MODEL SR FLIGHT ENVIRONMENTAL SYSTEMS. 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 34-00) 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 8 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 8 VDC supplied through the -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 080 w/ PFD, 08 & 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 000 thru 036, 038 thru 04 after SB X-34-, 037, 043 & 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 malfunctioning. 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 000 thru 0434, 0435 thru 080 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), Outside 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 8 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 080 w/ PFD, 08 & subs: The PFD receives an OAT signal from a temperature sensor integral to the magnetometer installed in the RH wing. Serials 000 thru 60, 603 thru 643, 645 thru 66 w/ EMax Engine Monitoring: The Multifunction Display (MFD) receives an OAT signal from a temperature sensor installed immediately forward of the copilot s door. Serials 60, 644, 663 & subs: The MFD receives an OAT signal from a temperature sensor integral to the magnetometer installed in the RH wing. All Page
MODEL SR 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 000 thru 0434, 0435 thru 080 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 080 w/ PFD, 08 & 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 o clock position indicates airspeed. Range of the instrument is 0 to 0 knots. Serials 000 thru 0434, 0435 thru 080 w/o PFD: The airspeed indicator is located in the upper LH portion of the pilot s instrument panel. Serials 0435 thru 080 w/ PFD, 08 & 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 00, 000, and 0,000 feet, with a range of -000 to 0,000 feet. Serials 000 thru 0434, 0435 thru 080 w/o PFD: The altimeter is located in the upper mid portion of the instrument panel. Serials 0435 thru 080 w/ PFD, 08 & subs: The primary altimeter is on the PFD. The standby altimeter is located in the LH bolster panel. Page All
MODEL SR. TROUBLESHOOTING 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. Leaks in static and/or pitot line. Leaks or obstruction in static line. PITOT HEAT switch is set to OFF position. Check lines for leaks. Perform System Test - Static Plumbing System. (Refer to ) Check lines for leaks. Perform System Test - Pitot Plumbing System. (Refer to ) Repair or replace line. Remove obstruction. Set PITOT HEAT switch to ON position. Pitot tube does not heat or melt ice. Pitot Light ON. Circuit breaker out. Break in wiring. Insufficient current. Heating element burned out. Reset circuit breaker. Test and repair wiring. Check current drain of element. Replace element. Low or sluggish airspeed indication. Normal altimeter and vertical speed indication. Pitot tube deformed. Leak or obstruction in pitot line. Repair or replace damaged component. Trouble - Vertical Speed Ind. Probable Cause Remedy Pointer 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 Plumbing System. (Refer to ) 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 ) Pointer oscillates or fails to respond. Leaks in static line. Defective instrument. Excessive vibration caused by loose mounting screws. Check line for obstruction. Blow out lines. (Refer to ) Replace or repair instrument. Tighten mounting screws. All Page 3
MODEL SR 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 Plumbing System. (Refer to ) Tighten mounting screws. High reading. Static system leak. Inspect static system. (Refer to ) 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 indicates improperly. Leak in instrument case. Obstruction in pitot line. Replace or repair instrument. Check line for obstruction. Blow out lines. (Refer to ) 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 Plumbing System. (Refer to ) 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. Page 4 All
MODEL SR 3. MAINTENANCE PRACTICES A. Pitot Tube Assembly (See Figure ) () 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 securing pitot tube bracket to rib, then remove bracket. () 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 ) (e) Perform Operational Test - Pitot Heat. (Refer to ) (f) Install left wing tip. (Refer to 57-0) (g) Reset PITOT HEAT circuit breaker. (3) Operational Test - Pitot Heat (a) Set BAT, BAT, and AVIONICS switches to OFF positions. Note: The pitot tube may utilize an after-market cover. (b) (c) (d) (e) (f) (g) 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 annunciator light is on. Reset PITOT HEAT circuit breaker. Verify PITOT HEAT annunciator light is off. WARNING: Avoid prolonged exposure to heated pitot tube to prevent burns. (h) (i) (j) 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. All Page 5
MODEL SR B. Pitot Plumbing System (See Figure ) () 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 000 thru 0434, 0435 thru 080 w/o PFD: Remove glareshield. (Refer to 5-0) (b) Serials 0435 thru 080 w/ PFD, 08 & subs: Remove LH kickplate. (Refer to 5-0) (c) Disconnect pitot line at airspeed indicator, then cap off airspeed indicator. (d) Serials 0435 thru 080 w/ PFD, 08 & subs: Disconnect pitot line at PFD, then cap off PFD. CAUTION: Never blow air through the line toward the instruments. To do so will seriously 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 080 w/ PFD, 08 & subs: Connect pitot line at PFD. (h) Perform Functional Test - Pitot Plumbing System. (Refer to ) (i) Serials 000 thru 0434, 0435 thru 080 w/o PFD: Install glareshield. (Refer to 5-0) (j) Serials 0435 thru 080 w/ PFD, 08 & subs: Install LH kickplate. (Refer to 5-0) () 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 Set Model 393 a Aircraft Instrument Support Services, Inc. Round Rock, TX 78664 800-593-096 Simulate pitot air pressure. Sealant Tape GS 00 General Sealants Industry, CA 9745 800-76-44 a. or equivalent Cover pitot tube hole during leak test. (b) (c) 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. (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. Page 6 All
MODEL SR (e) 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. All Page 7
MODEL SR C. Alternate Static Source Valve (See Figure ) () 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 000 thru 036, 038 thru 04 after SB X-34-, 037, 043 & 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. () Installation - Alternate Static Source Valve (a) Position alternate static source valve to console, then install mounting screw. (b) Serials 000 thru 036, 038 thru 04 after SB X-34-, 037, 043 & 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 ) (f) Close and secure circuit breaker panel. Page 8 All
MODEL SR D. Static Plumbing System (See Figure ) () 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 037, 043 & subs, Serials 000 thru 036, 038 thru 04 after SB X-34-: 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 037, 043 & subs, Serials 000 thru 036, 038 thru 04 after SB X-34-: 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, 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 080 w/ PFD, 08 & subs: Disconnect pitot line at PFD, then cap off PFD. CAUTION: Never blow air through the line toward the instruments. To do so will seriously 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 080 w/ PFD, 08 & subs: Connect static line at PFD. (g) Perform Functional Test - Static Plumbing System. (Refer to ) (h) Close and secure circuit breaker panel. () Functional Test - Static Plumbing System (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Calibrated Pitot/Static Test Set Model 393 a Aircraft Instrument Support Services, Inc. Round Rock, TX 78664 800-593-096 Simulate static air pressure. Sealant Tape GS 00 General Sealants Industry, CA 9745 800-76-44 a. or equivalent Cover static air buttons during leak test. (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) Serials 0435 thru 080 w/ PFD, 08 & subs: Remove LH kickplate. (Refer to 5-0) All Page 9
MODEL SR CAUTION: Never apply positive pressure with airspeed indicator, vertical speed indicator, or PFD connected into static system. (g) (h) 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. 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. (i) (j) (k) (l) 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. (m) Perform Functional Test - Pitot Plumbing System. (Refer to ) (n) 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 Serials 000 thru 0434, 0435 thru 080 w/o PFD: Install LH kickplate. (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) Page 0 All
MODEL SR E. Altitude Encoder (See Figure ) () Removal - Altitude Encoder (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) Pull ENCODER/TRANSPONDER circuit breaker. (c) Remove trim panel from RH side of center console. (Refer to 5-0) (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. () 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 ) (g) Perform Functional Test - Static Plumbing System. (Refer to ) (h) Perform Functional Test - Altitude Encoder Calibration. (Refer to ) (i) Safety wire knurled nut to mounting tray. (j) Install trim panel to RH side of center console. (Refer to 5-0) (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) (b) Pull STARTER RELAY and FUEL PUMP RELAY circuit breakers. Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Calibrated Pitot/Static Test Set Model 393 a Aircraft Instrument Support Services, Inc. Round Rock, TX 78664 800-593-096 Simulate altitude. Sealant Tape GS 00 General Sealants Industry, CA 9745 800-76-44 a. or equivalent Cover static port. (c) (d) Connect 8 ± VDC external power to external power receptacle. Set BAT, BAT, and AVIONICS switches to ON positions. All Page
MODEL SR Note: Calibration must be done with the encoder and altimeter both 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. (e) (f) (g) (h) Turn on encoder and allow to warm up for a minimum period of 0 minutes. If power to the encoder is momentarily interrupted during calibration, wait a minimum of 3 minutes before continuing with the calibration. 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. CAUTION: Verify up or down arrow is not displayed on transponder prior to taking any reading. (i) (j) With calibrated pitot/static test set, simulate altitude ascent through 7950 feet. Verify transponder transitions to 8000 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. (l) (m) (n) Adjust H screw until transponder agrees with altimeter. With calibrated pitot/static test set, simulate altitude descent through 950 feet. Verify transponder transitions to 3000 feet. If transponder is out of tolerance, adjust low altitude settings. Note: Rotate L screw clockwise to increase altitude. (o) (p) (q) (r) Adjust L screw until transponder agrees with altimeter. Set BAT, BAT, and AVIONICS switches to OFF positions. Disconnect pitot/static test set from airplane and remove sealant tape. Disconnect 8 ± VDC external power from external power receptacle. Reset STARTER RELAY and FUEL PUMP RELAY circuit breakers. Page All
CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR TYPICAL INSTALLATION 6 5 INSTRUMENT PANEL 5 3 4 7 6 8 5 9 7 0 5 6 7 8 6 7 5 5 0 4 LEGEND. Pitot Tube. Static Tube 3. Grommet 4. Plug 5. Fitting 6. Tie Down 7. Cable Tie 8. Drain Tube 9. Union Tee 0. Bushing. Elbow. Tee 3. Fitting (pipe to flare) 4. Static Port 5. Static Line 6. Insert 7. Nylon Union Tee 8. Altimeter 9. Air Speed Indicator 0. Vertical Speed Indicator. Altitude Transducer 9 3 Serials 000 thru 0434, 0435 thru 080 w/o PFD before SB X-34-. SR_MM34_396C Figure Pitot-Static System - Serials 000 thru 0434, 0435 thru 080 w/o PFD before SB X-34- (Sheet of 7) Serials 000 thru 0434, 0435 thru 080 w/o PFD before SB X-34- Page 3
MODEL SR INSTRUMENT PANEL 3 4 8 CENTER CONSOLE 7 7 7 7 NOTE 7 6 3 Serials 0435 thru 080: Tie down on forward location. Serials 08 & subs: Grommet on forward location. 7 4 6 5 9 7 3 Serials 0435 thru 080 w/ PFD, 08 thru 80, 8 thru 839, 84 thru 86 before SB X-34-. LEGEND. Pitot Tube. Static Tube 3. Grommet 4. Plug 5. Fitting 6. Tie Down 7. Cable Tie 3. Fitting (Pipe to Flare) 4. Static Port 7. Nylon Union Tee 8. Altimeter 9. Air Speed Indicator. Altitude Transducer. PFD SR_MM34_65F Figure Pitot-Static System - Serials 0435-080 w/ PFD, 08-80, 8-839, 84-86 before SB X-34- (Sheet of 7) Page 4 Serials 0435-080 w/ PFD, 08-80, 8-839, 84-86 before SB X-34-
MODEL SR Serials 8, 840, 863 thru 036, 038 thru 04 before SB X-34-. INSTRUMENT PANEL 3 7 7 8 CENTER CONSOLE 9 5 4 6 7 Serials 037, 043 & subs, Serials 000 thru 036, 038 thru 04 after SB X-34-. 3 4 3 6 7 7 7 3 LEGEND. Pitot Tube 7. Static Tube 3. Grommet 4. Plug 5. Fitting 6. Tie Down 7. Cable Tie 3. Fitting (Pipe to Flare) 4. Static Port 7. Nylon Union Tee 8. Altimeter 9. Air Speed Indicator. Altitude Transducer Serials 8, 840, 863 thru 333, 335 thru 49, 4 thru 437.. PFD 3. Static Line Sump SR_MM34_34A Figure Pitot-Static System - Serials 8, 840, 863 thru 437 (Sheet 3 of 7) Serials 8, 840, 863 thru 437 Page 5
MODEL SR INSTRUMENT PANEL 3 8 CENTER CONSOLE 7 3 7 9 3 6 7 7 7 7 4 5 7 6 7 7 Serials 334, 40, 438 & subs. LEGEND. Pitot Tube. Static Tube 3. Grommet 4. Plug 5. Fitting 6. Tie Down 7. Cable Tie 7. Nylon Union Tee 8. Altimeter 9. Air Speed Indicator. Altitude Transducer. PFD 3. Static Line Sump SR_MM34_590 Page 6 Figure Pitot-Static System - Serials 438 & subs (Sheet 4 of 7) Serials 438 & subs
MODEL SR 7 6 Serials 000 thru 0434, 0435 thru 080 w/o PFD. TO DRAIN 9 8 3 30 3 3 7 33 36 34 34 37 34 8 CONSOLE ASSEMBLY 36 34 35 34 Serials 0435 thru 080 w/ PFD, 08 & subs. TO ALT STATIC SOURCE Serials 000 thru 036, 038 thru 04 before SB X-34-. 3 30 CONSOLE ASSEMBLY 47 PANEL LIGHTS WIRE HARNESS 3 8 8 8 7 46 LED ANGLE BRACKET Serials 037, 043 & subs, Serials 000 thru 036, 038 thru 04 after SB X-34-. 9 8 LEGEND. Static Tube 7. Nylon Union Tee 3. Alternate Static Source Valve 6. Mounting Tray 7. Altitude Encoder 8. Screw 9. Knob 30. Adel Clamp 3. Washer 3. Nut 33. Spring Clip 34. Hose Clamp 35. Nylon Coupling 36. Tubing 37. Nylon Tee 46. Plug 47. Spiral Wrap SR_MM34_397D All Figure Pitot-Static System (Sheet 5 of 7) Page 7
MODEL SR 7 38 33 7 SKYWATCH DIFFERENTIAL PRESSURE SWITCH 38 33 Serials 000 thru 80, 8 thru 839, 84 thru 86 after SB X-3-0. SKYWATCH DIFFERENTIAL PRESSURE SWITCH 33 33 38 38 # HOUR METER DIFFERENTIAL PRESSURE SWITCH 34 7 7 Serials 000 & subs w/ SKYWATCH. 38 34 45 34 Serials 8, 840, 863 & subs. LEGEND. Pitot Line. Static Line 7. Nylon Union Tee 33. Spring Clip 34. Hose Clamp 38. Hose 45. Nylon Tee SR_MM34_605 Page 8 Figure Pitot-Static System (Sheet 6 of 7) All
MODEL SR 39 CONDUIT 43 GROUND STRAP 6 4 6 40 48 4 6 3 3 WING RIB 3 8 3 3 8 WING SKIN 8 8 8 4 4 43 44 44 Serials 334, 40, 438 & subs. Serials 000 thru 333, 335 thru 49, 4 thru 437. LEGEND. Pitot Line. Elbow 6. Nylon Insert 8. Screw 3. Washer 3. Nut 39. Backing Plate 40. Tygon Tubing 4. Female Tube Connector 4. Bracket, Pitot Mast 43. Extension Tube 44. Pitot Mast 48. Pipe to Flare Fitting SR_MM34_398F All Figure Pitot-Static System (Sheet 7 of 7) Page 9
MODEL SR F. Vertical Speed Indicator (VSI) - Serials 000 thru 0434, 0435 thru 080 w/o PFD (See Figure 34-0) () Removal - VSI (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) Pull INSTRUMENT LIGHTS circuit breaker. (c) Remove MFD. (Refer to 3-60) (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. () 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 ) (e) Reset INSTRUMENT LIGHTS circuit breaker. (f) Perform Functional Test - VSI. (Refer to ) (g) Install MFD. (Refer to 3-60) (3) Functional Test - VSI (a) Set BAT 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 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) (f) Rotate screw clockwise to deflect the pointer downward as required. Rotate screw counter-clockwise to deflect the pointer upward as required. Page 0 Serials 000 thru 0434, 0435 thru 080 w/o PFD
MODEL SR TO ALTERNATE STATIC SOURCE TO ALTIMETER 4 3 INSTRUMENT PANEL 5 6 Serials 000 thru 0434, 0435 thru 080 w/o PFD. LEGEND. Vertical Speed Indicator. Tee Connector 3. Static Line 4. Connector 5. Washer 6. Screw SR_MM34_407B Figure VSI Installation - Serials 000 thru 0434, 0435 thru 080 w/o PFD Serials 000 thru 0434, 0435 thru 080 w/o PFD Page
MODEL SR G. Altimeter - Serials 000 thru 0434, 0435 thru 080 w/o PFD (See Figure 3) () Removal - Altimeter (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) Pull INSTRUMENT LIGHTS circuit breaker. (c) Remove MFD. (Refer to 3-60) (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. () 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 ) (f) Perform Functional Test - Static Plumbing System. (Refer to ) (g) Perform Functional Test - Altimeter. (Refer to ) (h) Perform Functional Test - Altitude Encoder Calibration. (Refer to ) (i) Install MFD. (Refer to 3-60) (3) Functional Test - Altimeter (a) Set AVIONICS switch to ON position. (b) On GNS 430, rotate [C] knob clockwise for COM/GPS power and volume. (c) Using COM, 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 00 General Sealants Industry, CA 9745 800-76-44 Cover static port. 4 CFR 43 Appendix E - Any Source Test. (b) 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. Page (c) (d) (e) Connect 8 ± VDC external power to external power receptacle. 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. Serials 000 thru 0434, 0435 thru 080 w/o PFD
MODEL SR (f) Apply sealant tape to cover other static port. (g) Comply with Appendix E of 4 CFR 43. (h) Disconnect altimeter test set from airplane and remove sealant tape. (i) Disconnect 8 ± VDC external power from external power receptacle. (j) Set BAT and BAT switches to OFF positions. Serials 000 thru 0434, 0435 thru 080 w/o PFD Page 3
MODEL SR H. Altimeter - Serials 0435 thru 080 w/ PFD, 08 & subs (See Figure 3) () Removal - Altimeter (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) Pull INSTRUMENT LIGHTS circuit breaker. (c) Remove LH kickplate. (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 INSTRUMENT LIGHTS circuit breaker. (e) Perform Functional Test - Pitot Plumbing System. (Refer to ) (f) Perform Functional Test - Static Plumbing System. (Refer to ) (g) Perform Functional Test - Altimeter. (Refer to ) (h) Perform Functional Test - Altitude Encoder Calibration. (Refer to ) (i) Install LH kickplate. (Refer to 5-0) (3) Functional Test - Altimeter (a) Set AVIONICS switch to ON position. (b) On GNS 430, rotate [C] knob clockwise for COM/GPS power and volume. (c) Using COM, 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 00 General Sealants Industry, CA 9745 800-76-44 Cover static port. 4 CFR 43 Appendix E - Any Source Test. (b) 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. Page 4 (c) (d) Connect 8 ± VDC external power to external power receptacle. 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. Serials 0435 thru 080 w/ PFD, 08 & subs
MODEL SR (e) (f) (g) (h) (i) (j) (k) (l) Once aligned, allow PFD to remain in aligned state for 0 additional minutes. 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. 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. 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. Serials 0435 thru 080 w/ PFD, 08 & subs Page 5
MODEL SR TO AIRSPEED INDICATOR 6 5 4 5 TO VERTICAL SPEED INDICATOR 3 INSTRUMENT PANEL Serials 000 thru 0434, 0435 thru 080 w/o PFD. LEGEND. Altimeter. Screw 3. Washer 4. Tee Connector 5. Static Line 6. Connector Page 6 Figure 3 Altimeter Installation - Serials 000 thru 0434, 0435 thru 080 w/o PFD (Sheet of ) SR_MM34_0A Serials 000 thru 0434, 0435 thru 080 w/o PFD
MODEL SR 6 7 5 3 BOLSTER PANEL Serials 0435 thru 080, w/ PFD, 08 & subs. LEGEND. Altimeter. Screw 3. Washer 5. Static Line 6. Connector 7. Nylon Fitting Figure 3 Altimeter Installation - Serials 0435 thru 080 w/ PFD, 08 & subs (Sheet of ) Serials 0435 thru 080 w/ PFD, 08 & subs SR_MM34_64C Page 7
MODEL SR I. Airspeed Indicator - Serials 000 thru 0434, 0435 thru 080 w/o PFD (See Figure 4) () Removal - Airspeed Indicator (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) Pull INSTRUMENT LIGHTS circuit breaker. (c) Remove glareshield. (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 instrument 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 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 ) (f) Perform Functional Test - Pitot Plumbing System. (Refer to ) (g) Perform Functional Test - Airspeed Indicator. (Refer to ) (h) Install glareshield. (Refer to 5-0) (3) Functional Test - Airspeed Indicator (a) Verify needle indicates zero (straight up, <40 kts). Page 8 Serials 000 thru 0434, 0435 thru 080 w/o PFD
MODEL SR J. Airspeed Indicator - Serials 0435 thru 080 w/ PFD, 08 & subs (See Figure 4) () Removal - Airspeed Indicator (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) Pull INSTRUMENT LIGHTS circuit breaker. (c) Remove LH kickplate. (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 INSTRUMENT LIGHTS circuit breaker. (e) Perform Functional Test - Static Plumbing System. (Refer to ) (f) Perform Functional Test - Pitot Plumbing System. (Refer to ) (g) Perform Functional Test - Airspeed Indicator. (Refer to ) (h) Install LH kickplate. (Refer to 5-0) (3) Functional Test - Airspeed Indicator (a) Verify needle indicates zero (straight up, <40 kts). Serials 0435 thru 080 w/ PFD, 08 & subs Page 9
MODEL SR 5 7 6 4 INSTRUMENT PANEL 3 Serials 000 thru 0434, 0435 thru 080 w/o PFD. Figure 4 Airspeed Indicator Installation - Serials 000 thru 0434, 0435 thru 080 w/o PFD (Sheet of ) Page 30 LEGEND. Airspeed Indicator. Screw 3. Washer 4. Nylon Fitting 5. Static Line 6. Pitot Line 7. Connector SR_MM34_06 Serials 000 thru 0434, 0435 thru 080 w/o PFD
MODEL SR 7 5 4 6 3 BOLSTER PANEL Figure 4 Airspeed Indicator Installation - Serials 0435 thru 080 w/ PFD, 08 & subs (Sheet of ) Serials 0435 thru 080 w/ PFD, 08 & subs LEGEND. Airspeed Indicator. Screw 3. Washer 4. Nylon Fitting 5. Static Line 6. Pitot Line 7. Connector SR_MM34_04A Page 3
MODEL SR K. Outside Air Temperature (OAT) Gage/Clock - Serials 000 thru 0434, 0435 thru 080 w/o PFD (See Figure 5) () Removal - OAT Gage/Clock (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) Pull INSTRUMENT LIGHTS circuit breaker. (c) Remove glareshield. (Refer to 5-0) (d) Disconnect electrical connector. (e) Remove screws securing OAT gage/clock to instrument panel, then remove from airplane. () 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 ) (e) Install glareshield. (Refer to 5-0) (3) Functional Test - OAT Gage/Clock (a) Pull STARTER RELAY and FUEL PUMP RELAY circuit breakers. (b) Set BAT switch to ON position. (c) Press [OAT/VOLTS] to display voltage. (d) Verify display indicates approximately 4.0E ± 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. Press [SELECT] to select Universal Time (UT). 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. Press [SELECT] to select Local Time (LT). 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. (i) (j) 3 Press [CONTROL] to change digit. 4 Press [SELECT] to exit. Set BAT switch to OFF position. Reset STARTER RELAY and FUEL PUMP RELAY circuit breakers. Page 3 Serials 000 thru 0434, 0435 thru 080 w/o PFD
MODEL SR L. Outside Air Temperature (OAT) Gage/Clock Battery - Serials 000-0434, 0435-080 w/o PFD (See Figure 5) () Removal - OAT Gage/Clock Battery The OAT gage/clock battery must be inspected every 4 months. Upon replacement, the battery must have a date stamp to indicate battery expiration date. (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) Pull INSTRUMENT LIGHTS circuit breaker. (c) Remove glareshield. (Refer to 5-0) (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. () 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 ) (d) Install glareshield. (Refer to 5-0) Serials 000-0434, 0435-080 w/o PFD Page 33
MODEL SR M. Outside Air Temperature (OAT) Gage/Clock Sensor - Serials 000-0434, 0435-080 w/o PFD (See Figure 5) () Removal - OAT Sensor (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) Remove glareshield. (Refer to 5-0) (c) Disconnect electrical connector. (d) Remove nut and washer securing OAT sensor to fuselage. () Installation - OAT Sensor (a) Position OAT sensor to fuselage and secure with washer and nut. (b) Connect electrical connector. (c) Install glareshield. (Refer to 5-0) Page 34 Serials 000-0434, 0435-080 w/o PFD
MODEL SR N. Outside Air Temperature (OAT) Sensor - Serials 000 thru 60, 603 thru 643, 645 thru 66 w/ EMax Engine Monitoring (See Figure 5) () Removal - OAT Sensor (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) Remove glareshield. (Refer to 5-0) (c) Disconnect electrical connector. (d) Remove nut and washer securing OAT sensor to fuselage. () 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.0 ohms. If resistance is greater than.0 ohms, burnish OAT sensor backshell contact as required. (d) Install glareshield. (Refer to 5-0) Serials 000 thru 60, 603 thru 643, 645 thru 66 w/ EMax Engine Monitoring Page 35
MODEL SR FUSELAGE 3 3 Serials 0300 thru 60, 603 thru 643, 645 thru 66 w/ EMax Engine Monitoring, Serials 000 thru 099 after SB -77-0. FUSELAGE Serials 000 thru 0434, 0435 thru 080 w/o PFD. INSTRUMENT PANEL 7 4 5 NOTE Verify resistance from OAT sensor case to airplane ground is less than.0 ohms. If resistance is greater than.0 ohms, burnish OAT sensor backshell contact as required. Serials 000-0434, 0435-080 w/o PFD, 000-60, 603-643, 645-66 w/ EMax. Page 36 SR_MM34_408C Figure 5 OAT and Clock Install - Serials 000-0434, 0435-080 w/o PFD, 000-60, 603-643, 645-66 w/ EMax 6 LEGEND. Nut. Washer 3. OAT Sensor 4. Connector 5. OAT/Clock Gage 6. Screw 7. Battery Serials 000-0434, 0435-080 w/o PFD, 000-60, 603-643, 645-66 w/ EMax