Flight Environmental Systems

Transcription

1 CIRRUS AIRPLANE MAINTENANCE MANUAL Flight Environmental Systems CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS GENERAL 34-0: FLIGHT ENVIRONMENTAL SYSTEMS. General This section covers that portion of the system which senses environmental conditions and uses the data to influence navigation of the airplane. This includes pitot-static, outside air temperature sensors, altimeter, airspeed indicator, air data attitude heading reference system (ADAHRS), and MD30 Standby Attitude Module. (See Figure ) For information pertaining to the Air Data Attitude Heading Reference System (ADAHRS), see Attitude and Direction. (Refer to 3-0) A. Pitot-Static The pitot system utilizes an L shaped mast with integral pitot tube and heater located on the LH wing just inboard of the wing tip to sense impact or ram air pressure. The pitot mast utilizes an electrical heating element to prevent ice from blocking ram air. Pitot heat is controlled by a switch located in the center of the bolster switch panel. The Crew Alerting System (CAS) displays a PITOT HEAT caution on the MFD if the PITOT HEAT switch is set to ON position and the pitot heater is not using power. A CAS PITOT HT RQD caution displays if the outside air temperature is less than or equal to 5 C. The pitot heat system operates on 8 VDC supplied through the 7.5-amp PITOT HEAT circuit breaker on Non-Essential Bus. The normal static system utilizes two ports, a static source water trap, an alternate static source selector valve, and the necessary plumbing to provide static air pressure sensing for the ADAHRS, airspeed indicator, and altimeter. Serials w/ MD30 Standby Attitude Module: The optional MD30 Standby Attitude Module is a combined standby airspeed indicator, standby altimeter, and standby attitude indicator. The normal static system provides the necessary plumbing to provide static air pressure sensing for the unit. The normal static ports are located on the LH and RH sides of the fuselage behind the aft cabin bulkhead. The static line runs from these ports to a tee connector mounted on the aft cabin bulkhead to a water trap located under access panel CFL. (Refer to 6-00) A static line sump mounted directly to the ports provides increased resistance against forced water intrusion. The alternate static source valve, located on the lower LH side of the console, provides an alternate source of static air pressure from inside the cabin in the event the normal static sources are plugged. NOTE The alternate static source is to be used when the normal system is inoperative or malfunctioning. When alternate static air is used, instrument readings will vary 3 Dec 06

2 CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS GENERAL CIRRUS AIRPLANE MAINTENANCE MANUAL from normal readings due to static air being obtained from the cabin. Refer to the Pilot s Operating Handbook for flight operation using alternate static air. B. Outside Air Temperature (OAT) Sensors The ADAHRS receives OAT signals from a temperature sensor installed in the RH wing. C. Airspeed Indicator () Airspeed Indicator - Serials w/o MD30 Standby Attitude Module The airspeed indicator is a differential air pressure gage which measures the difference between ram air pressure and static air pressure to indicate the speed of the airplane. An adjustment knob allows the pilot to correlate outside air temperature with pressure altitude, thereby allowing the airspeed indicator to show both true and indicated airspeeds. A movable pointer and a fixed dial with the 0 index at the o clock position indicates airspeed. Range of the instrument is 0 to 0 knots. The GSU 75 ADAHRS processes airspeed data for display on the PFD. A standby airspeed indicator is located in the LH bolster panel. () Airspeed Indicator - Serials w/ MD30 Standby Attitude Module The airspeed indicator is a differential air pressure gage which measures the difference between ram air pressure and static air pressure to indicate the speed of the airplane. A fixed pointer in the airspeed window indicates current airspeed on a scrolling airspeed tape. Range of the instrument is 0 to 500 knots. The GSU 75 ADAHRS processes airspeed data for display on the PFD. The optional MD30 Standby Attitude Module is a combined standby airspeed indicator, standby altimeter, and standby attitude indicator. The MD30 Standby Attitude Module is located in the LH bolster panel. D. Altimeter () Altimeter - Serials w/o MD30 Standby Attitude Module The altimeter converts static pressure into a visual indication of airplane altitude above sea level. Pointers on the instrument dial indicate altitude in increments of 00, 000, and 0,000 feet, with a range of -000 to 0,000 feet. The GSU 75 ADAHRS processes altitude data for display on the PFD. A standby altimeter is located in the LH bolster panel. 3 Dec 06

3 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS GENERAL () Altimeter - Serials w/ MD30 Standby Attitude Module The altimeter converts static pressure into a visual indication of airplane altitude above sea level. A fixed pointer in the altitude window indicates altitude in increments of 0, 00,,000 and 0,000 feet on a scrolling altitude tape. The range of the instrument is -,500 to 55,000 feet.the GSU 75 ADAHRS processes altitude data for display on the PFD. The optional MD30 Standby Attitude Module is a combined standby airspeed indicator, standby altimeter, and standby attitude indicator. The MD30 Standby Attitude Module is located in the LH bolster panel. E. Air Data Attitude Heading Reference System (ADAHRS) The GSU 75 ADAHRS, located behind the LH instrument panel, processes data from the pitot-static system and outside air temperature (OAT) sensors to provide pressure altitude, airspeed, vertical speed, and OAT information to the Perspective+ Avionics system. It also provides aircraft attitude and heading information to the PFD and primary GIA 63 integrated avionics unit. The ADAHRS contains advanced sensors (including accelerometers and rate sensors) and interfaces with the magnetometer to obtain magnetic field information and both GIA 63 integrated avionics unit to obtain GPS information. A second ADAHRS may be installed by option. 8 VDC for the standard ADAHRS is supplied through the 5-amp ADAHRS circuit breaker on Essential Bus. 8 VDC for the optional ADAHRS is supplied through the 5-amp ADAHRS circuit breaker on Main Bus. The GSU 75 ADAHRS is integral to the Perspective+ Avionics Integrated Avionics system. For an overview of the Perspective+ Avionics system, refer to Chapter 4, Integrated Modular Avionics. (Refer to 4-00) 3 3 Dec 06

4 CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS TROUBLESHOOTING. Troubleshooting CIRRUS AIRPLANE MAINTENANCE MANUAL Trouble - Pitot-Static Probable Cause Remedy Erroneous altimeter or vertical speed indication. Incorrect or sluggish response on all three pitot-static instruments. Pitot tube does not heat or melt ice. Pitot tube does not heat or melt ice. Pitot Light ON. Leaks in static and/or pitot line. Leaks or obstruction in static line. PITOT HEAT switch is set to OFF position. Circuit breaker out. Break in wiring. Insufficient current. Check lines for leaks. Perform System Test - Static System Plumbing. (Refer to 34-0) Check lines for leaks. Perform System Test - Pitot System Plumbing. (Refer to 34-0) Repair or replace line. Remove obstruction. Set PITOT HEAT switch to ON position. Reset circuit breaker. Test and repair wiring. Check current drain of element. Heating element burned out. Replace Pitot Mast (Refer to 34-0). Low or sluggish airspeed indication. Normal altimeter and vertical speed indication. Pitot tube deformed. Leak or obstruction in pitot line. Check pitot mast for condition. Perform Inspection/Check - Pitot Mast. (Refer to 34-0) Repair or replace damaged component. Trouble - Altimeter Probable Cause Remedy Pointer indicates erroneous data. Cracked or loose cover glass. Moisture in static traps and/or sump. Moisture in static line. Excessive vibration caused by loose mounting screws. Check traps and sump for moisture. Blow out lines. Check lines for moisture. Perform System Test - Static System Plumbing. (Refer to 34-0) Tighten mounting screws. High reading. Static system leak. Inspect static system. (Refer to 34-0) Excess scale error. Improper calibration adjustment. Replace instrument. Excessive pointer oscillation. Defective instrument. Replace or repair instrument. Difficult to rotate setting knob. Wrong or lack of lubrication. Replace or repair instrument. 4 3 Dec 06

5 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS TROUBLESHOOTING Trouble - Airspeed Indicator Probable Cause Remedy Pointer fails to respond or indicates improperly. Leak in instrument case. Obstruction in pitot line. Replace or repair instrument. Check line for obstruction. Blow out lines. (Refer to 34-0) Incorrect indication or pointer oscillates. Alternate static source valve open. Close for normal operation. Moisture in static traps and/or sump. Check traps and sump for moisture. Blow out lines. Pointer vibrates. Moisture in static line. Leak in pitot or static lines. Leaking or ruptured diaphragm. Excessive vibration caused by loose mounting screws. Excessive pitot tube vibration. Check lines for moisture. Perform System Test - Static System Plumbing. (Refer to 34-0) Repair or replace damaged lines. Tighten connections. Substitute known-good indicator and check reading. Replace or repair instrument. Tighten mounting screws. Tighten clamps and connections. 5 3 Dec 06

6 CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS TROUBLESHOOTING CIRRUS AIRPLANE MAINTENANCE MANUAL Serials w/ MD30 Standby Attitude Module: Trouble Probable Cause Remedy Altimeter indicates erroneous data. Moisture in static traps and/or sump. Moisture in static line. Check traps and sump for moisture. Blow out lines. Check lines for moisture. Perform System Test - Static System Plumbing. (Refer to 34-0) Altimeter indicates high reading. Static system leak. Inspect static system. (Refer to 34-0) Altimeter displays excess scale error. Improper calibration adjustment. Replace instrument. Excessive altitude indicator oscillation. Defective instrument. Replace or repair instrument. Difficult to rotate setting knob. Wrong or lack of lubrication. Replace or repair instrument. Airspeed indicator fails to respond or indicates improperly. Leak in instrument case. Obstruction in pitot line. Replace or repair instrument. Check line for obstruction. Blow out lines. (Refer to 34-0) Airspeed indicator oscillates or indicates improperly. Alternate static source valve open. Close for normal operation. Moisture in static traps and/or sump. Check traps and sump for moisture. Blow out lines. Attitude indicator horizon bar vibrates excessively, oscillates, or does not settle. Moisture in static line. Leak in pitot or static lines. Leaking or ruptured diaphragm. Excessive vibration caused by loose mounting screws. Excessive pitot tube vibration. Defective instrument. Excessive vibration caused by loose mounting screws. Check lines for moisture. Perform System Test - Static System Plumbing. (Refer to 34-0) Repair or replace damaged lines. Tighten connections. Substitute known-good indicator and check reading. Replace or repair instrument. Tighten mounting screws. Tighten clamps and connections. Replace instrument. Tighten mounting screws. For additional Troubleshooting, refer to the Model MD30 Series SAM Standby Attitude Module Installation Manual and Operating Instructions. (Refer to 5-00) 6 3 Dec 06

7 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS TROUBLESHOOTING Trouble - GSU 75 ADAHRS Probable Cause Remedy Airspeed, altitude, vertical speed, or ISA not receiving valid data. Software or configuration error. GSU 75 ADAHRS is offline. Check PFD Alert Window for PFD, MFD or GSU configuration, software or failed data path error messages. Correct any errors before proceeding. Replace GSU 75 configuration module. Verify GSUs are online by checking for a green checkmark next to GSU on MFD AUX SYSTEM STATUS page.. If GSU is not online (a Red-X will be present instead of a green check mark), check for wiring/power faults and GSU connector security.. Replace GSU 75 ADAHRS. Obstruction in pitot-static system. Inspect GSU 75 pitot-static ports and plumbing for blockage. OAT and TAS not receiving valid data. Faulty OAT sensor. Faulty OAT sensor wiring and connectors. Faulty OAT sensor. For TAS failure only, replace OAT sensor. Check OAT sensor wiring and connectors for faults or damage. Replace GSU 75 config module and pigtail harness. Replace OAT sensor. Faulty GSU 75 ADAHRS. Replace GSU 75 ADAHRS. (Refer to 34-0) 7 3 Dec 06

8 CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS 3. Maintenance Practices CIRRUS AIRPLANE MAINTENANCE MANUAL A. Pitot Tube Assembly (See Figure 34-0-) () Removal - Pitot Tube Assembly (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) Pull PITOT HEAT circuit breaker. (c) Remove left wing tip. (Refer to 57-0) (d) Identify and disconnect pitot line at low point on connector projecting from top of pitot bracket. Cap off connector. (e) Remove screws securing pitot tube assembly to bracket, disconnect pitot heat electrical connector, and remove pitot tube. (f) Remove screws, washers, and nuts securing pitot tube bracket to wing skin. Remove bracket from airplane. () Installation - Pitot Tube Assembly (a) Position pitot tube bracket to wing skin and secure with screws, washers, and nuts. (b) Slide pitot tube assembly into bracket, connect pitot heat electrical connector, then connect pitot line. (c) Install screws securing pitot tube to bracket. (d) Perform Functional Test - Pitot System Plumbing. (Refer to 34-0) (e) Perform Operational Test - Pitot Heat. (Refer to 34-0) (f) Install left wing tip. (Refer to 57-0) (g) Reset PITOT HEAT circuit breaker. 8 3 Dec 06

9 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS (3) Operational Test - Pitot Heat (a) (b) (c) (d) (e) (f) (g) (h) (i) (j) Set BAT, BAT, and AVIONICS switches to ON positions. NOTE The pitot tube may utilize an after-market cover. On lower outboard side of LH wing, remove cover from pitot tube if installed. Pull PITOT HEAT circuit breaker. Set PITOT HEAT switch to ON position. Verify PITOT HEAT caution displays on the PFD. Reset PITOT HEAT circuit breaker. Verify PITOT HEAT caution no longer displays on the PFD. WARNING Avoid prolonged exposure to heated pitot tube to prevent burns. Carefully touch pitot tube to verify that it heats up. Set PITOT HEAT switch to OFF position. If applicable, allow pitot tube to cool and reinstall cover. B. Pitot System Plumbing (See Figure 34-0-) () System Test - Pitot System Plumbing Pitot system lines must be kept clear and connections tight. A water trap and plug, located at the low point of the pitot system under access panel CFL, is used to trap and then drain water from the system. However, moisture may collect at other points of the system. To purge the pitot system, proceed as follows: (a) Remove LH kick plate. (Refer to 5-0) (b) Serials w/o MD30 Standby Attitude Module: Identify and disconnect lower pitot line at airspeed indicator branch tee, then cap off branch tee. Disconnect pitot line at pitot mast. 9 3 Dec 06

10 CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL (c) CAUTION Never blow air through the line toward the instruments. To do so will seriously damage the instruments. 3 Blow clean, low-pressure air from disconnected line at airspeed indicator branch tee to disconnected line at pitot mast. 4 Blow clean, low-pressure air through pitot mast. 5 Connect pitot line at pitot mast. 6 Connect pitot line at airspeed indicator branch tee. Serials w/ MD30 Standby Attitude Module: Identify and disconnect lower pitot line at MD30 branch tee, then cap off branch tee. Disconnect pitot line at pitot mast. CAUTION Never blow air through the line toward the instruments. To do so will seriously damage the instruments. 3 Blow clean, low-pressure air from disconnected line at MD30 branch tee to disconnected line at pitot mast. 4 Blow clean, low-pressure air through pitot mast. 5 Connect pitot line at pitot mast. 6 Connect pitot line at MD30 branch tee. (d) Perform Functional Test - Pitot System Plumbing. (Refer to 34-0) (e) Install LH kick plate. (Refer to 5-0) () Functional Test - Pitot System Plumbing The following procedure outlines inspection and testing of the pitot system. Perform this test any time an instrument, fitting, line, or pitot head is disconnected. (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Sealant Tape GS 00 General Sealants Cover pitot tube hole during leak test. 0

11 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS Description P/N or Spec. Supplier Purpose Calibrated Pitot/Static Test Set Model 650 a Laversab, Inc. Simulate pitot air pressure. DPS000a Barfield Model 393a Aircraft Instrument Support Services, Inc. a. or equivalent (b) (c) (d) (e) Connect 8± VDC external power to external power receptacle. Set BAT, BAT, and AVIONICS switches to ON positions. NOTE Ensure small hole on forward, bottom portion of the pitot tube is covered by the pitot line sleeve or sealant tape. Connect pitot line from pitot/static test set to pitot mast on airplane. CAUTION Verify pump is turned off and plug in tester power cord. Perform pitot leak test procedure. Close pitot, static and cross feed control valves. Close pitot and static bleed/vent valves. Set vacuum pressure selector to pressure source. Turn pump on. 3 Apply pressure to the pitot system by slowly opening the pitot control valve until the airspeed indicator reads 80 KTS. Close pitot control valve. Turn pump off. 4 Observe airspeed indicator for minute. If leak is present, indicated airspeed will decrease. 5 Slowly release pitot bleed/vent valve and reduce pressure gradually to prevent instrument damage until the indicator returns to zero or its rest position. 6 If test reveals a leak, check all connections for tightness and repair faulty components.

12 CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL C. Alternate Static Source Valve (See Figure 34-0-) () Removal - Alternate Static Source Valve (a) (b) (c) (d) (e) Open circuit breaker panel to gain access to alternate static source valve. Disconnect line at alternate static source valve, then cap off line. From back-side of alternate static source valve knob, press insert out from knob to access screw. Remove screw securing knob to alternate static source valve, then remove knob. Remove screw securing alternate static source valve to console. Remove valve from airplane. () Installation - Alternate Static Source Valve (a) Position alternate static source valve to console and secure with screw. (b) Connect static line to alternate static source valve. (c) Position knob to alternate static source valve and secure with screw. (d) Position insert to knob and press to secure. (e) Perform Functional Test - Static System Plumbing. (Refer to 34-0) (f) Close and secure circuit breaker panel. D. Static System Plumbing (See Figure 34-0-) Static air pressure lines must be kept clear and connections tight. A water trap and plug, located at the low point of the static system under access panel CF3L, is used to trap and then drain water from the system. A second water trap and plug, located forward of the alternate static source valve in the LH center console, is used to trap and then drain water from the system. A static line sump, located aft of bulkhead, is used to prevent water from entering the system. However, moisture may collect at other points of the system. To purge the static system, perform System Test - Static System Plumbing. (Refer to 34-0)

13 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS () System Test - Static System Plumbing (a) Remove LH kick plate. (Refer to 5-0) (b) Serials w/o MD30 Standby Attitude Module: Identify and disconnect lower static line at airspeed indicator branch tee, then cap off branch tee. (c) CAUTION Never blow air through the line toward the instruments. To do so will seriously damage the instruments. Blow clean, low-pressure air from disconnected line at airspeed indicator branch tee to static ports. 3 Connect lower static line at airspeed indicator branch tee. Serials w/ MD30 Standby Attitude Module: Identify and disconnect lower static line at MD30 branch tee, then cap off branch tee. CAUTION Never blow air through the line toward the instruments. To do so will seriously damage the instruments. Blow clean, low-pressure air from disconnected line at MD30 branch tee to static ports. 3 Connect lower static line at MD30 branch tee. (d) Perform Functional Test - Static System Plumbing. (Refer to 34-0) (e) Install LH kick plate. (Refer to 5-0) () Functional Test - Static System Plumbing (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Sealant Tape GS 00 General Sealants Cover static air buttons during leak test. 3

14 CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL Description P/N or Spec. Supplier Purpose Calibrated Pitot/Static Test Set Model 650 a Laversab, Inc. Simulate static air pressure. DPS000a Barfield Model 393a Aircraft Instrument Support Services, Inc. (b) Connect 8± VDC external power to external power receptacle. (c) Set BAT, BAT, and AVIONICS switches to ON positions. (d) Remove glareshield. (Refer to 5-0) (e) Remove trim panel from RH side of center console. (Refer to 5-0) (f) Remove LH kick plate. (Refer to 5-0) (g) (h) (i) (j) (k) (l) (m) a. or equivalent CAUTION Never apply positive pressure with airspeed indicator, vertical speed indicator, MD30 Standby Attitude Module, PFD, or ADAHRS connected into static system. Serials w/o MD30 Standby Attitude Module: Disconnect altimeter, airspeed indicator, ADAHRS, and if applicable, altitude transducer. Use suitable fittings to re-connect the static pressure lines with no instruments connected into the static pressure system. Serials w/ MD30 Standby Attitude Module: Disconnect MD30 Standby Attitude Module and ADAHRS. Use suitable fittings to re-connect the static pressure lines with no instruments connected into the static pressure system. Set barometric scale on tester altimeter to 9.9 inhg. NOTE Ensure small hole on forward, bottom portion of the pitot tube is covered by the pitot line sleeve or sealant tape. Connect pitot line from pitot/static test set to pitot mast on airplane. Connect static line from pitot/static test set to a static port on airplane. Apply sealant tape to cover other static port on airplane. At circuit breaker panel, verify alternate static source valve is in the NORMAL position. CAUTION Verify pump is turned off and plug in tester power cord. (n) Perform Functional Test - Pitot System Plumbing. (Refer to 34-0) 4

15 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS (o) Perform static leak test procedure. Close pitot and static control valves. Close pitot and static bleed/vent valves. 3 Open cross feed valve fully and set source selector to vacuum. Turn pump on. CAUTION Do not climb more than 6,000 FPM. 4 Apply vacuum to the static system by slowly opening the static control valve until the altimeter rises to approximately,000 feet above the starting altitude. 5 Close static control valve. Turn pump off. Allow the Altimeter to stabilize (approximately one minute). 6 Observe altimeter for one minute. Any decrease in indicated altitude cannot be greater than 0 ft. CAUTION Do not descend more than 6,000 FPM during bleed down. 7 Slowly open static bleed/vent valve to increase the static pressure. 8 Install LH kick plate. (Refer to 5-0) 9 Install trim panel to RH side of center console. (Refer to 5-0) 0 Install glareshield. (Refer to 5-0) E. Pitot Mast (See Figure 34-0-) () Removal - Pitot Mast (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) Pull PITOT HEAT circuit breaker. (c) Remove wing tip. (Refer to 57-0) (d) Disconnect pitot mast fitting from pitot tube fitting, then cap off pitot tube. (e) Remove screws securing pitot mast to bracket. 5

16 CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL () Installation - Pitot Mast (a) Position pitot mast to bracket and secure with screws. (b) Connect pitot mast fitting to pitot tube fitting. Torque 80 in-lb (9 Nm). (Refer to 0-60) (c) Reset PITOT HEAT circuit breaker. (d) Perform Functional Test - Pitot System Plumbing. (Refer to 34-0) (e) Install wing tip. (Refer to 57-0) (3) Inspection/Check - Pitot Mast (See Figure 34-0-) (a) Remove wing tip. (Refer to 57-0) (b) Disconnect pitot mast fitting from pitot tube fitting, then cap off pitot tube. (c) (d) CAUTION Never blow air through the line toward the instruments. To do so will seriously damage the instruments. Blow clean, low-pressure air from the pitot mast fitting to the pitot mast entry tip. Verify electrical connections are secured, clean, and free of damage. NOTE Cosmetic damage (plating, discoloration and flaking) does not affect pitot mast operation or require pitot mast replacement. (e) At pitot mast entry tip, verify any blunting of tip does not exceed 0.03 inch (0.8 mm) at any location, or exceed 0.0 inch (0.5 mm) around entire circumference. (f) Identify any damage (chips, gouges, dents, blisters or other defects) on surfaces of pitot mast. At forward inches (5 mm) of pitot mast entry tip, verify damage does not exceed 0.03 inch (0.8 mm) in depth or height and does not exceed 0.06 inch (.5 mm) in length or width. At aft.6 inches (4 mm) of pitot mast entry tip, verify damage does not exceed 0.09 inch (.3 mm) in depth or height. 3 At remaining sections of pitot mast, verify damage does not exceed 0.5 inch (3.8 mm) in depth or height. (g) Verify lower forward drain hole is not eroded beyond 0.05 inch (.7 mm). (h) Verify upper aft drain hole is not eroded beyond 0.09 inch (.8 mm). 6

17 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS (i) CAUTION Eroded drain holes may result in pressure loss leading to an airspeed reduction of 0.5 percent. In pitot mast housing, verify heater and plug do not show signs of erosion or cracking. CAUTION Erosion material in pitot mast housing may cause blockage of drain hole. (j) If damage exceeds limitations indicated above, replace pitot mast. (Refer to 34-0) (k) Connect pitot mast fitting to pitot tube fitting. (l) Perform Functional Test - Pitot System Plumbing. (Refer to 34-0) (m) Install wing tip. (Refer to 57-0) 7

18 CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL Figure 34-0-: Pitot-Static System - Serials w/o MD30 Standby Attitude Module ( of 3) CENTER CONSOLE (REF) NOTE 9 Optional dual ADAHRS installation shown. Tee is positioned at LH CAPS enclosure and centered between rivet holes Serials w/o MD30 Standby Attitude Module. LEGEND. Pitot Tube. Static Tube 3. Grommet 4. Plug 5. Fitting 6. Tie Down 7. Cable Tie 8. Drain Tube 9. Tee 0. Bushing. ADAHRS. ADAHRS 3. Static Port 4. Altimeter 5. Air Speed Indicator 6. Static Line Sump SR_MM34_5095 8

19 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS Figure 34-0-: Pitot-Static System - Serials w/ MD30 Standby Attitude Module ( of 3) 7 CENTER CONSOLE (REF) NOTE Optional dual ADAHRS installation shown. Tee is positioned at LH CAPS enclosure and centered between rivet holes Serials w/ MD30 Standby Attitude Module. LEGEND. Pitot Tube. Static Tube 3. Grommet 4. Plug 5. Fitting 6. Tie Down 7. Cable Tie 8. Drain Tube 9. Tee 0. Bushing. ADAHRS. ADAHRS 3. Static Port 6. Static Line Sump 7. MD30 Standby Attitude Module SR_MM34_5097 9

20 CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL Figure 34-0-: Pitot-Static System (3 of 3) 0 CONSOLE ASSEMBLY (REF) GROUND STRAP (REF) WING SKIN (REF) 8 LEGEND. Pitot Line. Static Tube 4. Plug 5. Fitting 9. Tee 7. Alternate Static Source Valve 8. Screw 9. Knob 0. Adel Clamp. Washer. Nut 3. Spiral Wrap 4. Pitot Mast 5. Insert 6. Extension Tube 7. Tube Connector 8. Pitot Mast Bracket DETAIL B SR_MM34_5099 0

21 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS Figure 34-0-: Inspection/Check - Pitot Mast 0.09 inch (.8 mm) PITOT MAST HOUSING 0.05 inch (.7 mm). inches (7.9 mm) 3.6 inches (9.4 mm) PITOT MAST ENTRY TIP NOTE At pitot mast entry tip, verify any blunting of tip does not exceed 0.03 inch (0.8 mm) at any location, or exceed 0.0 inch (0.5 mm) around entire circumference. At forward inches (5 mm) of pitot mast entry tip, verify damage does not exceed 0.03 inch (0.8 mm) in depth or height and does not exceed 0.06 inch (.5 mm) in length or width. At aft.6 inches (4 mm) of pitot mast entry tip, verify damage does not exceed 0.09 inch (.3 mm) in depth or height. At remaining sections of pitot mast, verify damage does not exceed 0.5 inch (3.8 mm) in depth or height. Verify lower forward drain hole is not eroded beyond 0.05 inch (.7 mm). Verify upper aft drain hole is not eroded beyond 0.09 inch (.8 mm). In pitot mast housing, verify heater and plug do not show signs of erosion or cracking. LEGEND. Pitot Mast SR_MM34_5089

22 CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL F. Altimeter - Serials w/o MD30 Standby Attitude Module (See Figure ) () Removal - Altimeter (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) Pull STDBY ATTD A, STDBY ATTD B, and CABIN LIGHTS/OXYGEN circuit breakers. (c) Remove LH kick plate. (Refer to 5-0) (d) Remove and cap off static line. (e) Disconnect electrical connector. (f) While supporting altimeter, remove screws securing unit to bolster panel. (g) Cap off fitting on back of altimeter to prevent possible contamination, then remove from airplane. () Installation - Altimeter (a) Position altimeter in bolster panel and attach with screws. (b) Connect electrical connector. (c) Attach static line. (d) Reset STDBY ATTD A, STDBY ATTD B, and CABIN LIGHTS/OXYGEN circuit breakers. (e) Perform Functional Test - Pitot System Plumbing. (Refer to 34-0) (f) Perform Functional Test - Static System Plumbing. (Refer to 34-0) (g) Perform Functional Test - Altimeter. (Refer to 34-0) (h) Install LH kick plate. (Refer to 5-0) (3) Functional Test - Altimeter (a) (b) (c) (d) Set AVIONICS switch to ON position. On audio control panel, select COM audio selector button. Using COM, listen to ATIS. Obtain current altimeter barometric pressure setting. Set barometric pressure in altimeter window.

23 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS (e) (f) Verify correct altitude is indicated. Set AVIONICS switch to OFF position. (4) Adjustment/Test - Altimeter (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Calibrated Altimeter Test Set - Any Source Simulate altitude. Sealant Tape GS 00 General Sealants Cover static port. 4 CFR 43 Appendix E - Any Source Test. (b) (c) (d) (e) (f) (g) (h) Set BAT and BAT switches to ON positions. NOTE Calibration must be done with the altimeter at ambient temperature within the range of 55 to 95 F (3 to 35 C). Verify external power is applied to aircraft to preserve battery life and system is up to proper operating power. Connect 8± VDC external power to external power receptacle. Allow system to acquire and display AHRS and air data on the PFD and MFD. Connect pitot line from altimeter test set to pitot mast on airplane. Connect static line from altimeter test set to a static port on airplane. Apply sealant tape to cover other static port. Comply with Appendix E of 4 CFR 43 for PFD altimeter and backup altimeter observing the following guidelines: For scale error tests, the first test point entry calls for pressure altitude setting of -000 feet on test equipment. If indicated measurement is out-of-range, increase target pressure in calibrated altimeter test set in smallest increment available. Verify that indicated measurement is in-range. If not, continue to increase pressure altitude value incrementally until indicated measurement is in-range. 3

24 CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL If calibrated altimeter test set setting is between -000 and -950 feet, and digital altitude indication on PFD is between -0 and 0 feet of value shown on calibrated altimeter test set, the test point is passed. (i) (j) (k) For barometric scale error test, set base altitude to +000 MSL or higher on calibrated altimeter test set. Values indicated as Altitude difference in procedure are offset from base altitude. 3 Skip friction test. The friction test is intended to evaluate pointer mechanical friction and is not applicable to PFD. Disconnect altimeter test set from airplane and remove sealant tape. Disconnect 8± VDC external power from external power receptacle. Set BAT and BAT switches to OFF positions. 4

25 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS Figure : Altimeter Installation - Serials w/o MD30 Standby Attitude Module A BOLSTER PANEL (REF) Serials w/o MD30. DETAIL A LEGEND. Altimeter. Screw 3. Washer 4. Static Line 5. Connector 6. Nylon Fitting SR_MM34_4949 5

26 CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL G. Airspeed Indicator - Serials w/o MD30 Standby Attitude Module (See Figure ) () Removal - Airspeed Indicator (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) Pull STDBY ATTD A, STDBY ATTD B, and CABIN LIGHTS/OXYGEN circuit breakers. (c) Remove LH kick plate. (Refer to 5-0) (d) Remove and cap off static and pitot line. (e) Disconnect electrical connector. (f) While supporting airspeed indicator, remove screws securing unit to bolster panel. (g) Cap off fitting on back of airspeed indicator to prevent possible contamination, then remove from airplane. () Installation - Airspeed Indicator (a) Position airspeed indicator in bolster panel, then attach with screws. (b) Connect electrical connector. (c) Attach static and pitot line. (d) Reset STDBY ATTD A, STDBY ATTD B, and CABIN LIGHTS/OXYGEN circuit breakers. (e) Perform Functional Test - Static System Plumbing. (Refer to 34-0) (f) Perform Functional Test - Pitot System Plumbing. (Refer to 34-0) (g) Perform Functional Test - Airspeed Indicator. (Refer to 34-0) (h) Install LH kick plate. (Refer to 5-0) (3) Functional Test - Airspeed Indicator (a) Verify needle indicates zero (straight up, <40 kts). 6

27 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS Figure : Airspeed Indicator Installation - Serials w/o MD30 Standby Attitude Module A BOLSTER PANEL (REF) Serials w/o MD30. DETAIL A LEGEND. Airspeed Indicator. Screw 3. Washer 4. Nylon Fitting 5. Static Line 6. Pitot Line 7. Connector SR_MM34_495 7

28 CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL H. MD30 Standby Attitude Module - Serials w/ MD30 Standby Attitude Module (See Figure ) () Removal - MD30 Standby Attitude Module (a) (b) (c) Set BAT, BAT, and AVIONICS switches to OFF positions. Pull STDBY ATTD A, STDBY ATTD B, and CABIN LIGHTS/OXYGEN circuit breakers. Remove and discard MD30 overlay. CAUTION Do not use heat gun or solvent/cleaning products on MD30. Use caution while using putty knife to avoid scratching or otherwise damaging the unit. Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Clean Cloth (white, lint- free) - Any Source Wash. Plastic Putty Knife - Any Source Remove overlay and residual adhesive. CAUTION Exercise caution while cutting slit in overlay to avoid scratching or otherwise damaging the unit. Cut slit in overlay as shown. (See Figure ) 3 Beginning at each side of slit, peel overlay away from surface of unit, using putty knife if necessary. 4 Remove residual adhesive with clean cloth slightly dampened with water and putty knife if necessary. (d) Remove LH kick plate. (Refer to 5-0) (e) Remove and cap off static and pitot line. (f) Disconnect electrical connector. (g) While supporting MD30 Standby Attitude Module, remove screws securing unit to bolster panel. (h) Cap off fittings on back of MD30 Standby Attitude Module to prevent possible contamination, then remove from airplane. 8

29 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS () Installation - MD30 Standby Attitude Module (a) Position MD30 Standby Attitude Module in bolster panel and secure with screws. (b) Connect electrical connector. (c) Attach static and pitot line. (d) Reset STDBY ATTD A, STDBY ATTD B, and CABIN LIGHTS/OXYGEN circuit breakers. (e) Perform Functional Test - Pitot System Plumbing. (Refer to 34-0) (f) Perform Functional Test - Static System Plumbing. (Refer to 34-0) (g) If MD30 has been replaced with a new or different unit, or original unit has been repaired, perform Adjustment/Test - MD30 Standby Attitude Module Software Loading. (Refer to 34-0) (h) Perform Functional Test - MD30 Standby Attitude Module. (Refer to 34-0) (i) Install LH kick plate. (Refer to 5-0) (j) Install MD30 overlay. Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Clean Cloth (white, lint- free) - Any Source Wash. Rubber Roller - Any Source Install overlay. Slightly dampen clean cloth with water and wash overlay installation area. 3 Cut slit in overlay as shown.(see Figure ) 4 Remove protective backing from top half of overlay using care not to contaminate adhesive surface. NOTE Ensure slit is positioned downwards. 5 Align overlay half with protective backing still in place on unit and press exposed overlay half onto unit. 6 Bend overlay back and peel remaining protective backing from overlay. 7 Carefully work overlay toward bottom of unit, using slit in overlay to wrap around unit knob. 8 Press bubbles and wrinkles out with rubber roller. Ensure all edges are firmly adhered. 9

30 CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL (3) Functional Test - MD30 Standby Attitude Module (a) (b) (c) (d) (e) Set BAT, BAT, and AVIONICS switches to ON positions. Unit will display INTRODUCTION page for approximately 5 seconds, followed by the FLIGHT MODE page. Check function of altimeter. On audio control panel, select COM audio selector button. Using COM, listen to ATIS. Obtain current altimeter barometric pressure setting. 3 Set barometric pressure in altimeter window. 4 Verify correct altitude is indicated. Check function of airspeed indicator. Verify airspeed tape indicates zero. Check function of attitude indicator. Verify attitude indicator is stabilized with artificial horizon resting horizontally and slip indicator ball is centered. (4) Adjustment/Test - MD30 Standby Attitude Module (a) Perform Adjustment/Test - Altimeter. (Refer to 34-0) (5) Adjustment/Test - MD30 Standby Attitude Module Software Loading (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose MidContinent Software Loader USB Flash Drive a - MidContinent Instruments and Avionics Upload software. a. It is also permissible to download the approved software file to the root directory of a standard FAT-formatted USB flash drive from (b) Connect 8± VDC external power to external power receptacle. (c) Pull STARTER and FUEL PUMP circuit breakers. (d) Ensure unit is powered off. (e) Remove LH kick plate. (Refer to 5-0) 30

31 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS NOTE It is not necessary to remove unit from bolster panel when loading software. (f) Perform Adjustment/Test - MD30 Standby Attitude Module Configuration Loading. (Refer to 34-0) (g) Install LH kick plate. (Refer to 5-0) (h) Reset STARTER and FUEL PUMP circuit breakers. (i) Disconnect 8± VDC external power from external power receptacle. (6) Adjustment/Test - MD30 Standby Attitude Module Configuration Loading (a) (b) (c) Connect 8± VDC external power to external power receptacle. Pull STARTER and FUEL PUMP circuit breakers. Ensure unit is powered off. NOTE It is not necessary to remove unit from bolster panel when loading software. (d) Program the unit by holding down knob when applying aircraft power at BAT switch. After 6 seconds, the message "CONTINUTE HOLDING TO ENTER CONFIG MODE" will appear. Continue holding the knob until the CONFIGURE MENU appears. Use the control knob to set the following values. CONFIGURE AIRCRAFT: PANEL TILT 4.0 PANEL ROLL 0.0 (nominal, ±.0) a RANGE MMO 0.00 RANGE MARKING FULL, WHITE 64-0 HALF, GREEN 74-0 FULL, GREEN 0-76 FULL, YELLOW FULL, RED FULL, RED

32 CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL VNE TABLE ALT/KNOTS 0, 05 ALT/KNOTS -7 (unused, 0) a. Panel Roll allowable ±.0 to account for installation tolerances. CONFIGURE ARINC: ARINC_SPEED HIGH 3 CONFIGURE DIMMING: DIMMING CONTROL EXT_8V DIMMING CURVE 8, 8, 9, 0, 4, 5, 4 CONFIGURE DISPLAY: ROLL DISPLAY AIRSPEED UNITS Serials thru -4593, Serials T-460, T-47, T-473 thru T-657, T-660 thru T-69: AIRSPEED MINIMUM Seirals & subs:, T-658, T-659, T-69 & subs: AIRSPEED MINIMUM DISPLAY ORIENTATION HORIZON DISPLAY FIXED_POINTER KNOTS 0_KNOTS 40_KNOTS HORIZONTAL FLAT 5 CONFIGURE HEADING: CONFIGURE HEADING DISPLAY OFF (e) 6 Select "ACCEPT CHANGES" to save configuration selections into MD30 memory and to the configuration module in the aircraft harness. Cycle power at BAT switch to reboot the MD30. After power on is complete (approximately 0 seconds) verify instrument shows no red Xs for airspeed, altimeter or attitude indicator. 3

33 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS (f) Verify settings by holding the control knob when unit is powered on until the menu appears. (g) Select the menu item "INFO >". (h) Scroll through the settings to verify correct settings per tables above. (i) Verify airspeed indicator reads 0. (j) Ensure slip indicator ball matches indication on PFD. (k) Turn on the audio panel. Select the COM audio selector button. (l) Using COM, listen to local weather and obtain current altimeter barometric pressure setting. (m) Set barometric pressure in altimeter window. (n) Verify altitude indicates local elevation ±75 ft. (o) Reset STARTER and FUEL PUMP circuit breakers. (p) Disconnect 8± VDC external power from external power receptacle. 33

34 CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL Figure : MD30 Standby Attitude Module Installation A DETAIL A 3 4 VIEW 7 A 5 A A BOLSTER PANEL (REF) A 6 NOTE Cut slit in overlay as shown. Ensure slit is positioned downwards. DETAIL A Serials w/ MD30 Standby Attitude Module. LEGEND. Screw. MD30 Standby Attitude Module 3. Connector 4. Static Line 5. Pitot Line 6. MD30 Overlay 7. USB Access Door SR_MM34_509 34

35 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS I. Outside Air Temperature (OAT) Sensor (See Figure ) () Removal - OAT Sensor (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) Remove wing access panel RW. (Refer to 6-00) (c) Disconnect electrical connector. (d) Remove nut and washer securing OAT sensor to access panel. () Installation - OAT Sensor (a) Acquire necessary tools, equipment, and supplies. (b) (c) (d) Description P/N or Spec. Supplier Purpose Threadlocker Loctite 4 Any Source Lock threads. Apply threadlocker to OAT sensor threads. Position OAT sensor to access panel and secure with washer and nut. Torque nut 50 to 00 in-lb (5.6 to.3 Nm). (Refer to 0-60) Connect electrical connector. (e) Install wing access panel RW. (Refer to 6-00) 35

36 CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL Figure : OAT Sensor Installation UPPER WING SKIN (REF) 4 ACCESS PANEL (REF) 3 5 LEGEND. OAT Sensor. Washer 3. Nut 4. Connector 5. Screw SR_MM34_

37 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS J. GSU 75 Air Data Attitude Heading Reference System (ADAHRS) (See Figure ) () Removal - GSU 75 ADAHRS (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) For single ADAHRS installation: Pull ADAHRS circuit breaker. (c) For dual ADAHRS installation: Pull ADAHRS and ADAHRS circuit breakers. (d) Remove MFD. (Refer to 3-60) (e) Disconnect electrical connector from ADAHRS. (f) Disconnect and cap pitot line from ADAHRS. (g) Disconnect and cap static line from ADAHRS. (h) Cap pitot and static fittings on ADAHRS. (i) Remove bolts securing ADAHRS to mounting rack. Remove ADAHRS from airplane. () Installation - GSU 75 ADAHRS (a) Position ADAHRS to mounting rack and secure with bolts. (b) Perform Inspection/Check - Electrical Bonding and Shielding. (Refer to 5-80) (c) Remove caps from pitot and static fittings on ADAHRS. (d) Remove cap and connect pitot line to ADAHRS. (e) Remove cap and connect static line to ADAHRS. (f) Perform Functional Test - Pitot System Plumbing. (Refer to 34-0) (g) Perform Functional Test - Static System Plumbing. (Refer to 34-0) (h) Connect electrical connector to ADAHRS. (i) Install MFD. (Refer to 3-60) (j) For single ADAHRS installation: Reset ADAHRS circuit breaker. (k) For dual ADAHRS installation: Reset ADAHRS and ADAHRS circuit breakers. (l) If GSU 75 has been replaced with a new or different unit, or original unit has been repaired, perform Adjustment/Test - Component Software and Configuration Loading. (Refer to 4-00) 37

38 CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL (m) If rack was loosened during procedure: Perform Adjustment/Test - GSU 75 ADAHRS Pitch/Roll Offset Calibration. (Refer to 34-0) Perform Adjustment/Test - GMU 44 Magnetometer Calibration. (Refer to 34-0) 3 Perform Adjustment/Test - GSU 75 Engine Run-Up Vibration Test. (Refer to 34-0) (3) Removal - GSU 75 ADAHRS Mounting Rack (a) Remove ADHRS. (Refer to 34-0) (b) NOTE At the ADAHRS mounting rack, a clamp, washer, and nut are installed at the forward inboard attachment hole. Remove screws and washers securing mounting rack to console. (4) Installation - GSU 75 ADAHRS Mounting Rack (a) Position and secure mounting rack to console with washers and screws. NOTE At the ADAHRS mounting rack, a clamp, washer, and nut are installed at the forward inboard attachment hole. (b) Install ADHRS. (Refer to 34-0) (5) Adjustment/Test - GSU 75 ADAHRS Pitch/Roll Offset Calibration (a) Perform GSU 75 ADAHRS Pitch/Roll Offset Calibration according to Cirrus Perspective+ Line Maintenance Manual. 38

39 CIRRUS AIRPLANE MAINTENANCE MANUAL CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS (6) Adjustment/Test - GSU 75 Engine Run-Up Vibration Test NOTE Perform this procedure to verify AHRS mounting is sufficiently rigid and insensitive to vibration. (a) (b) (c) (d) Start the engine in accordance with Pilot s Operating Handbook procedures. NOTE If needed, advise the Control Tower or Ground Control you may temporarily not be able to receive or transmit on your COM radios during this procedure before restarting the system in config mode. Power on PFD and MFD in Configuration mode. While holding far right softkey on PFD and MFD, set BAT and AVIONICS switches to ON positions. When INITIALIZING SYSTEM appears in upper left corner of displays, release softkeys. NOTE Engine instruments may be monitored on this page during this procedure. On PFD, use inner [FMS] knob to select GSU/GMU CALIBRATION page. Perform GSU 75 ADAHRS Engine Run-Up Vibration Test according to Cirrus Perspective+ Line Maintenance Manual. 39

40 CHAPTER 34-0: FLIGHT ENVIRONMENTAL SYSTEMS CIRRUS AIRPLANE MAINTENANCE MANUAL Figure : ADAHRS Installation CONSOLE (REF) NOTE At the ADAHRS mounting rack, a clamp, washer, and nut are installed at the forward inboard attachment hole. LEGEND. GSU 75 ADAHRS. GSU 75 ADAHRS 3. Bolt 4. Screw 5. Washer 6. GSU Rack 7. Clamp 8. Nut SR_MM34_560 40