Independent Position Determining

Transcription

1 GENERAL Independent Position Determining 34-40: INDEPENDENT POSITION DETERMINING 1. General This section covers that portion of the system which provides information to determine position from sources which are mainly independent of ground installations. This includes the Terrain Awareness and Warning System (TAWS), Synthetic Vision System, Enhanced Vision System (EVS), and Garmin Traffic System (GTS 855). A. Terrain Awareness and Warning System (TAWS) The Terrain Awareness/Warning System receives data from the GPS receiver to determine horizontal position and altitude and compares this information to the onboard terrain and obstacle databases to calculate and predict the aircraft s flight path in relation to the surrounding terrain and obstacles. In this manner, TAWS provides advanced alerts of predicted dangerous terrain conditions via aural alerts communicated through the pilot headset and color-coded terrain annunciations displayed on the PFD. B. Synthetic Vision System The Synthetic Vision System (SVS) is intended to provide the pilot with enhance situational awareness by placing a three dimensional depiction of terrain, obstacles, traffic, and the desired flight path on the PFD so that proximity and location is more easily understood during instrument scanning. The SVS database is created from a digital elevation model with a 9 arc-sec (approximately 885 ft (270m)) horizontal resolution. The synthetic vision system is not intended to be used independently of traditional attitude instrumentation. Consequently, SVS is disabled when traditional attitude instrumentation is not available. Otherwise, the traditional attitude instrumentation will always be visible in the foreground with SVS features in the background. The PFD with SVS installed includes: Perspective depiction of surrounding terrain, Zero pitch line, Perspective depiction of runways, Perspective depiction of large bodies of water, Perspective depiction of obstacles, Flight path marker, Terrain warning system, Field of view depiction on the MFD Navigation Page Dec 2016

2 GENERAL C. Enhanced Vision System (EVS) The Enhanced Vision System (EVS) is an electro-optical system that uses a Long-Wave Infrared (IR) camera to enhance situational awareness. Infrared is particularly effective at night, smoke, haze, and smog in addition to a broad spectrum of rain, snow, and radiation-type fog. EVS is an aid to visual acquisitions of: Ground vehicles and other ground-based equipment/obstacles, Aircraft on taxi-ways and runways, Other traffic during takeoff, approach, and landing, Runway and taxi lights, Runway and terrain features during climb, descent, and low altitude maneuvering. The EVS sensor, located in the LH nose of the aircraft, contains a long-wave infrared camera that produces a infrared image and a low-light CMOS camera that produces a visible image. The two images are then combined to produce a single monochrome image that is transmitted directly to the MFD. Upon power-up the sensor requires approximately 90 seconds to produce a usable image. 28 VDC for Enhanced Vision System operation is supplied through the 3-amp EVS circuit breaker on MAIN FN1. For additional information on the EVS system, see manufacturer s approved Instructions For Continued Airworthiness. (Refer to 5-00) D. Garmin Traffic Collision Avoidance System (GTS 855) The Garmin Traffic System (GTS 855) consists of an antenna located on top and bottom of the fuselage and a Line Replaceable Unit (LRU) box mounted on the aft avionics shelf. GTS 855 is an airborne Traffic Collision Avoidance System (TCAS-1) that advises the pilot of transponder-equipped aircraft that may pose a collision threat. Traffic advisory information is displayed on the PFD and indicates the relative range, bearing, and altitude of intruder aircraft. The system utilizes inputs from the secondary Integrated Avionics Units via the primary Air Data Computer and is controlled via the MFD or touchscreen controllers. The GTS 855 system is powered by 28 VDC through the 3-amp TRAFFIC circuit breaker on MAIN A1. Serials 0005 thru 0093: For additional information on the GTS 855 system, see Perspective Touch Integrated Avionics System Pilot s Guide. (Refer to 5-00) Serials 0094 & subs: For additional information on the GTS 855 system, see Perspective Touch+ Integrated Avionics System Pilot s Guide. (Refer to 5-00) 2 03 Dec 2018

3 GENERAL E. Garmin Weather Radar (GWX 70) CAUTION When power is applied to the aircraft, the GWX Weather Radar (if installed) will execute its self-test, which includes a sweep of the GWX array on all axes to verify full range of motion before entering Standby mode. The self-test does not activate radiated sweeps, however ensure appropriate precautions are taken with regard to array movement per the instructions above.to avoid accidental radar hard contact with the radome when the aircraft is jacked, pull RADAR (M3) circuit breaker to disable the radar. Before applying power, ensure that: The aircraft is grounded. External power is applied to aircraft (28±1.0 VDC). All personnel are off of aircraft or are aware that power is coming on. Circuit breakers for equipment under test have been reset. Verify that antennas or appropriate termination loads are installed on all transmitting hardware. If GWX Weather Radar is installed, verify that aircraft radome is either installed according to production specification or fully removed with EVS camera electrical wiring disconnected and mating connector properly stowed. Ensure that GWX array is clear of any interference/obstructions. The Garmin Airborne Weather Radar (GWX 70), mounted in the nose of the aircraft, is a microprocessor-based LRU which outputs weather radar data to the MFD. It communicates through the high-speed data bus. There are five modes: Standby - provides a warm-up period. No RF is transmitted. Test - the system runs a self-test function. Ground - the ground mapping mode to display terrain data. Operate - the normal operating mode to display weather data. The GWX 70 system is powered by 28 VDC through the 3-amp RADAR circuit breaker on MAIN FN1. Serials 0005 thru 0093: For additional information on the GWX 70 system, see Perspective Touch Integrated Avionics System Pilot s Guide. (Refer to 5-00) Serials 0005 thru 0093: For additional information on the GWX 70 system, see Perspective Touch+ Integrated Avionics System Pilot s Guide. (Refer to 5-00) 3

4 TROUBLESHOOTING 2. Troubleshooting Trouble - GTS 855 Probable Cause Remedy Unit does not power up - Data failed message. GTS 8XX Install Tool won't display any pages.a No Audio alerts. Configuration Fault. Improper wiring; circuit breaker open. Improper configuration. Improper wiring; circuit breaker open. Improper wiring; Volume not set correctly. Both internal and external configuration checks failed. Ensure power is properly wired to GTS 8XX and circuit breaker is closed. Using USB Install Tool, verify GTS 8XX is configured correctly for the desired display. a Ensure USB is properly wired to GTS 8XX and circuit breaker is closed. Ensure audio is properly wired from the GTS 8XX and volume is not set too low. Verify configuration via GTS 8XX Install Tool.a Verify wiring to the configuration module and replace if necessary. FPGA Fault. Internal Fault. Return to Garmin for service. ROM Fault. Internal Fault. Return to Garmin for service. Execution Fault. Internal Fault. Return to Garmin for service. Electrical Fault. Internal Fault. Return to Garmin for service. Whisper Shout Fault. Internal Fault. Return to Garmin for service. Transmit Power Fault. Internal voltages are out of tolerance. Verify input voltage and if it continues return to Garmin for service MHz Fault. Internal Fault. Return to Garmin for service MHz Fault. Internal Fault. Return to Garmin for service. Receiver Fault. Transmitter Fault. Antenna connections or internal fault. Antenna connections or internal fault. Ensure all antenna connections are correct otherwise return to Garmin for Service. Ensure all antenna connections are correct otherwise return to Garmin for Service Dec 2016

5 TROUBLESHOOTING Trouble - GTS 855 Probable Cause Remedy Baro Altitude Fault. Baro Altimeter is not powered on or improper wiring. Improper configuration settings. Verify baro altimeter has power and is properly wired. Verify configuration is set correctly using the GTS 8XX Install Tool.a Temperature Fault. Fan is not operating, Poor ventilation at the mounting location. Verify fan is running and unit is getting adequate ventilation Red 'X' on a data port on the configuration page. Improper wiring; wrong port or speed selected. Ensure port is properly wired to GTS 8XX and correct settings are selected on configuration page. a. Call Cirrus Aircraft for information on obtaining the GTS 8XX Install Tool. Trouble - EVS Probable Cause Remedy Video image not displayed. Software not configured. Perform Adjustment/Test - Software and Configuration Loading, selecting the EVS option. (Refer to 42-00) No power to EVS unit. Display not receiving image information. Following initial power-up, listen for series of clicks as camera shutters open and close. If camera doesn t power on, verify security of connectors and wire harness. Verify security of connectors and wire harness. Halo Images. As sensor windows are heated, infrared detector not able to compensate for signal from window, as compared to outside view, so a white (hot) area may appear around image perimeter. Turn system on during preflight or run-up to stabilize window and body heaters prior to flight and allow thermal stabilization. Image degraded, or possibly even displayed as solid black or solid white. Display is visible but has an X and some bars through the image. Improper display settings. Anti-Tamper device not connected properly. Faulty wiring. Following initial power-up, adjust brightness and contrast settings to obtain best image. Verify anti-tamper device is connected to proper pin. Check wiring connecting anti-tamper device. 5

6 NOTE Serials 0005 thru 0093: Troubleshooting procedures for the GWX 70 Weather Radar are described in the Cirrus Perspective Touch Integrated Avionics System Line Maintenance Manual, P/N Serials 0004 & subs: Troubleshooting procedures for the GWX 70 Weather Radar are described in the Cirrus Perspective Touch+ Integrated Avionics System Line Maintenance Manual. 3. Maintenance Practices A. Terrain Awareness & Warning (TAWS) (1) Operational Test - Terrain Awareness & Warning (TAWS) NOTE This test requires a Garmin TAWS unlock card. Without the TAWS unlock card, the GTC button for [TAWS] will be replaced with [Terrain Proximity]. (a) (b) (c) (d) (e) (f) From GTC MFD Home screen, select [MAP] - [TAWS]. Verify title at top of page reads "MAP - TAWS". If TAWS has not been enabled, select [Terrain Proximity] and map will display TERRAIN PROXIMITY at the top. Press [MENU], and then select "Test TAWS" from pop-up menu. After TAWS test has completed, verify "TAWS system test OK" is heard in either pilot or co-pilot headset. Press [MENU], select "Inhibit TAWS" from pop-up menu, and then press [ENT]. Verify "TAWS INHB" is displayed on PFD. Press [MENU] again, select Enable TAWS from the pop-up menu, and then press [ENT]. Verify TAWS INHB annunciation on PFD has extinguished Dec 2018

7 B. Enhanced Vision System (EVS) Camera (See Figure ) (1) Removal - EVS Camera (a) Set BAT 1 and BAT 2 switches to OFF positions. (b) Pull EVS CAMERA circuit breaker. (c) Remove radome. (Refer to 53-50) (d) Disconnect wire harness connector from camera. (e) Remove screws and washers securing camera to bracket. Remove camera from airplane. (2) Installation - EVS Camera (a) Position and secure camera to bracket with screws and washers. (b) Connect wire harness connector to camera. (c) Install radome. (Refer to 53-50) (d) Reset EVS CAMERA circuit breaker. (e) Perform Operational Test - EVS Camera. (Refer to 34-40) 7 03 Dec 2018

8 (3) Operational Test - EVS Camera NOTE The EVS camera is focused to infinity, so ensure anything within the field of view closer than 15 feet from the sensor. The aircraft should be level in a configuration as close as possible to straight and level flight to check the horizon alignment between the camera angle and the PFD display. Two technicians are required to simultaneously test EVS field of vision and monitor video output. (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Flashlight, Bright LED - Any Source Test sensor. (b) (c) (d) (e) (f) (g) (h) (i) Pull IGNITER 1, IGNITER 2, and FUEL PUMP CTRL circuit breakers. Set BAT 1 switch to ON position. Using GTC, turn on EVS sensor. Following EVS camera startup, verify MFD displays sensor imagery. As technician stands in EVS field of vision and waves right arm, verify image is upright and not mirrored. NOTE The EVS sensor has a Non Uniformity Function (NUC) that provides for optimal performance from the infrared sensor. It automatically activates to stabilize the thermal sensor temperature. During the NUC function, a green square will appear in the top right corner of the display. As technician aims flashlight at sensor window and cycles light on and off, verify image can be distinguished between thermal and visible light targets. Set BAT 1 switch to OFF position. Reset IGNITER 1, IGNITER 2, and FUEL PUMP CTRL circuit breakers Dec 2018

9 Figure : EVS Camera A LEGEND 1. Screw 2. Washer 3. EVS Camera 4. Bracket 5. Connector 6. Ground Wire 7. Bolt DETAIL A SF50_MM34_0039 9

10 C. Garmin GTS 855 Line Replaceable Unit (LRU) (See Figure ) (1) Removal - Garmin GTS 855 Line Replaceable Unit (LRU) (a) Set BAT 1 and BAT 2 switches to OFF positions. (b) Pull IGNITER 1, IGNITER 2, and FUEL PUMP CTRL circuit breakers. (c) Remove gallery trim. (Refer to 25-10) (d) Disconnect cables and wiring from LRU. (e) Loosen knurled nut on retainer bracket to detach LRU and remove from airplane. (2) Installation - Garmin GTS 855 Line Replaceable Unit (LRU) (a) (b) (c) (d) (e) Slide LRU onto retainer bracket and hand tighten knurled nut. Connect wiring harnesses to LRU. Connect antenna cables to LRU. Reset IGNITER 1, IGNITER 2, and FUEL PUMP CTRL circuit breakers. Perform Operational Test - Garmin GTS 855 Line Replaceable Unit (LRU). (Refer to 34-40) (f) Install gallery trim. (Refer to 25-10) (3) Operational Test - Garmin GTS 855 Line Replaceable Unit (LRU) (a) (b) (c) Set BAT 1 and BAT 2 switches to ON positions. Display traffic data on the MFD. 1 From GTC Home screen, select [TRAFFIC] - [Traffic Settings] - [Operate]. 2 Verify traffic data is displayed on traffic map. Pull TRAFFIC circuit breaker. Verify TCAS information becomes invalid on the MFD. 1 The traffic map displays "NO DATA" in the center. 2 The Navigation map displays "NO TRAFFIC DATA" in lower left. 3 Go to GTC Message center and verify message alert "Traffic Fail" Dec 2018

11 (d) (e) Reset TRAFFIC circuit breaker. Verify traffic information returns to normal and error message clears. Set BAT 1 and BAT 2 switches to OFF positions. D. Garmin GTS 855 Upper Antenna (See Figure ) (1) Removal - Garmin GTS 855 Upper Antenna (a) Set BAT 1 AND BAT 2 switches to OFF positions. (b) Pull ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers. (c) Remove forward center nacelle panel. (Refer to 54-20) (d) Disconnect cables from antenna. (e) Remove screws, washers, and nuts securing antenna to nacelle panel. (f) Remove antenna and gasket from nacelle panel. (g) Remove remaining sealant from nacelle panel. (2) Installation - Garmin GTS 855 Upper Antenna (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Caulk Sealant (Refer to 51-30) (Refer to 51-30) Seal antenna. Utility Knife - Any Source Trim gasket. (b) (c) To improve cosmetic appearance of gasket installation, use utility knife to remove 0.2 inch (0.5 cm) from perimeter of new gasket. With arrow on antenna facing forward, place antenna and gasket into position. NOTE Ensure antenna gasket is evenly compressed between antenna and nacelle skin per visual inspection from all sides. 11

12 (d) Install screws, washers and nuts securing antenna and gasket to nacelle panel. Tighten each screw until gasket material is evenly compressed on all sides of antenna. (e) Fillet seal antenna perimeter. (Refer to 20-10) (f) Using sealant, fill screw recesses flush to top surface. (g) Connect cables to antenna. (h) Reset ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers. (i) Install forward center engine nacelle panel. (Refer to 54-20) E. Garmin GTS 855 Lower Antenna (See Figure ) (1) Removal - Garmin GTS 855 Lower Antenna (a) Set BAT 1 and BAT 2 switches to OFF positions. (b) Pull ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers. (c) Remove access panel FB4L. (Refer to 6-00) (d) Disconnect antenna cable from antenna. (e) Remove washers and nuts securing antenna to fuselage. (f) Remove antenna and gasket from fuselage. (g) Remove remaining sealant from fuselage. (2) Installation - Garmin GTS 855 Lower Antenna (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Caulk Sealant (Refer to 51-30) (Refer to 51-30) Seal antenna. Utility Knife - Any Source Trim gasket. (b) (c) To improve cosmetic appearance of gasket installation, use utility knife to remove 0.2 inch (0.5 cm) from perimeter of new gasket. With arrow on antenna facing forward, place antenna and gasket into position. 12

13 NOTE Ensure antenna gasket is evenly compressed between antenna and fuselage skin per visual inspection from all sides. (d) Install washers and nuts securing antenna and gasket to fuselage. Tighten each nut until gasket material is evenly compressed on all sides of antenna. (e) Fillet seal antenna perimeter. (Refer to 20-10) (f) Connect cable to antenna. (g) Reset ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers. (h) Install access panel FB4L. (Refer to 6-00) 13

14 Figure : Garmin GTS 855 LRU and Antennas (Sheet 1 of 2) B A C CAPS SHELF (REF) DETAIL A 7 8 LEGEND 1. GTS 855 LRU 2. Electrical Connector 3. Antenna Connector 4. Cap 5. Screw 6. Bracket 7. Washer 8. Nut SF50_MM34_ Dec 2018

15 Figure : Garmin GTS 855 LRU and Antennas (Sheet 2 of 2) NACELLE PANEL (REF) DETAIL B WING BELLY FAIRING (REF) LEGEND 3. Antenna Connector 5. Screw 7. Washer 8. Nut 9. Antenna 10. Gasket DETAIL C SF50_MM34_

16 F. Garmin Weather Radar (GWX 70) (See Figure ) (1) Removal - Garmin Weather Radar (GWX 70) (a) Set BAT 1 and BAT 2 switches to OFF positions. (b) Pull RADAR circuit breaker. (c) Remove radome. (Refer to 53-50) (d) Disconnect wire harness connector from radar assembly. (e) Remove nuts, washers, and screws securing radar assembly to nose bulkhead. Remove radar assembly from airplane. (2) Installation - Garmin Weather Radar (GWX 70) (a) Position and secure radar assembly to nose bulkhead with screws, washers, and nuts. (b) Connect wire harness connector to radar assembly. (c) Install radome. (Refer to 53-50) (d) Reset RADAR circuit breaker. (e) Perform Operational Test - Garmin Weather Radar (GWX 70). (Refer to 34-40) (3) Operational Test - Garmin Weather Radar (GWX 70) (a) (b) (c) (d) (e) Pull IGNITER 1, IGNITER 2, and FUEL PUMP CTRL circuit breakers. Set BAT 1 switch to ON position. Using GTC, navigate to Weather Radar page. Test mode: NOTE No transmission will occur in test mode. 1 Place Weather Radar in Test mode. 2 After self-test is complete, verify test pattern is displayed on radar screen. 3 Verify "Weather" is displayed as source in upper left corner of radar screen. Operate mode: 16

17 (f) (g) (h) WARNING The radar produces microwave radiation. Follow all safety precautions and instructions in the Garmin operating and install manuals. Do not transmit until it is safe to do so. When transmitting while the aircraft is on the ground, no personnel or objects should be within vicinity. The 12-inch antenna minimum safe distance is 9.6 feet from antenna as determined by Garmin and published in the Garmin GWX 70 Installation Manual, Never operate the radar when aircraft is being fueled or de-fueled. 1 Ensure no personnel are within vicinity. 2 Place Weather Radar in Operate mode. 3 Select various ranges and scan patterns. 4 Verify any weather conditions within sight are displayed on radar screen. Set BAT 1 switch to OFF position. Reset IGNITER 1, IGNITER 2, and FUEL PUMP CTRL circuit breakers. Perform flight test to verify proper operation of Weather Radar. 17

18 Figure : Weather Radar A DETAIL A LEGEND 1. Screw 2. Garmin Weather Radar (GWX 70) 3. Connector SF50_MM34_