400/500 Series Garmin Optional Displays

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58 Section 3 TAWS Alerts RTC/ITI Severity Levels CAUTION—Estimated potential impact in approximately 60 seconds after pop-up alert and annunciation. RTC/ITI caution alerts are accompanied by the aural message “Caution Terrain; Caution Terrain” OR “Terrain Ahead; Terrain Ahead”. Similarily, a “Caution Obstacle; Caution Obstacle” or “Obstacle Ahead; Obstacle Ahead” alert is also provided. WARNING—Estimated potential impact in approximately 30 seconds after pop-up alert and annunciation. RTC/ITI warning alerts are accompanied by the aural message “Terrain, Terrain; Pull Up, Pull Up” OR “Terrain Ahead, Pull Up; Terrain Ahead, Pull Up”. Similarily, a “Obstacle, Obstacle; Pull Up, Pull Up” OR “Obstacle Ahead, Pull Up; Obstacle Ahead, Pull Up” alert is also provided. Forward Looking Terrain Avoidance The Forward Looking TERRAIN Avoidance alert, or FLTA, is used by TAWS and is composed of two elements: Reduced Required Terrain Clearance (RTC) Avoidance — Provides alerts when the aircraft flight path is above terrain, yet is projected to come within minimum clearance values outlined in Table 3-1. When an RTC alert is issued, a potential impact point (see page 52) is displayed on the TAWS Page. Imminent Terrain Impact (ITI) Avoidance — Provides alerts when the aircraft is below the elevation of a terrain cell in the aircraft’s projected path. ITI alerts are accompanied by a potential impact point displayed on the TAWS Page. The alert is given when the projected vertical flight path is calculated to come within minimum clearance altitudes in the following table. TAWS Phase of Flight Level Flight Descending Enroute 700 ft. <strong>500</strong> ft. Terminal 350 ft. 300 ft. Approach 150 ft. 100 ft. Departure 100 ft. 100 ft. Table 3-1: Minimum Terrain and Obstacle Clearance Values for FLTA Alerts NOTE: See the TAWS Phase of Flight definition beginning on page 55. During the final approach phase of flight, RTC/ITI alerts are automatically inhibited when the aircraft is below 200’ AGL while within 0.5 nm of the approach runway or is below 125’ AGL while within 1 nm of the threshold.
Premature Descent Alerting (PDA) <strong>Garmin</strong> TAWS issues a Premature Descent alert when the system detects that the aircraft is significantly below the normal approach path to a runway. There are three different scenarios to consider with PDA: • No Approach Loaded—PDA alerting begins when the aircraft is within 15 nm of the destination airport and ends when the aircraft is either 0.5 nm from the runway threshold OR is at an altitude of 125’ AGL while within 1 nm of the threshold. During the final descent, algorithms will set a threshold for alerting based on altitude, distance, and other parameters. • Non-Precision Approach Loaded—PDA alerting begins when the aircraft is within 15 nm of the destination airport and the aircraft is on the flight plan path. Again, algorithms are used to set a threshold for alerting based upon various parameters (Figure 3-2). PDA alerting ends at 0.5 nm from the runway threshold OR at an altitude of 125’ AGL while within 1 nm of the threshold. • ILS Approach Loaded—PDA alerting begins when the aircraft is within 15 nm of the destination airport and the aircraft is on the flight plan path. Prior to crossing the FAF, the pilot will receive a PDA alert if the aircraft descends more than 200’ below the FAF crossing altitude. Once the aircraft crosses the FAF and is inbound to the runway, PDA will alert the pilot if the aircraft descends 0.7° below the ILS glideslope (Figure 3-3). PDA alerting ends 0.5 nm from the runway threshold OR at an altitude of 125’ AGL while within 1 nm of the threshold. Runway Threshold 0.5 nm PDA Alert is 0.7 Below Glideslope 15 nm Final Approach Fix CAUTION Figure 3-3: An example of a PDA alert threshold for an ILS approach Glideslope Intercept 200' below FAF Altitude Runway Threshold 0.5 nm Section 3 TAWS Alerts PDA Severity Levels CAUTION — The above annunciation and pop-up terrain alert are displayed during a PDA alert. For TAWS, the PDA alert is acompanied by the aural message “Too Low, Terrain”. Final Approach Fix 15 nm 200' below FAF Altitude CAUTION Figure 3-2: Example of Non-Precision Approach PDA alert threshold. The threshold for the descent is computed by algorithms based on varying flight conditions. 59
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400/500 Series Garmin Optional Disp
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WARNING: Terrain data is obtained f
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Section 2: NEXRAD Overview ........
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TERRAIN Phase of Flight ...........
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PART ONE: TRAFFIC INFORMATION SERVI
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TIS information is collected one ra
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Section 2: Control and Display TIS
Page 15 and 16: Map Page TIS traffic is displayed o
Page 17 and 18: Section 3: TIS Operational Procedur
Page 19 and 20: Section 1: Introduction PART TWO: W
Page 21 and 22: NEXRAD Intensity Colors are used to
Page 23 and 24: NOTE: It is recommended that the pi
Page 25 and 26: Displaying NEXRAD Data on the Map P
Page 27 and 28: Data Link Request Log Page (GDL 49
Page 29 and 30: 4. Enter the type of METAR Data you
Page 31 and 32: Displaying Textual METARS Once rece
Page 33 and 34: Section 6: Troubleshooting Although
Page 35 and 36: GDL 69/69A Datalink Status • Sat
Page 37 and 38: Section 1: Introduction Overview PA
Page 39 and 40: When an instrument approach is load
Page 41 and 42: Seven display ranges are available,
Page 43 and 44: General Database Information The Ga
Page 45 and 46: TERRAIN Phase of Flight The TERRAIN
Page 47 and 48: Section 3: TERRAIN Alerts TERRAIN a
Page 49 and 50: Premature Descent Alerting (PDA) Th
Page 51 and 52: TERRAIN Alert Summary Table 3-2 sum
Page 53 and 54: Section 1: Introduction Overview PA
Page 55 and 56: PDA alerting is provided for both n
Page 57 and 58: To display a 120˚ view: 1. Select
Page 59 and 60: TAWS Manual Test Garmin TAWS provid
Page 61 and 62: General Database Information Garmin
Page 63 and 64: TAWS Phase of Flight The TAWS Phase
Page 65: Section 3: TAWS Alerts Alerts are i
Page 69 and 70: Negative Climb Rate After Takeoff A
Page 71 and 72: TAWS Alert Summary The aural alert
Page 73 and 74: Standard Aviation Forecast Abbrevia
Page 75 and 76: Winds Wind Vector — The wind vect
Page 78: © 2004 - 2006 Garmin Ltd. or its s
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