On the EFlS APISAS SWITCH panel, set the APlSAS switch to the ON position. Complete the 

APISAS self-test. 



5) Plug in pilot headsets. 

6) Engage the autopilot using the AP button on the KMS 540 mode select panel. 

7) Press the pilot's AP DlSC switch to disconnect the autopilot. Verify the AP DlSC tone in the pilot's 

headsets. 

8) Push the PUSH-TEST button on the KAV 485 ALTNSI. At the end of the test sequence, verify 

that the altitude alert tone and the VNE warning tone is heard in the pilot headsets. 

9) Press the RALT TST button on the pilot's CP 470 EFlS control panel. Verify the DH tone is heard 

in the pilot's headsets. 



11) On the EFlS APISAS SWITCH panel, set the APISAS switch to the OFF position. Complete the 

APISAS self-test. 



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BENDXlKIN6" IFRAVIONICS I KFC goo 



OFF position. 

22. Electronic Standby Instrument System (ESIS) 

This section applies to Two-Tube Category A installations only. 

A. Inspection 

1) lnspect the GH-3000 indicator for damage. No damage allowed. 

2) lnspect the DCM-3000 detachable configuration module for damage. No damage allowed. 

3) lnspect the ADC-3000 air data computer for damage. No damage allowed. 

4) lnspect the MAG-3000 magnetometer for damage. No damage allowed. 

B. ESIS Operation 

1) GH-3000 Indicator Operation 

Perform this procedure whenever the GH-3000 indicator or the DCM-3000 detachable 

configuration module is repaired or replaced. 

a) On the ELECTRICAL MASTER panel, set POWER to the ON position. 

b) Allow the GH-3000 indicator to complete its Built-in-Test (BIT) sequence. Normal display will 

be viewed within approximately three minutes. The display should reflect the attitude of the 

aircraft as it rests on the ramp. 

c) Loosen the indicator mounting screws but do not remove the unit from the instrument panel. 

d) Observe that indicator is functioning properly. Carefully extract the unit from the instrument 

panel. Using a gravity oriented protractor, digital protractor or equivalent device, compare the 

angles displayed on the GH-3000 to the actual angles. Tolerance should be +4.0° in the pitch 

and roll axes. 

e) Reinstall the indicator into the instrument panel. 

f) On the EFlS APISAS SWITCH panel, set the RT EFlS switch to the OFF position. 

g) On the ELECTRICAL MASTER panel, set POWER to the OFF position. 

NOTE: Pitch is referenced to the configured aircraft instrument panel angle of 15". 

2) ADC-3000 Air Data Computer Operation. 

Perform this procedure whenever the ADC-3000 air data computer is repaired or replaced 

a) On the ELECTRICAL MASTER panel, set POWER to the ON position. 

b) Allow the GH-3000 indicator to complete its Built-in-Test (BIT) sequence. Normal display will 

be viewed within approximately three minutes. The display should reflect the attitude of the 

aircraft as it rests on the ramp. 

c) Set the barometric knob on the GH-3000 indicator to standard (29.92 in. Hg). 

d) Using an air data test set, adjust pitot and static pressures to provide a vertical velocity of 

between 1,000 and 3,000 feet per minute. Observe that the indicator altitude tape moves 

smoothly and properly displays altitude. 

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BENDXIKING" IFRAVIONICS I KFC goo 


e) Stop the air data test set at 10,000 ft, 15,000 ft and 20,000 ft. Compare values displayed on 

the GH-3000 to the test set at 10,000 ft (k20 feet), 15,000 ft (k25 feet) and 20,000 ft (+30 

feet). 

f) Use the air data test set to provide an adequate increasing (higheripositive) airspeed rate of 

change to observe airspeed tape operation. 

g) To verify VNE operation of the GH-3000, use the air data test set to provide an airspeed 

greater than VNE (>I40 kts.) Observe the indicator change to a red color on the air speed 

tape and window value. Note: The VNE annunciator(s) and audio alert are connected to the 

KAD 480T Air Data System only and are not operated by the GH-3000 system. 

h) Using the air data test set, adjust the pressures to provide a descending vertical velocity 

between 1,000 and 3,000 feet per minute to ambient pressure. Observe that the indicator 

altitude tape moves smoothly and properly displays altitude in the window. 

i) Adjust the air data test set pressures to provide a decreasing airspeed rate of change to 

observe the airspeed tape operation. Observe that the indicator airspeed tape moves 

smoothly and properly displays airspeed in the window. 

j) Release pitot and static pressure and disconnect the air data test set from the aircraft. 

Observe that the indicator display has returned to field altitude at current barometric setting 

with no airspeed indicated. 

k) On the ELECTRICAL MASTER panel, set POWER to the OFF position. 

MAGNETOMETER CALIBRATION 

This procedure must be performed whenever the MAG-3000 magnetometer or the DCM-3000 

detachable configuration module is repaired or replaced. 

The following equipment is required for the calibration of the magnetometer. It is the installer's 

responsibility to obtain the test equipment from Goodrich Avionics Systems. The equipment 

should be calibrated and in good working order. 

MAG-3000 Calibration Panel 

Model: JT-147A 

Part No: 570-8552-01 

Magnetometer Attitude Transmitter 

Model: MAT-3000A 

Part No: 501-1846-01 

The MAG-3000 aircraft calibration procedures are to be performed on the ground with the aid of a 

compass rose. The MAG-3000 aircraft calibration must be performed in a similar ambient 

magnetic field on the ground as will exist when the aircraft is in flight, i.e. aircraft engines should 

be running and all avionics equipment should be powered. Avoid being near anything that may 

alter the magnetic field around the MAG-3000. 

To "Fast Erect the GH-300OU, momentarily press the "M" (menu) button on the front of the GH- 

3000, select the FAST ERECT option from the pop-up menu that appears on the display, then 

momentarily press the BAR0 knob. 

Unless otherwise specified, all references to "switches" and "buttons" used in this section refer to 

the JT-147A MAG-3000 calibration panel. 

a) Attitude Compensation procedure. This compensation will not affect the GH-3000 computed 

pitch display. Attitude differences between the GH-3000 and MAG-3000 will be compensated 

for automatically in the following steps: 


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i) Remove the GH-3000 from the instrument panel and connect the JT-147A 

harness in series as follows: 

e 

Disconnect the GH-3000 input cable from J1 and reconnect it to J1 on the JT-147A 

harness. 

Connect PI on the JT-147A harness to J1 on the GH-3000. 

Unscrew the DCM-3000 module from J2 on the GH-3000 and reattach it to J2 on the 

JT-147A harness. 

Connect P2 on the JT-147A harness to J2 on the GH-3000. 

ii) Reinstall the GH-3000 into the instrument panel. (The GH-3000 must be at the 

correct panel angle during calibration.) 

iii) Remove the MAG-3000 from the aircraft and install the MAT-3000A in its place. 

iv) On the ELECTRICAL MASTER panel, set POWER to the ON position. 

v) Wait (approximately 3 minutes) for the "ALIGNMENT IN PROGRESS" message 

to disappear from the GH-3000 display. 

vi) Fast Erect the GH-3000, wait approximately 3 seconds, then momentarily press 

the DATA ENTRY button. Wait while the attitude compensation data is being 

written to the DCM-3000. When prompted by the message on the JT-147A. 

vii) On the ELECTRICAL MASTER panel, set POWER to the OFF position. 

viii) Remove the MAT-3000A from the aircraft and reinstall the MAG-3000. 

b) Heading Calibration Procedure 

i) On the ELECTRICAL MASTER panel, set POWER to the ON position. 

ii) Wait (approximately 3 minutes) for the "ALIGNMENT IN PROGRESS" message 


NOTE HDG will be flagged on the GH-3000 during HDG calibration. 

iii) Align the aircraft to a cardinal heading (North, East, South or West) 

NOTE Up to 5" of misalignment error may be compensated for using the JT-147A. Use the INCIDEC 

switch as required to make the "AIRCRAFT HEADING" number displayed on the JT-147A agree 

with the actual aircraft heading. 

iv) Fast Erect the GH-3000, wait approximately 3 seconds, then momentarily press 

the DATA ENTRY button. 

v) Repeat steps iii.) and iv.) for each of the remaining cardinal headings. 

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BENDIXIKINGG" IFR AVIONICS I KFC goo 


NOTE The headings may be sequenced in any order. If a mistake is made, data for a heading may be 

re-entered. Only the last data entered for each heading will be saved. 

vi) After data have been entered for each of the four cardinal headings, press the 

DISPLAY SELECT button twice to go to the JT-147A EXPECTED RESULTS 

(write) screen. 

NOTE Access to the EXPECTED RESULTS screen will only be available if data have been entered for 

each of the four cardinal headings. 

vii) Momentarily press the DATA ENTRY button and wait while the heading 

calibration data is being written to the DCM-3000. When prompted by the 

message on the JT-147A. 

viii) On the ELECTRICAL MASTER panel, set POWER to the OFF position. 

ix) Remove the JT-147A calibration panel from the aircraft, returning the GH-3000 

and DCM-3000 to a normal installation configuration. 

c) Calibration Checkout Procedure 


ii) Wait (approximately 3 minutes) for the "ALIGNMENT IN PROGRESS" message 


iii) Align the aircraft to a cardinal heading. Fast erect the GH-3000, wait 

approximately 3 seconds, then read the heading displayed on the GH-3000. The 

displayed heading shall not deviate from the actual heading by more than +2O. 

iv) Repeat step iii.) for each of the remaining cardinal headings plus a minimum of 

one intermediate heading 

v) On the ELECTRICAL MASTER panel, set POWER to the OFF position. 

d) System Operation 


ii) During the power on sequence, the following events will occur: 

"Power On Self Test" initiated. 

"Sensor Alignment" 

"Normal Operating Mode" 

NOTE Sensor alignment time is typically less than three minutes under normal conditions. During 

Sensor alignment, the aircraft MUST remain stationary. Any movement may result in sensor 

alignment delay of up to six minutes. 


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iii) Self Test 



Upon application of power, the indicator initiates self test, during which the display will 

be blank for about 15 seconds. 

When self test is complete, the indicator will display an identification screen 

containing the words "Goodrich Avionics Systems, Inc.", software identification 

number, total number of operating hours, and results of the self test. 

A failure in self test will result in the identification screen being replaced by "System 

Test Failure" with a specific failure code. The indicator will remain in this status as 

long as power is applied. No attempt to align sensors or enter normal operating mode 

will be made. 

Another type of test is for configuration failure. This is determined by the state of 

three configuration pins on connector J1. 

9 If an un-configured combination is selected, the display will show "Invalid 

Strapping". 

> If configuration data is not available from the external configuration module, the 

display will show "Configuration Required". 

9 Either "Invalid Strapping" or "Configuration Required" will keep the indicator in 

that status until power is removed. No attempt to align sensors or enter normal 

operating mode will be made. 

All self tests pass: Upon successful completion of self test, the aircraft "type" (where 

type is determined by configuration) will be displayed for approximately five seconds 

before entering sensor alignment. 

iv) Sensor Alignment and Background Self Test 

When the indicator enters sensor alignment, the display will show the "ATT FAIL" with 

the additional message "Alignment in Progress" and a counter displayed below the 

aircraft reference symbol. 

The counter displays remaining time in seconds of sensor alignment. 

Failure of sensor alignment will result in the "ATT FAIL" display remaining until power 

is removed. 

Continuous background self tests begin with sensor alignment and remain operational 

without disrupting normal operation. 

Any background failure that could result in displaying Hazardously Misleading 

Information (HMI) will result in the display going solid black with no information 

viewable. 

Any failure limited to specific information, such as attitude, air data or navigation will 

be displayed as a failure indication specific to that function. 

Page 672 

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97-00-00 




v) Normal Operational Mode: Upon successful completion of self test and sensor 

alignment, the display will resume the last mode used prior to the indicator being 

powered down. The indicator continues to run background self test while in this 

mode. 

Pitch and Roll Attitude Display 

9 The displayed attitude information is a self-contained function of this indicator, 

without benefit of external sources except + 28.0 VDC input power, 

9 No other operator interaction is required unless FAST ERECT is required, Use 

the menu mode to initiate FASTERECT, FAST ERECT willcause rapid 

alignment of the verfical axis of the navigation frame to the vertical axis of the 

aircraft local level frame. 

Slip Skid Indicator 

9 This symbol will displace to the right for clockwise rotation, and to the left for 

counter-clockwise rofation. 

9 Maximum deflection is 2.5 rectangular widths (107, wifh minimum sensitivity of 

1.0' roll on a test bench resulting in perceptible displacement from the zero 

position. 

Air Data Display 

9 Altifude: Altifude data displayed is calculated from pressure altifude supplied by 

the air dafa compufer and corrected by the BAR0 correction setting. 

k /AS: Indicated airspeed is supplied by the air data compufer. 

9 Mach: Mach is supplied by fhe air data compufer. 

9 Invalidifies: All input data is time tested for activity and sfatus which is handled 

as follows: 

J Altitude fape will appear flagged if data label is missing for more than two 

seconds, or stafus indicates "No Compufed Data" or "Failure Warning", 

J /AS tape will appear flagged if data label is missing for more than two 

seconds or status indicafes "No Computed Data" or "Failure Warning", 

J Mach number dafa will be replaced with amber dashes if mach data is 

missing for more fhan fwo seconds, or stafus indicates "No Compufed Dafa" 

or "Failure Warning': 

J Both alfitude and /AS fapes will revert to a flagged sfatus if the air data 

discrete data is missing for more fhan five seconds, sfatus indicates "No 

Compufed Dafa" or "Failure Warning", any failure bits are set fo fail, or fhe 

aircraft ID Label specifies an aircraft that does not match the configuration 

dafa. 

J The red VNE bar will be missing if Maximum Allowable Airspeed dafa is 

missing for more than fwo seconds or status indicates "No Computed Data" 

or "Failure Warningr1. 

7 


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NAV Mode: The NAV Mode consists of VORIILS and FMS (GPS). Use the menu 

function to select VORIILS or GPS (FMS). 

J Instrument Landing System (ILS) 

Navigation receiver must be tuned to an ILS frequency. 

dependent upon received information. 

Displayed data is 

ILS display data consists of ILS appearing in the top left corner of the display, the 

presence of a localizer needle and a glide slope needle, and the presence of 

marker information in the top right corner of the display, as applicable. 

J ILS-BC (Back Course) 

This mode must be entered via the menu mode selection process. 

The ILS annunciator changes to ILS BC and localizer phase information is 

reversed to provide normal approach procedures. The glide slope needle is 

removed. 

J Marker Descriptors 

Marker beacon information is annunciated, as applicable, with the descriptor 

flashing at a two hertz rate in the top right display area. 

Descriptors are OM for outer marker, MM or middle marker and IM for inner 

marker. 

J VOR 

Navigation receiver must be tuned to an VOR frequency. Displayed data is 

dependent upon received information. 

VOR display data consists of VOR appearing in the top left corner of the display, 

the presence of a LEFTIRIGHT needle and the presence of the TOIFROM 

indicator. 

J GPS (FMS) 

The GPS receiver must be receiving an adequate number of satellites for 

navigation. Displayed data is dependent upon received information. 

GPS (or FMS) display data consists of GPS appearing in the top left corner of the 

display, the presence of a LEFTIRIGHT needle and the presence of the 

TOIFROM indicator. 


Emergency Locator Transmitter (ELI) 

Inspect the ELT for (1) proper installation; (2) battery corrosion; (3) operation of the controls and 

crash sensor; and (4) the presence of a sufficient signal radiated from its antenna. 

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BENDIX/KING@ IFRAVIONICS I KFC goo 


98-00-00 

WIRING - 


1. Effectivity 

A. Aircraft SIN 900-00010 thru 900-00051 

The MD900 wiring defined by STC Number SR00436WI-D has been installed for operation in the IFR 

environment. Serial number effectivity is noted as it applies in the wiring diagrams. Other effectivities are 

also defined based on the "MOD" status of the installed wiring harness. 

Category A wiring diagrams do not apply to the serial number range 0900-00010 through 900-00051. 

' 

B. Aircraft SIN 900-00052 and Subsequent 

The MD900 wiring defined by STC Number SR00436WI-D has been installed for operation in the IFR 

environment. Serial number effectivity is noted as it applies in the wiring diagrams. Other effectivities are 

also defined based on the "MOD" status of the installed wiring harness. 

Category A wiring diagrams do apply to the serial number range 0900-00052 and subsequent. 

2. Chapter Content 

This chapter contains four sections; Wiring, Electrical Equipment, Standard Practices and Wiring 

Diagrams. 

3. Section Content 

Wiring (Section 98-00-00) - contains the Description and Operation which explains the content and 

usage of Chapter 98-00-00. 

Electrical Equipment (Section 98-10-00) - contains all hardware, by reference designator, description, 

Honeywell part number and standard part number (if applicable). For equipment part numbers applicable 

to STC number SR00436WI-D, reference Honeywell Installation Manual 006-00750-0000 Revision AE or 

later revision. 

System Wiring Diagrams (Section 98-40-00) - contains the wiring diagrams for the systems installed in 

accordance with STC number SR00436WI-D. 

4. Illustration Layout Convention 

The connector reference designators for the equipment installed by STC number SR00436WI-D are 

assigned in accordance with the unitlsystem identification. As an example the number 1 KX 165 

NAVICOMM transceiver connector 1 is designated as 1 P1651. The second connector is designated as 

1P1652. The number 2 KX 165 NAVICOMM transceiver connector 1 is designated as 2P1651. The 

second connector is designated 2P1652. 

Existing aircraft connector designators follow the convention defined in the existing MD900 Maintenance 

Manual. 


98-00-00 

Page 1 

Revision AD



5. Wiring Diagram Symbology 

Reference Figure 33. 

For ease of reading the wiring diagrams, all lower case letters are shown in capital with an asterisk (*) 

following the actual pin letter. As an example, pin "a" is designated as "A*". 

Wire splices reside nearest to the connector shown in the wiring diagram. In some cases, the splice could 

reside further back in the harness due to congestion and/or interference. 

In the case of an interface to an existing aircraft connector or termination, the existing aircraft wiring may 

not always be shown. 

+ 

n 

w SINGLE CONDUCTOR SHIELDED NO CONNECTION 

W n 

BI I TWISTED PAIR SHIELDED 

WlRE SPLICE CONNECTION 

w 

+- 

W- n 

TWISTED PAlR 

BI I I I DOUBLE SHIELDED 

w- 

W n 

BI I 

01 I 

w 

TWISTED TRIPLE SHIELDED 

Wnn 

BI I I I TWISTED TRIPLE 

01 1 I I DOUBLE SHIELDED 

VW 

--- 

EXISTING AIRCRAFT WIRING 

SHOWN FOR REFERENCE ONLY 

cv CAPPED WIRE 

c9 

Figure 33: Wiring Diagram Symbology 

CONNECTOR BACKSHELL 

GROUND (TYPICAL) 

CONNECTOR STRAIN 

RELIEF GROUND 

(TYPICAL) 

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98-00-00 


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BENDIX/KlNAIG" IFRAVIONICSI KFC goo 


98-1 0-00 

Electrical Equipment List 

1. Equipment List Usage 

The equipment list is an alphanumerical listing of all of the equipment reference designators, 

descriptions, Honeywell part numbers and standard part numbers. 

Note the following designations: 

A601 - Essential Circuit Breaker Panel 

A610 - External Power Box Assembly 

A620 - Electrical Load Center 


I 

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IFR AVIONICS I KFC 900 


Table 4: Electrical I Equipment List 

PANEL 

REFERENCE 

DESIGNATOR 

A9 S2 

A9 S2 

PFAN 

PFAN 

Jh4STR2 

S3 

S3 

DESCRIPTION 

RING TERMINAL, #8 

RING TERMINAL, % 

RING TERMINAL, #8 (M4) 

3M PROTECTIVE TAPE 

COAXIAL CABLE, RGU 142 

COAXIAL CABLE, RGS 393 

COAXIAL CABLE, RG 400 

WIRE, INSULATED, 22 GAUGE 





WIRE, SHIELDED, TWISTED TRIPLE, 22 GAUGE 


WIRE. INSULATED, 10 GAUGE 

WIRE, SHIELDED, 22 GAUGE 

WIRE, SHIELDED, TWISTED PAIR, 22 GAUGE 

DECAL SHEET 

GEN FIELD OVERLAY 

COOLING FAN, PANEL 

HEAT SHRINK TUBING 




PILOT TRIM SWITCH ASSY 

COPILOT TRIM SWITCH ASSY 

LH CYCLIC DISCONNECT PLUG ASSY 

RACK FAN ASSY 

CONNECTOR PLUG 

TERMINAL MALE 

FAN 28V ECDC 

TBG HT SHRNK WHT 


ASSY DRAWING 

LEET EFIS MASTER ASSY 

LACING CORD 18DR 

WIRE INSUL 20 GAUGE 

FLANGE CONNECTOR, SPIN MALE 

2 POLE SWITCH 

PIN CONTACT 

SOLDER SLEEVE 62 

ASSY DRAWING 

I 

I 

I 

HONEYWELL 

PARTNUMBER 

010-00067-0015 

010-00067-0025 

010-00068-0024 

012-01589-0001 

024-00002-0050 

024-00075-0000 

026-00015-0050 

025-00091-0001 

025-00091-0002 

025-00091-0003 

025-00091-0004 

025-00091-0006 

025-00091-0005 

025-00091-0006 

025-00091-0007 

025-05056-0003 

025-05056-0004 

057-05805-0001 

088-03245-0001 

148-05189-0001 

150-00126-0009 

150-00128-0009 

150-00129-0009 

150-00130-0009 

200-05647-0039 

200-05647-0039 

200-05647-0040 

200-05647-0007 

030-02548-0000 

030-02550-0001 

148-05183-0000 

159-00127-0009 

159-00129-0009 

300-05647-0007 

I STANDARD PART 

Dm, XPDR 


VHF NAV, VHF COMM, GPS, MRKR, 

4-TUBE EFIS OPTION 


AFCS 

AFCS 

AFCS 

GPS 

GPS 

GPS 

P900D 

P900D 

PLITE 

JMSTRI 

S2 

S2 

S 1 

S 1 

DIAGNOSTIC HARNESS ASSY 



WHITE PV TAPE 


WIRE, SHIELDED, TWISTED P a 22 GAUGE 

SOCKET CONTACT 20 GAUGE 

SUB-D CONNECTOR HOUSING 9s 

CONNECTOR HOOD WIJACKSCREWS 


SUB-D CONNECTOR HOUSING 9S 

CONNECTOR HOOD WIJACKSCREWS 

CONECTOR BACKSHELL 

CONNECTOR 37PIN MALE 

CABLE LABEL 

SOLDER SLEEVE .62 

ASSY DRAWING 

MASTER SWITCH PANEL 

CRIMP TERMINAL 4s 

LACING CORD l8DR 


RECEPTACLE 

FLANGE CONNECTOR 18 PIN MALE 

2 POLE SWITCH 

PIN CONTACT 

4 POLE SWITCH 

PIN CONTACT 

STANDOFF 

FRONT PLATE 

PANEL PLATE 

OVERLAY 

HOLE PLUG 

NUT, LOCK 4-40 

NUT, LOCK, 6-32 

SCREW, 4.40~318 

SCREW, 6-32x318 

SCREW, 642x318 

WASHER, LOCK #6 

WASHER, FLAT, 4x.125 

WASHER, FLAT, 6x375 

I 

Page 2 


- -- -- 

EFFECTIVIN: MD900

+ 

REFERENCE 

PANEL DESIGNATOR 

J0102 

J0102 

J0102 

PLITE 

S4 

S3 

S5 

S8 

S 1 

S2 

S9 



DESCRlPTION 


ASSY DRAWING 

AVIONICS SWITCH PANEL 

CRIMP TERMINAL 4S 


DC RTV 3 145 


D-SUB CONNECTOR 25 PIN 

PIN CONTACT 

LOCKING TAB 

RECEPTACLE 

SPDT TOGGLE SWITCH 

SP3T TOGGLE SWITCH 



PUSH BUTTON MOMENTARY SWITCH 



STANDOFF 

FRONT PLATE 

AV PANEL PLATE 

OVERLAY 


SCREW, 6-32x318 

SCREW, 6.32~318 

WASHER, LOCK, #6 



ASSY DRAWING 

HONEYWELL 

PARTNUMBER 

150-00130-0009 

STANDARD PART 

NUMBER 

M2305315-106-9 

PCRl 

PCR2 

XDSl 

J3 

12 

J1 

CBI 

CB2 

CB3 

CB4 

CB5 

CB6 

CB7 

CB8 

CB9 

CBlO 

CBll 

CB12 

CB13 

CB14 

CB15 

CB16 

CB17 

CB18 

CB19 

CB20 

CB21 

CB22 

CB23 

CB24 

CB25 

CB26 

CB27 

CB28 

CB29 

CB30 

CB3 1 

CB32 

CB33 

CB34 

CB35 

CB36 


ESSENTIAL CIRCUIT BREAKER PANEL 

POWER DIODE 

POWER DIODE 

RING TERMINAL #8 

RING TERMINAL 4s 

RING TERMINAL #6 (M3 5) 

RING TERMINAL U8 1M4) 

5 POSITION BUS BAR ' 

6 POSITION BUS BAR 




WIRE. INSULATED, I8 GAUGE 

WIRE. INSIJLAI'ED. I6 GAUGE 

WIRE: INSULATED; 12 GAUGE 

RECEPTACLE 

CIRCULAR CONNECTOR 



CIRCUIT BREAKER 30 

CIRCUIT BREAKER 5A 



CIRCUIT BIlEAKEIl SA 


CIRCUIT BREAKER 7%A 



CIRCUIT BUEAKER 5A 


CIRCUIT BREAKEll5A 



CIRCUIT BIEAKER 10A 

CIRCUIT BREAKER IOA 




ClRCUlT BREAKER 5A 

CIRCUIT BREAKER SA 






CIucurr BREAKER 7 % ~ 

CLRCUIT BREAKER 7%A 






CIIlCUl'I' BREAKER 5A 


CIRCUIT BREAKEll 5A 

STANDOFF 

BUSBAR 

BUS ANGLE 

4CFT SiN 900-00010 THRU 900-00051 

Page 3 

Revision AD


PANEL 

A60 1 

A601 

A60 1 

A601 

A601 

A60 1 

A60 1 

A60 1 

A60 1 

A60 1 

A60 1 

A601 

A60 1 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A60 1 

A601 

A60 I 

A60 1 

A60 1 

A601 

A60 1 

A60 1 

A60 1 

A60 1 

A60 1 

A60 1 

A60 1 

A60 1 

A60 1 

A601 

A60 1 

A60 1 

A601 

A60 1 

A60 1 

A60 1 

A601 

A60 1 

REFERENCE 

DESIGNATOR 

DESCRIPTION 

C/B PLATE, FRONT 

C/B PLATE. REAR 

C/B PANEL OVERLAY 





SCREW PUP. 4-40~3.8 

SCRtW PHP. 6.32~318 

SCREW PHP, 10-32x112 

SCREW FHP, 6-32x318 

SCREW FHP, 6-32x1 

SCREW 



WASHER, FLAT, 6x 375 

WASHER, FALT, 10x.438 



ASSY DRAWING 

RING TERMINAL, #8 

RING TFRMINAL, r16 (M3 5) 

KING TERMINAL . #8 1M4) ~~, 

BUS BAR, 5 POSITION 

BUS BAR, 6 POSITION 

STANDOFF 

BUSBAR 

BUS ANGLE 

C/B PLATE, FRONT ASSY 

C/B PLATE, REAR 

C/B PANEL OVERLAY 





SCREW, 4-40x318 

SCREW, 6.32~318 

SCREW, 10-32x112 

SCREW, 6-32x318 

SCREW, 6-32x1 

SCREW 





TBG HT SHRNK 2&5/16G 


ASSY DRAWING 

HONEYWELL 

STANDARD PART 

NUMBER 

MS25226-ION-5 

MS25226- 10n-6 

M2305315-106-9 

ESSENTIAL CIRCUIT BREAKER PANEL 

POWER DIODE 

POWER DIODE 

RING TERMINAL #8 

RING TERMINAL 4s 

RING TERMINAL #6 (M3.5) 

RING TERMINAL #8 (M4) 





WIRE. INSULATED. 20 GAUGE 

ACFT SM 900-00052 & SUBS 

Page 4 

Revision AD 

WIRE. INSULATED, 16 GAUGE 

WIRE. INSULATED. I2 GAUGE 


CIRCUI.AR CONNECTOR 

CIRCULAK CONNECTOR 

CIRCUIT BREAKER 30 

CIRCUIT BREAKER $A 




SWITCHABLE CIRCUIT BREAKER 7%A 







ClllCUlT BREAKER SA 



CIRCUIT BREAKER IOA 




CIKCUIT BREAKER SA 


I EFFECTIVITY:


PANEL 

A601 

A601 

A601 

A601 

A601 

A601 

A60 1 

A60 1 

A60 1 

A60 1 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

A601 

REFERENCE 

DESIGNATOR 

CB22 

CB23 

DESCRIPTION 


CIRCUIT BREAKER SA 

SWITCHABLE CIRCUIT BREAKER 7%A 


ClRCUl r BREAKER 5A 

CIRCUIT BREAKER 7'+\ 


ClRCUlT BREAKER 5A 




CIRCUIT BREAKER (A 

CIRCUIT BREAKER 5h 



STANDOFF 

BUSBAR 

BUS ANGLE 

CB PLATE, FRONT ASSY 

CiB PLATE, REAR 

CiB PANEL OVERLAY 





SCREW PHP, 4.40~318 

SCREW PHP, 6-32x318 

SCREW PHF', 10-32x112 

SCREW FHP, 6.32~318 

SCREW FHP. 6-32x1 

SCREW 







ASSY DRAWING 

HONEYWELL I STANDARD PART I 

PARTNUNIBER 

036-00073-0005 

NUMBER 

MS3320-5 

XDS l 

P9000 

CB I 

CB2 

CB3 

CB4 

CB5 

CB6 

ESSENTIAL CLRCUIT BREAKER PANEL EXTENSION 

RING TERMINAL 4S 

RING TERMINAL #6 (M3.5) 

RING TEhMMAL #8 (M4) 




RECEPTACLE 

CONNECTOR 


CLRCUIT BREAKER 5A 





SIDE CB PANEL BRACKET ASSY 

SIDE CB PANEL OVERLAY 

AIRCRAFT SCREW 


FLAT WASHER, 6-,032 

FLAT WASHER, 6-,032 

HEX NUT 

NUT, SELF LOCK 6-32 

NUT SELF LOCK 

SCREW 4-40 X ,375 

PHF', STEEL SCREW 6-32 

ACFT SiN 900-00052 & SUBS 

2-TUBE EFIS & CAT A OPTION 

A610 

A610 

A610 

A610 

A610 

A610 

A610 

A610 

A610 

A610 

A610 

A610 

A610 

A620 

A620 

A620 

A620 

A620 

A620 

A620 

A620 

A610 CBI 

A610 CBZ 

A610 CB3 

A620 CB32 

A620 CB33 

A620 CB34 

A620 CB36 

A620 CB37 

A620 CB39 

PITCH SYNC SWITCH 

PITCH SYNC SWITCH 


DIODE MOUNTING PLATE 

PHENOLIC BLOCK 

NUT 

NUT 

SCREW 

BOLT, 8-32 

SCREW, 8-32 

SCREW 

WASHER 

CIRCUIT BREAKER, 50A 



BUS BAR. 2 POSITION 

BUS BAR, 4 POSI1 ION 








ACFT SiN 900-00010 THRU 900-00051 

ACFT SM 900-00010 THRU 900-00051 

ACFT SM 900-00010 THRU 900-00051 

ACFT SiN 900-00010 THRU 900-00051 

ACFT SM 900-00010 THRU 900-00051 

ACFT SM 900-00010 THRU 900.00051 

ACFT SM 900-00010 THRU 900-00051 

~ACFT SM 900-00010 THRU 900-00051 

ACPT SM 900-00010 THRU 900-00051 

IACPT SIN 900-00010 THRU 900-00051 

ACFT SM 900-00010 THRU 900-00051 

ACFT SIN 900-00010 THRU 900-00051 

ACFT SM 900-00010 THRU 900-00051 

ACFT SIN 900-00010 THRU 900-00051 

Page 5 

Revision AD



PANEL 

A620 

A620 

A620 

A620 

A620 

A620 

A620 

A620 

A620 

A620 

A620 

A620 

A620 

A620 

A620 

A620 

A620 

A620 

A620 

A620 

A620 

A620 

A674 

A674 

REFERENCE 

DESIGNATOR 

A620 CB39 

A620 CB40 

A620 CB40 

A620 CB48 

A620 CB66 

A620 CB68 

A620 CB69 

A620 CB70 

A620 CB71 

A620 CB72 

A620 CB77 

A620 CB78 

A620 CB79 

A620 CB80 

A620 CB83 

A620 CB84 

A620 CB85 

A620 CB86 

A620 CB87 

A620 CB88 

A620 CB89 

A620 CB95 

A674 TB1 

A674 TB1 

DESCRIPTION 























TERMINAL BLOCK 

SOCKET CONTACT 

HONEYWELL 

PARTNUMBER 

036-00073-0007 

036-00073-0005 

036-00073-0005 

036-00073-0005 

036-00150-0000 

036-00073-0005 

036-00073-0003 

036-00073-0005 

036-00073-0000 

036-00073-0000 

036-00073-0005 

036-00073-0005 

036-00073-0005 

036-00073-0005 

036-00073-0005 

036-00073-0007 

036-00073-0003 

036-00073-0003 

036-00073-0005 

036-00073-0005 

036-00073-0005 

036-00073-0005 

030-0331 1-0005 

030-01459-0001 

STANDARD PART 

NUMBER 

MS3320-705 

MS3320-5 

MS3320-5 

MS3320-5 

MS3320-5 

MS3320-3 

MS3320-5 

MS3320-1 

MS3320-1 

MS3320-5 

MS3320-5 

MS3320-5 

MS3320-5 

MS3320-5 

MS3320-10 

MS3320-3 

MS3320-3 

MS3320-5 

MS3320-5 

MS3320-5 

MS3320-5 

M81714160-22-06 

M39029122- 192 

EFFECTIVITYICOMMENTS 

ACFT SIN 900-00010 THRU 900-00051 

JTBARl 

JTBARl 

8K500 

8K500 

8K500 

PI28 

P9010 

P9010 

LEDEX TRIM SWITCH HARNESS ASSY 



WHITE PV TAPE 


CABLE CONNECTOR 50 PIN MALE 

PM CONTACT, 20 GAUGE 

RELAY SOCKET 


SOCKETCONTACT 


CABLE LABEL 

CONNECTOR 55s 

STRAIN RELIEF 

SOLDER SLEEVE 62 

ASSY DRAWING 

300-09848-0501 

012-01006-0000 

012-01589-0001 

012-01662-0001 

025-00091-0002 

030-01078-0000 

M39029134-271 

033-00235-0001 

030-01485-0001 

030-01485-0001 

030-03239-0001 

091-00623-0001 

M83723-75R2255N 

M85049152-1-22N 

150-00072-0004 

300-09848-01 

M22759116-22-9 

M39029134-271 

M12883144-01 

M390291101-553 

M390291101-553 

M3902915-115 

M83723-75R2255N 

M85049152-1-22N 

CBlOO 

CBlOl 

15300 

IJEAN 

IRAN 

1K500 

1K500 

1K500 

1K63 

1K63 

1K63 

1P1121 

1P1651 

1P1651 

1P1652 

lP1652 

1P1652 

lP1654 

1P1655 

1P300 

1P300 

1P33 I 

1P331 

1P3000 

1P3331 

1P3331 

1P3331 

1P3331 

1P3331 

1P3601 

1P4611 

1P4611 

1P4611 

1P4611 

1P4621 

1P4621 

1 P462 1 

1P4621 

1P4651AIB 

IP465XAIB 

IP4652AIB 

1P4653 

1P4653 

1P4653 

Page 6 

Revision AD 

PITCH STRING POT 

ROLL STRING POT 

APISAS ANNUNCIATOR PANEL 

CIRCUIT BREAKER, %A 

CIRCUIT BREAKER, %A 

CONNECTOR 

CONNECTOR 

CONTACT 

RELAY, 4-POLE 

RELAY SOCKET 


RELAY, 4-POLE 

RELAY SOCKET 


CONNECTOR 

CONNECTOR 

TERMINAL CONTACT 

CONNECTOR 

CONNECTOR 


RF CONNECTOR 

RF CONNECTOR 

STRAIN RELIEF 

CONNECTOR 

CONNECTOR 


CONNECTOR 41 S 


RINGTERMINAL, #I0 


CONNECTOR 

CONNECTOR HOOD, EMI 

CONNECTOR 



CONNECTOR 




CONNECTOR 

CONNECTOR HOOD, E M 

CONNECTOR 

PIN CONTACT 

CONNECTOR 

SOCKETCONTACT 

CONNECTOR 

CONNECTOR HOOD 

98-10-00 

133-00572-0001 

133-00572-0002 

037-00228-0001 

036-001 52-0001 

036-001 52-0001 

030-03309-0010 

030-02549-0000 

030-02551-0000 

032-00153-0001 

033-00235-0001 

030-01485-0001 

032-00153-0001 

033-00235-0001 

030-01485-0001 

030-02190-0000 

030-01094-0060 

030-01 107-0001 

030-01094-0059 

030-01094-08880 

030-01 107-0001 

030-00101-0002 

030-00101-0002 

030-01476-0002 

030-03308-0009 

030-02549-0001 

030-02551-0000 

010-00068-0026 

010-00068-0028 

030-01 157-0011 

030-01 175-0000 

030-01428-0004 

MS3116F10-6S 

010-00135-0000 

030-01 157-001 1 

030-01 176-0010 

030-01428-0000 

010-00135-0000 

030-01 157-001 1 

030-01 176-0010 

030-01428-0000 

030-02707-0002 

030-013 11-0000 

030-02707-0000 

030-01 157-001 1 

030-02346-0001 

030-02351-0005 

EFFECTIVITY: 

D3899912OWE99SN 

M8353616-022M 

M12883144-01 

M390291101-553 

M8353616-022M 

M12883144-01 

M390291101-553 

M85049139-17W 

D38999126WE99PN 

MS3 126F20-41s 

MS3 116F10-6S 

MD900 

KX 165M 265A NAVICOMM 


KX 165 NAVICOMM 

KX 165ANAVlCOMM 

KX 165M 265ANAVlCOMM 

CAT A OPTION


PANEL 

REFERENCE 

DESIGNATOR 

I 1P465X 

I EFFECTIVITY: 

DESCRlPTION 

I CONNECTOR PLATE 

CONNECTOR COVER 


SCREW 

SCREW 

SCREW 

WASHER 


CONNECTOR 

CONNECTOR HOOD, EM1 

CONNECTOR 


CONNECTOR 


CONNECTOR 


RING TERMINAL, #6 (M3.5) 

CONNECTOR 




CONNECTOR 





CONNECTOR 

CONNECTOR 

CONNECTOR 

CONNECTOR 

CONNECTOR 


CONNECTOR 

CONNECTOR 

SOCKETCONTACT 

RELAY, 4-POLE 

RELAY SOCKET 

SOCKETCONTACT 

CONNECTOR 

CONNECTOR 


CONNECTOR 

CONNECTOR 


RF CONNECTOR 

RF CONNECTOR 

RF CONNECTOR 

STRAIN RELIEF 

CONNECTOR 

CONNECTOR 



CONNECTOR 

RING TERMINAL, #I0 


CONNECTOR 


CONNECTOR 

RING TERMINAL, #2 (MZ) 


CONNECTOR 




CONNECTOR 


CONNECTOR 

PIN CONTACT 

CONNECTOR 


CONNECTOR 


CONNECTOR PLATE 

CONNECTOR COVER 


SCREW 

SCREW 

SCREW 

WASHER 


CONNECTOR 


CONNECTOR 



CONNECTOR 




HONEYWELL 

PARTNUMBER 

047-09823-0002 

047-09830-0002 

071-00061-0000 

089-05878-0010 

089-06008-0004 

089-06008-0007 

STANDARD PART 

NUMBER 




KX 165m 265~ NAVICOMM 

KX 165KX 265A NAVICOMM 

KX 165 NAVICOMM 

KX 165A NAVICOMM 


CAT A OPTION 

OPTION 




4-TUBE EFlS OPTION 














4-TUUE EFlS OPTION 









Page 7 

Revision AD


PANEL 

REFERENCE 

DESIGNATOR 

2P92 1 

2P921 

2P924 

2P924 

2P924 

2P924 

2PSHDl 

2PSHD2 

2PSHD3 

2PSHD4 

2PSHDX 

3J3000 

3JFAN 

3JFAN 

3K500 

3K500 

3K500 

3P500 

3P500 

3P573 1 

3P573 1 

3P573 1 

3PCFG 

3PCFG 

3PCFG 

3PSHDI 

3PSHD2 

3PSHDX 

4JFAN 

4JFAN 

4K500 

4K500 

4K500 

4P500 

4P500 

4PFAN 

4PFAN 

5JF AN 

5JFAN 

SKSOO 

5K500 

5K500 

SPFAN 

5PFAN 

6K500 

6K500 

6K500 

7K500 

7K500 

7K500 

9K500 

9K500 

9K500 

CRllO 

CR900 

CR901 

GBOl 

GBOl 

GB02 

GBOZ 

GB03 

GB03 

GB04 

GB04 

GBOS 

GBO5 

GB06 

GB06 

GB07 

GB07 

GBO8 

GB08 

GB09 

GB09 

GBlO 

GBlO 

GSlOO 

JO 102 

10 I02 

10102 

10 102 

J0102 

10 102 

J0115 

10115 

J1 

11 

JlOO 

JlOO 

Page 8 

Revision AD 

DESCRIPTION 

CONNECTOR 




CONNECTOR HOOD, E M 

CONNECTOR 

CONNECTOR 

CONNECTOR 

CONNECTOR 

CONNECTOR 


CONECTOR 

CONNECTOR 


RELAY, 4-POLE 

RELAY SOCKET 


CONNECTOR 


STRAIN RELIEF 

CONNECTOR 



CONNECTOR 


CONNECTOR 

CONNECTOR 


CONNECTOR 


RELAY, 4-POLE 

RELAY SOCKET 


CONNECTOR 


CONNECTOR 


CONNECTOR 


RELAY, 4-POLE 

RELAY SOCKET 


CONNECTOR 


RELAY, 4-POLE 

RELAY SOCKET 


RELAY, 4-POLE 

RELAY SOCKET 


RELAY, 4-POLE 

RELAY SOCKET 


DIODE MODULE 

ZENER DIODE 

DIODE 

GROUND BLOCK 


GROUND BLOCK 


GROUND BLOCK 


GROUND BLOCK 


GROUND BLOCK 


GROUND BLOCK 


GROUND BLOCK 


GROUND BLOCK 


GROUND BLOCK 


GROUND BLOCK 



CONNECTOR 

PIN CONTACTS 

LOCKING TAB 


SCREW, 4-40x7116 


PIN CONTACT 

CONNECTOR 

CONNECTOR 

CONNECTOR 


STRAM RELIEF 

HONEYWELL 

PARTNUMBER 

030-01 172-0000 

030-01472-0001 

010-00135-0000 

030-01458-0000 

030-0 1472-0002 

030-02667-0001 

030-01094-0002 

030-01094-0002 

030-01094-0002 

030-01094-0002 

030-01432-0000 

MS27499ElOF35S 

030-02549-0000 

030-02551-0000 

032-00153-0001 

033-00235-0001 

030-01485-0001 

030-03228-0000 

030-03239-0001 

030-01475-0004 

030-03309-0001 

030-01480-0001 

030-01157-001 1 

030-02346-0000 

030-02351-0005 

030-01094-0006 

030-01094-0006 

030-01432-0001 

030-02537-0001 

030-02550-0000 

032-00153-0001 

033-00235-0001 

030-01485-0001 

030-03228-0000 

030-03239-0001 

030-02459-0001 

030-02551-0000 

030-02537-0001 

030-02550-0000 

032-001 53-0001 

033-00235-0001 

030-01485-0001 

030-02459-0001 

030-02551-0000 

032-00153-0001 

033-00235-0001 

030-01485-0001 

032-00153-0001 

033-00235-0001 

030-01485-0001 

032-00153-0001 

033-00235-0001 

030-01485-0001 

030-03450-0001 

007-05032-001 1 

007-06048-0000 

030-03314-0001 

030-01459-0001 

030-03314-0001 

030-01459-0001 

030-03314-0001 

030-01459-0001 

030-03314-0001 

030-01459-0001 

STANDARD PART 

NUMBER 

M8353616-022M 

M12883144-01 

M390291101-553 

MS3474L12- IOS 

M3902915-115 

M85049138-9W 

D38999120WA98SA 

M39029156-348 


EFFECTIVITY/COIM~.IENTS 




4- fUBE EFlS OPTION 

4-TLBE EFIS OPTION 







CAT A OPTION 



4-TUDE EFIS OPTION 





CAT A OPTION 

CAT A OPTION 

CAT A OPTION 

CAT A OPTION 

OPTION


PANEL 

REFERENCE 

DESIGNATOR 

1100 

111 

112 

J2 

52 

J200 

J200 

J200 

J900D 

J900D 

1900D 

J9000 

JC I 

JCZ 

JNI 

L GEN FIELD 

L GEN FIELD 

L GEN FIELD 

POI00 

POI00 

POI00 

POI00 

POI00 

POI00 

POI00 

POlOl 

POlOl 

POlOl 

POlOl 

POlOl 

POlOl 

POlOl 

PO 102 

PO 102 

PO 102 

PO102 

PO 104 

PO 104 

PO104 

PO104 

PO 104 

PO104 

PO 104 

PO 106 

PO 106 

PO 106 

PO106 

PO 106 

PO 106 

PO106 

PO107 

PO107 

PO107 

PO108 

PO108 

PO108 

PO108 

PO108 

PO108 

PO109 

PO109 

PO 109 

PO109 

PO109 

POI10 

POI10 

Poll0 

POI10 

Poll0 

POI10 

POI10 

POlll 

POlll 

POlll 

POlll 

POlll 

POlll 

Poll2 

POI 12 

POI 12 

PO112 

POI 12 

PO112 

PO115 

PO115 

PO115 

PO115 

PO115 

PO115 

DESCRIPTION 

CONNECTOR 

RF BULKHEAD 

RF BULKHEAD 

CONNECTOR 

CONNECTOR 


STRAIN RELIEF 

CONNECTOR 


STRAIN RELIEF 

CONNECTOR 

CONNECTOR 

RF BULKHEAD 

RF BULKHEAD 

RF BULKHEAD 

PIN CONTACT 

REMOTE CONTROL CB, 10A 

INSULATOR BOOT 


CONNECTOR 

SWITCH BODY 

SPACER 

MOUNTING SLEEVE 

LAMP CAPSULE 

REPLACEMENT LAMPIBULB 


CONNECTOR 

SWITCH BODY 

SPACER 


LAMP CAPSULE 

REPI.ACEMENT LAMPIBULB 

KING TERaMINM. #2 IM2I 

~OC~ETCONTACT ' ' 

CONNECTOR 



CONNECTOR 

SWITCH BODY 

SPACER 


LAMP CAPSULE 


SOCKETCONTACT 

CONNECTOR 

SWITCH BODY 

SPACER 



LAMP CAPSULE 


CONNECTORHOOD 

CONNECTOR 


CONNECTOR 

SWITCH BODY 

SPACER 


LAMP CAPSULE 


CONNECTOR 

INDICATOR HOUSING 

INDICATOR MODULE 

REPLACEMENT LAMP MODULE 


CONNECTOR 

SWITCH BODY 

SPACER 


LAMP CAPSULE 



CONNECTOR 

SWITCH BODY 

SPACER 


LAMP CAPSULE 



CONNECTOR 





CONNECTOR 

SWITCH BODY 


SPACER 

LAMP CAPSULE 

HONEYWELL 

STANDARD PART 

NUMBER 

D38999120WE35SN 




















4-TUBE EFlS OFL'ION 



















4-TUBE RFlS OPTION 



Page 9 

Revision AD

BENDIXlKIN6" IFRAVIONICS I KFC goo 


PANEL 

' 

REFERENCE 

DESIGNATOR 

PO115 

POI I5 (2 PIN) 

POI I5 (2 PIN) 

PO116 

PO116 

PO116 

PO116 

PO116 

PO117 

PO117 

PO117 

PO117 

PO117 

PI00 

PI00 

PI00 

P102AI 

P102A1 

PI1 

PI2 

PI27 

PI27 

PI44 

PI44 

PI44 

PI46 

PI46 

PI46 

PI721 

PI721 

PI721 

PI722 

P 1722 

PI722 

P182A1 

P182A1 

P182A1 

P182A1 

P200 

P200 

P200 

P2000 

PZOOO 

P2000 

P2001 

P200l 

P2001 

P2001 

P2061 

P2061 

P2061 

P261 

P3 

P4 

P401 

P401 

P401 

P402 

P402 

P402 

P403 

P403 

P403 

P4051 

P405 1 

P405B1 

P405BI 

P4052 

P4053 

P4801 

P4801 

P4801 

P4801 

P481T1 

P481T1 

P481T1 

P485 1 

P4851 

P485 1 

P5 

P51B1 

P51B2 

P5201 

P5202 

P5202 

P5203 

P5203 

P520X 

P520X 

Page 10 

Revision AD 

DESCRIPTION 


CONNECTOR 



CONNECTOR 





CONNECTOR 





STRAIN RELIEF 

CONNECTOR 


CONNECTOR 

RF CONNECTOR 

RF CONNECTOR 

STRIN RELIEF 

CONNECTOR 

RING TERMINAL, #6 (m3 5) 

STRAIN RELIEF 

CONNECTOR 

RING TERMINAL, #6 (M3 5) 

STRAIN RELIEF 

CONNECTOR 


CONNECTOR 



CONNECTOR 




CONNECTOR 


RING TERMINAL, #6 (M3 5) 

STRIN RELIEF 

CONNECTOR 


CONNECTOR 

CONNECTORHOOD 



CONNECTOR 

CONNECTOR HOOD, EM 

SOCKET CONTACTS 

CONNECTORHOOD 

CONNECTOR 

RF CONNECTOR 

RF CONNECTOR 

RF CONNECTOR 


CONNECTOR 



CONNECTOR 



CONNECTOR 



CONNECTOR 


CONNECTOR 

RF CONNECTOR 

RF CONNECTOR 


STRAIN RELIEF 

CONNECTOR 


RMG TERMINAL, #8 (M4) 

CONNECTOR 



CONNECTOR 


RF CONNECTOR 

CONNECTOR 

CONNECTOR 

PIN CONTACT 20 GAUGE 




SOCKET CONTACT16 GAUGE 

CONNECTOR 

CONNECTOR BRACKET 

98-10-00 

HONEYWELL 

PARTNUMBER 

030-02417-0000 

030-02417-0001 

030-01458-0000 

037-00225-0000 

037-00225-0002 

037-00225-0104 

037-00225-0010 

030-01451-0000 

037-00225-0000 

037-00225-0002 

037-00225-0104 

037-00225-0010 

030-01451-0000 

030-01475-0003 

030-03308-0007 

030-02154-0000 

030-02221-0000 

030-00465-0000 

030-00465-0000 

030-01476-0002 

030-03284-0000 

010-00068-0016 

030-01475-0004 

030-03308-0001 

010-00068-0016 

030-01475-0004 

030-03308-0001 

030-01157-0011 

030-01172-0000 

030-02351-0001 

030-01157-0011 

030-01176-0000 

030-2351-0004 

010-00135-0000 

030-01157-0011 

030-01175-0000 

030-01428-0004 

010-00068-0016 

030-01475-0001 

030-03308-0004 

030-01157-0011 

030-01171-0000 

030-02351-0000 

010-00135-0000 

030-01157-0011 

030-01176-0000 

030-01428-0006 

030-01080-0000 

030-02154-0000 

030-2272-0000 

030-00459-0000 

030-00465-0000 

030-00465-0000 

030-01157-0011 

030-01176-0000 

030-02351-0004 

030-01157-0011 

030-01175-0000 

030-02351-0003 

030-01157-0011 

030-01176-0000 

030-02351-0004 

010-00068-0026 

030-02211-0006 

010-00068-0026 

030-02077-0004 

030-00108-0000 

030-00108-0000 

010-00068-0026 

030-01478-0001 

030-03238-0000 

010-00068-0026 

030-02564-0004 

030-01284-0000 

010-00068-0026 

030-02656-0014 

030-01284-0000 

030-00465-0000 

030-02423-0000 

030-02421-0000 

030-0131 1-0000 

030-01393-0000 

030-01393-0001 

030-01393-0000 

030-01393-0001 

030-03039-0001 

047-10407-0002 

EFFECTIVITY: 

STANDARD PART 

NUMBER 

MS3338-6839 

M39029157-354 

M39029157-354 

M39029157-354 

M85049138-17W 

D38999126WE35PN 

M39012116B0004 

M39012116B0004 

M85049139-17W 

D38999126WD97PN 

M85049138-13W 

D38999126WA35SN 

M85049138-13W 

D38999126WA35SN 

M85049138-13W 

D38999126WC35PN 

M39012/16B0004 

M39012I16B0004 

M85049152S 14N 

M83723-75R1407N 

M3902915-115 

M39029132-259 

M39029132-259 

M39012116B0004 


EFFECTNITYICOiVIiVlENTS 



CAT A OPTION 

CAT A OPTION 

CAT A OPTION 

CAT A OPTION 

CAT A OPTION 

CAT A OPTION 4-TUBE EFIS 





OPTION 

OPTION 

RADAR OPTION 

RADAR OPTION 

RADAR OPTION 

RADAR OPTION 



RADAR OPTION 

RADAR OPTION 

RADAR OPTION 

RADAR OPTION 

RADAR OPTION 

RADAR OPTION 

RADAR OPTION 

KRA 405 

KRA 405 

KRA 405B 

KRA 405B 

OPTION 

OPTION



I 

PANEL 

. 

REFERENCE 

DESIGNATOR 

P520X 

P520X 

P525AI 

P525AI 

P525A2 

P525A2 

P5401 (AFCS) 

P5401 (AFCS) 

P5401 (AFCS) 

2P5401 (MFD) 

2P5401 (MFD) 

2P5402 (MFD) 

2P5402 (MFD) 

P54All 

P54A21 

P5B I 

P5B1 

P5B1 

P6 

P601 

P63 1 

P63 1 

P631 

P63 1 

P632 

P6301 

P6301 

P6301 

96751 

P6751 

P6751 

P675 1 

P7 

P825 

P826 

P871 

P871 

P872 

P872 

P872 

P90B I 

P90B1 

P9OBI 

P90B1 

P90B2 

P91l 

PAC l 

PC1 

PC2 

PC3 

PMSTRI 

PMSTRI 

PMSTRZ 

PMSTRZ 

PN1 

PTBARI 

PTBARI 

R GEN FIELD 

R GEN FIELD 

R GEN FIELD 

S6 

S7 

S900 

TBlOO 

TB100-K 

TB100-K 

TBIOO-L 

TB100-L 

TB100-M 

TB100-M 

TB100-N 

TB100-N 

TBIOO-P 

TB 100-P 

TB100-R 

TB 100-R 

TB100-S 

TBIOO-S 

TB100-T 

TB100-T 

TBIOO-U 

TB 100-U 

TBIOO-V 

TB100-V 

TB100-W 

TB 100-W 

TBIOO-X 

TBIOO-X 

TBlOl 

EFFECTIVITY: 

DESCRIPTION 

SCREW 

SCREW 

CONNECTOR 



CONNECTOR 


CONNECTOR 


SOCKET CONTACT, 20 GAUGE 

CONNECTOR 

SOCKET CONTACT, 20 GAUGE 

RF CONNECTOR 

RF CONNECTOR 


STRAIN RELIEF 

CONNECTOR 

RF CONNECTOR 

RF CONNECTOR, BNC RT ANGLE 

CONNECTOR 


CONNECTORHOOD 

SCREW 

RF CONNECTOR 


CONNECTOR 


LEVER & PIVOT ASSY 


CONNECTOR 

SCREW 

RF CONNECTOR 

RF CONNECTOR 

RF CONNECTOR 

CONNECTOR 


RF CONNECTOR 

FERRULE 

CABLE ASSEMBLY 



CONNECTOR 


RF CONNECTOR 

RF CONNECTOR 

RF CONNECTOR 

RF CONNECTOR 

RF CONNECTOR 

RF CONNECTOR 

STRAIN RELIEF 

CONNECTOR 

STRAIN RELIEF 

CONNECTOR 

RF CONNECTOR 

CONNECTOR 


PIN CONTACT 

REMOTE CONTROL CB, 10A 

INSULATOR BOOT 

SWITCH, TOGGLE 

SWITCH, TOGGLE 

SWITCH, DPDT 

TERMINAL BLOCK RAIL 


SOCKETCONTACT 


SOCKETCONTACT 












SOCKETCONTACT 


SOCKETCONTACT 


SOCKETCONTACT 




SOCKETCONTACT 

TERMINAL BLOCK RAIL 


HONEYWELL 

PARTNUMBER 

089-05903-0008 

089-06008-0006 

030-02153-0000 

030-02154-0000 

030-02154-0000 

030-02178-0000 

010-00068-0026 

030-02563-0000 

030-01284-0000 

030-01157-001 1 

030-01 175-0010 

030-01157-0011 

030-01175-0010 

030-00266-0002 

030-00108-0000 

010-00068-0026 

030-01477-0001 

030-033 15-0001 

030-00465-0000 

030-00459-0000 

030-01094-0056 

030-01 107-0001 

088-00752-0000 

089-06541-0000 

030-00465-0000 

030-01 157-0011 

030-01 173-0000 

030-02351-0002 

030-01060-0000 

030-01062-0000 

030-02181-0000 

089-06541-0000 

030-00465-0000 

030-00459-0000 

030-00101-0002 

030-01094-0051 

030-01 107-0001 

030-00101-0000 

076-01042-0001 

200-02586-0000 

010-00135-0000 

030-01157-0011 

030-01 176-0000 

030-01428-0000 

030-00101-0002 

030-00134-0001 

030-00465-0000 

030-00465-0000 

030-00465-0000 

030-00465-0000 

030-01475-0002 

030-03308-0005 

030-01475-0001 

030-03308-0003 

030-00465-0000 

030-01076-0000 

030-01 153-0000 

030-01462-0000 

036-00151-0001 

150-00102-0000 

03 1-00222-1001 

03 1-00222-1002 

03 1-00222-0026 

030-01482-0010 

030-0331 1-0001 

030-01459-0000 

030-0331 1-0005 

030-01459-0001 

030-0331 1-0004 

030-01459-0001 

030-0331 1-0004 

030-01459-0001 

030-0331 1-0004 

030-01459-0001 

030-0331 1-0004 

030-01459-0001 

030-0331 1-0004 

030-01459-0001 

030-0331 1-0003 

030-01459-0001 

030-0331 1-0001 

030-01459-0000 

030-0331 1-0003 

030-01459-0001 

030-0331 1-0004 

030-01459-0001 

030-0331 1-0004 

030-01459-0001 

030-01482-0010 

STANDARD PART 

NUMBER 

M39029132-259 

M85049141-IOA 

M3 106B18-9S 

M39012/16B0004 

M39012116B0004 

M39012/16B0004 

~39012116~0004 

M39012116B0004 

M39012116B0004 

M39012116B0004 

M85049138-15W 

D38999126WD18SN 

M85049138-13W 

D38999126WC8SN 

M39012116B0004 

M3902911-101 

M83383102-03 

MS25171-IS 

M8 1714160-20-02 

M39029122-I92 

M8 1714160-22-06 

M39029122-191 

M8 1714160-22-04 

M39029122-191 

M81714160-22-04 

M39029122-191 

M81714160-22-04 

M39029122-191 

M8 1714160-22-04 

M39029122-191 

M81714160-22-04 

M39029122-191 

M8 17 14160-22-02 

M39029122-191 

M81714160-20-02 

M39029122-192 

M81714160-22-02 

M39029122-19 1 

M81714160-22-04 

M39029122-191 

M81714160-22-04 

M39029122-191 

98-10-00 


OPTION 

OPTION 

OPTION 

OPTION 

MFD OPTION 

MFD OPTION 

MFD OPTION 

MTD OPTION 





Page 11 

Revision AD


PANEL 

I 

REFERENCE 

DESIGNATOR DESCRIF'TION 

TBIOI-P 


TB101-P 


TBIOI-R 


TBIOI-R I SOCKET CONTACT 

TB101-S 


TB101-S 


TB101-T 


TB101-T 


TBIO1-U TERMINAL BLOCK 

TB101-U SOCKET CONTACT 

TB101-V 


TB101-V SOCKET CONTACT 

TB101-W TERMINAL BLOCK 

TB101-W SOCKET CONTACT 

TB101-X 


TBIOI-X 


T-BAR 

TRIM RELAY 

LEDEX 

TRIM SWITCH 

APISAS 

LOW A/S LENS 

ANNUNCIATOR 

PANEL 

APISAS 

REPLACEMENT LAMP/BULB 

ANNUNCIATOR 

PANEL 

I 

HONEYWELL 

PARTNUMBER 

030-033 1 1-0007 

030-01459-0000 

STANDARD PART 

NUMBER 

M8 1714160-20-03 

M39029122-192 


OPTION 

OPTION 

OPTION 

OPTION 



4-TUBE EFIS OP'I'ION 


CAT A OPTION 

Page I 2 

Revision AD 


BENDIXIKING" IFRAVIONICS IKFC goo 


PI31 

FIRE/OVERHEAT CONTROL 

- 

14 HZ2822 3 (B&j& N&gj+K DETECTOR) 

4 HZ28223 ------------------------- 3 

PI28 REF 

19iE-----A 

r---------------------- 

- - - - - - - - - - - 

LlOC12 3 - - - - - - - - - - - - - - - - - - - - - ~610' 

7 -->-' - 

r FORWARD CB PANEL 

xl I I 

I 

I 

K5 REF 

I 

LANDING LIGHT RELAY 

I 

I 

I 

REF 

A655 

LIGHT DIMMER PWR SUPPLY 

14 L40B22 3 A INST LT PWR (CH 3) 

1 -- 

26 

C2B223 

C2822 3 

---mi 

A612 FWD INTCON PNL 

PI72 REF 

r----------------- 

REF TB1 -5 ~6757 

TERMINAL BOARD (AVIONICS) I 

-AMS4354A22N 3- 7 

! 

I REF TBI-6 

A675 

1 TERMINAL BOARD(AVIONICS) 1 

I 

I 

I 

REF TB1-7 

REF 

SHEET NOTES 

S/N 900-00010 THRU 900-00051 

S/N 900-00052 & SUBSEQUENT 

MOO 2 OR EARLIER HARNESS WlTH KX 165 

MOD 3 OR LATER HARNESS WlTH KX 165A 

OR AIRCRAFT MODIFIED BY 159-081 40-201 3 

Modifications to Basic Aircraft Wiring 

Page Il(2 blank) 

Revision AD

BENDIX/KING@ IFRAVIONICSI KFC goo 


I F~RWARD C8 PANEL 

I 

AIR DATA 

I 2BVDC RIGHT 1ADC-100A22 H 1ADC-100822 

I 

BUS 

1ADC-101A22 J ~Blol-~@ 

1ADC- 105A22 

+28VDC POWER 

28VDC LIGHTING HI 

KAV 485 ALT/VSI 

KDC 481T 

1 AIR DATA COMPUTER klil GBOl K 

I 

IADC-101B22 

1ADC-109A22N 

E KDC 481T RACK 

I 

GBOl L 

GBOl M 

1ADC-107A22N 

1ADC-108A22N 


POWER GROUND 

CHASSIS GROUND 

LIGHTING LO 

485 429 XMTR 1A 

485 429 XMTR 10 

481 429 INST 1 XMTR A J* 

481 429 INST 1 XMTR B M 

-W 

I IB 

f 

1ADC- 103A22 

485 429 RCVR 1A 

485 429 RCVR 10 

481 FLT CTRL RCVR 

A I L-: 

481 FLT CTRL RCVR 8 PP N 

REF AFCS PAGE 11 

rn 

20 FT RESOLUTION 

STRAP COMMON 

K ALT ALERT AUDIO HI 

REF AUDIO PAGE 45 

ALT ALERT AUDIO LO 

REF CAT A OPTION PAGE 1214~ 

TEMP PROBE HI 

TEMP PROBE LO 

OVERSPEED WARNING 

(GND = OVERSPEED) 

> 50 KNOTS 

(GND = >50 KNOTS) 

I I P4801 

GG 

1ADC-11 lA22 

REF CAT A OPTION PAGE 121 

PI72 REF 

XPDR ALTITUDE A1 CC 1ADC-114A22 44 

XPDR ALTITUDE A2 

XPDR ALTITUDE A4 

XPDR ALTITUDE 01 



XPDR ALTITUDE C1 




XPDR ALTITUDE COMMON 

1 

TEMP PROBE 

TEMP PROBE HI 

TEMP PROBE LO 

REF A612 

FWD INTCON PANEL 

ADC GEN PUR 429 XMTR A 

ADC GEN PUR 429 XMTR B 

TB100-L 

-w w - 

P90B1 

KLN 900 GPS 

I 10 ADC- 113822 

9 AIR DATA 429 RCVR A 

.A, 1 8 AIR DATA 429 RCVR B 

481 FLT CTRL XMTR A 

481 FLT CTRL XMTR 0 

KCP 520 AFCS COMPUTER 

AIR DATA 429 RCVR A 

AIR DATA 429 RCVR A 

AIR DATA 429 RCVR B 

AIR DATA 429 RCVR 8 

P5201 

AIRCRAFT EFFECTIVITY CODES 

S/N 900-00052 &. SUBSEQUENT WITH CATEGORY A INSTALLATION 

MOD 2 AND EARLIER HARNESSES ONLY 

MOD 3 OR LATER HARNESSES ONLY. 

KAD 480T Digital Air Data System 

Page 31(4 blank) 

Revision AD

BENDIXlKlN6" IFR AVIONICS 1 KFC goo 


E~ECTRICAL LOAD CENTER 

I 

AOF 

1J300 1P300 

I 28VOC AVIONICS@%?- 

RIGHT 1AOF-1 OOA22 -- U 

I BUS cBB5 

I 

I 

I 

AOF REF 

I 

NO. 2 SG 465 


NO. 1 SG 465 


26VAC 400HZ REF 1 HI 101 

26VAC 400HZ REF 1 LO 74 

AOF 1 28VOC SUPERFLAG 76 

ADF 1 OC SIN HI 77 

AOF 1 DC COS HI 64 

AOF 1 OC SIN/COS LO 63 

I\ 

U 

- 1 I lB 

A w 

-a 

lAOF-lOlB22 

' 

PlOO JlOO 

1AOF-106822 

8 . 

A W w- 

110 

BI I- Z! 

1 I 0 

1ADF-104022 

0, I 

: , I0 

Y_ g Y 

-h\r @ -$- GB03 C 

I 

28VOC AOF SUPERFLAG 

OC SIN HI 

OC COS HI 

DC SIN/COS 

REFERENCE 

PART OF ,-TUBE 

CONFIGURATION ONLY 

rh - 0 

KA 448 AOF ANTENNA 

P44B1 

GB03 J 

REF AUDIO SHEET 20 

1AOF-1 lOA2N,?- 1 

TOP/BOTTOM ANTENNA 

AIRCRAFT GROUND 



AIRCRAFT GROUNO 


1 28VDC LIGHTING HI 

lo AOF AUOlO HI 

WHlTE RE0 

ANTENNA POWER 1 A WHITE RED 

ANTENNA POWER 

WHlTE GREEN1 1 

LOOP ENABLE 2 I :;liE GREEN 

LOOP ENABLE 

WHITE1 I 

':,H;/;~: :EE I 1 WHITE ORANGE WHITE ORANGE1 I 32HZ < +/-go OEG 

1 1 WHITE BLUE WHITE BLUE1 1 :5 

32HZ < 0 OEG 

GROUNO 

1 AOF-200A RF INPUT 

KR 87 Automatic Direction Finder 

Pane - 5/(6 blank) 

Revision AD

BEAlDIXlKING" IFRAVION~CSI KFC goo 


I 


POWER GROUND 

+5VOC POWER OUT 

DATA 

ENABLE 

CLOCK 

P5202 

AFCS- 100022 

AFCS-100E22 

AFCS- 106A20N 

3PCFG 

' " POWER 

- A-lOlA22 

AFCS-102A22 

AFCS- 103A22 

53 AFCS- 104A22 4 CLOCK 

GROUND AFCS- 105A22 2 GROUND 

KCP 520 CONFIG MODULE 

------------------- 

~6201 

ELECTRICAL LOAD CENTER I 

FLT OIR 

I 

28VDC AUX I 

AFCS- 100A22 

AFCS- 100A22 

AFCS- 100C22 

ESSENTIAL 

BUS 

AFCS- 100F22 M* 

N* 

AFCS-100D22 M* 

N' 

GBOl@- AFCS- 1 O9A22N P* 

Q* 

GBO1@- AFCS-111A22N G* 

I 

I 

p54d 

GBOl @- AFCS-112A22N -1 H* Sol LSB 

TBlO1 -T @- 

TB101 -V @- 

AFCS-113A22 

AFCS- 1 13A22 

KMS 540 

AUTOPILOT MODE SEL PNL 1 

+28VDC POWER 

+28VOC POWER 

+28VOC POWER 

+28VOC POWER 

POWER GROUNO 

POWER GROUNO 

LIGHTING LO 

28VOC LIGHTING HI 


-W 

I IB 

- 

AFCS CTRL 429 XMTR A 87 

I l -w 

AFCS CTRL 429 XMTR B 59 

&- 

AP ENGAGE 64 

SCAS ENGAGE 106 

I 

PERFORMANCE STRAP P2 1 71 1- AFCS-283A22N -@GBO~ 

AFCS DISCONNECT AUDIO HI 

., 

AFCS DISCONNECT AUDIO LO REF AUDIO PAGE 45 

AFCS OISCONNECT AUDIO HI 

2l 

AFCS DISCONNECT AUDIO LO 66 

1 62 1- 

AFCS- 1 14A22 

-11 IS AFCS-115A22 

AFCS- 116A22 

AFCS- 11 OA22 

AFCS- 117A22 

PRE-FLIGHT TEST 77 AFCS- 1 18A22 

(GROUND = TEST) 1 

1 

REF PAGE 13 

MSP CTRL 429 XMTR A 

MSP CTRL 429 XMTR B 

AFCS CTRL 429 RCVR A 

AFCS CTRL 429 RCVR B 

AP ENGAGE 

SAS ENGAGE 

LAMP TEST 

ROLL TRlM LEFT 1 

ROLL TRlM RIGHT 1 

PITCH TRlM UP 1 

PITCH TRlM DOWN 1 

I , I AP/SAS TEST SWITCH I 

POWER GROUNO w- 

KA 172 

/ ANNUNCIATOR BOX 

KMS 540 LAMP TEST 

I 

AFCS-123A2ON -@~B09 

S/N 900-00010 THRU 900-00051 ONLY 

S/N 900-00052 & SUBSEQUENT ONLY 

S/N 900-00052 & SUBSEQUENT WITH CATEGORY A INSTALLATION 

KFC 900 AFCS Mode Selector, Configuration Module and Flight Director Switching 

Page 7/(8 blank) 

Revision AD

BENBIX/KIAle;b IFRAVIONICSI KFC goo 



P5202 

AFCS- 120B22 

1 

15 

FLIGHT DIRECTOR L/R 

KA 172 

ANNUNCIATOR BOX 

PI 722 

TB100-V A AFCS- 124A22 A 

1 TB100-V C AFCS- 125A22 

1 

NO. 1 SG 465 


1 FLT SIR RIGHT/rrn L21 J L AFCS-120022 - 

AFCS- 120C22 

GBOZR 

w 

AFCS-126A22 

AFCS-127A22 

AFCS-128A22N 

AFCS-120F22 

AFCS- 120A22 

j-7:~ 

B/NC 

REF PAGE 1 5 i 

B/NO 

C/NC 

REF PAGE 29 4 1 0 

KFC 900 AFCS Flight Director Switching (4-Tube Configuration Only) 


Revision AD

RENDIXIKING" IFRAVIONICSI KFC 900 


NO. 2 SG 465 

AFCS- 129A22 

P481T1 

KDC 481T 


AFCS- 130A22 

wr. 

01 I 

T 

I 

-w 

I 1 18 AFCS- 130D22 

T 

I I 

AFCS- 129C22 

J900D 

NO. 1 EFS 429 RCVR A 

NO. 1 EFS 429 RCVR 0 

ADC 429 RCVR 2A 

ADC 429 RCVR 1A 

ADC 429 RCVR 10 

ADC 429 RCVR 20 

AHRS 1 429 RCVR A 

AHRS 1 429 RCVR 0 


AHRS 2 429 RCVR 0 

1 

P5202 

AFCS 2 3 

AFCS RS232 COMMON 14 

AFCS RS 232 RXD 25 

1 

REF RADAR ALTIMETER PAGE 99 OR 101 

AFCS-132A22 

P5203 

PART OF 4-TUBE 


1 EFS 

NO. 1 SG 465 


VF- 

EFS GENERAL 429 XMTR A 0 34 

AFCS- 130022 

AFCS- 131 022 

KFC 900 AFCS Sensor Inputs 

Paae 111112 blank)



DIODE NOT PRESENT ON MOD 2 OR LATER AFCS HARNESS. 

1 1 1 LAFCS-214622 

AFCS-213622 

W n 

I 

@ 

Wn 

" 

p54d 

C 

D 

A 

6 

@+ 

KMS 540 

AUTOPILOT MODE SEL PNL] 

ROLL TRlM LEFl 1 

ROLL TRIM RIGHT 1 

PITCH TRlM UP 1 

PITCH TRlM DOWN 1 

KFC 900 AFCS Pitch and Roll Trim switching (T-BAR Relay Scheme) 

Paae 131l14 blank)



I A601 

I FORWARD CB PANEL 

CIA22 3 - 

AFCS-145C22 - 

I 

J2 PI28 

4 

I 2BVOC RIGHT 

6 

BUS AFCS-145E22 ---- 21 

I 

- 

L---------------------2~ 

- AFCS-284A22 

---- AFCS-285A22 

L REF F'AGE 19 

FLIGHT DIRECTOR L/R 

SWITCH 

r 7 

AFCS-145F22 --- 03 REF EXISTING WlRE + -- 

16 

02 AFCS-289A22 

3 

AFCS-286A22 REF EXISTING WlRE + -- 

4 

REF EXISTING WIRE -- 

5 

C2 

AFCS-290A22 

AFCS-287A22 

19 

FO LEFr 83 REF PAGE 29 

REF PAGE 9 82 -1 REF PAGE 121 a 

20 

REF PAGE 1211 81 

A3 -$- 

A2 

J142 (REF) 

5~500 AP ENGAGED RELAY 5~500 REF EXISTING WIRE+ - -'Z 

FWD~ 

n 

A6 

RH CYCLIC 

SYNCH 


AFCS- 178F20 

(GND=ENGAGEO) 

AFCS-29 1A22 

A7 

LH CYCLIC 

REF EXISTING WlRE 

+ REF EXISTING WlRE 

+ REF EXISTING WlRE 

16- - REF EXISTING WIRE 

p-ElL:l REF PAGE 29 


LEOEX SWITCH SCHEME ONLY 

KFC 900 AFCS Autopilot Engage (4-Tube Configuration Only) 


Revision AD



r--------------------- 

A601 


L--------------------- 

J142 (REF) 

REF EXISTING WIRE+ - -% 

REF EXISTING WIRE+ - - 16 

AFCS-284A22 3 

AFCS-285A22 REF EXISTING WIRE - - 4 

AFCS- 145E22 REF EXISTING WlRE + - - 5 

REF PAGE 31 

i 

: 

19 

20 

+ 

A6 

RH CYCLIC 

. 

SYNCH 

A 

AFCS- 178F20 

AFCS-291A22 

- REF EXISTING WlRE 

S/N 

900-00052 & SUBSEQUENT WITH CATEGORY A INSTALLATION 

LEOEX SWITCH SCHEME ONLY 

KFC 900 AFCS Autopilot Engage (2-Tube Configuration Only) 


Revision AD

BENDIX/KINGd IFR AVIONICS I KFC goo 


(MATES WITH 

AFCS PITCH TRlM DRlVE IN -( 

PTBAR I ) 

JTBAR 1 

F 

N 

AFCS-141822W 

AFCS-1410220 

pgOIO 

LEDEX TRlM SWITCH 

CYCLIC PITCH TRlM DRlVE IN -( 

R 

X 

- AFCS- 143822W 14 

n 

- AFCS- 1430228 17 

115 

AIRCRAFT GROUNO -( 

PITCH TRlM MOTOR POWER RETURN -( 

CYCLIC PITCH TRlM DRIVE OUT -( 

AFCS PITCH TRlM DRlVE OUT 4 

DL 

F* 

T 

z 

D - 

L 

18 

AFCS-146822N 20 

AFCS- 140822 

AFcs-13mzzw wi 

13 1 

AFCS- 1390220 16 

AFCS- 138822W 

AFCS-1380220 

1 

AFCS ROLL TRlM DRlVE IN -( 

E - AFCS- 159822W 24 

M 

AFCS-1590228 

CYCLIC ROLL TRlM DRlVE IN -( 

P 

W 

AFCS- 163822W 

AFCS-1630220 

AIRCRAFT GROUNO -( 

ROLL TRlM MOTOR POWER RETURN -( 

CYCLlC ROLL TRlM DRlVE OUT -( 

AFCS ROLL TRlM DRlVE OUT -( 

C I AFCW 6DW2W w] 2; 

K I AFCS- 1600228 

TRlM CONTROL RELAY 

8K500 

8K500 

----------------------- I: t-" 

' A601 

I FORWARD C8 PANEL 

I 

I 28VOC RIGHT 

I 

I 

BUS 

3 

CIA22 3 

AFCS- 145C22 

AFCS-145E22 

--------- - 

/ AFCS- 144822W 

I I NORMALLY CLOSED 

INTERRUPTER $ 

KFC 900 AFCS Roll and Pitch Trim Switching (LEDEX Switch Scheme) 

Pane 19/(20 blank)

BENDI'XlKIN6" IFR AVIONICS 1 KFC goo 


KCP 520 AFCS COMPUTER P5202 NO. 2 KSM 575 

2P5751 ROLL LINEAR ACTUATOR 

LVOT+ 2 

-nw 

LVOT- 19 ! ; ;: AFCS- 152A22 

I V ~ T r 7n 

IVOT c 

ROLL LVOT EXCITATION HI 34 - z: 

AFCS-153A22 

ROLL LVDT EXCITATION LO 11 R LVDT EXCITATION LO 

@ 

N G 

SHIELD 

D 

AFcs-154A22 C BRAKE LO 

PlTCH MOTOR DRIVE HI 58 

PlTCH MOTOR DRIVE LO 59 

LVDT + 

I 

LVDT - 

LVDTC 

PlTCH LVDT EXCITATION HI 

PlTCH LVDT EXCITATION LO 

PITCH BRAKE HI 

PlTCH BRAKE LO 

35 

12 

22 

G: 

m 

6 

G: 

36 

+ @ 

ROLL BRAKE HI 6 -W 

ROLL W E LO hj 

I I IB 

I lo 

P5203 

3 ,: 

12 

@ 

iB 

d 

-3 AFCS-133A22 

AFCS- 134A22 

AFCS- 135A22 

AFCS- 136A22 

A 

P5751 

B I 

K 

V 

M 

N 

2P500 

MOTOR DRIVE HI LO 

SHIELD 

NO. 1 KSM 575 

PlTCH LINEAR ACTUATOR 

INNER SHIELD 

OUTER SHIELD 

SHIELD 

ROLL POSITION SYNCHRO 

SIN LO 

26VAC EXCITATION HI 

26VAC EXCITATION LO 

ROLL POS SIN HI 38' G: 

ROLL POS COS HI 22 

ROLL POS SIN/COS LO 23 

lo 

AFCS-165A22 

@ Ilk- AFCS-166A22N 

PITCH POS SIN HI 25 

z: 

PITCH POS COS HI 39 

lo 

PITCH POS SIN/COS LO 24 

II~- 

AFCS-147A22 

AFCS-148A22N 

P500 

PlTCH POSITION SYNCHRO 

TBIO~-U@ G: 

AFCS- 150H22 

TBIO~-U(+~ 

11,AFCS-149A22N 

KFC 900 AFCS Linear Actuators and Pitch and Roll Synchros 

Page 21/(22 blank)



CP 520 AFCS COMPUTER 

THRUSTER DRIVE HI 

THRUSTER DRIVE LO 

THRUSTER BRAKE HI 

THRUSTER BRAKE LO 

P5203 

64 

65 

22 

23 

nz 

@ 

GB07 M 

AFCS- 168A22 

AFCS-169A22N 

n! AFCS- 170A22 

@ 

1 P572 1 

1 P5722 

KSA 572 

DIRECTIONAL SERVO 

MOTOR DRIVE HI 

MOTOR DRIVE LO 

SHIELD 

BRAKE HI 

BRAKE LO 

THRUSTER CLUTCH HI 

THRUSTER CLUTCH LO 

24 

25 

n! AFCS- 172A22 

@ GB07 P AFCS-280A22N 

I I I REF EXISTING 

ROLL STRING POT RETRACT 

ROLL STRING POT WIPER 

ROLL STRING POT EXTEND 

11 

BLK- 

10 AFCS-28lA22 

WHT- 

34 REO- 

ROLL SPRING CARTIDGE 

STRING POT 

RETRACT 

WIPER 

EXTEND 1 

PITCH STRING POT RETRACT 32 

PITCH STRING POT WIPER 46 

PITCH STRING POT EXTEND 20 - 

AFCS-28.22 

w- 

BI I 

01 1 

RED- 

BLK- 

WHT- 

RETRACT 

WIPER 

EXTEND 

YAW FLY THRU DETENT 

P5201 

92 AFCS-171A22 

KSC 573 YAW SPRING 

CARTRIDGE DETENT SWITCH 

GB07 H 

AFCS- 175A22N 

r--------------------- 

MASTER SWITCH PANEL^ 

REF PAGE 25 PMsTRiI_ AP/sAs MASTER I 

AFCS- 178C20 AFCS- 178A20 H 3 ON 

QCo2 

I 

AFCS- 178020 AFCS-178020 G I 

I 

Bo I 

REF PAGE 55 OR 17 

I 

I 

J H G 

TBlO1-V D LTG-112A22 U 40 I 

TB100-U M L K 

OFF 

I 

GB03 K 

LTG- 113A22N 

T 

AFCS- 178E20 + 

+ AFCS-178C20 AFCS-178A20 -+ I 

AFCS-177020 t I 

AFCS- 178020 + AFCS-177020 E I 

AFCS-178F20 ------I -&- I 

20 GAUGE L---------------------~ 

+ AFCS-178020 r--------------------- 

~ 6110 

1ADC-507A20 + I FORWARD CB PANEL I 

PI31 J1 1 


AFCS-177A20 

AFCS- 177C20 

. . 

L---------------------J 

I 

TERMINAL BLOCK TB1 IS INSTALLED INTO THE EXISTING A674 RAIL. 

FIGURE BELOW REPRESENTS PHYSICAL LAYOUR OF A674 TB1 

I 

KFC 900 AFCS Master Switch, String Pots, Directional Servo and Spring Cartridge 

Paae 231124 blank1

BEAIDIXIKMG" IFR AVIONICS I KFC 900 


KA 172 


PI722 

P0107 AP/SAS ANNUNUNCIATOR 

PANEL 

I AP/SAS PANEL TEST 137 1 AFCS-180A22 -1 1 I PRESS-TO-TEST 

I 


P5202 

TB100-T 

M 

REF AVIONICS FANS PAGE 63 

REF INVERTER PAGE 71 

AFCS- 179A22 

E203 

AP ON ANNUNCIATE 

I 1 38) AFCS-185A22 

FAN FAlL ANNUNCIATE 

INV FAlL ANNUNCIATE 

DAY/NITE POWER 

PITCH FAlL ANNUNCIATE 

ROLL FAlL ANNUNCIATE 

YAW FAlL ANNUNCIATE 

REF PAGE 121 t-I 

LOW A/S ANNUNCIATE 

(GNO=ENGAGEO) -1 1 AP ON ANNUNCIATE 

3 

I 

SAS ON ANNUNCIATE 50 

(GND=ENGAGED) 

AFCS-186A22 

SAS ON ANNUNCIATE 

AP FAIL ANNUNCIATE 40 

AFCS-184A22 

VSCS FAlL ANNUNCIATE 

(OPEN=VALIO GNO=FAIL) 

SAS FAlL ANNUNCIATE 

5 AP FAlL ANNUNCIATE I 

I 

VSCS FAlL ANNUNCIATE 72 

(OPEN=VALID GNO=FAIL) 

1 K ~OO AP/SAS FAIL RELAY 

I I I 

SAS FAIL ANNUNCIATE 74 

(GND=VALID OPEN=FAIL) 

PEDAL POS SIN HI 20 

PEDAL POS COS HI 21 

PEDAL POS SIN/COS LO 37 

I 

I 

I 

AFCS-187A22 

AFCS- 188A22 

AFCS- 189A22N 

AFCS- 190A22 

TB100-U 8 AFCS- 178E20 

AFCS-191A20 

nz 

AFCS-200A22 

Go 

@ IIP- AFCS-201A22N 

1 

1 

G 

82 

C2 

D2 

03 

0 1 

C3 

C 1 

83 

8 1 

3P500 

- 

. 

4 

- 

3- 

A1 -A 

PEDAL POSITION SYNCHRO 

Y 

-W 

COLLECTIVE POS SIN HI 19 

SIN LO 

COLLECTIVE POS COS HI 35 I 

COLLECTIVE POS SIN/COS LO 36 

- W 

LoL 

I 16 

AFCS-150E22 


@ 

I v 


I 

-W 

26VAC SCAS/AP REF HI 33 

26VAC SCAS/AP REF 

- 

-1 

COLLECTIVE POSITION 

4P500 

SYNCHRO 

r--------------------- 

1 

A620 

I ELECTRICAL LOAD CENTER 

AFCS-203A22 

I SAS/AP REF 2J300 2P300 

26VAC 400HZ AFCS-150A22 lib- AFCS-204A22N G 

I 

AFCS- 150C22 

TBlD1-U 

I 

I 

AFCS- 150822 

I E5 E AFCS-150J22N 

AFCS- 150D22 

AFCS- 150F22 



I 

I 

lib- AFCS-205A22N 

REF PAGE 71 

I 

SIN LO 

SIN HI 

COS HI 

COS LO 

1 '1 

KFC 900 AFCS Pedal and Collective Synchros and Mode Annunciation 

Page 25/(26 blank)

BENDIXIKINNG" IFRAVIONICSIKFC 900 


r--------------------- 

A612 FWD INTCON PANEL 

' I 

T84-5 

REF 

I T120A24 3 - TI20824 3 -- 

I 

I 

I 

,(REF) 

2K500 

I AFCS-199022 AFCS-199A22 & 

I AFCS-194A22 A3 

I 

I 

I 

I 

I 

AFCS- 194022 

1 

I 

KCP 520 AFCS COMPUTER ~5202 

I/-----x------------lT 

I . r G B O ~ ~ Y 

- 

VSCS RELAY 

P5203 

7 

VSCS m E HI 52 c: 1 1 ; w- 

AFCS- 196A22 81 1 

VSCS ENGAGE LO 53 

@ 

I ; 

GB08 

I ; I 

A AFCS-247A22N 

VSCS POSITION HI 33 

z: AFCS- 192A22 W A 

VSCS POSITION LO 30 

Yk 

- 

81 I 

L---- RVSCS32B22 3 ---fl- --- 

RVSCS30A22 3 -- + + --- 

RVSCS5A22 WHT 5 -L L -- RVSCS6A22 BLU 5 - 4 t --- 

---- ----- RVSCS7A22 WHT 5 - ---- 

;;;EA.OR 1 

- - - - - - - - - - RVSCS8A22 BLU 5 - I - - - - 

V 

R VSCS FAlL 

(FAIL = GROUND) 1 

KFC 900 AFCS and Right Side VSCS Switching 


Revision AD

BENDIX/KINGw IFRAVIONICS 1 KFC goo 


KFC 900 AFCS Cyclic and Collective Switches (4-Tube Configuration Only) 

Page 291(30 blank)

BENDIX/KINGGe IFR AVIONICS I KFC goo 


NO. 2 KRG 333 

TRlAXlAL RATE AND 

C 

ACCELERATION SENSOR 2P3331 

POWER GROUND 20' AFCS-250A22N 

POWER GROUND 

PlTCH RATE (OUT) 

PlTCH RATE (REF) 

21 

13 

14 

AFCS-251A22N 

-W 

' IB AFCS-252A22 

e4 

C\W 

TEST INPUT (GND = TEST) 17 

AFCS-254A22 -1 

RATE VALID #1 (O/G) 18 

1 114 W- I 

P5201 


PlTCH RATE 2 HI 

ROLL RATE 2 HI 

ROLL/PITCH RATE 2 LO 

ACCELERATION SENSOR 

- 

-W 

LATERAL ACCEL (OUT) 5 

' IB AFCS-225A22 

LATERAL ACCEL (REF) 6 

NORMAL ACCEL (OUT) 7 

NORMAL ACCEL (REF) 8 

LONGITUDINAL ACCEL (OUT) 

LONGITUDINAL ACCEL (REF) 

8 

-W 

IB 

@ 

AFCS-226A22 

RATE TEST OUTPUT 

RATE 1 VALlO 

ACCEL 1 VALlO 

LATERAL ACCEL 1 HI 

LATERAL ACCEL 1 LO 

NORMAL ACCEL 1 HI 

NORMAL ACCEL 1 LO 

NORMAL ACCEL 1 HI 

NORMAL ACCEL 1 LO 

ROLL RATE (OUT) 

ROLL RATE (REF) 

PlTCH RATE (OUT) 

PlTCH RATE (REF) 

YAW RATE (OUT) 

YAW RATE (REF) 

POWER GROUND 

POWER GROUNO 

+28VOC POWER 

+28VDC POWER 

- w 

a 

I 10 -4 

AFCS-231A22 

AFCS-232022 

YAW 

31 YAW RATE 1 HI 

M E 1 LO 

P5202 

55 RATE 2 VALID 

57 SAS/AP ALERT POWER^ 

r--------------------- 

AFCS-232A22 

28 M630-100A22 

~601' 

FORWARD CB PANEL I 

WARN AUDIO 

I 

S/N 900-00010 THRU 900-00051 ONLY 


rn PART OF CATEGORY A INSTALLATION ONLY 

I 

PI31 J1 

r--------------------- 

- 

AFCS-232A22 

AFCS-233C22 

AFCS-233A22 

L---------------------J 

~ 6d 

0 

FORWARD CB PANEL I 

AP/SAS ALERT I 

g~P:~~:f~~ 

BUS I 

I 

AP/SAS ACCEL I 

28VDC LEFT I 

i 

KFC 900 AFCS Rate and Acceleration Sensors 


Revision AD



-W 

MSU A A I IB 

MSU B 0 

MSU C 

- 

B .zO 

1AHRS-115A22 

MSU A 

MSU B 

MSU C 

NO. 2 SG 465 


AHRS 429 XMTR 1A 

AHRS 429 XMTR 10 rn 

NO. 1 SG 465 

I SYMBOL GENERATOR h4652A P 1 O E O O I 


AHRS 429 XMTR 28 


TB100-R 

1AHRS-118822 


CONFIGURATION ONLY. 

1AHRS-118C22 

4 GROUND = AIRBORNE I 

NO. 1 LCR-92 AHRS 

Pane 35/(36 blank)

BENDIXIKlNG" IFR AVIONICS I KFC goo 



I 

I AHRS 2 

2J300 2P300 

I 

2AHRS-100A22 

I 

I 

AHRS 2 AUX 

1J300 1P300 

I 1 28:~&~:;@p 2AHRS-101A22 

I 

BUS 

L---------------------J 

SWITCH PANEL 

PO 102 

GB06 B 

GB06 C 

2AHRS-100B22 

2AHRS-101822 

2AHRS- 102A22N 

2P921 

2AHRS- 103A22N 12 

NO. 2 LCR-92 

+28VOC PRIMARY POWER 

+28VOC PRIMARY POWER 

+28VOC AUX POWER 

+28VOC AUX POWER 

PRIMARY POWER GROUNO 

PRIMARY POWER GROUNO 

AUX POWER GROUND 

AUX POWER GROUNO 

AHRS 

11 

22 

OG 1 @ 

zO-P-- 

0 3 

5,P4 

0 6 

SLVD 

CCW 

2 -1 

- 1 3 

OlSC REF 28VOC RETURN 

GROUNO OlSC REF 

OG MODE SELECT 

SLEW CW 

SLEW CCW 

I 

NO. 2 KMT 11 2 

FLUX VALVE 

EXCITATION HI 

EXCITATION LO 

2P1121 

5 

cw 

2 4 

A 6 

-1 H E ' c! , 2AHRS-114A22 

-W 

MSU A A 

MSU B 0 I: 2AHRS-115A22 

MSU C B , 

- 

1 

PARITY 

SYSTEM NO. 2 

PROGRAM PIN 

MSU REF HI OUT 

MSU REF HI IN 

MSU EXCITATION HI 

MSU EXCITATION LO 

NO. 2 SG 465 


2P46528 



NO. 1 SG 465 

SYMBOL GENERATOR 1 P4652B P 1 0 ~ 0 0 




P5201 

No. 2 LCR-92 AHRS (4-Tube Configuration Only) 

Paae 37/(38 blank)

BENDIXIKINI;" IFRAVIONICSI KFC goo 


NO. 2 SG 465 


2P4652B 

NO. 1 AHRS 1/2 SWITCH 

KA 172 

PI 722 

TB100-T A 2AHRS-128A22 

ANNUNCIATOR BOX TB100-T C 2AHRS- 129A22 

NO. 2 AHRS L TEST 24 

NO. 2 AHRS R TEST 23 GBOl F 2AHRS-130A22N 

NO. 1 AHRS L TEST 22 2AHRS-131A22 

NO. 1 SG 465 


1 P4652B 

AHRS Switching (4-Tube Configuration Only) 


Revision AD

BENDIX/KINGB IFRAVIONICSI KFC 900 


1 FORWARD CB PANEL 

I 

ANNUN PWR 

I 28VOC RIGHT 

I 

I 

ANN-101A22 

I 

KA 172 


PI721 

/ +2BVOC OAY/NIGHT POWER / 1 ANN-lOlC22 

DAY SELECT 2 ANN-103A22 

NIGHT SELECT 

TB100-K 

REFERENCE AVIONICS COOLING 

FANS, PAGE 63 

GB03 Y 

11 ~ 

A6 

DAY 

ANNUN 

TFT 

1 1 

VISIBLE WHITE VOLTAGE REF 

VISIBLE WHITE 16V SEL 

VISIBLE WHITE 18V SEL 

OEAOFACE VOLTAGE REF 

OEADFACE 11V SEL 

DEAOFACE 13V SEL 

VISIBLE WHITE LEGENO PWR 

DEAOFACE LEGENO PWR 

VISIBLE WHITE LEGENO PWR 

a DEAOFACE LEGENO PWR 

POWER GROUNC 

CHASSIS GROUNC 

GROUNC 

ANNUNCIATOR TEST 

NO. 1 CMPST TEST 

NO. 2 CMPST TEST 

NO. 1 AHRS L TEST 

NO. 1 AHRS R TEST 

NO. 2 AHRS L TEST 

NO. 2 AHRS R TEST 

GPS CRS SEL L TEST 

GPS CRS SEL R TEST 

GPS CRS OBS TEST 

GPS CRS LEG TEST 

GPS APR ARM ANNUN/TEST 

GPS APR ARM IN 

GPS APR ACN ANNUN/TEST 

: 

23 

:i 

28 

27 

15 

16 

13 

1 REF AHRS SWITCHING PAGE 39 

REF KLN 900 GPS PAGE 67 



- REF KLN 908 GPS PAGE 69 

- REF KFC 900 AFCS PAGE 9 

-REF KFC 900 AFCS PAGE 25 

- REF KFC 900 AFCS PAGE 7 

- REF CAT A PAGE 121 

Annunciator Lighting Power Supply (4-Tube Configuration Only) 


Revision AD

BENDIX/K/NG0 IFRAVIONICS I KFC goo 


A652 REF 

AUDlO PANEL (AMS 43) 

COMM 1 MIC AUDlO H 

COMM 1 MIC AUDlO LC 

COMM 1 MIC KD 

COMM 1 AUDlO H 

COMM 1 AUDlO LC 

NAV 1 AUDlO H 

NAV 1 AUDlO LC 

COMM 2 MIC AUDlO H 

COMM 2 MIC KEI 

COMM 2 MIC AUDIO LC 

COMM 2 AUDlO H 

COMM 2 AUDlO LC 

P502 REF 

GS109-A 

r----------------- 

I 

I 

~67? 

TERMINAL BOARD (AVIONICS) I 

TB1-8 

I 

; ! 1 NAV- I 40A22 

V 

I 

I 

TB1-8 

I GBD3 @- 1 NAV-141A22N 

TB1-8 

I 1B 

I 

V 

, 

4 

1 NAV- 142A22 

I 

I 

1 TB1-7 TO, -n I 

I TB1 -8 I 

- - - - - _ - - - - - - --I_ _ _ - ; ! 

I 

lNAV-l43A22 -dHd 

1 NAV-144A22 

V I 

I 

I 

I TB1-9 I GB03 @- 1 NAV- 145A22N 

I 

I 

P501 REF I I 

TB1-9 

I 

-" 

I 1B 2NAV- 10DA22 

I---- - - 1 

25 

I 

I 

I 

TB1-9 

I GB03 @- 

2NAV-101A22N 

532 REF I 

I 

TB1-9 

NO. 1 KX 165/KX 165) 

NAV/COML 

COMM MIC AUDlO HI 

COMM MIC KEY 

COMM AUDlO HI 

COMM AUDlO LO 

REMOTE COMM TRANSFER 

1 REMOTE COMM TRANSFER I 

COMM AUDlO HI 

COMM AUDlO LO 



NAV 2 AUDlO HI 

NAV 2 AUDlO LO 

8 

27 

NAV AUDlO HI 

NAV AUDlO LO 

ADF AUDlO HI 9 

I 

P871 

KR 87 ADF RCVR 

MARKER AUDlO 

MARKER AUDlO 

I I 

P6751 KMR 675 MARKER RECEIVER 

P631 

DME AUDlO HI 

DME AUDIO LO 1 

KN 63 DME 

1 P4652B 

NO. 1 SG 465 


S/N 900-00052 Br SUBSEQUENT WITH CATEGORY A INSTALLATION 

THE KX 165 USES PIN R FOR XFER. THE KX 165A USES PIN 23 

rn PART OF 4-TUBE CONFIGURATION ONLY 

I M630-lO2A22 -u 

2P465A 

SYMBOL NO. GENERATOR 

1 SG 465 

RALT-106022 -k1 OH ALERT 

I 

OH 

DB SYSTEMS MODEL 630 

AURAL WARNING GENERATOR 1 

ALERT 

I 

Audio System (Sheet 1 of 2) 

Paae 431144 blan kl

BENDIX/KlNG@ IFRAVIONIGSIKFC 900 


= t 

- -w 

I 

Aw 

I 10 

- 

KCP 

1AUD-103A22N S GB03 

1AOC-104A22 

AFCS-119A22 

P4851 

P5201 


ALTITUDE ALERT AUDIO HI 

ALTITUDE ALERT AUDIO LO 

J' 


520 AFCS COMPUTER 

l a 

#2 DIRECT AUDIO HI 

#2 DIRECT AUDIO LO 

08 SYSTEMS MODEL 630 

p6d AURAL WARNING GENERATOR I 

S/N 900-00052 8r SUBSEQUENT WITH CATEGORY A INSTALLATIONS 

Audio System (Sheet 2 of 2) 

98-40-00 

- 


Revision AD

NO. 2 SG 465 


DME 1 RETURN 95 

DME 1 DATA 180 

IDME-lllD22 

1OME-109D22 

1 DME-108D22 

1 DME-107D22 



r 

KN 63 DME 

GB05 G 1DME-101A22N 11 i% 

GBD5 H 1 DME- 102A22N 1 POWER GROUND 

A POWER GROUND 

,-. 

t4 

1 DME- 1D5D22 

NO. 1 SG 465 

IDME-106A22N 

1DME-107C22 1 DME-107822 1 OME-107A22 6 DMEDATA 

DME 1 RETURN 1 DME-108A22 12 GROUND 

TB100-M 

DME 1 SYNCH 82 

I D M E - 1 0 9 C 2 2 4 IDME-109022 11 DME- DME- 1109A22 1 OA22N 

D DME REQUEST 

GB05 L 

1 DME- 1 12A22N 

1 DME-113A22 1 

4 SUPPRESSION HI 

IDME-200A 

DME ANTENNA 

P601 

CI-105-6 

DME ANTENNA 

A803 

P824 (REF) TRANSPONDER (KT 70) 

GB03 W 

1DME-114A22N 

KN 63 Distance Measuring Equipment (Sheet 1 of 2) 

98-40-00 

Page - 471(48 blank) 

Revision AD



r------------------------- 

1 

I 

OME 

I 28VOC RIGHT 

1 ~~~~s:zp- 1 DME- 1 OOA22 1OME-100022 

I 

C095 

P0102 

DME HOLD SEL SWITCH 

OME HOLD SEL RELAY 

1 K63 

1 OME- 120A22 

KN 63 Distance Measuring Equipment (Sheet 2 of 2) 

Pane 49/(50 blank)

BENDIXIKING" IFRAVIONICSIKFC goo 


NO. 1 SG 465 


AD1 +27.5VDC FLTRO PWR 

AD1 GROUND 

AD1 GROUND 

AD1 GROUND 

AD1 +85VDC POWER 

A01 +30VDC POWER 

A01 -3DVDC POWER 


AD1 -15VDC POWER 


AD1 -7VDC P E R 

A01 DISPLAY UNIT FAULT 

AD1 VlDEO RED HI 

AD1 VlDEO RED LO 

I 

I 

AD1 VlDEO GREEN HI 

AD1 VlDEO GREEN LO 

AD1 VlDEO BLUE HI 

AD1 VlDEO BLUE LO 

AD1 MODE HI 

AD1 MODE LO 

A01 X DEFLECTION HI 

AD1 X DEFLECTION LO 

A01 Y DEFLECTION HI 

AD1 Y DEFLECTION LO 

26 

27 

53 

54 

EADl POWER GROUND 91 



@ 

1EAOI-113A22 

W^ 

I 

NO. 1 ED 462 EADl 

+27.5VDC FILTERED POWER 

GROUNO 

GROUNO 

GROUND 

+85VDC +30VOC POWER 

-30VOC POWER 

+15VDC POWER 

-15VDC POWER 

+7VDC POWER 

-7VDC POWER 

DISPLAY UNIT FAULT 

VlDEO RED HI 

VlDEO RED LO 

1 EAOI- 1 14A22 

;: 37 VlDEO BLUE HI 

22 VlDEO BLUE LO 

1EAOI-115A22 

W-I a I 

@ 4sI I 

I 

@ 

@ 

41 VlDEO GREEN HI 

40 VlDEO GREEN LO 

I 

I 28 MODE HI 

27 MODE LO 

-W 

I IB 1 EAOI- 1 17A22 

; 43 Y DEFLECTION HI 

44 Y DEFLECTION LO 

1 EAOI-122A22N 



@- 

~~101-T 

GBOl @-. 

DISPLAY DOWN 

DISPLAY DOWN RETURN 

BRIGHTNESS RETURN 

BRIGHTNESS HI 

I 

1EADI-121A22 


1 EADI- 120A22N LIGHTING LO 

1P4701 

NO. 1 CP 470 

CONTROL PANEL 

TBlO1 -T @-. 1CP-100A22 -/14 1 28VOC LIGHTING HI 

I 

GBOl 6- 

GBO1@- 

1CP-101A22N 

1CP-102A22N 

REF RADAR ALT PAGE 99 OR 101 4; 

6 

11 

LIGHTING LO 

RAD ALT TEST RETURN 1 

RAD ALT TEST RETURN 2 

A01 BRIGHTNESS HI 

AD ERIGHTNESS LO 

RAD ALT TEST 1 

RAO ALT TEST 2 

I 

REF SHEET 53 

+28VDC EADl POWER 

+28VDC EAOl POWER 

+28VOC EADl POWER 

RT EFlS MASTER 

92 1 EADI- 125A22 

SWITCH 

JMSTRl 

3 

r 

PMSTRI 

1 EAOI- 126822 

I FORWARD CB PANEL ! 

I 

28VDC RIGHT I 

1 EAOI-126A22 ESSENTIAL I 

I 

+28VOC EHSl POWER 

+28VDC EHSl POWER 

+28VDC EHSl POWEfi 

1P4651A 

1 EHSI-145A20 

22 GAUGE 1 EHSI-145820 

I 

28VDC LEFT L 1 EHSI-144620 1 EHSI-144A20 ESSENTIAL I 

I 

No. 1 EFS 40(Sheet 1 of 3) 

Page 51/(52 blank)

@ 



NO. 1 SG 465 


1P4652B 

CONTROL PANEL OH SEL 1 70 

CONTROL PANEL OH SEL 2 97 

CONTROL PANEL OH W 84 

CONTROL PANEL RETURN 57 

1 EHSI-103822 

CONTROL PANEL MODE 1 




CONTROL PANEL HEADING 1 

CONTROL PANEL HEADING 2 

CONTROL PANEL COURSE 1 


98 

71 

85 

58 

86 

59 

99 

72 

+ 

1EHSI-106A22 

1EHSI-107A22 

1EHSI-108A22 

1EHSI-109A22 

- IEHSI-110A22 

IEHSI-11 lA22 

IEHSI-112A22 

IEHSI-113A22 

1P4651A 

TBlOl-T 0 1 EHSI-104A22 

GBOl E 

1EHSI-105A22N 

1P4611 

& 

7 

8 

9 

10 

11 

12 

15 

14 

5 

4 

NO 

CP RETURN 

28VOC LIGHTING HI 

LIGHTING LO 

MODE 1 

MODE 2 

MODE 3 

MODE 4 

HEADING 1 

HEADING 2 

COURSE 1 

COURSE 2 

1 ED 461 EHSl 

HSI +27.5VDC 

FLTRD PWR 7 IEHSI-115A22 

10 

IEHSI-116A22 

11 

1EHSI-117A22 

23 

IEHSI-118A22 

93 

IEHSI-119A22 

79 

1EHSI-120A22 

12 

1EHSI-121A22 

66 

1EHSI-122A22 

25 

1 EHSI- 123A22 

52 

1EHSI-124A22 

39 

1EHSI-125A22 

78 

1EHSI-126A22 

HSI GROUND 

HSI GROUND 

HSI GROUNO 

HSI +85VDC POWER 

HSI +3OVDC POWER 

HSI -30VDC POWER 

HSI +15VOC POWER 

HSI -15VOC POWER 

HSI +NOC POWER 

HSI -7VDC P E R 

HSI DISPLAY UNlT FAULT 

HSI VlDEO RE0 HI 

HSI VIDEO RE0 LO 

28 

29 

2: 1 EHSI-127A22 W; 

@ 

B@ 

1 

2 

19 

36 

34 

33 

49 

17 

50 

16 

48 

42 

39 

38 

+27.5VOC FILTERED POWER 

GROUND 

GROUND 

GROUND 

+85VDC POWER 

+3OVDC POWER 

-30VOC POWER 

+15VDC POWER 

-1 5VDC POWER 

+7VDC POWER 

-7VDC POWER- 


VlDEO RED HI 

VIDEO RE0 LO 

I 

1 

I 

I 

EHSI-129A22 :;; 

37 VIDEO BLUE HI 

22 VlOEO BLUE LO 

I I@ G/ 

HSI MODE HI 15 ;: 

1 EHSI-130A22 z; 28 

MODE HI 

HSI MODE LO 16 

2 7 LO 

HSI X DEFLECTION HI 82 

~z 

1EHSI-131A22 

HSI X DEFLECTION LO 96 

I I@ 1 

W- 

1 EHSI-132A22 

' 43 Y DEFLECTION HI 

44 Y DEFLECTION LO 

& 

.. .---. . 

A01 PITCH SYNCH h 1SG-109B22 1 1 

I COMPOSITE I 22 I I I I - 

KA 172 


PI722 

TB100-T D 1 EHSI-140A22 

NO. 1 CMPST TEST 25 

1EHSI-141A22 

SIN 900-00052 

& SUBSEQUENT ONLY 

G B O ~ ~ 1EHSI-142A22N 

No. 1 EFS 40 (Sheet 2 of 3) 

Page 53454 blank)

BEMDIXIKING" IFRAVIONICSI KFC goo 


NO. 1 SG 465 


1P4651A 

26VAC 400HZ REF 1 H 

26VAC 400HZ REF 1 LC 

RAOAR ALTIMETER H 

RAOAR ALTIMETER LC 

RAOAR ALTIMETER VALlC 

REF WOAR ALTIMETR PAGE 99 OR 101 

1 P4652A lJFAN PFAN 

NO. 1 SG COOLING FAN 

FAN POWER HI 102 1SG-107A22 FAN HI 

FAN POWER LO 101 1 SG- 108A22 FAN LO 

SG CONFIG GROUND 103 

1 SG- 100A22 

SG CONFIG POWER 104 

1SG-101A22 

SG CONFIG CLOCK 64 

1 SG- 102A22 

SG CONFIG CR2 105 

1 SG- 103A22 


1 SG- 104A22 

SG CONFIG DATA IN 92 

1 SG- 105A22 

SG CONFIG DATA OUT 91 1 SG- 106A22 

it,"," 1 :;: :%: :," 

EF," 1 :;: :," :< 

1 REF NO. 1 AHRS PAGE 35 

1 REF KLN 906 GPS PAGE 67 

1;: :," I it 1 REF NO 1 KX l65/165A COMM/NAV PAGE 75 OR 77 

REF KN 63 OME PAGE 47 

REF NO. 2 EFS 40 PAGE 61 rn 


Cot 

PART OF ROR 2000 V 

1 P4652B 

1 REF AHRS PAGE 37 rn 

REF AHRS SWITCHING PAGE 39 

1 REF KLN 906 GPS PAGE 67 

COMM/NAV PAGE 79 OR 81 

REF KFC 900 AFCS PAGE 11 

EFS 1 429 XTALK XMTR P 

$1 REF NO. 2 EFS 40 PAGE 61 rn 

EFS 1 429 XTALK XMTR E 

No. 1 EFS 40 (Sheet 3 of 3) 


Revision AD



NO. 2 SG 465 


AD1 +27 5VDC FLTRD PWR 

A01 GROUND 

AD1 GROUND 

AD1 GROUND 

A01 +85VDC POWER 


AD1 -3DVDC POWER 


A01 -15VDC POWER 


AD1 -7VDC P E R 

AD1 DISPLAY UNIT FAULT 

AD1 VIDEO RED HI 

A01 VlDEO RED LO 

2P465 1 B 

8 

102 

90 

89 

79 

66 

11 

52 

12 

39 

25 

17 

13 

14 

I I, 

z: 

@ 

2EADI-113A22 

2EADI-115A22 

AD1 X DEFLECTION HI 67 fi: 

2EADI-116A22 

AD1 X DEFLECTION LO 68 

'I 

I @$ 

W-I 

NO. 2 ED 462 GE 

+27.5VDC FILTERED POWER 

GROUNO 

GROUNO 

GROUNO 

+85VDC POWER 

+3DVDC POWER 

-30VDC +15VOC POWER 

I 

-15VOC 

POWER 

VlDEO RED HI 

VlDEO RED LO 

41 VlDEO GREEN HI 

40 VlDEO GREEN LO 

28 MODE HI 

I 

27 MODE LO 

a I 




ZEADI-122A22N 

2EADI-123A22N 

2EADI-124A22N 

DISPLAY DOWN 

DISPLAY DOWN RETURN 

BRIGHTNESS RETURN 

BRIGHTNESS HI 

REF RADAR ALT SHEET 99 OR 101 11 

i :- 

REF PAGE 59 

6 

11 

10 

9 

1 

2 

AD1 BRIGHTNESS HI 

AD1 BRIGHTNESS 

LO 



DECISION HEIGHT SELECT 1 

DECISION HEIGHT SELECT 2 

DECISION HEIGHT 

RETURN 

I 

I 

r------------------ 

1 

LT EFlS MASTER 

SWITCH 

I 

PMSTR2 JMSTRZ 

ON 

+28VDC EAOl POWER 

3 JMSTRZ I PMSTRP 

2EAOI- 125A22 

H 

2 . 

+28VDC EADl POWER 

A 

93 2EADI-125022 G 

1 F I 

B 

+28VDC EADl POWER 106 I 

2EADI-126822 

2EAOI-126D22 

2P30( 

2EADI- 126A22 

2EADI-126C22 

~6201 


I 

I 

I 



+28VOC EHSl POWER 

GAUGE 

GAUGE 

GAUGE 

OFF 

No. 2 EFS 40 (Sheet 1 of 3) (4-Tube Configuration Only) 

Paae 571158 blank)



NO. 2 SG 465 

2P4652B 


2P4701 NO. 2 CP 470 

CONTROL PANEL 

CONTROL PANEL DH SEL 1 70 

CONTROL PANEL DH SELA 97 

CONTROL PANEL DH ON 84 

CONTROL PANEL RETURN 57 


TB101-T G 2EHSI- 104A22 

GB02 D 

2EHSI- 105A22N 

2P4611 

/;;; 

NO 2 ED 461 

CP RETURN 


LIGHTING LO 

2EHSI- 106A22 9 MODE 1 

2EHSI- 107A22 10 MODE 2 

2EHSI- 108A22 11 MODE 3 

2EHSI- 109A22 12 MODE 4 

2EHSI-110A22 15 HEADING 1 

2EHSI-111A22 14 HEADING 2 

2EHSI-112A22 5 COURSE I 

2EHSI-113A22 4 COURSE 2 

7 

8 

HSI +27.5VDC FLTRD PWR 

HSI GROUND 

HSI GROUND 

HSI GROUND 



HSI -3OVDC POWER 


HSI -15VDC POWER 


HSI -7VDC P E R 

HSI DISPLAY UNlT FAULT 

HSI VlDEO RE0 HI 

HSI VlOEO RED LO 

+30VDC POWER 

+15VDC -30VDC POWER 

-15VDC POWER 

+7VDC POWER 

-7VDC POWER 


VlDEO RED HI 

VlDEO RED LO 

I 

2EHSI-130A22 

HSI VlOEO GREEN HI 

HSI VlOEO GREEN LO 

HSI VlDEO BLUE HI 55 

G: 2EHSI-129A22 

HSI VlDEO BLUE LO 56 

:; 

HSI X DEFLECTION HI 82 

;: 

HSI X DEFLECTION LO 96 

HSI Y DEFLECTION HI 

HSI Y DEFLECTION LO 

69 

70 

a,.. I I 

@ 

: 

2EHSI-131A22 

;: 2EHSI-132A22 

& 

VlDEO GREEN HI 

VlOEO GREEN LO 

37 VIDEO BLUE HI 

22 VlDEO BLUE LO 

28 MOOE HI 

27 MOOE LO 

(24 I 

X DEFLECTION HI 

' 46 X DEFLECTION LO 

43 Y DEFLECTION HI 

' 44 Y DEFLECTION LO 

1 5 

a 

EHSl POWER GROUND 90 





2EHSI-136A20N 



J141 (REF) I KI PITC&;:~F 1 

2P4652.4 

A01 PITCH SYNCH 85 2SG-109822 

COMPOSITE 22 I 

1 1 

1 

~ 1 7 2 


PI722 

TB100-V 

G 

NO. 2 COMPOSITE SWITCH 

S/N 900-00010 THRU 900-00051 ONLY 

S/N 900-00052 h SUBSEQUENT ONLY 

NO2 


98-40-00 

- 


Revision AD

BENDiX/KINGd IFRAVIONICSIKFC~QO , 


10. 2 SG 465 

YMBOL GENERATOR 

AOF 1 DC SIN HI 

AOF 1 DC COS HI 

ADF 1 DC SIN/COS LO 

ADF 1 28VOC SUPERFLAG 

26VAC 400HZ REF 1 HI 

26VAC 400HZ REF 1 LO 

2P4651A 

101 

74 

REF KR 87 AOF PAGE 5 

RADAR ALTIMETER HI 

RAOAR ALTIMETER LO 

RAOAR ALTIMETER VALID 

FAN POWER HI 

FAN POWER LO 

SG CONFIG GROUND 103 

2SG-100A22 

SG CONFIG POWER 104 

2SG-101A22 

SG CONFIG CLOCK 64 

2SG- 102A22 


2SG- 103A22 

SG CONFIG CRl 106 

2SG- 104A22 

SG CONFIG DATA IN 92 

2SG- 105A22 

SG CONFIG DATA OUT 91 2SG- 106A22 

LJbAN WAN 

2P4653 

FAN HI 

FAN LO 

NO. 2 SG COOLING FAN 

NO. 2 CONFIG MODULE 

1 CONFIG GROUNO 

5 CONFIG POWER 

6 CONFIG CLOCK 

9 CONFIG CR2 

2 CONFIG CR1 

4 CONFIG DATA OUT 

8 CONFIG DATA IN 

I 

DME 1 CLOCK 94. 

OME 1 DATA 80 

OME 1 RETURN 195 I I 

DME 1 HOLD 

FLT OIR L E F T m 

EFS 2 429 XTALK RCVR A 

EFS 2 429 XTALK RCVR B 

2SG-109A22 

1 P4652B 

NO. 1 SG 465 


EFS 1 429 XTALK XMTR A 

EFS 1 429 XTALK XMTR 8 

EFS 2 429 XTALK XMTR A 

EFS 2 429 XTALK XMTR B 


AHRS 2 429 RCVR B 

A$,":!: 

WI:~:: A; 

:?j: l: 

;$ Ag 

OH SELECT OUT 

t: ; :?j: :ER Ag 

WX CONTROL 429 RCVR A 

WX CONTROL 429 RCVR 8 

Eg ; :; 4;: ;: 

WX 453 RCVR A 

WX 453 RCVR B 

\ 

48 r;; 

2SG- 11 OA22 EFS 1 429 XTALK RCVR A 

2 1 EFS 1 429 XTALK RCVR 8 

90 

104 

88 

ig 

9 

35 

22 

49 

1 REF AHRS PAGE 37 

1 REF AHRS SWITCHING PAGE 39 

1 REF KLN 90B GPS PAGE 67 

1 REF AUDIO PAGE 43 

REF NO. 2 KX 165/165A COMM/NAV PAGE 79 OR 81 

1 

REF RDR 2000 WX RADAR PAGE 105 OR 103 


rn PART OF RDR 2000 WEATHER RADAR OPTION ONLY 

u 


98-40-00 

- 

Pane 61/(62 blank) 

Revision AD



r--------------------- 

A620 1 


I 

lJ300 1P300 

- 3JFAN PFAN 

GB09 E 

FANS-1 00F20 

FANS- 103A22N 

FAN HI 

FAN LO 

KCP 520 COOLING FAN 

I 

I 

2 8 ~ 0 RIGHTrji" 

GENERATOR 

BUS 

' 

1 7 GB02 

H 

FANS- 100B20 

FANS-lOlA22N 

FANS- 109A22 

FANS-1 08A22 

NO. 1 KA 33 COOLING FAN 

1 P331 

KLN 900 

n 

5 FAN FAlL OUT 

(FAN FAlL = +28VOC) 

1 +28VOC MONITOR POWER^ 

FANS- 107A22 

FANS- 100020 

NO. 2 KA 33 COOLING FAN 

1 

2P331 

PEDESTAL AVIONICS 

+28VOC MONITOR POWER^ 

1 3 1 +28VOC FAN POWER 

FANS-102A22N 

FANS-1 04A22 

(FAN FAlL = +28VOC) rn 

PO107 AP/SAS ANNUNCIATOR PANEL 

FANS-105A22 -1 12 1 FAN FAIL ANNUNCIATE I 

17 

NO. 3 FAN FAIL RELAY 7~500 rn 

,:'r 

- E-\r 

NO. 2 FAN FAlL RELAY 6~500 

FANS- 105822 

FANS-1 17A22N 

A 

A1 

,. X 1 

FANS- 11 SAP2 

X2 

+ 

- 1 

FANS-105C22 1 18A22N --a GBOB 

GBOB 

SJFAN 5PFAN rn rn LH BOT INSTRUMENT PANEL 

COOLING FAN 

3 a 

FANS-1 13A22 

FAN HI 

GB02 W FANS-1 14A22N 

a BLACK 

- FAN LO 

FANS-120A22 

FANS- 1 1 lA22 

FANS-1 12A22N 

1 I 

a 5-7. 

BLACK 

BLUE 

FAN LO 

FAN MONITOR 

(OPEN = FAN FAIL) 

4JFAN 4PFAN 

RH BOT INSTRUMENT PANEL 

COOLING FAN 

FAN HI 

BLACK 

FAN LO 

BLUE 

RH FWD INSTRUMENT PANEL 

COOLING FAN 

FAN HI 

FAN LO 

FAN MONITOR 

(OPEN = FAN FAIL) 

PART OF 4-TUBE CONFIGURATION ONLY 

MOO 1 OR EARLIER CNI HARNESS ASSEMBLIES ONLY 

NOT PART OF MOO 2 OR LATER CNI HARNESS ASSEMBLIES 

Avionics Cooling Fans 


Revision AD

BENDIX/KING@ IFRAVIONICSIKFC goo 


r--------------------------- 

, A61 2 FWD INTCON PANEL 

J2 REf 

r 

1 

LTG-101B22 

PEDESTAL LIGHTING 

) KAV 485 LIGHTING HI 

REF SHEET 4 

KI 206 LIGHTING 

REF SHEET 41 

LTG- 100822 

S900 

NORMAL 

AOG-101A22 

AOG- 102A22 

TEST 

, 

GROUNO = ON GROUNO 

2 

AOG- 

GROUND = AIRBORNE 

MOO 2 OR EARLIER CNI HARNESS ASSEMBLY ONLY. 

NOT PRESENT AS PART OF MOO 3 OR LATER 

CNI HARNESS. 

Instrument and Console Lighting and WOW Logic 

98-40-00 

Page - 65466 blank) 

Revision AD

BENDIX/KINGd IFRAVIONICSI KFC goo 


Fb, 

KA 92 GPS ANTENNA 

P12J12 

HORIZONTAL 

NOTAR 

~ 1 1 ~ 1 1 CABIN P90B2 KLN 900 GPS RCVR 

GPS-2OOC GPS-2000 GPS-2OOA - 

r--------------------- 

. A601 1 


I 

I 28VDC RIGHT 

GPS- 100A22 

GPS-100B22 

r--------------------- 

FORWARD CIRCUIT BREAKER PANEL EXTENSION 

I 

28VDC LEFT 

I ESSENTIAL GPS-100A22 GPS-100C22 

BUS 

I m 

RS232 OUT 

+28VDC POWER 

NO. 2 SG 465 


DATA LOADER IN 

DATA LOADER OUT 

LNAV 429 XMTR A 

LNAV 429 XMTR E 

GPS 1 429 RCVR A 

GPS 1 429 RCVR 6 

GB02 J 

GPS-103A22N 

GB02 K 

GPS-104A22N 

REF AIR OATA SHEET 47 

ADC-113022 

POWER GROUND 

ALTITUDE ALERT 

LIGHTING LO 

AIR OATA 429 RCVR A 

AIR OATA 429 RCVR B 

NO. 1 SG 465 


- W I 

I I I 

TB101-T H GPS- 105A22 28 1 2BVDC LIGHTING HI 

JlOO 

REF MFO SHEET 103 OR 105' 

GPS-106D22 

GPS 1 429 RCVR P 

GPS 1 429 RCVR E 

GPS- 106A22 

REF PAGE 123 ' 

GH3000-13E22 

GPS 429 XMTR A 

GPS 429 XMTR B 

l 

429 

LNAV 429 XMTR P 

LNAV 429 XMTR E 

LNAV 429 XMTR 

x"R AM- 

B 20 

GPS-113B22 

-4 

1 

GPS-113A22 

GPS- 107A22 

PI722 

EFS 429 RCVR A 

EFS 429 RCVR B 

EFS 429 RCVR A 

EFS 429 RCVR B 

KA 172 


30 GPS CRS SEL R TEST 

I I I 

S/N 900-00010 THRU 900-0005 ONLY 

S/N 900-00052 h SUBSEQUENT ONLY 

PART OF 4-TUBE CONFIGURATION ONLY 

rn PART OF KMD 550/850 MFD OPTION ONLY 

PART OF 2-TUBE CATEGORY A INSTALLATION ONLY 

KLN 90B Global Positioning System (Sheet 1 of 2) 

98-40-00 

Page - 67/(68 blank) 

Revision AD



MSG/WPT ANNUN 

KA 172 


PI 722 TB100-V R GPS- 1 17A22 

COP MSG ANNUN/TEST 5 GPS-118A22 

COP WPT ANNUN/TEST 8 GPS-119A22 14 

APR ACTV ANNUNCIATE 

APR ARM ANNUNCIATE 

MSG ANNUNCIATE 

WPT ANNUNCIATE 

14 

16 

6 

7 

GPS- 132A22 

GPS- 133A22 

GPS-134A22 

GPS-135A22 

16 

17 

15 

14 

30 

33 

4. 

KLN 900 GPS RCVR 

APPROACH ACTIVE ANNUN 

APPROACH ARM ANNUN 

MSG ANNUNCIATE 

WPT ANNUNCIATE 

APPROACH 

GPS COURSE W S 

GPS CRS/OBS/LEG 

OBS TEST 

LEG TEST 

GPS-136A22 

GPS- 137A22 

GPS-138A22N 

GPS-139A22 

GPS- 140A22 

TB100-T F GPS-141A22 

TB100-T H GPS- 142A22 

GPS APR/ARM/ACTV 

ARM ANNUN/TEST 

ACTV ANNUN/TEST 

GB02 S 

GPS-143A22N 

GPS- 144A22 

GPS- 145A22 

I 

PO109 

TB100-T L GPS-146A22 13 

GPS- 147A22 

GPS- 148A22 14 

MSG/WPT ANNUN 

I 



KLN 90B Global Positioning System (Sheet 2 of 2) 


Revision AD

BENBIXlKIAl6" IFR AVIONICS 1 KFC goo 


r--------------------- 

I FORWARD CIRCUIT BREAKER PANEL EXTENSION 1 

I 

I 

P9000 J9000 

I 28VDC LEFT 

I ESSENTIAL INV- 100A22 INV- 100C22 

I 

BUS 

L---------------------l 

r--------------------- 

A620 1 


I 

I 1J300 1P300 

I 

I 

LEFT 

BUS 

INV- 100A22 INV- 100822 A +28VDC POWER 

I ADF REF I 

GB05 

I 

@- 

INV-108A22N 

I 

I 

2J300 - 2P300 GB05 @- INV- 103A22N 

INV-101B22 ---- J 

I TI! 

INV-101A22 

~ 5 @ INV-101C22N A K 

I 

I 

I L 

INV- 104A22 

I - 

I 

1 

L---------------------J 

PO107 

ANNUNCIATOR PANEL 

S/N 900-00010 THRU 900-00051 ONLY. 


INV- 106A22 11 

3K500 

G 

82 

C2 

D2 

D3 

- 

D 1 

C3 

C1 

83 

B 1 

A3 

A1 

INV FAIL ANNUNCIATE 

4" 

INVERTER FAIL RELAY 

Q. 

26VAC 400Hz Power 


Revision AD

BEAlDIX/K/~G@ IFR AVIONICS I KFC goo 


I ELECTRCAL LOAD CENTER 

I 

I I 

MKR BCN 

I 28VDC LEFT 

MRKR-100A22 

MRKR-100B22 

I 

REF AUDIO 43 

L-------------------------l 

KN 40 NAV CONVERTER GB06 H R - -1 F 1 AIRFRAME GROUND 

P402 1 

MRKR-103A22 

7 

MRKR- 104A22 

8 

I I 

MRKR- 105A22 

BLUE MARKER LIGHT 

AMBER MARKER LlGHl 

WHITE MARKER LIGHT 

AMBER MARKER LIGHT B 

KA 26 MARKER ANTENNA 

P261 

PHOTOCELL 

PHOTOCELL 

MARKER ANTENNA 

SHIELD 

SWITCH COMMON 

MARKER TEST 

KMR 675 Marker Beacon Receiver 

98-40-00 


Revision AD

BENQIXIKING" IFRAVIONICSI KFC goo 


fl 

NO. 2 SG 465 


NAV 1 429 RCVR A 

NAV 1 429 RCVR B 

2P4652A 

16 

29 

A 

I 

a 

NO. 1 SG 465 

SYMBOL GENERATOR 1NAv-100c22 PlOO JlOO 

I 

MOD 2 OR EARLIER CNI HARNESS ONLY 



NAV 1 429 RCVR A 16 

NAV 1 429 RCVR B 29 

1 NAV-100822 


CATEGORY A INSTALLATION ONLY 

KN 40 NAV CONVERTER P401 

I I 

NAV- 1 OOA22 ' 1 

I ~vL1NAV-101A22N J GB06 

NAV 1 429 XMTR 2A 44 

rn 

A 

NAV 1 429 XMTR 20 45 ' GH3000-10E22 REF GH3000 PAGE 123 rn 

1P1651 

1 :E ::: 1 1 

NAV 1 GS + FLAG 

NAV 1 GS - FLAG 

34 

18 

NAV 1 GS DEVIATION UP 36 

NAV 1 GS DEVIATION + DN 

I ) 1 

NAV 1 COMPOSITE 6 

35 2' 

1 NAV- 105A22 =Il5 

P402 

A 

- 

1 NAV- 1 1 lA22N L GB06 

r 

NAV- 1 1 OA22N f)?) ~ ~ 0 6 

mr 

NO. 1 KX 165 NAV/COMM 

1 NAV- 103A22 17 GS + FLAG 

1 NAV- 104A22 14 GS - FLAG 

16 

GS + UP DOWN 

GB04 A 1 NAV- 106A22N 2 

GB04 B 

1 NAV-107A22 

rn1~1E.52 

I 

NAV 1 TS IN 13 

RNAV REQUEST 14 

1 NAV- 109A22 

1 NAV- 1 17A22 

DME REQUEST 15 - 

1DME-109E22 

- REF KMR 675 MARKER PAGE 73 

AMBER MARKER LIGHT B 31 

WHITE MARKER LIGHT B 130 

+28VDC NAV 2 POWER 36 

+28VOC NAV 2 POWER 37 

NAV 2 IN 25 


POWER GROUND 27 

POWER GROUND 28 

ROTOR C 19 

ROTOR F 21 

GROUND 20 

+28VDC NAV 1 POWER 

I 

REF PAGE 79 

1 DME- 108F22 

1NAV-114818 

I 

,-. 

Y 

GB04 D 

1 DME-105E22 1 3 I CLOCK BUS 

1 NAV- 1 15A22N 

1 DME- 107E22 5 DATA BUS 

0 DME COMMON 

15 AIRCRAFT GROUND 

S AIRCRAFT GROUND 

2 COMM MIC AUDIO HI 

6 COMM MIC KEY 


r* 9 COMM AUDIO HI 

r------------------------ 

, A610 

, ESSENTIAL CB PANEL 

I 28VDC RIGHT 

1NAV-114A18 I 

1 ESSENTIAL^^ 1NAV-114C18 

I BUS CB15 

1NAV-114D18 

L 

NAV AUDIO LO 

1 ' 

No. 1 KX 165 VHF COMMINAV 

98-40-00 


Revision AD

BEHD'/d(KlNG" IFRAVIONICS I KFC 988 


NO. 2 SG 465 

SYMBOL GENERATOR 2P4652A 

El 

U 

NO. 1 SG 465 


1 P4652A 

1 NAV- 100C22 

1 MOO 3 CNI HARNESS OR LATER CNI HARNESS OR MOD 2 OR EARLIER 

CNI HARNESS MODIFIED IN ACCORDANCE WITH WIRING DIAGRAM 

159-081 40-201 4. KX 165A RETROFIT. 

PART OF ,-TUBE 


1 NAV- 100B22 




NAV 1 429 XMTR 2A 44 

NAV 1 429 XMTR 20 1 45 

I 

-L 

1NAV-101A22N 

J GBD6 

GH3000-lOE22 REF GH3OOO PAGE 123 

- 

NO. 1 KX 165A NAV/COMM 

m1P1651 

NAV 1 GS + FLAG 34 1NAV-103A22 7(11 

NAV 1 GS DEVIATION + UP 

NAV 1 GS OWIATION + DN 

RNAV REQUEST 14 

F 

1 E2 3 

NAV 1 GS - FLAG1181 

,,, 1 NAV- 104A22 

36 R: 

35 - 

+fl 

1 NAV- 105A22 

P402 GB04 A 

1 NAV-106A22N - 

7 - 


1 NAV- 107A22 VOR/LOC 

1 NAV- 1 l OA22N K GB06 GB04 B 1 NAV-I 08A22N 

NAV 1 G I N 13 

1 NAV- 109A22 8 ILS ENERGIZE 

COMPOSITE OUT 

RNAV/CHAN REQUEST 

DME REQUEST 15 

1 OME- 109E22 

- 

TB100-M 

25 

28VOC LlGHlTNG HI 

POWER GROUNO 10 

GROUNO 17 

BLUE MARKER LIGHT A 

AMBER MARKER LIGHT A 

WHITE MARKER LIGHT A 

BLUE MARKER LIGHT B 

AMBER MARKER LIGHT B 

WHITE MARKER LIGHT B 



NAV 2 G IN 

NAV 2 COMPOSITE 

POWER GROUND 

POWER GROUNO 

ROTOR C 

ROTOR F 

GROUNO 

9 

7 

8 

29 

31 

30 

36 

37 

25 

32 

27 

28 

19 

21 

20 

1NAV-11 lA22N 

I 

REF KMR 675 MARKER PAGE 79 

I 

REF PAGE 81 

L GB06 

I\ 

U 

GB04 E 

1 DME- 105E22 

1 NAV- 1 15A22N 

1 DME-107E22 

1 NAV- 1 16A22N 

3 

5 

D 

CLOCK BUS 

DATA BUS 

DME COMMON 

GROUND 1 11 

15 AIRCRAFT GROUNO 

+28VOC NAV 1 POWER 1 

S AIRCRAFT GROUND 

+28VDC NAV 1 POWER 2 2 COMM MIC AUDIO HI 

6 COMM MIC KEY 

r------------------------- 

I A610 

ESSENTIAL CB PANEL 

NAV/COMM 1 

I 1 28VDC ESSENTIAL^ 

RIGHT 

I BUS CB15 

1NAV-114A18 

1NAV-114C18 

13 

9 COMM AUDIO HI 


K COMM AUOlO LO 

23 COMM REMOTE TRANSFER 

10 NAV AUDIO HI 

L NAV AUDIO LO 

13 +28VDC POWER 

P I +28VDC POWER 

No. 1 KX 165A VHF COMMINAV 

Page 771(78 blank)

BENDIXIKlN6". IFR AVIONICS 1 KFC goo 


NO. 2 SG 465 


2P4652B 

NO. 1 SG 465 


lP4652B 

KN 40 NAV CONVERTER P403 

I1 

- 

. ,- I 

@ 

PlOO JlOO 

n w 

I 1B 

NAV 2 429 RCVR B 25 2NAV-116B22 

I 

@ 

MOD 2 OR EARLIER CNI HARNESS ONLY 




NAV 2 GS DEVIATION + DN 2NAV- 108A22 

~-1 

15IGS 


2P1651 

14 GS - FLAG I 

-1 7 I GS + FLAG 

+ UP 

16 GS + DOWN 

I 

ROTOR C 19' nW 

ROTOR F 21 

GROUND 20 

2NAV- 124A22 


POWER GROUND 

POWER GROUND 

VOR/LOC 

COMPOSITE IN 

NAV 2 E IN 

+2BVDC POWER 

+28VDC POWER 

VOR/LOC COMPOSITE OUT 

ILS ENERGIZE 

i A601 

I 

FORWARD CB PANEL 

I 

NAV/COMM 2 

I 

2NAV-115A16 

2NAV-115B16 

I 2 w 2NAV-115Cl6 

~ 2NAV-115016 ~ ~ ~ 

I 

CB33 

+28VDC POWER 

+28VDC POWER 



/gl 

COMM MIC AUDIO HI 

COMM MIC KEY 

COMM AUDlO HI 

REF AUDIO PAGE 43 COMM AUDlO LO 

COMM REMOTE TRANSFER 

NAV AUDlO HI 

NAV AUDIO LO 

No. 2 KX 165 VHF COMMINAV 

Page 791(80 blank)



NO. 2 SG 465 


2P4652B 

NAV 2 429 RCVR A 38 

I NAV 2 429 RCVR B 1 25 1 -1 118 

- .. 2NAV- 116B22 

1 MOO 3 CNI HARNESS OR LATER CNI HARNESS OR MOO 2 OR EARLIER 


159-081 40-201 4. KX 165A RETROFIT. 




NAV 2 429 XMTR 1A 

NAV 2 429 XMTR 18 

NAV 2 GS + FLAG 

NAV 2 GS - FLAG 


NAV 2 GS ONlATlON + ON 

ROTOR C 

ROTOR F 

GROUND 

P403 

41' C\W 

42 I IB 2NAV- 1 16A22 1 

34 

18 

19' 

21 

20 

IB 

2NAV-117A22N .-@GBO~ 

NO. 2 KX 165A NAV/COMM 

m 2 ~ 1 6 5 1 

2NAV-106A22 17 GS + FLAG 

2NAV-107A22 14 

2NAV-108A22 -1 

~u 

GS - FLAG 

15lGS 16 + UP DOWN 

ROTOR C 

2NAV-124A22 

3 ROTOR F 

M GROUND 


VOR/LOC 

COMPOSITE OUT 

POWER GROUNO 

POWER GROUND 

NAV 2 E IN 

+28VDC POWER 

+28VDC POWER 

#20 . 

m 

r------------------------- 

I A601 1 

FORWARD CB PANEL 

I 

NAV/COMM 2 

I 

2NAV-115A16 

I 28v\% f,,p= 

2NAV-I 15C16 

I 

CB33 

2NAV-115816 

2NAV-115016 

ILS ENERGIZE 

+28VOC POWER 

+28VDC POWER 

No. 2 KX 165A VHF COMMINAV 


Revision AD

BENDXIKING" IFRAVIONICSI KFC goo 


HORIZONTAL 

STABILIZER 

------- 

r- --- NOTAR 1 

I 

I 

I I CABIN 

CABIN 

KLX135C99 2 - - - - - - - - KLX135A99 2 - - - - 

P840 REF 

NO 

1 KX I ~ ~ / K X 165~ 

NAV/COMM 

COMM ANTENNA 

CI- 1 20 VOR/LOC/GS 

LEFT NAV BLADE ANTENNA 

- 

CI-120 

I 

I 

I 

I 

I 

I 

I 

I 

I 

I 

NAV ANTENNA 

COUPLER 

PAC1 

I 

I 

I 

I 

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I 

I 

I 

I 

I 

I 

PNl JN1 

CABIN 

1P1654 

1 KX165-300A GLIDESLOPE 

200-05647-0019 

1P1655 

1 KX165-203A VOR/LOC ANTENNA 

200-05647-001 6 

P3 

P6 

P5 

3J 

DM H69-1 

OUAORAPLEXER 

NAV COM RCVR 

GLIDE SLOPE RCVR 

COAX CABLES AND COUPLER SUPPLIED WITH ANTENNAS 

CI- 120 VOR/LOC/GS 

RIGHT NAV BLADE ANTENNA 

A 

A 

KX165-2020 

KX165-202A 

200-05627-0005 200-05647-0015 

P7 

ANT 

GLIDE SLOPE REC 

I 

I 

I 

I 

HORIZONTAL I I 2~1654 

STABILIZER 2~x165-~OOA GLIDESLOPE ANTENNA 

KX165-200C 

KX165-2008 

200-05627-0010 200-05627-0009 

A 

I 

I 

I 

I 

I 

I 

I 

I 

I 

PC1 JCl 

1 CABIN 

A 

- 

I 2KX165-203A 

I 

200-05647-001 7 

KX165-200A 

200-05647-0021 

2P1655 

A 

NO 

P4 

COMM ANTENNA 

NAV COM RCVR 

2 KX 165 KX 165A 

nlAv/coMM 

VOR/LOC ANTENNA 

COMMINAV Antennas 


Revision AD



[ f f] 

1 

1NAV-125422 

Wr 

1 NAV- 1 22A22 81 

F GB04 

Wr 

1 NAV-124A22 81 

Wr 

8 1 

L 

7- 1 NAV- 126A22N 

GB04 

- 

Wr 

1 NAV-I 27A22 B I 

. 

CORSE DEVIATION + RIGHT 5 Wr 

1 NAV- 13OA22 8 I 

COURSE DEVIATION + LEFT K 

A 

NAV + FLAG B 1 NAV- 132A22 

NAV - FLAG 1 1 NAV- 133A22 

. 

INAV-131A22N H GB04 

1 NAV- 134A22 

1 NAV- 135A22 

L 

L 

KI 206 COURSE DEVlATlOh 

INDICATOR 

13/0~ RESOLVER 

(0) 

(El 

GS + UP 

GS + DOWN 

GS + FLAG 

GS - FLAG 

COURSE DEVIATION + RIGHT 

COURSE DEVIATION + LEFT 

NAV + FLAG 

NAV - FLAG 

+ FROM 

+ TO 

GBOl N 

1 NAV-136A22N 


GBOl P 

1 NAV-137A22N 

LIGHTING LO 

MOD 2 AN0 EARLIER HARNESSES ONLY 

MOO 3 AN0 LATER HARNESSES ONLY 

~~101-R@ 

~B101-~@ 

1 NAV- 138A22 

1 NAV-138A22 

CR901 



KI 206 NAV 2 Indicator 

Pane 85/(86 blank)

+- 

BENDIXIKING@' IFRAVIONICSIKFC 900 


r------------------------------------------------------------ 

A620 


K5 

W OC BUS FOR 

I AT % P113G1O 3 40 A P113H10 3 

CB36 

I 

- - - - - P54Af6 3- - - - - - - - - - - - - - - - - - - - - 

L GEN FIELD 

I 

TO A601 ESSENTVV 

;~I;~BREAKER P m a 

I 

I 

L----P46C163---- 

REF 

-- L RCCB2422N -41 CB34 

L PWR RLY 

FIRE HRO REF 

EHSl 

I 

I 

I 

2J300 2P300 

Z/WRS-100A22 ---- Y 

L RCCB1A22 - B 

2EAOI-126.420 - S 

2WI-126C20 - T 

I W7-TBI 1EHSI-144M.O --- 

U 

I 

IEHSI-144C20 - V 

I 

I 

AHRS 1 AUX 

I 

P113E12 

C837 

1AHRS-101A22 - R 

I 

I 

ROR R/T 

I 

I WX-100A22 - W 

1 ROR IN0 OR MFO 

I WX-IOIA22 - Z 

MKR BCN 

PI15812 MRKR-100A22 - N 

RIU) bLT 

C886 RAL-1WA22 - X 

P31E20 --- A 

M 

El E 

IW-101C22N 

L 

K 

IW-101B22 - J 

PO115 50115 

EETETAmFfiZLT 7ZOiiTCOLl 

l OVERLAY 

I 

TBIOI-V F LTG-114A22 I 

GB04 W 

LTG-1 15A22N 

I 

I 

L---I-- ----- J 

GENERATOR FIELD 

CONTROL R 

CBIW 

R RCCBIBZZ R RCCB3A22N -.-a GBO3 

I 

AFCS-150A22 ---- H 

AFCS-150022 - G 

lJ300 

IAOF-101A22 -c 

I 

ADF-102A22N ---- R 

I 

FO SYNC 

I 

I 

AFCS-174A22 - X 

AUX LEFT ESS BUS OIR 

I 

I AFCS-10oA22 - F 

I 

MODE SEL 

I 

NCS-1WC22 

I 

- v 

I 

I IN-100A22 - G 

PI16812 

P9WO-104A1 

P9000-103A16 

CB85 

ADF I 

FM I RT 

FM CTRL 

1AOF-100A22 - U 

C5WO-10OA18- 

C5000-114MO---- 

W 

Y 

1P3W 

OME 

P116C1 1OME-100A22 - T 

I 

I 

I 

I 

RCCB2A22N -41 

P1 14E12 

R PWR RLY 

K4 

- P78C16 3- - - - % 0 

BLO AIR HEAT 

H15A22 3 - S 

ELT100-1WUO- 

I 

CB70 Z/WRS-l01A22--- P 

H 

R RCCBlA22 - B 

GENERATOR FIELO 

CONTROL L 

CBlOI 

R GBO3 

FANS-10OA20 

FANS-10OC20 

L 

N 

M 

K 

7 

CB48 

L - - - - pa, 6 3 - - - - - - - - - - - - - - - - - - - - - 

L------------------------------------------------------------l 

R BUS TIE RLY 

K6 

I 

RH OC BUS FOR 

I TO A601 ESSENTN 

P I I 4 G 1 40 0 3 A P114H10 3 -?CIRCUIT BREAKER PANEL 

CB66 

I PAGE 89 

A620 Electrical Load Center SIN 900-00010 thru 900-00051 

Pane 87/(88 blank)

BENDIXIKENG" IFR AVIONICS 1 KFC goo 


r------------------------------------------------------------ 

A60 1 

I ESS CIRCUIT BREAKER PANEL 

P77B22N 3 @ P76822N 3 

I 

I 

J2 PI28 

06A22 3 

FUEL PROBE 

06D22 3 

FUEL 

03A22 3 

-- 

04A22 3 

WlA22 3 

E137A22 3 / 

ESS BUS L 

LTESS-1 812 

AFCS-233A22 

AFCS-233C22 

PITOT HEAT R 

- RTESS-IAI2 CB6 H31A20 3 

FUEL VLV R 

L RTEss-lo12 

2EL5%--, 

ENG FIRE R 

XMSN FIRE 

ESS BUS R 

AP SAS ALERT 

Q5A22 3 

WA22 3 

W3A22 3 

L40A22 3 ;: 

AFCS-232A22 

1 

AFCS-224A22 

AFCS-177A20 

AFCS- 177C20 

1 EHSI-140A20 

1 EHSI-140C20 

3AX- 100A22 

INSTR FLOOD 

10 LVSCSlA20 3 

18 LVSCS3D20 3 

20 LvSCs4020 3 

23 2NAV-115A16 

27 2NAV-115C16 

I 

LOAD PAGE CENTER 87* P113H10 3 

POWER BOX 

PAGE 91- 

I 

I 

I I L 

I 

! 

I 

L------------------------------------------------------------J 

Pll4HlO 3 1 TO A620 ELECTRICAL 

LOAD CENTER 

I 'PAGE 87 

I P38A10 3 I 5 TO A61 0 EXTERNAL 

POWER BOX 

PAGE 91 

A601 Essential Circuit Breaker Panel SIN 900-00010 thru 900-00051 


Revision AD

BENDIX/KlNG" IFRAVIONICSI KFC goo 


r------------------------------------------------------- 

~6 101 

I 

EXTERNAL POWER BOX I 

I 

EXT PWR RLY BATT RLY I 

I 

r----------------- 

K2 

I 

I I A2 

A620 


I 

I 

I 

I 

I 

2J300 2P300 

PI20 J1 

C83 

I 

I 

P31E20 P31 020 P31C20 I 

I 

I 

I 

I 

I 

I 

I 

I 

I 

I I I 

I I r------------ I 

I I TO A601 ESSENTIAL -P38A10 

ESS BUS RLY I 

CIRCUIT BREAKER PANEL I L -P30C10 3- 

I I CR4 

K3 

PAGE 89 I 

A2 

A1 I 

I 

I 

P31A10 3 - -P30B10 3- - - -P30A10 3- - G 

CB78 O 1 

I 

I I I I 

I 

I 

L-------------------------------------------------------J 

I 

I 

I 

I 

Left Hand Auxiliary Essential Bus SIN 900-00010 thru 900-00051 


Revision AD

BNDIIXIKIRIG" IFR AVIONICS 1 KFC goo 


A620 


I 

K5 

I 

LH DC BUS FOR 

% -P113GIO 3- - P113H10 3 -- - 

CB36 

TO A601 ESSENTIAL 

- + CIRCUIT BREAKER PANEL 

REF EXISTING WIRE 

?'" REF 

FIRE HRD REF 

I 25301 

L RCCB2422N -* CB34 2AHRS-100A22 

I 4 

I 

I 

L RCCBlA22 

I 

A1 LINE 

I 

T 

PO115 JO115 

~E~~EKASR-FTEL~~ TONTKO~ 

l OVERLAY 

I 

TB101-V F LTG-1 l4A22 I 

GBO4 W 

LTG-115A22N 

1 bbb I 

L---1-- ----- 1 

I 

I 

I 

I 

I 

I 

I 

P46CI6 3- --- 2WI-126C20 

REF 

I 

1EHSI-144AZO 

P113El2 

RDR IN0 OR MFO 

CB88 

WX-101A22 

I 

I 

REF 

TB2-7/8 

1 AFCS-15OA22 

26VAC 4OOHZ BUS 

4 

AFCS-150822 

R PWR RLY 

K4 

- - - - P78C16 3- - - - y ^ I ^ * d 

I 

R GEN FIELD 

7 

> 

5A -- R RCC82422N -* 

58 

6 

4 

53 

S2 

C B 7 O L 2AHRS-101A22 

Sl 

- 

I 1 REF J6 P378 REF 

L - - - - ,86A16 3- - - - - - - - - - - - - - - - - - - - - 

a 

I 

I 

R BUS TIE RLY 

I K6 RH DC BUS FOR 

I TO A601 ESSENTIAL 

I A;' -P114GlO 3- - P114H10 3 -- 2 +CIRCUIT BREAKER PANEL 

I 

C866 I REF EXISTING WlRE 

I 

I 

I 

L____-___----------------------------------------------------J 

CB47 

A620 Electrical Load Center SIN 900-00052 and Subsequent 

GENERATOR FIELD 

CONTROL L 

CBlOl 

L 

Pane 931(94 blank)



r------------------------------------------------------------ 

A601 1 

I ESS CIRCUIT BREAKER PANEL 

I 

PlTOT HEAT L 

RTESS-lAl2 y- 

PlTOT HEAT R 

H31A20 3 

FUEL VLV R 

FUEL PROBE 

RTESS-1012 Q5A22 3 

XMSN FlRE 

ENG FlRE R 

W3A22 3 

CB3 W2A22 3 

LTESS-1016 

GCU L 

ESS BUS L 

LTESS-1012 - 

I LRTESS-1012- 

ESS BUS R 

- 1 

INSTR LTG 

L40A22 3 

AFCS-233A22 

AFCS-233C22 

AFCS-224A22 

AFCS-177C20 

1 EHSI-140A20 

1 EHSI- 140C20 

3An- 100A22 

AFCS-232A22 

M630-100A22 

R20A22 3 

AFCS-145C22 

CIA22 3 

AFCS-145E22 

RVSCS4020 3 

RVSCSIAZO 3 

RVSCS302O 3 

T103A20 3 

TIA20 3 

TI020 3 

INSTR FLOOD 

LVSCSlA20 3 

LVSCS3020 3 

20 LVSCS4020 3 

23 2NAV-115A16 

27 2NAV-115C16 

1AOC-100A22 

1AOC-101A22 

L10A12 3 

1NAV-114A18 

1NAV-114C18 

1AHRS-100A22 

1EAOI-126A22 

1 EAOI- 126C22 

POWER BOX tt - - 

I 

BLO AIR HEAT 

--- 

' TO A620 ELECTRICAL 

I 

P114H10 3 

CENTER 

I 

I REF EXISTING WIRE 

I L--------- P38A10 3 -- 4 TO A61 0 EXTERNAL 

I I POWER BOX 

L ------------------------------------------------------------ 1 REF EXISTING WIRE 

- - LLOAO 

A601 Essential Circuit Breaker Panel SIN 900-00052 and Subsequent 

Page 95(96 blank)

BENDIX/KINGo IFRAVIONICSI KFC goo 


; A620 r----------------- 

I 

EXTERNAL POWER BOX I 

I PSI D2O I 

I 

I 

ELECTRICAL LOAD CENTER ~ 6 1 0 ~ 



I 

J9000 P9000 

- 

M 

GH3000-1 E22 

CMPST OlSP 

I 

I 

I 

M 

A 

GPS- 100A22 

28VOC LEFT 

D 

AFCS- 100C22 

r---------------------------------- 

I A601 1 

ESS CIRCUIT BREAKER PANEL 

I 

I 

I 

I 

I 

I 

J1 PI31 

-- 

LTESS-1812 REF PAGE 95 

I 

I 

LTESS-ID16 

19 

I 

I - - - - - P31A10 3 - - REF EXISTING 

I 

I 

I XDSl@- LTG- 117A22 - 

I 0 LTG-118A22N - 

I 

L----------------------------------A 

- 

25 

26 

7 

8 

LTESS-1E16 

LTG-117C22 

LTG-118C22NP 

8 INV-100A22 

28VDC LEFT 

F 

AFCS- 174A22 

I 

I 

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AFCS- 100A22 

I 

I 

I 

G LTESS-IF16 I 

I 

H 

LTG-117D22 

I 

I 

J 

LTG-118D22N d 

-- I 

L-------------------------A 

Left Hand Auxiliary Essential Bus SIN 900-00052 and Subsequent 

Pane 97(98 blank)

BENDIX/KINGG" IFR AVIONICS 1 KFC goo 


NO. 2 SG 465 


b46510 

! ELECTRICAL LOAD CENTER I 

I 

RAD ALT 

2J300 2P300 

I 1 28VDC AVIONICS- LEFT RALT-lOOA22 4 

I BUS C086 

RALT- 100022 

P4051 

+28VDC POWER 

I 


RADAR ALTIMETER LO 


AID COMMON 

40 FOOT AID 

2P46520 

REF AUDIO SHEET 20 

NO. 1 SG 465 


1 P4652B 

OH SELECT OUT 

+' 

GB04 Y RALT- 104A22N 

RADAR ALTIMETER VALID 



1 88 1 ' REF AUDIO SHEET 20 I I I I 

,--. w 

110 

1P46510 @ PlOO JlOO 

99 I 

RALT- 103022 RALT- 103A22 

G004 Z 

RALT- 105A22N 

AlRCRAFl GROUND 

POWER GROUND 


RAO ALT -lOrnV/FT LO 

RAO ALT -lOrnV/FT HI 


RALT- 106022 

W ,--. 

TB100-5 

RALT- 106A22 

RALT-I07022 

RALT- 107A22 

MOO 2 OR EARLIER CNI HARNESS ONLY 



NO. 2 CP 470 

CONTROL PANEL 

2P4701 

71 

RAO ALT TEST #I 6 1CP-103022 

RAO ALT TEST #2 11 1CP-104022 

vb 

1 1 

NO. 1 CP 470 

CONTROL PANEL 

lP4701 

LH KA 54A RALT ANTENNA 

P54All 

KRA405-200A RECIEVE ANTENNA 

200-05647-0027 

I 

RH KA 54A RALT ANTENNA 

P54A21 

2;p;,","27'_";,"13~d TRANSMIT ANTENNA 

I 

KRA 405 Radar Altimeter 

Pane 99/(100 blank)

BENDlXIKING@ IFR AVIONICS 1 KFC goo 


NO. 2 SG 465 

SYMBOL GENERATOR h4652A rn 

HI 

I 1 "1- RALT-lOlC22 

RADAR ALTIMETER LO 98 

r--------------------- 

1 

I :Z&RIcAL LOAD CENTER 

I 

I 

2J300 2P300 

RAD ALT 

I 28VDC LEFT 

I AVIONICSQ?h- RALT- I00A22 RALT-1OOB22 

I BUS CB86 

L---------------------J 

3 

RALT- 103C22 

1 

l REF AUDIO SHEET 20 

NO. 2 CP 470 

CONTROL PANEL k 7 01 

RAD ALT TEST #2 11 

1 CP-104B22 

RAD ALT TEST #I 6 1 CP-I 03622 

vk 

NO. 1 CP 470 

CONTROL PANEL 

I OH XiET OUT 188 1-l REF AUDIO SHEET 20 1 I I GB04 Y RALT- 104A22N - 

RADAR ALTIMETER VALID 



+ I 

- w 

I I IR 

, .- 

1 P4651 B 

1 1 @ 

I 

PlOO JlOO 

GB04 Z RALT- 105A22N - 

99 I I RALT-101322 34 RALT- 103A22 - 

W- 

RALT-101B22 

Bl I 

'c 

;; 

RALT- 101 A22 BI I 

373 

2 

w - 

+ L 

J 


POWER GROUND 

I RADAR ALTIMETER VALID 

RAD ALT -1OmV/FT LO 

RAD ALT -10mV/FT HI 

NO CONNECTION 

A* NO CONNECTION 



RALT- 107B22 

LH KA 54A RALT ANTENNA 

22y;5","477f,","27~d 

I 

P54All 

RECEVE ANTENNA 

1 MOD 3 CNI HARNESS OR LATER CNI HARNESS OR MOD 2 OR EARLIER 


159-08140-2003 OR 159-08140-2012. HARNESS TERMINATION. 

WIRE NOT PRESENT ON MOD 3 OR LATER CNI HARNESS. 

RH KA 54A RALT ANTENNA 

P54A2 1 

KRA405-201A 

200-05627-0013 

TRANSMIT ANTENNA 



KRA 405B Radar Altimeter 

98-40-00 

- 

Pane 1011(102 blank) 

Revision AD



IN 182A 

WX RADAR INDICATOR 

+28VOC POWER 

+2BVOC POWER 


I 

ROR R/T 

I 

BUS 

I 

L------------- 

WX-103A22N 

WX-1OOA22 

WX-101A22 

- - - - - - - - 

T GBOl 

29 WX-104A22N W GBOl 

INDICATOR STRAP 1 8 1- WX-105A22N Y GBOl 


R/T m/OFF 


GS100 

POWER GROUNO 

CONFIG TO ART OATA 

ART TO CONFIG CHlP SEL 1 

ART TO CONFIG CHlP SEL 2 

ART TO CONFIG CLOCK 

ART TO CONFIG OATA 

+5VOC POWER 

P2000 

WX-100822 

WX-102A22N 

113A22 50 

WX-114A22 49 

it-WX- 

WX-115A22 46 

WX- 116A22 47 

WX-117A22 45 

WX- 11BA22 48 

WX-119A22 44 

ART 2000 

WEATHER RADAR R/T 

+2BVDC POWER 

+28VOC POWER 

CHASSIS/POWER GROUNO 

CHASSIS/POWER GROUNO 

MODULE GROUND OUT 

CONFIG/RT DATA IN 

RT/CONFIG CHlP SEL 1 


RT/CONFIG CLOCK OUT 

RT/CONFIG DATA OUT 

MODULE +5VDC OUT 

WX CONTROL 429 XMTR A 

WX CONTROL 429 XMTR B 

1 - *W 

WX 453 OATA RCVR A 

WX 453 OATA RCVR 8 20 

LIB 

WX CONTROL 429 RCVR 1A 

WX CONTROL 429 RCVR 1B 

I 

Z GBOl 

I 

WX-A22 1 

42 WX 453 OATA XMTR A 

43 WX 453 OATA XMTR B 

NO. 1 SG 465 


1 P4652B 


WX CONTROL 429 RCVR B 

9 

35 

I '6 

wx-lllD22 

wx-108C22 

;& wx-lorn22 

-' 

I 

@ 

EFS WX XMTR A 

EFS WX XMTR B 


WX CONTROL 429 RCVR 28 

NO. 2 SG 465 




-:& 

EFS WX 429 XMTR A 

EFS WX 429 XMTR B 81 

2P4652B 

9 -W 

35 IB 

@ 

WX- 120822 WX-12OA22 -1 

6 

AIR/GROUNO LOGIC 

GROUND = ON GROUNO 

7 WX CONTROL 429 RCVR 38 3A [ 



RDR 2000 Weather Radar WllN 182A Indicator Option 

Paae 1031~104 blank)

BENDIX/KING@ IFRAVIONICSIKFC goo 


1 A620 


I RDJR R/1 

I 

- WX- 1 DOA22 -4 I 

" 4, 

W 

I 28VDC LEFT CB89 


WX-lOlA22 'p 

KMD 540 MULT-FUNCTION 

2~5401 'L..................... POWER GROUND 1 

DISPLAY UNIT 

WX-101022 I CONFIG TO ART DATA 4 

+2BVDC POWER 

ART TO CONFIG CHIP SEL 1 2 

+2BVDC POWER 

MFD-100A22 

ART TO CONFIG CHIP SEL 2 9 

AlRCRAFl GROUND 24 MFO-101A22N T GBOl ART TO CONFIG CLOCK 6 

AlRCRAFl GROUND 25 ART TO CONFIG DATA 8 

+SVOC POWER 5 

1 28VDC LIGHTING HI 16 

-W 

WX CONTROL 429 XMTR A 7 

IB 

WX CONTROL 429 XMTR B 8 

SHIELD GROUND 26 

- 

WX 453 DATA RCVR A 27 

WX 453 DATA RCVR B 28 

SHIELD GROUND 9 3 

- 

2P5402 

I 1- MFD-102422 N TBIO1-T 

+28VDC POWER 

+28VDC POWER 

CHASSIS/POWER GROUND 

CHASSIS/POWER GROUND 

MODULE GROUND OUT 

CONFIG/RT DATA IN 



RT/CONFIG CLOCK OUT 

RT/CONFIG OATA OUT 

MODULE +5VDC OUT 


WX CONTROL 429 RCVR 1 B 

WX 453 DATA XMTR A 

WX 453 DATA XMTR B 

SHIELD GROUND 31 

GPS- 106022 

KLN 900 GPS RECEIVER 

P90B1 

-W 

GPS 429 XMTR A 24 

GPS 429 XMTR B 

7 kB 

NO. 1 SG 465 


I I IB ;REF KLN 90 GPS PAGE 67 

WX 453 DATA RCVR B 49 

7.w 

WX CONTROL 429 RCVR A 9 - - I IB 

WX CONTROL 429 RCVR B 35 

WX- 108022 

,-. w 

I IB 

EFS WX XMTR A 68 G! 

EFS WX XMTR B 81 

WX- 1 12A22 

C 

V 

NO. 2 SG 465 




WX-121A22 

WX 453 DATA RCVR A 

WX 453 DATA RCVR B 

EFS WX 429 XMTR A 

EFS WX 429 XMTR 8 

1 MOD 3 OR LATER CNI HARNESS AND MOO 2 OR LATER WX HARNESS 

OR MODIFIED IN ACCORDANCE WITH WIRING DIAGRAM 159-08140-2013 

REV A OR LATER. KMD 550/850 RETROFIT. 

AHRS 429 RCVR A 

AHRS 429 RCVR B 

4-TUBE 


RDR 2000 Weather Radar WlKMD 850 Multi-Function Display Option 

Page 1051(106 blank)



KLN 900 GPS RECEIVER 

P9081 

I I 

@ 

-=I 

I 

I 

L---------------------J TBIO1-T T MFO-101A22N 24 AIRCRAFT GROUND 

25 AIRCRAFT GROUNO 

TBlO1-T N MFD-102A22 

-4 

2P5402 

GPS 429 RCVR A 

GPS- 106D22 

13 GPS 429 RCVR B 

31 SHIELD GROUNO 

r\W 

IB I REF KLN 908 GPS SHEET 67 

75 OHM NTSC VIDEO INPUT 

1 MOD 3 CNI HARNESS OR LATER OR MODIFIED IN ACCORDANCE 

WITH WIRING DIAGRAM 159-08140-2013. KMD 550,850 RETROFIT. 

KMD 550 Multi-Function Display 

98-40-00 

- 


Revision AD

BENDIX/KIN6" IFR AVIONICS 1 KFC 900 


I ESSENTAIL CB PANEL I 1P3601 

I 

STBY ATT 

I 28VDC LEFT 

I ESSENTIAL @- 3ATT- 1 OOA22 SAT- 100B22 

I 

BUS 

L---------------------J GBOl S 3ATT- 102A22N 

AI-360 ATITUDE GYRO 

+28VDC POWER 


GBOl R 

3ATT-101A22N 

POWER GROUND 

TB101-T W 3AT- 103A22 

28VDC LIGHTING LO 


AI-360 Standby Attitude Indicator 

Pane 109/(110 blank)



I FORWARD INTCON PANEL 

I 

I 

-I-_--- 

I 

lr I 

I 

I 

I 

I 

I 

I 

fi REF 

-------- 

GSIOZ-B(+ - - - 

- - - - - - - - L97824 3 

GSIOZ-E(+ - - - L98B24N 3 

--- L95C24 3 - - - - - - - - - L95824 3 

I 

I RUMENT PANEL ~~102-D(+ - - - L96824N 3 

L------------------___, 

J118 REF PI18 REF 

--I 

--- 

--- 

-- --- 

W136 SP3 

L91A24 3 - - - - - WHT - - - 

L92A24 3 

W136 SP4 

-- + ---BLK--- 

WlXX SPX 

L97A24 3 - - --0-- - - - WHT - - - 

1--- L98A24 3 -- WlXX --0-- SPX --- BLK --- 

Wl XX SPX 

L95A24 3 --* - 

- WHT- - - 

PART OF 4-TUBE CONFIGURATION OR 

MECHANICAL GYRO OPTION 

Existing Instrument Lighting 

Page 1111(112 blank)

BENDIXlKlN6" IFR AVIONICS I KFC goo 


- 7 

GPS-101A22 

REF KLN 908 APPROACH GPS PAGE 67 


REF KAO 480 AIR DIGITAL DATA SYSTEM PAGE 3 4 7 

GPS-102A22N 

AOC-113C22 

&f?l 

Y 

J9000 

REF KFC 900 AFCS SYSTEM PAGE 114 9 

1- &di: 

AFCS- I 14822 

REF KFC 900 AFCS SYSTEM PAGE 11 - 

AFCS- 131 C22 

* 

REF NO. 1 LCR-92 AHRS PAGE 3547 

l ~ ~ ~ s - 1 1 8 ~ 2 2 

;: 

rn REF NO. 2 LCR-92 AHRS PAGE 3747 

~AHRS-,18022 &J 2: 

REF NO. 1 LCR-92 AHRS PAGE 35 1-1AHRS-126A22N -4 

P9000 

AFCS 

1 10 AFCS-132B24 

36 1AHRS-I 2 6 8 2 2 ~ ~ 

GPS 

GPS-101824 

GPS-102822N 


CONFIGURATION ONLY. 

NOT INSTALLED IN AIRCRAFT 

Diagnostic Interface and Interface Cable 

98-40-00 

Page - 113/(114 blank) 

Revision AD



TB100-K 

ANN-101B22 - 

FANS-1 16A22 - 

FANS- 108A22 - 

ANN-101C22 - 

FANS-1 19A22 - 

FANS-107A22 - 

G FANS- 100H20 - 

1ADC-113A22 (EL) - 

l ADC-1 13822 (EL) ---- 

1ADC-113C22 (EL) - 

1ADC-125A22 

(WH)- 

1ADC-125822 (EL) - 

1ADC-125A22 (EL) - 

IADC-125E22 (EL) - 

1AOC-113A22 

1ADC-113822 

1AOC-113C22 

(SHD)- 

(SHD)- 

(SHD)-. 

1 DME-109A22 - 

1 DME-109822 - 

1 DME- 109E22 - 

1DME- 109A22 (SHD)- 

DME-109822 

OME-109E22 

(SHD)- 

(SH0)- 

1DME-lllA22 - 

1DME-lllE22 - 

1DME-108A22 - 

1 OME-108J22 

1 DME- 108H22 - 

1 DME- 108E22 - 

1 DME- 108822 - 

1 OME-108G22N - 

2AHRS- 140A22N - 

1 AHRS- 129A22N --- 

1 DME- 108F22 - 

WX-122A22 (WH) - 

1AHRS-118822 

(WH)- 

1 AHRS- 1 18C22 (BL) - 

1AHRS-11BA22 (EL) - 

TB100-S 

TI31 00-T 

RALT-106A22 (WH) - 

RALT-106822 (WH) - 

RALT-106A22 (EL) - 

RALT-106822 (EL) - 

RALT- 106A22 (SHD) - 

RALT- 106822 (SHO) - 

RALT- 107A22 - 

RALT-107822 --- 

2AHRS-128A22 - 

1 EHSI- 139A22 - 

GPS-136A22 - 

GPS-141A22 - 

ANN-107A22 - 

2AHRS- 129A22 - 

1 EHSI- 140A22 - 

GPS-137A22 - 

GPS-142A22 - 

GPS-146A22 - 

AFCS-179A22 - 

ANN-108A22 - 

AFCS- 1 78A20 - 

AFCS-178E20 - 

AFCS-178C20 - 

AFCS-178820 --- 

AFCS- 178F20 - 

AFCS-178D20 - 

TB100-W 

ANN-109A22 - 

AFCS- 125A22 - 

2AHRS-135A22 - 

2EHSI-140A22 - 

GPS-109A22 --- 

AFCS-13DOPZ 

AFCS-130C22 

AFCS-130E22 

AFCS-130822 

(WH)- 

(WH)-------- 

(WH)- 

(WH)- 

AFCS- 130A22 (WH)- 

AFCS-130022 (EL) - 

AFCS-130C22 (BL) - 

AFCS-130E22 (EL) - 

AFCS-130822 (EL) - 

AFCS- 130A22 (BL) - 

FCS- 130C22 (SHD)- 

FCS-130D22 

(SHD)- 

FCS- 130822 (SHD)- 

FCS- 130E22 (SHD)- 

FCS-130A22 

(SH0)------ 

AFCS-206A22 - 

AFCS-206822 - 

AFCS-206C22 - 

AFCS-206022 - 

1DME-111822 - 

1 OME-100822 - 

1OME-100C22 - 

1 OME- 100D22 - 

1- 2AHRS-3922 

WX-122A22 (SHD) - 

1 AHRS- 1 18822 (SHD)- 

1ADC-507A20 AFCS- 178020 - a 

- PART MOO 3 OF AFCS CATEGORY HARNESS A INSTALLATION 

ASSEMBLY OR 

1AHRS- 128A22 - 

c 

Terminal Blocks TB100 and TBlOl (Sheet 1 of 3) 

98-40-00 

- 

Pane 1151~116 blank) 

R'evision AD



FANS- 109A22 - 

DIODE 007-06048-0000 

(IN4007) 2 PLCS. 

FANS- 1 1 OA22 

FANS- 104A22 

TE101-T 

AFCS- 113A22 

IEADI-121A22 

1 CP-100A22 

1 EHSI-104A22 

2EADI-121A22 

2CP-100A22 

2EHSI-104A22 

GPS-105A22 

1 ADC- 105A22 

LTG- 100C22 

WX-106A22 

1 NAV- 138A22 

MFD-102A22 

TElOI-W 

AFCS-131C22 (WH) - 

AFCS-131822 (WH) ---- 

AFCS-131A22 (WH) - 

AFCS-131C22 (EL) - 

AFCS-131E22 (EL) - 

AFCS-131A22 (EL) - 

AFCS-131 C22 (SHD)- 

AFCS- 131 E22 (SHD)- 

AFCS-131A22 (SHO) - 

DIODE. 007-06048-0000 

1- 

1 

LTG-100C22 - 

NAV- 138A22 ---- 

TEIOI-U 

AFCS-150022 (WH) - 

AFCS-150H22 (WH) - 

AFCS-150G22 (WH) - 

AFCS-150E22 (WH) - 

AFCS-150F22 (WH) ----------- 

TElOl-X 

AFCS-129822 (WH)-------- 

AFCS- 129C22 (WH)- 

AFCS-129A22 (WH)- 

2AHRS-118E22 (WH)- 

2AHRS-118D22 (EL)- 

2AHRS- 118A22 (EL)- 

2AHRS-118822 (EL)- 

AHRS-118A22 (SHD)- 

AHRS-11 ED22 (SHD)---------- 

AFCS-150D22 (EL) - 

AFCS-150H22 (EL) ---- 

AFCS-150G22 (EL) - 

AFCS-150E22 (EL) --- 

AFCS- 150F22 (EL) - 

AFCS- 150D22 (SHD)------ 

AFCS-150H22 

AFCS-150G22 

(SHD)- 

(SH0)- 

AFCS-150E22 (SHD)- 

AFCS-150F22 (SHD)- 

AFCS- 129822 (EL) ---------- 

AFCS-129A22 (EL)- 

AFCS- 129C22 (EL)- 

AFCS-281A22 - 

AFCS-120C22 - 

FCS- 129E22 (SH0)- 

FCS- 129C22 (SHD)- 

FCS- 129A22 (SHD)- 

AHRS-118822 

(SH0)- 

WX-1221A22 - 

AOG-102A22 ---- 

LTGlOlE22 - 

1ADF-108A22 - 

LTG-1 lOA22 - 

LTG- 1 1 2A22 ------------ 

I NAV- 170A22 - 

-1 

LTG-114A22 - 

2NAV- 170A22 

AFCS- 1 1 3A22 ---- 

MOD 2 OR EARLIER HARNESSES ONLY 

MOD 3 OR LATER HARNESSES ONLY. 

CAT A INSTALLATIONS ONLY. 

Terminal Blocks TBIOO and TBlOl (Sheet 2 of 3) 

98-40-00 

\ 

- 


Revision AD

BENDIX/KINGB IFRAVIONICS I KFC goo 


AFCS-109A22N 

AFCS-1 I 1A22N 

AFCS-1 12A22N 

1 EADI-120A22N 

1 EHSI-105A22N 

2AHRS-130A22N 

ICP-101A22N 

ICP-102A22N 

1 EHSI-142A22N 

1AOC-106A22N 

1ADC-107A22N 

1ADC-108A22N 

1 NAV-136A22N 

1 NAV- 137A22N 

3AlV101A22N 

3ATT- 102A22N 

WX-103A22N 

MFD-101A22N 

WX-104A22N 

WX- 105A22N 

WX- 109A22N 

2EADI-120A22N 

2CP-101 A22N 

2CP- 102A22N 

2EHSI-105A22N 

AFCS- 128A22N 

2AHRS- 136A22N 


FANS-lOlA22N 

GPS- 103A22N 

GPS- 104A22N 

GPS-I lOA22N - 

GPS- 1 14A22N - 

GPS- 1 16A22N ---- 

GPS- 138A22N - 

GPS- 143A22N - 

FANS-1 12A22N --- 

FANS- 1 14A22N --------- 

GB04 

1 NAV- 106A22N 

1 NAV- 108A22N 

1 NAV- 118A22N 

1 NAV- 115A22N 

1 NAV-116A22N 

1 NAV-123A22N 

1 NAV-126A22N 

1NAV-131A22N 

AFCS-164A22N 

AFCS-242A22N 

AFCS-238A22N 

AFCS-239A22N 

AFCS-146A22N 

AFCS-243A22N 

AFCS-244A22N 

GPS- 102A22N 

1AHRS-126A22N 

LTG- 115A22N 

RALT-104A22N 

RALT- 105A22N 

1DME-101A22N 

1 OME- 102A22N 

1 OME-106A22N 

1 OME-I 1 OA22N 

1DME-112A22N 

INV-208A22N 

INV-103A22N 

FANS- 102A22N 

GB08 

AFCS-207A22N - 

AFCS- 169A22N - 



AFCS-247A22N 

AFCS-246A22N 

INV- 105A22N 

AFCS- 189A22N 

AFCS-209A22N 

AFCS-21 0A22N 

VSCS SHD GND 

FANS-1 06A22N 

2SG-1 lOA22N 

AFCS-292A22N 

FANS- 1 17A22N 

FANS-1 18A22N 

1ADC-508A22N 

GBD3 

1 NAV-141A22N 

1 NAV- 145A22N 

1ADF-105A22N 

1ADF-107A22N 

2NAV-101A22N 

2NAV-105A22N 

2NAV-109A22N 

2NAV-I 11A22N 

1ADF-llOA22N 

LTG-113A22N 

AOG- 100A22N 

L RCCB3A22N 

1AUD-103A22N 

R RCCB3A22N 

1DME-1 14A22N 

ANN- 100A22N 

LTG-11 lA22N 

MRKR- 102A22N 

1NAV-101A22N 

1 NAV- I 1 OA22N 

1NAV-I 1 lA22N 

1 NAV- 119A22N 

2NAV- 117A22N 

2NAV- 112A22N 

2NAV-113A22 

ANN- 105A22N 

AFCS- 106A20N - 

AFCS-12IA2ON - 

AFCS- 122A20N ---- 

AFCS- 123A20N - 

FANS-103A22N - 


MOD 3 OR LATER HARNESSES ONLY 

2 S/N 900-00052 & SUBSEQUENT WITH CATEGORY A INSTALLATION 

R O D 2 OR LATER AFCS HARNESS OR MODIFIED IN ACCORDANCE 

WITH WIRING DIAGRAM 159-08140-2010 REV C OR LATER, CAT A UPGRADE 

Terminal Blocks TBIOO and TB101 (Sheet 3 of 3) 

Page 119/(120 blank)

BENBIXlKIN6" IFRAVIONICS 1 KFC goo 



P4851 

I 

ALTITUDE ALERT M 

- 

1ADC- 

r--------------------- 

A601 

I ESSENTAIL CB PANEL 

1 

I 

I WARN AUDIO ~ - 2 PI28 ' 

I 

I 

M630-100A22 ---- 28 

- 

M630-101A22 

(GND = ALERT) I I -1 16 1 ALTITUDE ALERT INPUT 

I 

-w 

ALTITUDE ALERT AUDIO 1; rn 1 IB 

104A22 

h 

KCP 520 AFCS COMPUTER P5201 

AFCS DISCONNECT HI 62 

AUDIO{ LO 1 66 

AFCS-119A22 

A652 REF 

I 

,Lr 

1AUD-103A22N 

AUDIO PANEL (AMS 431 k5" REF I a 0 0 

28VDC RIGHT 

I ESSENTIAL AFCS-232A22 - 24 

GBlO F 

M630-100022 

M630-104A22N - 

AP/SAS 

DISCONNECT INPUT 

H~ Lot AP~SAS wA N AUDIO DISCONNECT 1 IN 

:A} 

:At 

WARN AUDIO 2 OUT 

WARN AUDlO 1 OUT 

DECISION HEIGHT INPUT 

POWER GROUND 

GBlO E 

M630-106A22N 


KDC 481T 


OVERSPEED WARN (VNE) 

(GNO = OVERSPEEO) 

P481T1 

A 

a 

1AOC-500A22 

(GND = >50 KNOTS) 

1ADC-505A22 

9~500 

rn WIRING CAPPED FOR CATEGORY A INSTALLATION 

El WIRE AFCS-17020 RELOCATED TO PIN M. NEW 20 

GAUGE JUMPER WlRE ADDED BETWEEN PINS F AND G. 

I LOW A/S RELAY 1 9~500 AOOED NEW WIRE 1ADC-507A20. 


CATEGORY A CONFIGURATION ONLY 

I AP ENGAGED RELAY 

5K500 

I AP DISENGAGED h I 

REF PAGE 15 

LOW A/S 

ANNUNCIATE 

KA 172 


PI722 

OVERSPEED WARN (VNE) IN 1 1ADC-500822 

1ADC-501A22 

I 

TB100-V S 1ADC-502A22 13 

a 

T 

pol 

7 

14 

COPILOT VNE ANNUNCIATOR 

PILOT VNE ANNUNCIATOR 

1ADC-503A22 

TB100-T Z 1AOC-504A22 

T 

SIN 900052 & Subsequent with Category A Option 

98-40-00 

Page - 1211(122 blank) 

Revision AD

BENDIXIKING" IFRAVlONlCSI KFC 900 


r--------------------- 

AUX FWD ESSENTAIL CB PANEL 1 

I 

LMV3l V13V 

281:&egh\- GH3000-1 E20 

BUS C81 

GH3000-1 F20 

GH-3000H ELECTRONIC 

STANDBY INDICATOR 

+28VOC POWER 

MAG-3000 MAGNETOMETER 3J3000 

+28VDC POWER 

+28VOC RETURN 


POWER GROUND 

RS-422 

OUTPUT 

RS-422 

INPUl 

SHIELD 

LIGHTING LO 

AOC-3OOOH 


2P3000 

I +28VDC POWER 1 1 1- GH3ODO-1H22 

POWER GROUND 

GH3000-6E22N 

A GBlO 

CHASSIS GROUNO 



SHIELD GROUND 

ADC-3000 AIR DATA A 

COMPUTER 429 XMTR{B 

GH3000-7E22N 

B GBlO 

A ADC 3000 AIR DATA 

B/ CO~&TER 429 RCVR 

I KN 40 NAV CONVERTER I 

L 

p4nr 

NAV 1 429 XMTR 2 A 

GH3000-13E22 .*u 

A KN 40 NAV 1 

81 429 RCVR 

GPS 429 RCVR 

rn PART Of KMO 550/850 

MFO OPTION ONLY 

PlOO JlOO 

27 

+ 

REF KMO 550/850 MFO PAGES 105 OR 107 

SIN 906052 & Subsequent with 2-Tube Category A Configuration 




I A620 

ELECTRICAL LOAD CENTER I 1 AIRCRAFT MODIFIED IN ACCORDANCE WITH WIRING 

pa DIAGRAM 159-081 40-2002. MECHANICAL GYROS. 

I GENERATOR 

I 

2EADI-126A22 

CB40 

AI-360 

+28VOC POWER 


28VDC LIGHTING LO 


POWER GROUND 

ATTITUDE GYRO 

I 

KG 102A 

DIRECTIONAL GYRO 

I UNREGULATED GROUND 0 

I 

+5VDC 

DIGITAL GROUND 

+ 15VDC REGULATED 

SIGNAL GROUND 

- 15VOC REGULATED 

+15VOC UNREGULATEO 

KG1 02- 100A20 

I 1- KG102-102A22 

KI 525A 

PICTORIAL NAV INDICATOR 


LIGHTING LO 

UNREGULATED GROUNO 

+5VDC 

DIGITAL GROUNO 

+ 15VOC REGULATEO 

SIGNAL GROUNO 

- 15VDC REGULATEO 

+ 15VDC UNREGULATED 

KI 525A VALID 

DRlVE MOTOR 1 

DRIVE MOTOR 2 

DRlVE MOTOR 3 

DRlVE MOTOR 4 

SLVG CTRL XFMR H) 

SLVG CTRL XFMR {C) 

KI 525A VALID 

DRlVE MOTOR 1 

DRlVE MOTOR 2 

DRlVE MOTOR 3 

DRlVE MOTOR 4 

SLVG CTRL XFMR H 

SLVG CTRL XFMR {C] 

POWER GROUND 

SLVG CTRL XFMR (X) 

SLVG CTRL XFMR Y) 

SLVG CTRL XFMR IZ) 

P51B2 

KA 518 SLAVING ACCESORY 

SIGNAL GROUND 

SLAVING METER 

SLAVING SWITCH 

SLAVE CW SWITCH 

SLAVE CCW SWITCH 

+5VDC 

SLAVING METER 

0 SWING SWITCH 

/ I 

E SLAVE CW SWITCH 

I 

I B I SLAVE CCW SWITCH 

FLUX VALVE EXCITATION (H) 

FLUX VALVE EXCITATION (C) 

I 6 KG102-113822 

NO. 2 KMT 112 - 

FLUX VALVE 2P1121 1 

FLUX VALVE EXCITATION (H) H -W 

I FLUX VALVE EXCITATION (C) 1 

*u 

E ] 2' 

r) SLVG CTRL XFMR (X) -W 

SLVG CTRL XFMR (Y) I IB 

SLVG CTRL XFMR 

1 

SLVG CTRL XFMR (Z) 

10 KMT112-100A22 01 H SLVG CTRL XFMR Y) 

O w 0 SLVG CTRL XFMR 2) 

- 

1 

Copilot AI-360 Attitude Indicator and KCS 55A Compass System Option (Sheet 1 of 2) (2-Tube Configuration Only) 


Revision AD




p: 

SWl%!E POWER 

p525d 

KI 525A 

PICTORIAL NAV INDICATOR I 

2NAV- 135A22 H 2BVDC NAV FLAG POWER 

+ FROM 

+ TO 

NAV + FLAG 

NAV - FLAG 

GS - FLAG 

COURSE DEVIATION + RIGHT 

COURSE DEVIATION + LEFT 

2P1651 

9 2NAV- 123A22 

T NAV 2 + FROM 

I 

H 1- 2NAV-124A22 I Z 1 NAV 2 + TO I 

8 1- 2NAV-125A22 I K 1 NAV 2 + FLAG 

I 

I 1- 

2NAV-126A22 

F NAV 2 - FLAG 

I 

R 1- 2NAV-127A22 1 W 1 NAV 2 GS - FLAG I 

GS + UP 

GS + DOWN 

OBS RESOLVER (0) 

OBS RESOLVER (E) 

OBS RESOLVER (F) 

OBS RESOLVER (G) 

08s RESOLVER (H) 

OBS RESOLVER (C) 

GS + FLAG 

A w 

2NAV- 130A22 V NAV OBS RESOLVER (0) 

! Y NAV 2 OBS RESOLVER (E) . . 

3 I IB 

L w 

2NAV-131A22 NAV OBS RESOLVER (F) 

NAV 2 OBS RESOLVER (G) 

I - -W 

Wn 

2NAV-132A22 

X NAV 2 OBS RESOLVER H 

Bz A* NAV 2 OBS RESOLVER [C] 

2NAV- 133A22N Z GB02 

2NAV-134A22 A J NAV 2 GS + FLAG 

+- 

\& 


w- f- 

19 ROTOR C 

BI 

2NAV- 124A22 21 ROTOR F 

20 GROUND 

+ 

qh 

W-l 

I 

WIRING REMOVED AND CAPPED FOR THIS OPTION. 

Copilot KCS 55A Compass System Option (Sheet 2 of 2) (2-Tube Configuration Only) 


5ENDIX/KlNGG" IFRAVIONICSI KFC goo 


Index to Wiring Diagrams 

Descristion 

Pa~e 

Modifications to Basic Aircraft Wiring .............................................................................................................. 1 

KAD 480T Digital Air Data System .................................................................................................................. 3 

KR 87 Automatic Direction Finder ..................................................................................................................... 5 

KFC 900 AFCS Mode Selector, Configuration Module and Flight Director Switching .................................. 7 

KFC 900 AFCS Flight Director Switching (4-Tube Configuration Only) ........................................................ 9 

KFC 900 AFCS Sensor Inputs .......................................................................................................................... 11 

KFC 900 AFCS Pitch and Roll Trim Switching (T-Bar Relay Scheme) .......................................................... 13 

KFC 900 AFCS Autopilot Engage (4-Tube Configuration Only) ............................................................... 15 

KFC 900 AFCS Autopilot Engage (2-Tube Configuration Only) ..................................................................... 17 

KFC 900 AFCS Roll and Pitch Trim Switching (LEDEX Switch Scheme) ..................................................... 19 

KFC 900 AFCS Linear Actuators and Pitch and Roll Synchros ....................................................................... 21 

KFC 900 AFCS Master Switch, String Pots, Directional Servo and Spring Cartridge ..............................; 

23 

KFC 900 AFCS Pedal and Collective Synchros and Mode Annunciation ...................................................... 25 

KFC 900 AFCS and Right Side VSCS Switching ......................................................................................... 27 

KFC 900 AFCS Cyclic and Collective Switches (4-Tube Configuration Only) ............................................... 29 

KFC 900 AFCS Cyclic and Collective Switches (2-Tube Configuration Only) ............................................. 31 

KFC 900 AFCS Rate and Acceleration Sensors ......................................................................................... 33 

NO . 1 LCR-92 AHRS ........................................................................................................................................ 35 

No . 2 LCR-92 AHRS (4-Tube Configuration Only) ......................................................................................... 37 

AHRS Switching (4-Tube Configuration Only) ................................................................................................ 39 

Annunciator Lighting Power Supply (4-Tube Configuration Only) .................................................................. 41 

Audio System (Sheet 1 of 2) ............................................................................................................................. 43 

Audio System (Sheet 2 or 2) ............................................................................................................................. 45 

KN 63 Distance Measuring Equipment (Sheet 1 of 2) ...................................................................................... 47 

KN 63 Distance Measuring Equipment (Sheet 2 of 2) ...................................................................................... 49 

No 1 EFS 40 (Sheet 1 of 3) .............................................................................................................................. 51 

No . 1 EFS 40 (Sheet 2 of 3) .............................................................................................................................. 53 

No . 1 EFS 40 (Sheet 3 of 3) .............................................................................................................................. 55 

No . 2 EFS 40 (Sheet 1 of 3) (4-Tube Configuration Only) ............................................................................ 57 

No . 2 EFS 40 (Sheet 2 of 3) (4-Tube Configuration Only) .......................................................................... 59 

No . 2 EFS 40 (Sheet 3 of 3) (4-Tube Configuration Only) .............................................................................. 61 

Avionics Cooling Fans ...................................................................................................................................... 63 

Instrument and Console Lighting and WOW Logic ....................................................................................... 65 

KLN 90B Global Positioning System (Sheet 1 of 2) ..................................................................................... 67 

KLN 90B Global Positioning System (Sheet 2 of 2) ........................................................................................ 69 

26VAC 400Hz Power ....................................................................................................................................... 71 

KMR 675 Marker Beacon Receiver ................................................................................................................. 73 

No . 1 KX 165 VHF COMM7NAV ................................................................................................................... 75 

No . 1 KX 165A VHF COMM/NAV ................................................................................................................. 77 

No . 2 KX 165 VHF COMM/NAV ................................................................................................................... 79 

No . 2 KX 165A VHF COMM/NAV ................................................................................................................. 81 

COMMlNAV Antennas .................................................................................................................................... 83 

KI 206 NAV 2 Indicator ................................................................................................................................... 85 

A620 Electrical Load Center S/N 900-00010 thru 900-00051 ......................................................................... 87 

A601 Essential Circuit Breaker Panel S/N 900-00010 thru 900-00051 ............................................................ 89 

Page 129 

Revision AD

BENDIX/K/NGG" IFRAVIONICS I KFC goo 


Left Hand Auxiliary Essential Bus S/N 900-00010 thru 900-00051 ................................................................. 91 

A620 Electrical Load Center S/N 900-00052 and Subsequent ......................................................................... 93 

A601 Essential Circuit Breaker Panel S/N 900-00052 and Subsequent ............................................................ 95 

Left Hand Auxiliary Essential Bus S/N 900-00052 and Subsequent ................................................................ 97 

KRA 405 Radar Altimeter ................................................................................................................................ 99 

KRA 405B Radar Altimeter ............................................................................................................................ 101 

RDR 2000 Weather Radar W/IN 182A Indicator Option ............................................................................. 103 

RDR 2000 Weather Radar WIKMD 850 Multi-Function Display Option ...................................................... 105 

KMD 550 Multi-Function Display ................................................................................................................ 107 

AI-360 Standby Attitude Indicator .................................................................................................................. 109 

Existing Instrument Lighting ........................................................................................................................... 111 

Diagnostic Interface and Interface Cable ........................................................................................................ 113 

Terminal Blocks TB 100 and TB 101 (Sheet 1 of 3) ...................................................................................... 115 

Terminal Blocks TB 100 and TB 101 (Sheet 2 of 3) ...................................................................................... 117 

Terminal Blocks TB 100 and TB 101 (Sheet 3 of 3) .....................................,. ............................................. 119 

S/N 900-0052 & Subsequent with Category A Option ............................................................................... 121 

S/N 900-0052 & Subsequent with 2-Tube Category A Option ...................................................................... 123 

Copilot AI-360 Attitude Indicator and KCS 55A Compass System Option (Sheet 1 of 2)(2-Tube Config.) .. 125 

Copilot AI-360 Attitude Indicator and KCS 55A Compass System Option (Sheet 2 of 2)(2-Tube Config.) .. 127 

Page 130 

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effectivity: md900 - MD Helicopters

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