Independent Position Determining

CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-40: INDEPENDENT POSITION DETERMINING 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 Stormscope, Terrain Awareness and Warning System (TAWS), Synthetic Vision System, and Garmin Traffic System (GTS 800). A. Stormscope System The Stormscope system consists of an antenna located on top of the fuselage and a processor unit mounted under the aft baggage floor. The antenna detects the electrical and magnetic fields generated by intra-cloud, inter-cloud, or cloud to ground electrical discharges occurring within 200 nm of the airplane and sends the discharge data to the processor. The processor digitizes, analyzes, and converts the discharge signals into range and bearing data and communicates the data to the MFD every two seconds. The Stormscope system is powered by 28 VDC through the 5-amp DATA LINK/WEATHER circuit breaker on Avionics Bus. For additional information on the Stormscope system, refer to the Stormscope WX-500 User s Guide. (Refer to 5-00) B. 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 s headset and color-coded terrain annunciations displayed on the PFD. C. 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 (approx. 885 ft (270m)) horizontal resolution. 1

CHAPTER 34-40: INDEPENDENT POSITION DETERMINING GENERAL CIRRUS AIRPLANE MAINTENANCE MANUAL 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. D. Garmin Traffic System (GTS 800) The Garmin Traffic System (GTS 800) consists of antennas located on top (GA 58 antenna) and bottom (monopole antenna) of the fuselage and a Line Replaceable Unit (LRU) box installed below the LH cabin seat. GTS 800 is an airborne Traffic Advisory System (TAS) 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 ADAHRS and is controlled via the MFD or Flight Management System Keyboard. The GTS 800 system is powered by 28 VDC through the 5-amp TRAFFIC circuit breaker on Avionics Bus. For additional information on the GTS 800 system, refer to the Cirrus Perspective+ Integrated Avionics System Pilot s Guide. (Refer to 5-00) 2

CIRRUS AIRPLANE MAINTENANCE MANUAL 2. Troubleshooting CHAPTER 34-40: INDEPENDENT POSITION DETERMINING TROUBLESHOOTING Serials w/ Garmin Traffic System (GTS 800): Trouble 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 the GTS 8XX and the circuit breaker is closed. Verify using the USB Install Tool that the GTS 8XX is configured correctly for the desired display. a Ensure USB is properly wired to the GTS 8XX and the circuit breaker is closed. Ensure the audio is properly wired from the GTS 8XX and volume is not set too low. Verify the configuration via the 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. 1030 MHz Fault. Internal Fault. Return to Garmin for service. 1090 MHz Fault. Internal Fault. Return to Garmin for service. Receiver Fault. Antenna connections or internal fault. Ensure all antenna connections are correct otherwise return to Garmin for Service. 3

CHAPTER 34-40: INDEPENDENT POSITION DETERMINING TROUBLESHOOTING CIRRUS AIRPLANE MAINTENANCE MANUAL Trouble Probable Cause Remedy Transmitter Fault. Baro Altitude Fault. Temperature Fault. Red 'X' on a data port on the configuration page. Antenna connections or internal fault. Baro Altimeter is not powered on or improper wiring. Improper configuration settings. Fan is not operating, Poor ventilation at the mounting location. Improper wiring; wrong port or speed selected. Ensure all antenna connections are correct otherwise return to Garmin for Service. Verify that the baro altimeter has power and is properly wired. Verify the configuration is set correctly using the GTS 8XX Install Tool. a Verify the fan is running and the unit is getting adequate ventilation Ensure the port is properly wired to the GTS 8XX and the correct settings are selected on the configuration page. a. Call Cirrus Design for information on obtain the GTS 8XX Install Tool. 4

CIRRUS AIRPLANE MAINTENANCE MANUAL 3. Maintenance Practices CHAPTER 34-40: INDEPENDENT POSITION DETERMINING A. Stormscope Processor and Tray (See Figure 34-40-1) (1) Removal - Stormscope Processor and Tray (c) (d) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. Pull DATA LINK/WEATHER circuit breaker. Remove processor. 1 Remove baggage compartment access panel CF5. (Refer to 6-00) 2 Remove safety wire securing knurled nut to mounting tray, then loosen and swing knurled nut away from clasp. 3 Pull processor straight out of mounting tray and remove from airplane. Remove processor tray. 1 Remove cabin headliner. (Refer to 25-10) 2 Remove LH rear headliner trim. (Refer to 25-10) 3 Remove cable ties securing antenna cable to fuselage wall. 4 Disconnect antenna cable from antenna and remove cable from access panel CF5. 5 Remove fasteners securing tray to baggage floor and remove from airplane. 5

CHAPTER 34-40: INDEPENDENT POSITION DETERMINING CIRRUS AIRPLANE MAINTENANCE MANUAL (2) Installation - Stormscope Processor and Tray Install processor tray. 1 Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Threadlocker - Any Source Lock threads. 2 Position mounting tray washers over floor mounting holes, then secure washers to underside of the floor with masking tape. 3 Position mounting tray assembly against the taped washers, then secure with threadlocker and fasteners. Remove tape. (Refer to 20-40) 4 At access panel CF5, route antenna cable along cabin wall and connect cable to antenna. Secure cable with cable ties as required. 5 Install cabin headliner. (Refer to 25-10) 6 Install LH rear headliner trim. (Refer to 25-10) Install processor. 1 With medium pressure, push processor into mounting tray to engage connectors, then secure with knurled nut. 2 Reset DATA LINK/WEATHER circuit breaker. 3 Perform Functional Test - Stormscope System. (Refer to 34-40) 4 Perform Functional Test - Engine Run-Up with Stormscope System. (Refer to 34-40) 5 Safety wire knurled nut to processor handle. 6 Install access panel CF5 and baggage floor carpet. (Refer to 6-00) (3) Functional Test - Stormscope System (c) Set BAT 1, BAT 2, and AVIONICS switches to ON positions. Pull STARTER and FUEL PUMP circuit breakers. Perform Self-Test and Strike Test procedures. 1 Pull PFD A, PFD B, MFD A, and MFD B circuit breakers. 2 While holding far right softkey on PFD and MFD, restore power to displays by resetting PFD and MFD circuit breakers. 3 When the words INITIALIZING SYSTEM appear in the upper left corner of the displays, release the softkeys. 6

CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-40: INDEPENDENT POSITION DETERMINING (d) (e) 4 On PFD, use [FMS] knob to select OTHER page group. 5 On STORMSCOPE page, use [FMS] knob to activate cursor and move to the MODE field (default to Weather) in the test window. NOTE If processor has been repaired or is a new or different unit from originally installed unit, the words ANTENNA ON TOP? YES OR NO may appear. Select YES to proceed with test. 6 Select SELF TEST and press [ENT] to initiate a SELF TEST. Verify test passes. 7 Select STRIKE TEST and press [ENT] to initiate a STRIKE TEST. Verify test passes. 8 Pull PFD A, PFD B, MFD A, and MFD B circuit breakers. 9 Reset PFD and MFD circuit breakers to restart displays in normal operating mode. Reset STARTER and FUEL PUMP circuit breakers. Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (4) Functional Test - Engine Run-Up with Stormscope System NOTE The Engine Run-up Test must be performed when thunderstorms are not present within 200 nautical miles. Set BAT 1, BAT 2, and AVIONICS switches to ON positions. With the airplane secured outdoors, start engine. (c) Set ALT 1 and ALT 2 switches to ON positions. (d) Set [Range] knob to select 200. (e) Run engine up to 1,500 RPMs, with one or both alternators operating, then verify MFD display is free from erroneous strikes. (f) NOTE Call Cirrus Design Customer Service if test fails. (Refer to AMM-Intro-00) Stop engine, then set all switches to OFF positions. 7

CHAPTER 34-40: INDEPENDENT POSITION DETERMINING CIRRUS AIRPLANE MAINTENANCE MANUAL B. Stormscope Antenna (See Figure 34-40-1) (1) Removal - Stormscope Antenna Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. Pull DATA LINK/WEATHER circuit breaker. (c) Remove cabin headliner. (Refer to 25-10) (d) Disconnect antenna cable from antenna. (e) Remove nuts and washers securing antenna to fuselage. (f) Remove antenna and gasket from top of fuselage. (g) Peel off remaining sealant from fuselage. (2) Installation - Stormscope Antenna Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Caulk Sealant (Refer to 51-30) (Refer to 51-30) Weather sealant. Position antenna gasket and antenna over installation holes, then insert washers and screws. (c) Loosely install the antenna with washers and nuts. (d) Route antenna cable up through installation hole, then connect cable to antenna connector. (e) Place the antenna ground wire terminal ring on the forward mounting screw, then secure both antenna-mounting screws. (f) Install cabin headliner. (Refer to 25-10) (g) Fillet seal antenna perimeter. (Refer to 20-10) (h) Reset DATA LINK/WEATHER circuit breaker. (i) Perform Functional Test - Stormscope System. (Refer to 34-40) (j) Perform Functional Test - Engine Run-Up with Stormscope System. (Refer to 34-40) 8

CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-40: INDEPENDENT POSITION DETERMINING Figure 34-40-1: Stormscope System Installation 1 2 3 4 FUSELAGE (REF) 2 5 6 AFT CABIN FLOOR (REF) 1 7 10 9 2 8 1 LEGEND 1. Screw 2. Washer 3. Antenna 4. Antenna Gasket 5. Terminal Ring 6. Nut 7. Processor 8. Standoff 9. Mounting Tray 10. Knurled Nut SR22_MM34_4903 9

CHAPTER 34-40: INDEPENDENT POSITION DETERMINING CIRRUS AIRPLANE MAINTENANCE MANUAL C. Terrain Awareness & Warning (TAWS) (1) Operational Test - Terrain Awareness & Warning (TAWS) (c) (d) (e) (f) (g) On MFD, select TAWS page from MAP group. Verify title at top of page reads "MAP - TAWS". If TAWS has not been enabled, the title will read MAP - TERRAIN PROXIMITY or MAP - TERRAIN. Press [MENU] then select "Test TAWS" from pop-up menu. After TAWS test has completed, verify "TAWS system test OK" is heard over cockpit speaker. Press [MENU], select "Inhibit TAWS" from pop-up menu, then press [ENT]. Verify "TAWS INHB" is displayed on PFD. With a GPS position acquired, shield or disconnect GPS antennas to remove GPS signal. Verify "DR" is displayed on MFD and "TAWS N/A" annunciation is displayed on both MFD and PFD. Remove shield or reconnect GPS antennas. Verify MFD indications and PFD annunciation are removed and verify that "TAWS Available" is heard over cockpit speaker after about 10 seconds from the moment a 3D GPS solution is reacquired. D. GTS 800 Line Replaceable Unit (LRU) (See Figure 34-40-2) (1) Removal - GTS 800 Line Replaceable Unit (LRU) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. Pull TRAFFIC circuit breaker. (c) Remove LH crew seat. (Refer to 25-10) (d) Remove bolts securing cover panel and lanyard assembly to fuselage floor. (e) Disconnect cables and wiring from LRU. (f) If reinstalling existing LRU, maintain QMA termination plug installations on J2 BTM, J3 BTM, and J4 BTM connectors. (g) If installing new LRU, remove and retain QMA termination plugs from J2 BTM, J3 BTM, and J4 BTM connectors. (h) Loosen knurled nut on LRU rack to detach LRU and remove from airplane. 10

CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-40: INDEPENDENT POSITION DETERMINING (2) Installation - GTS 800 Line Replaceable Unit (LRU) (c) (d) (e) (f) (g) (h) Slide LRU onto LRU rack and hand tighten knurled nut. Connect wiring harnesses to LRU. Connect upper antenna cables to LRU. 1 Connect yellow tagged upper antenna cable to yellow colored J1 TOP LRU connector. 2 Connect black tagged upper antenna cable to black colored J2 TOP LRU connector. 3 Connect blue tagged upper antenna cable to blue colored J3 TOP LRU connector. 4 Connect red tagged upper antenna cable to red colored J4 TOP LRU connector. Connect lower antenna cable/qma termination plugs to LRU. 1 Connect yellow tagged lower antenna cable to yellow colored J1 BTM LRU connector. 2 If not already installed, connect QMA termination plug to black colored J2 BTM LRU connector. 3 If not already installed, connect QMA termination plug to blue colored J3 BTM LRU connector. 4 If not already installed, connect QMA termination plug to red colored J4 BTM LRU connector. Position cover panel and lanyard assembly to fuselage floor and secure with bolts. Reset TRAFFIC circuit breaker. If LRU is a different unit from the originally installed LRU: 1 Perform Adjustment/Test - Component Software and Configuration Loading. (Refer to 42-00) 2 Perform Functional Test - GTS 800 System. (Refer to 34-40) If LRU is the same unit as the originally installed LRU: 1 Perform Functional Test - GTS 800 System. (Refer to 34-40) (i) Install LH crew seat. (Refer to 25-10) (3) Functional Test - GTS 800 System Perform GTS 800 TAS Testing according to Cirrus Perspective+ Line Maintenance Manual. 11

CHAPTER 34-40: INDEPENDENT POSITION DETERMINING CIRRUS AIRPLANE MAINTENANCE MANUAL E. GTS 800 Line Replaceable Unit (LRU) Rack (See Figure 34-40-2) (1) Removal - GTS 800 Line Replaceable Unit (LRU) Rack Remove Garmin GTS 800 LRU. (Refer to 34-40) (c) (d) NOTE Nutplates may be secured to cabin floor surface with 5-minute epoxy. Remove washers and bolts securing mounting brackets to nutplates and cabin floor. Remove screws securing LRU rack to mounting brackets. Remove retainer plates from slots in rack. Remove rack from airplane. (2) Installation - GTS 800 Line Replaceable Unit (LRU) Rack (c) (d) Install retainer plates into slots in rack. Position mounting brackets to LRU rack and secure with screws. NOTE Nutplates may be secured to cabin floor surface with 5-minute epoxy. Position nutplates to installation area below cabin floor surface. Install bolts and washers securing mounting brackets to nutplates and cabin floor. (e) Install GTS 800 LRU. (Refer to 34-40) F. GTS 800 Upper Antenna (See Figure 34-40-2) (1) Removal - GTS 800 Upper Antenna Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. Pull TRAFFIC circuit breaker. 12

CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-40: INDEPENDENT POSITION DETERMINING (c) Remove cabin headliner. (Refer to 25-10) (d) Disconnect antenna cables from antenna. (e) Remove screws, washers, and nuts securing antenna to fuselage. (f) Remove antenna and gasket from top of fuselage. (g) Remove remaining sealant from fuselage. (2) Installation - GTS 800 Upper Antenna Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Caulk Sealant (Refer to 51-30) (Refer to 51-30) Weather sealant. Utility Knife - Any Source Trim gasket. (c) (d) (e) (f) (g) (h) 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 Install longer screws on RH side of upper antenna. Secure antenna using screws, washers, and nuts. Tighten each screw until gasket material is evenly compressed on all sides of antenna. Apply a continuous bead of sealant around perimeter of antenna and fuselage mating surfaces. Using sealant, fill screw recesses flush to top surface. Connect cables to antenna. 1 Connect blue tagged antenna cable to blue colored aft antenna connector (J3). 2 Connect black tagged antenna cable to black colored aft antenna connector (J2). 3 Connect red tagged antenna cable to red colored forward antenna connector (J4). 4 Connect yellow tagged antenna cable to yellow colored forward antenna connector (J1). Reset TRAFFIC circuit breaker. 13

CHAPTER 34-40: INDEPENDENT POSITION DETERMINING CIRRUS AIRPLANE MAINTENANCE MANUAL (i) Perform Functional Test - GTS 800 System. (Refer to 34-40) (j) Install cabin headliner. (Refer to 25-10) G. GTS 800 Lower Antenna (See Figure 34-40-2) (1) Removal - GTS 800 Lower Antenna Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. Pull TRAFFIC circuit breaker. (c) Remove passenger seats. (Refer to 25-10) (d) Remove cabin floor covering. (Refer to 25-10) (e) Remove access panel CF4C. (Refer to 6-00) (f) Disconnect antenna cable from antenna. (g) Remove washers and nuts securing antenna to fuselage. (h) Remove antenna and gasket from bottom of fuselage. (i) Remove remaining sealant from fuselage. (2) Installation - GTS 800 Lower Antenna Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Caulk Sealant (Refer to 51-30) (Refer to 51-30) Weather sealant. Utility Knife - Any Source Trim gasket. (c) (d) (e) 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. Secure antenna using washers and nuts. Tighten each nut until gasket material is evenly compressed on all sides of antenna. Apply a continuous bead of sealant around perimeter of antenna and fuselage mating surfaces. 14

CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-40: INDEPENDENT POSITION DETERMINING (f) Connect cable to antenna. (g) Reset TRAFFIC circuit breaker. (h) Perform Functional Test - GTS 800 System. (Refer to 34-40) (i) Install access panel CF4C. (Refer to 6-00) (j) Install cabin floor covering. (Refer to 25-10) (k) Install passenger seats. (Refer to 25-10) 15

CHAPTER 34-40: INDEPENDENT POSITION DETERMINING CIRRUS AIRPLANE MAINTENANCE MANUAL Figure 34-40-2: GTS 800 System (1 of 2) B C A 11 5 12 P1323 TRAFFIC HARNESS (REF) J1321 TRAFFIC HARNESS (REF) TO CENTER CONSOLE 8 8 2 4 TO ANTENNAS 9 6 4 J1322 TRAFFIC HARNESS (REF) 3 5 7 8 5 4 5 8 1 CABIN FLOOR (REF) NOTE May be secured to cabin floor surface with 5-minute epoxy. QMA termination plugs installed at J2 BTM, J3 BTM, and J4 BTM. 6 LEGEND 1. Cover Panel 2. Mounting Bracket 3. Lanyard 4. Retainer Plate 5. Bolt 6. Nutplate 7. Screw 8. Washer 9. QMA Termination Plugs 10. GTS 800 LRU 11. GTS 800 LRU Rack SR22_MM34_5109 16

CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-40: INDEPENDENT POSITION DETERMINING Figure 34-40-2: GTS 800 System (2 of 2) 7 TO LRU 13 FUSELAGE (REF) 12 14 15 8 FUSELAGE (REF) 14 8 15 13 TO LRU DETAIL C 12 DETAIL B NOTE Install longer screws on RH side of upper antenna. LEGEND 7. Screw 8. Washer 12. Antenna Cable 13. Antenna 14. Gasket 15. Nut SR22_MM34_5113 17

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