Flight Environmental Systems

Home , Pitot tube, Primary flight display

CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

FLIGHT ENVIRONMENTAL SYSTEMS

1. DESCRIPTION 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, Vertical Speed Indicator (VSI), altimeter, airspeed indicator, and Outside Air Temperature (OAT) gage/clock. (See Figure 34-001) 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. An amber PITOT HEAT light on the annunciation panel will illuminate if the PITOT HEAT switch is set to ON position and the pitot heater is not using power. The pitot heat system operates on 28 VDC supplied through the 7.5-amp PITOT HEAT/COOLING FAN circuit breaker on the Non-Essential Bus. The PITOT HEAT warning light operates on 28 VDC supplied through the 2-amp ANNUN circuit breaker on the 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 airspeed indicator, vertical speed indicator, altimeter, altitude encoder, and altitude transducer. Serials 0435 thru 0820 w/ PFD, 0821 & subs: The primary flight display (PFD) receives static air pressure data through the static system. 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 directly forward of the pitot system water trap. Serials 0002 thru 2036, 2038 thru 2042 after SB 2X-34-22, 2037, 2043 & subs: 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 malfunc- tioning. When alternate static air is used, instrument readings will vary 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.

Serials 0002 thru 0434, 0435 thru 0820 w/o PFD: The Outside Air Temperature (OAT) gage/clock is located in the upper LH portion of the pilot’s instrument panel. The OAT gage is integral to the clock. The clock provides Universal Time (UT), Local Time (LT), Flight Time (FT) with alarm, Elapsed Time (ET), Out- side Air Temperature in °C or °F, and Voltmeter functions. All features and functions are selectable from control buttons on the clock face. The clock receives the OAT signal from a temperature sensor installed immediately forward of the pilots door. The clock operates on 28 VDC supplied through a 5-amp fuse connected to the airplane primary bus in the Master Control Unit (MCU). A replaceable AA battery is installed to provide up to three years battery back up. Serials 0435 thru 0820 w/ PFD, 0821 & subs: The PFD receives an OAT signal from a temperature sensor integral to the magnetometer installed in the RH wing. Serials 0002 thru 1601, 1603 thru 1643, 1645 thru 1662 w/ EMax Engine Monitoring: The Multifunction Display (MFD) receives an OAT signal from a temperature sensor installed immediately forward of the co- pilot’s door. Serials 1602, 1644, 1663 & subs: The MFD receives an OAT signal from a temperature sensor integral to the magnetometer installed in the RH wing.

EFFECTIVITY: All 34-10 Page 1 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

The Vertical Speed Indicator (VSI) measures the rate of change in static pressure when the airplane is climbing or descending. By means of a pointer, it indicates the rate of descent or ascent of the airplane in feet per minute. Serials 0002 thru 0434, 0435 thru 0820 w/o PFD: The VSI is located in the lower RH portion of the pilot’s instrument panel. A zero adjust screw is located on the front of the VSI in the lower LH corner to allow for pointer adjustment. Serials 0435 thru 0820 w/ PFD, 0821 & subs: The VSI is on the PFD with no standby indicator. 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 moveable pointer and a fixed dial with the 0 index at the 12 o’clock position indicates airspeed. Range of the instrument is 0 to 220 knots. Serials 0002 thru 0434, 0435 thru 0820 w/o PFD: The airspeed indicator is located in the upper LH portion of the pilot’s instrument panel. Serials 0435 thru 0820 w/ PFD, 0821 & subs: The primary airspeed indicator is on the PFD. The standby airspeed indicator is located in the LH bolster panel. 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 100, 1000, and 10,000 feet, with a range of -1000 to 20,000 feet. Serials 0002 thru 0434, 0435 thru 0820 w/o PFD: The altimeter is located in the upper mid portion of the instrument panel. Serials 0435 thru 0820 w/ PFD, 0821 & subs: The primary altimeter is on the PFD. The standby altimeter is located in the LH bolster panel.

EFFECTIVITY: 34-10 All Page 2 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

2. TROUBLESHOOTING

Trouble - Pitot-Static Probable Cause Remedy

Erroneous altimeter or vertical Leaks in static and/or pitot line. Check lines for leaks. Perform speed indication. System Test - Static Plumbing System. (Refer to 34-10)

Check lines for leaks. Perform System Test - Pitot Plumbing Sys- tem. (Refer to 34-10)

Incorrect or sluggish response on Leaks or obstruction in static line. Repair or replace line. Remove all three pitot-static instruments. obstruction.

Pitot tube does not heat or melt PITOT HEAT switch is set to OFF Set PITOT HEAT switch to ON ice. position. position.

Pitot tube does not heat or melt Circuit breaker out. Reset circuit breaker. ice. Pitot Light ON. Break in wiring. Test and repair wiring.

Insufficient current. Check current drain of element.

Heating element burned out. Replace element.

Low or sluggish airspeed indica- Pitot tube deformed. Repair or replace damaged com- tion. Normal altimeter and vertical Leak or obstruction in pitot line. ponent. speed indication.

Trouble - Vertical Speed Ind. Probable Cause Remedy

Pointer indicates erroneous data. Moisture in static traps and/or Check traps and sump for mois- sump. ture. Blow out lines.

Moisture in static line. Check lines for moisture. Perform System Test - Static Plumbing System. (Refer to 34-10)

Pointer does not set on zero. Leaking or ruptured diaphragm. Substitute known-good indicator and check reading. Replace or repair instrument.

Pointer fails to respond. Obstruction in static line. Check line for obstruction. Blow out lines. (Refer to 34-10)

Pointer oscillates or fails to Leaks in static line. Check line for obstruction. Blow respond. out lines. (Refer to 34-10)

Defective instrument. Replace or repair instrument.

Excessive vibration caused by Tighten mounting screws. loose mounting screws.

EFFECTIVITY: All 34-10 Page 3 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

Trouble - Altimeter Probable Cause Remedy

Pointer indicates erroneous data. Moisture in static traps and/or Check traps and sump for mois- sump. ture. Blow out lines.

Moisture in static line. Check lines for moisture. Perform System Test - Static Plumbing System. (Refer to 34-10)

Cracked or loose cover glass. Excessive vibration caused by Tighten mounting screws. loose mounting screws.

High reading. Static system leak. Inspect static system. (Refer to 34-10)

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.

Trouble - Airspeed Indicator Probable Cause Remedy

Pointer fails to respond or indi- Leak in instrument case. Replace or repair instrument. cates improperly.

Obstruction in pitot line. Check line for obstruction. Blow out lines. (Refer to 34-10)

Incorrect indication or pointer Alternate static source valve open. Close for normal operation. oscillates. Moisture in static traps and/or Check traps and sump for mois- sump. ture. Blow out lines.

Moisture in static line. Check lines for moisture. Perform System Test - Static Plumbing System. (Refer to 34-10)

Leak in pitot or static lines. Repair or replace damaged lines. Tighten connections.

Leaking or ruptured diaphragm. Substitute known-good indicator and check reading. Replace or repair instrument.

Pointer vibrates. Excessive vibration caused by Tighten mounting screws. loose mounting screws.

Excessive pitot tube vibration. Tighten clamps and connections.

EFFECTIVITY: 34-10 All Page 4 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

3. MAINTENANCE PRACTICES A. Pitot Tube Assembly (See Figure 34-101) (1) Removal - Pitot Tube Assembly (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull PITOT HEAT circuit breaker. (c) Remove left wing tip. (Refer to 57-20) (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 securing pitot tube bracket to rib, then remove bracket. (2) Installation - Pitot Tube Assembly (a) Align mounting holes on pitot tube bracket with screw holes in rib, then install screws. (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 Plumbing System. (Refer to 34-10) (e) Perform Operational Test - Pitot Heat. (Refer to 34-10) (f) Install left wing tip. (Refer to 57-20) (g) Reset PITOT HEAT circuit breaker. (3) Operational Test - Pitot Heat (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions.

Note: The pitot tube may utilize an after-market cover.

(b) On lower outboard side of LH wing, remove cover from pitot tube if installed. (c) Pull PITOT HEAT circuit breaker. (d) Set PITOT HEAT switch to ON position. (e) Verify PITOT HEAT annunciator light is on. (f) Reset PITOT HEAT circuit breaker. (g) Verify PITOT HEAT annunciator light is off.

WARNING: Avoid prolonged exposure to heated pitot tube to prevent burns.

(h) Carefully touch pitot tube to verify that it heats up. (i) Set PITOT HEAT switch to OFF position. (j) If applicable, allow pitot tube to cool and reinstall cover.

EFFECTIVITY: All 34-10 Page 5 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

B. Pitot Plumbing System (See Figure 34-101) (1) System Test - Pitot Plumbing System Pitot system lines must be kept clear and connections tight. A water trap and plug, located at the low point of the pitot system directly behind the center console and underneath the cabin floor, is used to trap and then drain water from the system. However, moisture may collect at other points of the system. To purge the static system, proceed as follows: (a) Serials 0002 thru 0434, 0435 thru 0820 w/o PFD: Remove glareshield. (Refer to 25-10) (b) Serials 0435 thru 0820 w/ PFD, 0821 & subs: Remove LH kickplate. (Refer to 25-10) (c) Disconnect pitot line at airspeed indicator, then cap off airspeed indicator. (d) Serials 0435 thru 0820 w/ PFD, 0821 & subs: Disconnect pitot line at PFD, then cap off PFD.

CAUTION: Never blow air through the line toward the instruments. To do so will seri- ously damage the instruments.

(e) Blow clean, low-pressure air from the disconnected line at the airspeed indicator to the pitot tube. (f) Connect pitot line at airspeed indicator. (g) Serials 0435 thru 0820 w/ PFD, 0821 & subs: Connect pitot line at PFD. (h) Perform Functional Test - Pitot Plumbing System. (Refer to 34-10) (i) Serials 0002 thru 0434, 0435 thru 0820 w/o PFD: Install glareshield. (Refer to 25-10) (j) Serials 0435 thru 0820 w/ PFD, 0821 & subs: Install LH kickplate. (Refer to 25-10) (2) Functional Test - Pitot Plumbing System 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

Calibrated Pitot/Static Test Model 393a Aircraft Instrument Support Simulate pitot Set Services, Inc. air pressure. Round Rock, TX 78664 800-593-2096

Sealant Tape GS 100 General Sealants Cover pitot tube Industry, CA 91745 hole during leak 800-762-1144 test. a. or equivalent

(b) Connect 28 ±1 VDC external power to external power receptacle. (c) Set BAT 1, BAT 2, 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.

(d) 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.

EFFECTIVITY: 34-10 All Page 6 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

(e) Perform pitot leak test procedure. 1 Close pitot, static and cross feed control valves. Close pitot and static bleed/vent valves. 2 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 180 KTS. Close pitot control valve. Turn pump off. 4 Observe airspeed indicator for 1 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 compo- nents.

EFFECTIVITY: All 34-10 Page 7 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

C. Alternate Static Source Valve (See Figure 34-101) (1) Removal - Alternate Static Source Valve (a) Open circuit breaker panel to gain access to alternate static source valve. (b) Identify, disconnect, then cap off line from alternate static source valve. (c) Serials 0002 thru 2036, 2038 thru 2042 after SB 2X-34-21, 2037, 2043 & subs: From back-side of alternate static source valve knob, press insert out from knob to facilitate access to screw. (d) Remove set screw attaching knob to alternate static source valve, then pull off knob. (e) Remove screw securing alternate static source valve to console, then remove valve. (2) Installation - Alternate Static Source Valve (a) Position alternate static source valve to console, then install mounting screw. (b) Serials 0002 thru 2036, 2038 thru 2042 after SB 2X-34-21, 2037, 2043 & subs: Slide insert into knob. (c) Connect static line to alternate static source valve. (d) Push knob onto alternate static source valve, then install set screw. (e) Perform Functional Test - Static Plumbing System. (Refer to 34-10) (f) Close and secure circuit breaker panel.

EFFECTIVITY: 34-10 All Page 8 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

D. Static Plumbing System (See Figure 34-101) (1) System Test - Static Plumbing System 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 directly behind the center console and underneath the cabin floor, is used to trap and then drain water from the system. Serials 2037, 2043 & subs, Serials 0002 thru 2036, 2038 thru 2042 after SB 2X-34-21: 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. Serials 2037, 2043 & subs, Serials 0002 thru 2036, 2038 thru 2042 after SB 2X-34-22: A static line sump, located aft of bulkhead 222, is used to prevent water from entering the system. However, moisture may collect at other points of the system. To purge the static system, proceed as follows: (a) Open circuit breaker panel to gain access to altitude encoder. (b) Identify and disconnect lower static line at altitude encoder branch tee and cap off branch tee. (c) Serials 0435 thru 0820 w/ PFD, 0821 & subs: Disconnect pitot line at PFD, then cap off PFD.

CAUTION: Never blow air through the line toward the instruments. To do so will seri- ously damage the instruments.

(d) Blow clean, low-pressure air from the disconnected line at the altitude encoder branch tee to the static ports. (e) Connect static line at altitude encoder branch tee. (f) Serials 0435 thru 0820 w/ PFD, 0821 & subs: Connect static line at PFD. (g) Perform Functional Test - Static Plumbing System. (Refer to 34-10) (h) Close and secure circuit breaker panel. (2) Functional Test - Static Plumbing System (a) Acquire necessary tools, equipment, and supplies.

Description P/N or Spec. Supplier Purpose

Calibrated Pitot/Static Test Model 393a Aircraft Instrument Support Simulate static Set Services, Inc. air pressure. Round Rock, TX 78664 800-593-2096

Sealant Tape GS 100 General Sealants Cover static air Industry, CA 91745 buttons during 800-762-1144 leak test. a. or equivalent

(b) Connect 28 ±1 VDC external power to external power receptacle. (c) Set BAT 1, BAT 2, and AVIONICS switches to ON positions. (d) Remove glareshield. (Refer to 25-10) (e) Remove trim panel from RH side of center console. (Refer to 25-10) (f) Serials 0435 thru 0820 w/ PFD, 0821 & subs: Remove LH kickplate. (Refer to 25-10)

EFFECTIVITY: All 34-10 Page 9 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

CAUTION: Never apply positive pressure with airspeed indicator, vertical speed indicator, or PFD connected into static system.

(g) Disconnect altimeter, airspeed indicator, altitude encoder, and if applicable, vertical speed indicator, altitude transducer, and PFD. Use suitable fittings to re-connect the static pressure lines with no instruments connected into the static pressure system. (h) Set barometric scale on tester altimeter to 29.92 inHg.

Note: Ensure small hole on forward, bottom portion of the pitot tube is covered by the pitot line sleeve or sealant tape.

(i) Connect pitot line from pitot/static test set to pitot mast on airplane. (j) Connect static line from pitot/static test set to a static port on airplane. (k) Apply sealant tape to cover other static port on airplane. (l) 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.

(m) Perform Functional Test - Pitot Plumbing System. (Refer to 34-10) (n) Perform static leak test procedure. 1 Close pitot and static control valves. 2 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 1,000 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 20 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 Serials 0002 thru 0434, 0435 thru 0820 w/o PFD: Install LH kickplate. (Refer to 25- 10) 9 Install trim panel to RH side of center console. (Refer to 25-10) 10 Install glareshield. (Refer to 25-10)

EFFECTIVITY: 34-10 All Page 10 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

E. Altitude Encoder (See Figure 34-101) (1) Removal - Altitude Encoder (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull ENCODER/TRANSPONDER circuit breaker. (c) Remove trim panel from RH side of center console. (Refer to 25-10) (d) Disconnect cable from altitude encoder. (e) Disconnect static line to altitude encoder. (f) Cut safety wire securing knurled nut. (g) Loosen knurled nut and remove altitude encoder from mounting tray. (2) Installation - Altitude Encoder (a) Acquire necessary tools, equipment, and supplies.

Description P/N or Spec. Supplier Purpose

Safety Wire - Any Source Secure.

(b) Position altitude encoder in mounting tray and tighten knurled nut. (c) Connect cable to altitude encoder. (d) Connect static line to altitude encoder. (e) Reset ENCODER/TRANSPONDER circuit breaker. (f) Perform Functional Test - Pitot Plumbing System. (Refer to 34-10) (g) Perform Functional Test - Static Plumbing System. (Refer to 34-10) (h) Perform Functional Test - Altitude Encoder Calibration. (Refer to 34-10) (i) Safety wire knurled nut to mounting tray. (j) Install trim panel to RH side of center console. (Refer to 25-10) (3) Functional Test - Altitude Encoder Calibration

CAUTION: The airplane may not be returned to service until a certified avionics service center has performed altitude encoder calibration.

(a) Pull STARTER RELAY and FUEL PUMP RELAY circuit breakers. (b) Acquire necessary tools, equipment, and supplies.

Description P/N or Spec. Supplier Purpose

Calibrated Pitot/Static Test Set Model 393a Aircraft Instrument Support Simulate Services, Inc. altitude. Round Rock, TX 78664 800-593-2096

Sealant Tape GS 100 General Sealants Cover static Industry, CA 91745 port. 800-762-1144 a. or equivalent

(c) Connect 28 ±1 VDC external power to external power receptacle. (d) Set BAT 1, BAT 2, and AVIONICS switches to ON positions.

EFFECTIVITY: All 34-10 Page 11 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

Note: Calibration must be done with the encoder and altimeter both at ambient temperature within the range of 55° to 95° F (13° to 35° C). Verify external power is applied to aircraft to preserve battery life and system is up to proper operating power.

(e) Turn on encoder and allow to warm up for a minimum period of 10 minutes. If power to the encoder is momentarily interrupted during calibration, wait a minimum of 3 minutes before continuing with the calibration. (f) Connect pitot line from pitot/static test set to pitot mast on airplane. (g) Connect static line from pitot/static test set to a static port on airplane. (h) Apply sealant tape to cover other static port on airplane.

CAUTION: Verify up or down arrow is not displayed on transponder prior to taking any reading.

(i) With calibrated pitot/static test set, simulate altitude ascent through 17950 feet. (j) Verify transponder transitions to 18000 feet.

CAUTION: Always adjust high altitude before low altitude.

(k) If transponder is out of tolerance, adjust high altitude settings.

Note: Rotate “H” screw clockwise to decrease altitude.

1 Adjust “H” screw until transponder agrees with altimeter. (l) With calibrated pitot/static test set, simulate altitude descent through 2950 feet. (m) Verify transponder transitions to 3000 feet. (n) If transponder is out of tolerance, adjust low altitude settings.

Note: Rotate “L” screw clockwise to increase altitude.

1 Adjust “L” screw until transponder agrees with altimeter. (o) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (p) Disconnect pitot/static test set from airplane and remove sealant tape. (q) Disconnect 28 ±1 VDC external power from external power receptacle. (r) Reset STARTER RELAY and FUEL PUMP RELAY circuit breakers.

EFFECTIVITY: 34-10 All Page 12 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

TYPICAL INSTALLATION

16 12

INSTRUMENT PANEL (REF) 7 15 18 6 13 14 5 19 2

17 2 11 2 5 2 1 20 5 21 7 2 6 8 6 7 10 2 1 5 2 4

2 1 LEGEND 9 1. Pitot Tube 3 2. Static Tube 1 3. Grommet 4. Plug 5. Fitting 6. Tie Down 7. Cable Tie 8. Drain Tube 9. Union Tee 10. Bushing 11. Elbow 12. Tee 13. Fitting (pipe to flare) 14. Static Port 15. Static Line 16. Insert 17. Nylon Union Tee Serials 0002 thru 0434, 0435 thru 0820 w/o PFD 18. Altimeter before SB 2X-34-22. 19. Air Speed Indicator 20. Vertical Speed Indicator 21. Altitude Transducer SR22_MM34_1396C

Figure 34-101 Pitot-Static System - Serials 0002 thru 0434, 0435 thru 0820 w/o PFD before SB 2X-34-22 (Sheet 1 of 7) EFFECTIVITY: Serials 0002 thru 0434, 0435 thru 0820 w/o PFD 34-10 Page 13 before SB 2X-34-22 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

22 INSTRUMENT PANEL (REF) 13 14

CENTER CONSOLE 21 18 (REF)

2 17

2 2 19 6 7 1 5 2 4 17 1 2 1 17 17 3 17 LEGEND 2 1. Pitot Tube 2. Static Tube 7 1 3. Grommet 4. Plug 6 5. Fitting 3 6. Tie Down 7. Cable Tie 13. Fitting (Pipe to Flare) 14. Static Port NOTE Serials 0435 thru 0820 w/ PFD, 0821 thru 1820, 17. Nylon Union Tee Serials 0435 thru 0820: 1822 thru 1839, 1841 thru 1862 before SB 2X-34-22. 18. Altimeter Tie down on forward location. 19. Air Speed Indicator 21. Altitude Transducer Serials 0821 & subs: 22. PFD Grommet on forward location. SR22_MM34_1625F

Figure 34-101 Pitot-Static System - Serials 0435-0820 w/ PFD, 0821-1820, 1822-1839, 1841-1862 before SB 2X-34-22 (Sheet 2 of 7) EFFECTIVITY: 34-10 Serials 0435-0820 w/ PFD, 0821-1820, 1822-1839, Page 14 15 Apr 2007 1841-1862 before SB 2X-34-22 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

Serials 1821, 1840, 1863 thru 2036, 2038 thru 2042 before SB 2X-34-22.

22 INSTRUMENT PANEL (REF)

Serials 2037, 2043 & subs, CENTER CONSOLE Serials 0002 thru 2036, 21 18 (REF) 2038 thru 2042 after SB 2X-34-22. 2 17 23 2 2 19 7 6 13 1 5 14 17 2 4 1

2 1 17 17 3 LEGEND 7 1. Pitot Tube 17 2. Static Tube 2 3. Grommet 6 1 4. Plug 5. Fitting 6. Tie Down 7. Cable Tie 13. Fitting (Pipe to Flare) 14. Static Port 17. Nylon Union Tee 18. Altimeter 19. Air Speed Indicator 21. Altitude Transducer Serials 1821, 1840, 1863 thru 2333, 2335 thru 2419, 2421 thru 2437. 22. PFD 23. Static Line Sump SR22_MM34_2342A

Figure 34-101 Pitot-Static System - Serials 1821, 1840, 1863 thru 2437 (Sheet 3 of 7) EFFECTIVITY: Serials 1821, 1840, 1863 thru 2437 34-10 Page 15 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

22 INSTRUMENT PANEL (REF)

CENTER CONSOLE 21 18 (REF)

2 17 23 2 2 19 1 2 17 1 3 2 1 17 17 17 17 7 7 2 LEGEND 6 1. Pitot Tube 6 5 4 1 2. Static Tube 3. Grommet 4. Plug 17 5. Fitting 6. Tie Down 7. Cable Tie 17. Nylon Union Tee 18. Altimeter 19. Air Speed Indicator 21. Altitude Transducer Serials 2334, 2420, 2438 & subs. 22. PFD 23. Static Line Sump SR22_MM34_2590

Figure 34-101 Pitot-Static System - Serials 2438 & subs (Sheet 4 of 7) EFFECTIVITY: 34-10 Serials 2438 & subs Page 16 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

2 Serials 0002 thru 0434, 0435 thru 0820 w/o PFD. 26

TO DRAIN 2 (REF) 27 2 34 23 37 30 29 34 2 28 32 31 34 33 36

CONSOLE ASSEMBLY 2 TO ALT STATIC (REF) 34 28 35 SOURCE (REF) 34 36 Serials 0435 thru 0820 w/ PFD, 0821 & subs.

Serials 0002 thru 2036, 32 2038 thru 2042 before SB 2X-34-21. 30

CONSOLE ASSEMBLY (REF)

47 23 2 28 28 2 PANEL LIGHTS WIRE HARNESS (REF) 28 28 17 LED LEGEND ANGLE BRACKET 2. Static Tube (REF) 29 17. Nylon Union Tee 23. Alternate Static Source Valve 26. Mounting Tray 2 27. Altitude Encoder 28. Screw 29. Knob 30. Adel Clamp 31. Washer 32. Nut 33. Spring Clip 34. Hose Clamp 46 35. Nylon Coupling Serials 2037, 2043 & subs, 36. Tubing Serials 0002 thru 2036, 37. Nylon Tee 2038 thru 2042 after SB 2X-34-21. 46. Plug 47. Spiral Wrap SR22_MM34_1397D

Figure 34-101 Pitot-Static System (Sheet 5 of 7) EFFECTIVITY: All 34-10 Page 17 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

17 2 17 1 38 33

SKYWATCH DIFFERENTIAL PRESSURE SWITCH (REF) 38

Serials 0002 thru 1820, 1822 thru 1839, 1841 thru 1862 after SB 2X-31-01.

SKYWATCH DIFFERENTIAL PRESSURE SWITCH (REF)

33 38 33

38 #2 HOUR METER 1 DIFFERENTIAL PRESSURE 2 SWITCH (REF) 34

17 38 2 34 45 17 34 1 2

Serials 0002 & subs w/ SKYWATCH. Serials 1821, 1840, 1863 & subs.

LEGEND 1. Pitot Line 2. Static Line 17. Nylon Union Tee 33. Spring Clip 34. Hose Clamp 38. Hose 45. Nylon Tee

SR22_MM34_2605

Figure 34-101 Pitot-Static System (Sheet 6 of 7) EFFECTIVITY: 34-10 All Page 18 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

CONDUIT 39 (REF) GROUND STRAP (REF) 43

16 1 41 40 48 16 11 41 32 16 31

32 31 28 WING SKIN WING RIB 28 31 (REF) (REF) 1 28 28 28 42 42

43 44

44 Serials 2334, 2420, 2438 & subs.

Serials 0002 thru 2333, 2335 thru 2419, 2421 thru 2437.

LEGEND 1. Pitot Line 11. Elbow 16. Nylon Insert 28. Screw 31. Washer 32. Nut 39. Backing Plate 40. Tygon Tubing 41. Female Tube Connector 42. Bracket, Pitot Mast 43. Extension Tube 44. Pitot Mast 48. Pipe to Flare Fitting

SR22_MM34_1398F

Figure 34-101 Pitot-Static System (Sheet 7 of 7) EFFECTIVITY: All 34-10 Page 19 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

F. Vertical Speed Indicator (VSI) - Serials 0002 thru 0434, 0435 thru 0820 w/o PFD (See Figure 34- 102) (1) Removal - VSI (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull INSTRUMENT LIGHTS circuit breaker. (c) Remove MFD. (Refer to 31-60) (d) Remove and cap off static line. (e) Disconnect electrical connector. (f) While supporting VSI, remove screws securing unit to instrument panel. (g) Cap off fitting on back of VSI, then remove from airplane. (2) Installation - VSI (a) Position VSI in instrument panel and attach with screws. (b) Connect electrical connector. (c) Attach static line. (d) Perform Functional Test - Static Plumbing System. (Refer to 34-10) (e) Reset INSTRUMENT LIGHTS circuit breaker. (f) Perform Functional Test - VSI. (Refer to 34-10) (g) Install MFD. (Refer to 31-60) (3) Functional Test - VSI (a) Set BAT 1 switch to ON position. (b) For INTERIOR/LIGHTS on the bolster panel, adjust INSTRUMENT knob. (c) Verify that instrumentation lighting is functioning and that intensity varies with adjustments to INSTRUMENT knob. (d) Set BAT 1 switch to OFF position.

Note: A zero adjust screw is located on the front, lower LH corner of the VSI to allow for pointer adjustment.

(e) Rotate screw clockwise to deflect the pointer downward as required. (f) Rotate screw counter-clockwise to deflect the pointer upward as required.

EFFECTIVITY: 34-10 Serials 0002 thru 0434, 0435 thru 0820 w/o PFD Page 20 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

TO ALTIMETER

TO 4 ALTERNATE STATIC SOURCE

5 6 INSTRUMENT PANEL (REF)

LEGEND 1. Vertical Speed Indicator 2. Tee Connector 3. Static Line 4. Connector 5. Washer 6. Screw Serials 0002 thru 0434, 0435 thru 0820 w/o PFD. SR22_MM34_1407B

Figure 34-102 VSI Installation - Serials 0002 thru 0434, 0435 thru 0820 w/o PFD EFFECTIVITY: Serials 0002 thru 0434, 0435 thru 0820 w/o PFD 34-10 Page 21 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

G. Altimeter - Serials 0002 thru 0434, 0435 thru 0820 w/o PFD (See Figure 34-103) (1) Removal - Altimeter (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull INSTRUMENT LIGHTS circuit breaker. (c) Remove MFD. (Refer to 31-60) (d) Remove and cap off static line. (e) Disconnect electrical connector. (f) While supporting altimeter, remove screws securing unit to instrument panel. (g) Cap off fitting on back of altimeter to prevent possible contamination, then remove from airplane. (2) Installation - Altimeter (a) Position altimeter in instrument panel, then attach with screws. (b) Connect electrical connector. (c) Attach static line. (d) Reset INSTRUMENT LIGHTS circuit breaker. (e) Perform Functional Test - Pitot Plumbing System. (Refer to 34-10) (f) Perform Functional Test - Static Plumbing System. (Refer to 34-10) (g) Perform Functional Test - Altimeter. (Refer to 34-10) (h) Perform Functional Test - Altitude Encoder Calibration. (Refer to 34-10) (i) Install MFD. (Refer to 31-60) (3) Functional Test - Altimeter (a) Set AVIONICS switch to ON position. (b) On GNS 430, rotate [C] knob clockwise for COM/GPS 1 power and volume. (c) Using COM 1, listen to ATIS. Obtain current altimeter barometric pressure setting. (d) Set barometric pressure in altimeter window. (e) Verify correct altitude is indicated. (f) 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 100 General Sealants Cover static Industry, CA 91745 port. 800-762-1144

14 CFR § 43 Appendix E - Any Source Test.

(b) Set BAT 1 and BAT 2 switches to ON positions.

Note: Calibration must be done with the altimeter at ambient temperature within the range of 55° to 95° F (13° to 35° C). Verify external power is applied to aircraft to preserve battery life and system is up to proper operating power.

(c) Connect 28 ±1 VDC external power to external power receptacle. (d) Connect pitot line from altimeter test set to pitot mast on airplane. (e) Connect static line from altimeter test set to a static port on airplane. EFFECTIVITY: 34-10 Serials 0002 thru 0434, 0435 thru 0820 w/o PFD Page 22 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

(f) Apply sealant tape to cover other static port. (g) Comply with Appendix E of 14 CFR § 43. (h) Disconnect altimeter test set from airplane and remove sealant tape. (i) Disconnect 28 ±1 VDC external power from external power receptacle. (j) Set BAT 1 and BAT 2 switches to OFF positions.

EFFECTIVITY: Serials 0002 thru 0434, 0435 thru 0820 w/o PFD 34-10 Page 23 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

H. Altimeter - Serials 0435 thru 0820 w/ PFD, 0821 & subs (See Figure 34-103) (1) Removal - Altimeter (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull INSTRUMENT LIGHTS circuit breaker. (c) Remove LH kickplate. (Refer to 25-10) (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. (2) Installation - Altimeter (a) Position altimeter in bolster panel and attach with screws. (b) Connect electrical connector. (c) Attach static line. (d) Reset INSTRUMENT LIGHTS circuit breaker. (e) Perform Functional Test - Pitot Plumbing System. (Refer to 34-10) (f) Perform Functional Test - Static Plumbing System. (Refer to 34-10) (g) Perform Functional Test - Altimeter. (Refer to 34-10) (h) Perform Functional Test - Altitude Encoder Calibration. (Refer to 34-10) (i) Install LH kickplate. (Refer to 25-10) (3) Functional Test - Altimeter (a) Set AVIONICS switch to ON position. (b) On GNS 430, rotate [C] knob clockwise for COM/GPS 1 power and volume. (c) Using COM 1, listen to ATIS. Obtain current altimeter barometric pressure setting. (d) Set barometric pressure in altimeter window. (e) Verify correct altitude is indicated. (f) 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 100 General Sealants Cover static Industry, CA 91745 port. 800-762-1144

14 CFR § 43 Appendix E - Any Source Test.

(b) Set BAT 1 and BAT 2 switches to ON positions.

(c) Connect 28 ±1 VDC external power to external power receptacle. (d) Allow PFD to align for approximately 3 minutes, until Air Data Attitude Heading Reference System (ADAHRS) countdown timer expires and gyro warm-up box disappears. EFFECTIVITY: 34-10 Serials 0435 thru 0820 w/ PFD, 0821 & subs Page 24 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

(e) Once aligned, allow PFD to remain in aligned state for 10 additional minutes. (f) Connect pitot line from altimeter test set to pitot mast on airplane. (g) Connect static line from altimeter test set to a static port on airplane. (h) Apply sealant tape to cover other static port. (i) Comply with Appendix E of 14 CFR § 43 for PFD altimeter and backup altimeter observing the following guidelines: 1 For scale error tests, the first test point entry calls for pressure altitude setting of -1000 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. If calibrated altimeter test set setting is between -1000 and -950 feet, and digital altitude indication on PFD is between -20 and 0 feet of value shown on calibrated altimeter test set, the test point is passed. 2 For barometric scale error test, set base altitude to +2000 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. (j) Disconnect altimeter test set from airplane and remove sealant tape. (k) Disconnect 28 ±1 VDC external power from external power receptacle. (l) Set BAT 1 and BAT 2 switches to OFF positions.

EFFECTIVITY: Serials 0435 thru 0820 w/ PFD, 0821 & subs 34-10 Page 25 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

6 TO AIRSPEED INDICATOR

1 5 4

TO 3 VERTICAL SPEED 2 INDICATOR

INSTRUMENT PANEL (REF)

LEGEND 1. Altimeter 2. Screw 3. Washer 4. Tee Connector Serials 0002 thru 0434, 0435 thru 0820 w/o PFD. 5. Static Line 6. Connector

SR22_MM34_2202A

Figure 34-103 Altimeter Installation - Serials 0002 thru 0434, 0435 thru 0820 w/o PFD (Sheet 1 of 2) EFFECTIVITY: 34-10 Serials 0002 thru 0434, 0435 thru 0820 w/o PFD Page 26 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

5 7

3 2

BOLSTER PANEL (REF)

LEGEND 1. Altimeter Serials 0435 thru 0820, w/ PFD, 0821 & subs. 2. Screw 3. Washer 5. Static Line 6. Connector 7. Nylon Fitting

SR22_MM34_1624C

Figure 34-103 Altimeter Installation - Serials 0435 thru 0820 w/ PFD, 0821 & subs (Sheet 2 of 2) EFFECTIVITY: Serials 0435 thru 0820 w/ PFD, 0821 & subs 34-10 Page 27 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

I. Airspeed Indicator - Serials 0002 thru 0434, 0435 thru 0820 w/o PFD (See Figure 34-104) (1) Removal - Airspeed Indicator (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull INSTRUMENT LIGHTS circuit breaker. (c) Remove glareshield. (Refer to 25-10) (d) Remove and cap off static and pitot line. (e) Disconnect electrical connector. (f) While supporting airspeed indicator, remove screws securing unit to instrument panel. (g) Cap off fitting on back of airspeed indicator to prevent possible contamination, then remove from airplane. (2) Installation - Airspeed Indicator (a) Position airspeed indicator in instrument panel, then attach with screws. (b) Connect electrical connector. (c) Attach static and pitot line. (d) Reset INSTRUMENT LIGHTS circuit breaker. (e) Perform Functional Test - Static Plumbing System. (Refer to 34-10) (f) Perform Functional Test - Pitot Plumbing System. (Refer to 34-10) (g) Perform Functional Test - Airspeed Indicator. (Refer to 34-10) (h) Install glareshield. (Refer to 25-10) (3) Functional Test - Airspeed Indicator (a) Verify needle indicates zero (straight up, <40 kts).

EFFECTIVITY: 34-10 Serials 0002 thru 0434, 0435 thru 0820 w/o PFD Page 28 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

J. Airspeed Indicator - Serials 0435 thru 0820 w/ PFD, 0821 & subs (See Figure 34-104) (1) Removal - Airspeed Indicator (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull INSTRUMENT LIGHTS circuit breaker. (c) Remove LH kickplate. (Refer to 25-10) (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. (2) 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 INSTRUMENT LIGHTS circuit breaker. (e) Perform Functional Test - Static Plumbing System. (Refer to 34-10) (f) Perform Functional Test - Pitot Plumbing System. (Refer to 34-10) (g) Perform Functional Test - Airspeed Indicator. (Refer to 34-10) (h) Install LH kickplate. (Refer to 25-10) (3) Functional Test - Airspeed Indicator (a) Verify needle indicates zero (straight up, <40 kts).

EFFECTIVITY: Serials 0435 thru 0820 w/ PFD, 0821 & subs 34-10 Page 29 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

7 5 INSTRUMENT 4 PANEL (REF) 6 1

3 2

Serials 0002 thru 0434, 0435 thru 0820 w/o PFD.

LEGEND 1. Airspeed Indicator 2. Screw 3. Washer 4. Nylon Fitting 5. Static Line 6. Pitot Line 7. Connector

SR22_MM34_2206

Figure 34-104 Airspeed Indicator Installation - Serials 0002 thru 0434, 0435 thru 0820 w/o PFD (Sheet 1 of 2) EFFECTIVITY: 34-10 Serials 0002 thru 0434, 0435 thru 0820 w/o PFD Page 30 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

6 4

3 2

BOLSTER PANEL (REF)

LEGEND 1. Airspeed Indicator 2. Screw 3. Washer 4. Nylon Fitting 5. Static Line 6. Pitot Line 7. Connector

SR22_MM34_2204A

Figure 34-104 Airspeed Indicator Installation - Serials 0435 thru 0820 w/ PFD, 0821 & subs (Sheet 2 of 2) EFFECTIVITY: Serials 0435 thru 0820 w/ PFD, 0821 & subs 34-10 Page 31 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

K. Outside Air Temperature (OAT) Gage/Clock - Serials 0002 thru 0434, 0435 thru 0820 w/o PFD (See Figure 34-105) (1) Removal - OAT Gage/Clock (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull INSTRUMENT LIGHTS circuit breaker. (c) Remove glareshield. (Refer to 25-10) (d) Disconnect electrical connector. (e) Remove screws securing OAT gage/clock to instrument panel, then remove from airplane. (2) Installation - OAT Gage/Clock (a) Position OAT gage/clock in instrument panel, then attach with screws. (b) Connect electrical connector. (c) Reset INSTRUMENT LIGHTS circuit breaker. (d) Perform Functional Test - OAT Gage/Clock. (Refer to 34-10) (e) Install glareshield. (Refer to 25-10) (3) Functional Test - OAT Gage/Clock (a) Pull STARTER RELAY and FUEL PUMP RELAY circuit breakers. (b) Set BAT 1 switch to ON position. (c) Press [OAT/VOLTS] to display voltage. (d) Verify display indicates approximately “24.0E” ±2 for ship voltage. (e) Press [OAT/VOLTS] to display ambient air temperature in fahrenheit. (f) Press [OAT/VOLTS] to display ambient air temperature in celsius. (g) Set Universal Time. 1 Press [SELECT] to select Universal Time (UT). 2 Press simultaneously both [SELECT] and [CONTROL]. The tens of hours digit flashes. 3 Press [CONTROL] to change digit. 4 Press [SELECT] to advance to the next digit. 5 On the last editable digit, press [SELECT] to exit. (h) Set Local Time. 1 Press [SELECT] to select Local Time (LT). 2 Press simultaneously both [SELECT] and [CONTROL]. The tens of hours digit flashes.

Note: Only the hours can be set for Local Time. The minutes are set under Universal Time.

3 Press [CONTROL] to change digit. 4 Press [SELECT] to exit. (i) Set BAT 1 switch to OFF position. (j) Reset STARTER RELAY and FUEL PUMP RELAY circuit breakers.

EFFECTIVITY: 34-10 Serials 0002 thru 0434, 0435 thru 0820 w/o PFD Page 32 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

L. Outside Air Temperature (OAT) Gage/Clock Battery - Serials 0002 - 0434, 0435 - 0820 w/o PFD (See Figure 34-105) (1) Removal - OAT Gage/Clock Battery The OAT gage/clock battery must be inspected every 24 months. Upon replacement, the battery must have a date stamp to indicate battery expiration date. (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull INSTRUMENT LIGHTS circuit breaker. (c) Remove glareshield. (Refer to 25-10) (d) Remove battery from OAT gage/clock.

CAUTION: Do not use abrasive cleaners or materials to clean battery contacts.

(e) Examine battery contacts for dirt or corrosion, then clean contacts as necessary. (2) Installation - OAT Gage/Clock Battery (a) Record the battery replacement date of new cell in Airplane Log Book. (b) Install new battery as indicated by battery polarity signs marked on cell holder. (c) Perform Functional Test - OAT Gage/Clock. (Refer to 34-10) (d) Install glareshield. (Refer to 25-10)

EFFECTIVITY: Serials 0002 - 0434, 0435 - 0820 w/o PFD 34-10 Page 33 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

M. Outside Air Temperature (OAT) Gage/Clock Sensor - Serials 0002 - 0434, 0435 - 0820 w/o PFD (See Figure 34-105) (1) Removal - OAT Sensor (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Remove glareshield. (Refer to 25-10) (c) Disconnect electrical connector. (d) Remove nut and washer securing OAT sensor to fuselage. (2) Installation - OAT Sensor (a) Position OAT sensor to fuselage and secure with washer and nut. (b) Connect electrical connector. (c) Install glareshield. (Refer to 25-10)

EFFECTIVITY: 34-10 Serials 0002 - 0434, 0435 - 0820 w/o PFD Page 34 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

N. Outside Air Temperature (OAT) Sensor - Serials 0002 thru 1601, 1603 thru 1643, 1645 thru 1662 w/ EMax Engine Monitoring (See Figure 34-105) (1) Removal - OAT Sensor (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Remove glareshield. (Refer to 25-10) (c) Disconnect electrical connector. (d) Remove nut and washer securing OAT sensor to fuselage. (2) Installation - OAT Sensor (a) Position OAT sensor to fuselage and secure with washer and nut. (b) Connect electrical connector. Ensure backshell is secured tightly to sensor assembly. (c) Verify resistance from OAT sensor case to airplane ground is less than 2.0 ohms. If resistance is greater than 2.0 ohms, burnish OAT sensor backshell contact as required. (d) Install glareshield. (Refer to 25-10)

EFFECTIVITY: Serials 0002 thru 1601, 1603 thru 1643, 1645 thru 34-10 Page 35 1662 w/ EMax Engine Monitoring 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22

FUSELAGE (REF)

1 3 2

Serials 0300 thru 1601, 1603 thru 1643, 1645 thru 1662 w/ EMax Engine Monitoring, Serials 0002 thru 0299 after SB 22-77-01. 3 2

FUSELAGE (REF)

INSTRUMENT Serials 0002 thru 0434, 0435 thru 0820 w/o PFD. PANEL (REF)

LEGEND 1. Nut 6 2. Washer NOTE 3. OAT Sensor 4. Connector Verify resistance from OAT sensor case to airplane 5. OAT/Clock Gage ground is less than 2.0 ohms. If resistance is greater 6. Screw than 2.0 ohms, burnish OAT sensor backshell contact 7. Battery as required. Serials 0002-0434, 0435-0820 w/o PFD, 0002-1601, 1603-1643, 1645-1662 w/ EMax. SR22_MM34_1408C

Figure 34-105 OAT and Clock Install - Serials 0002-0434, 0435-0820 w/o PFD, 0002-1601, 1603-1643, 1645-1662 w/ EMax EFFECTIVITY: 34-10 Serials 0002-0434, 0435-0820 w/o PFD, 0002-1601, Page 36 15 Apr 2007 1603-1643, 1645-1662 w/ EMax