MODEL SR0 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, outside air temperature gage/clock and sensors, vertical speed indicator, altimeter, airspeed indicator, air data computers and MD30 Standby Attitude Module. (See Figure 34-00) A. Pitot-Static - Serials 005 thru 05, 06 & subs w/o Perspective Avionics 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 337 thru 4 w/ PFD, 43 thru 05, 06 & subs w/o Perspective Avionics: 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 under access panel CF3L. (Refer to 06-00) Serials 706 & subs, Serials 005 thru 705 after SB X-34-: 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. B. Pitot-Static - Serials 06 & subs w/ Perspective Avionics 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 the 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 air data computer, airspeed indicator, altimeter, and altitude transducer (if equipped with the System 55X autopilot). Serials 73 & subs w/ MD30 Standby Attitude Module: The optional MD30 Standby Attitude Module is a combined standby airspeed indicator, standby altimeter, and standby attitude indicator. The All Page 5 Dec 04
MODEL SR0 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 06-00) 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 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. C. Outside Air Temperature Gage/Clock and Sensors Serials 005 thru 336, 337 thru 4 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 337 thru 4 w/ PFD, 43 thru 05, 06 & subs w/o Perspective Avionics: The PFD receives an OAT signal from a temperature sensor integral to the magnetometer installed in the RH wing. Serials 005 thru 58 w/ EMax Engine Monitoring: The Multi-Function Display (MFD) receives an OAT signal from a temperature sensor installed immediately forward of the co-pilot s door. Serials 58 thru 05, 06 & subs w/o Perspective Avionics: The MFD receives an OAT signal from a temperature sensor integral to the magnetometer installed in the RH wing. Serials 06 & subs w/ Perspective Avionics: The air data computer receives OAT signals from a temperature sensor installed in the RH wing. D. Vertical Speed Indicator 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 005 thru 336, 337 thru 4 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 337 thru 4 w/ PFD, 43 thru 05, 06 & subs w/o Perspective Avionics: The PFD processes and displays vertical speed data. Serials 06 & subs w/ Perspective Avionics: The GDC 74A air data computer processes vertical speed data for display on the PFD. E. 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 Page 5 Dec 04 All
MODEL SR0 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 005 thru 336, 337 thru 4 w/o PFD: The airspeed indicator is located in the upper LH portion of the pilot s instrument panel. Serials 337 thru 4 w/ PFD, 43 thru 05, 06 & subs w/o Perspective Avionics: The PFD processes and displays airspeed data. A standby airspeed indicator is located in the LH bolster panel. Serials 06 & subs w/ Perspective Avionics: The GDC 74A air data computer processes airspeed data for display on the PFD. A standby airspeed indicator is located in the LH bolster panel. () Airspeed Indicator - Serials 73 & subs w/ MD30 Standby Attitude Module The optional MD30 Standby Attitude Module is a combined standby airspeed indicator, standby altimeter, and standby attitude 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. 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 GDC 74A air data computer processes airspeed data for display on the PFD. The MD30 Standby Attitude Module is located in the LH bolster panel. F. 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. Serials 005 thru 336, 337 thru 4 w/o PFD: The altimeter is located in the upper mid portion of the instrument panel. Serials 337 thru 4 w/ PFD, 43 thru 05, 06 & subs w/o Perspective Avionics: The PFD processes and displays altitude data. A standby altimeter is located in the LH bolster panel. Serials 06 & subs w/ Perspective Avionics: The GDC 74A air data computer processes altitude data for display on the PFD. A standby altimeter is located in the LH bolster panel. () Altimeter - Serials 73 & subs w/ MD30 Standby Attitude Module The optional MD30 Standby Attitude Module is a combined standby airspeed indicator, standby altimeter, and standby attitude indicator. 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 GDC 74A air data computer processes altitude data for display on the PFD. The MD30 Standby Attitude Module is located in the LH bolster panel. G. Air Data Computer - Serials 06 & subs w/ Perspective Avionics The GDC 74A air data computer, located behind the RH 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. 8 VDC for the standard air data computer is supplied through the 5-amp ADC circuit breaker on Essential Bus. The GDC 74A air data computer 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) All Page 3 5 Dec 04
MODEL SR0. 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 System Plumbing. (Refer to ) Check lines for leaks. Perform System Test - Pitot System Plumbing. (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. 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 ) 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 System Plumbing. (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. Page 4 5 Dec 04 Leaks in static line. Defective instrument. Excessive vibration caused by loose mounting screws. All Check line for obstruction. Blow out lines. (Refer to ) Replace or repair instrument. Tighten mounting screws.
MODEL SR0 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 ) 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 turn 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 System Plumbing. (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. All Page 5 5 Jun 00
MODEL SR0 Serials 06 & subs w/ Perspective Avionics: Trouble Probable Cause Remedy Airspeed, altitude, vertical speed, or ISA not receiving valid data. Software or configuration error. GDC 74A air data computers are offline. Obstruction in pitot-static system. Faulty OAT sensor. Check PFD Alert Window for PFD, MFD or GDC configuration, software or failed data path error messages. Correct any errors before proceeding. Replace GDC 74A configuration module. Verify GDCs are online by checking for a green checkmark next to GDC on MFD Aux System Status page.. If GDC is not online (a Red-X will be present instead of a green check mark), check for wiring/ power faults and GDC connector security.. Replace GDC 74A air data computer. Inspect GDC 74A pitot-static ports and plumbing for blockage. For TAS failure only, replace OAT sensor. OAT and TAS not receiving valid data. Faulty OAT sensor wiring and connectors. Check OAT sensor wiring and connectors for faults or damage. Replace GDC 74A config module and pigtail harness. Faulty OAT sensor. Faulty GDC 74A air data computer. Replace OAT sensor. Replace GDC 74A air data computer. 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 ) Page 6 5 Dec 04 All
MODEL SR0 Trouble Probable Cause Remedy Altimeter indicates high reading. Static system leak. Inspect static system. (Refer to ) Altimeter displays excess scale error. Excessive altitude indicator oscillation. Improper calibration adjustment. Defective instrument. Replace 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 ) 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 ) 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 05-0) All Page 7 5 Dec 04
MODEL SR0 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) Serials 005 thru 885: Remove screws and washers securing pitot tube bracket to wing rib. Remove bracket from airplane. (g) Serials 886 & subs: Remove screws, washers, and nuts securing pitot tube bracket to wing skin. Remove bracket from airplane. () Installation - Pitot Tube Assembly (a) Serials 005 thru 885: Position pitot tube bracket to wing rib and secure with screws and washers. (b) Serials 886 & subs: Position pitot tube bracket to wing skin and secure with screws, washers, and nuts. (c) Slide pitot tube assembly into bracket, connect pitot heat electrical connector, then connect pitot line. (d) Install screws securing pitot tube to bracket. (e) Perform Functional Test - Pitot System Plumbing. (Refer to ) (f) Perform Operational Test - Pitot Heat. (Refer to ) (g) Install left wing tip. (Refer to 57-0) (h) 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) (h) (i) 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. Serials 005 thru 05, 06 & subs w/o Perspective Avionics: Verify PITOT HEAT annunciator light is on. Serials 06 & subs w/ Perspective Avionics: Verify PITOT HEAT caution displays on the PFD. Reset PITOT HEAT circuit breaker. Serials 005 thru 05, 06 & subs w/o Perspective Avionics: Verify PITOT HEAT annunciator light is off. Serials 06 & subs w/ Perspective Avionics: Verify PITOT HEAT caution no longer displays on the PFD. WARNING: Avoid prolonged exposure to heated pitot tube to prevent burns. Page 8 5 Dec 04 (j) (k) (l) 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
MODEL SR0 B. Pitot System Plumbing (See Figure ) () 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) Serials 005 thru 336, 337 thru 4 w/o PFD: Remove glareshield. (Refer to 5-0) (b) Serials 337 thru 4 w/ PFD, 43 & subs: Remove LH kickplate. (Refer to 5-0) (c) 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. CAUTION: Never blow air through the line toward the instruments. To do so will seriously damage the instruments. (d) 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. (e) Perform Functional Test - Pitot System Plumbing. (Refer to ) (f) Serials 005 thru 336, 337 thru 4 w/o PFD: Install glareshield. (Refer to 5-0) (g) Serials 337 thru 4 w/ PFD, 43 & subs: Install LH kickplate. (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 Calibrated Pitot/Static Test Set Model 393 a Aircraft Instrument Simulate pitot air Support Services, Inc. pressure. Round Rock, TX 78664 800-593-096 All Page 9 5 Dec 04
MODEL SR0 Description P/N or Spec. Supplier Purpose 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. (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. Page 0 5 Dec 04 All
MODEL SR0 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 005 thru 705 after SB X-34-, 706 & 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 005 thru 705 after SB X-34-, 706 & 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 System Plumbing. (Refer to ) (f) Close and secure circuit breaker panel. All Page 5 Dec 04
MODEL SR0 D. Static System Plumbing (See Figure ) 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. Serials 706 & subs, Serials 005 thru 705 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 706 & subs, Serials 005 thru 705 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, perform System Test - Static System Plumbing (Refer to ) () System Test - Static System Plumbing - Serials 005 thru 05, 06 & subs w/o Perspective Avionics (a) Open circuit breaker panel to gain access to altitude encoder. (b) Identify and disconnect lower static line at altitude encoder 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. (c) Blow clean, low-pressure air from disconnected line at altitude encoder branch tee to static ports. (d) Connect lower static line at altitude encoder branch tee. (e) Perform Functional Test - Static System Plumbing. (Refer to ) (f) Close and secure circuit breaker panel. () System Test - Static System Plumbing - Serials 06 & subs w/ Perspective Avionics (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. CAUTION: Never blow air through the line toward the instruments. To do so will seriously damage the instruments. (c) 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 ) (e) Install LH kick plate. (Refer to 5-0) Page 5 Dec 04 All
MODEL SR0 (3) Functional Test - Static System Plumbing (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Supplier Purpose Calibrated Pitot/Static Test Set Model 393 a Aircraft Instrument Simulate static air Support Services, Inc. pressure. Round Rock, TX 78664 800-593-096 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 337 thru 4 w/ PFD, 43 & subs: Remove LH kickplate. (Refer to 5-0) CAUTION: Never apply positive pressure with airspeed indicator, vertical speed indicator, MD30 Standby Attitude Module, PFD, or air data computer connected into static system. (g) (h) (i) (j) Serials 005 thru 05, 06 & subs w/o Perspective Avionics: 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. Serials 06 & subs w/ Perspective Avionics and w/o MD30 Standby Attitude Module: Disconnect altimeter, airspeed indicator, air data computer, 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 air data computer. 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. (k) (l) (m) (n) 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. All (o) Perform Functional Test - Pitot System Plumbing. (Refer to ) (p) Perform static leak test procedure. Close pitot and static control valves. Close pitot and static bleed/vent valves. Page 3 5 Dec 04
MODEL SR0 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 337 thru 4 w/ PFD, 43 & subs: 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 4 5 Dec 04 All
MODEL SR0 E. Altitude Encoder - Serials 005 thru 05, 06 & subs w/o Perspective Avionics (See Figure 34-0) () 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 System Plumbing. (Refer to ) (g) Perform Functional Test - Static System Plumbing. (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. Serials 005 thru 05, 06 & subs w/o Perspective Avionics Page 5 5 Dec 04
MODEL SR0 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 6 5 Dec 04 Serials 005 thru 05, 06 & subs w/o Perspective Avionics
MODEL SR0 F. Pitot Mast (See Figure ) () Removal - Pitot Mast (a) Set BAT, BAT, and AVIONICS switches to OFF positions. (b) Pull ENCODER/TRANSPONDER 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. () Installation - Pitot Mast (a) Position pitot mast to bracket and secure with screws. (b) Connect pitot mast fitting to pitot tube fitting. Torque to 80 in-lb (9 Nm). (c) Perform Functional Test - Pitot System Plumbing. (Refer to ) (d) Install wing tip. (Refer to 57-0) (3) Inspection/Check - Pitot Mast (See Figure ) (a) Remove wing tip. (Refer to 57-0) (b) Disconnect pitot mast fitting from pitot tube fitting, then cap off pitot tube. CAUTION: Never blow air through the line toward the instruments. To do so will seriously damage the instruments. (c) (d) 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) (f) (g) (h) 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. 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. 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). CAUTION: Eroded drain holes may result in pressure loss leading to an airspeed reduction of 0.5 percent. (i) 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 ) (k) Connect pitot mast fitting to pitot tube fitting. (l) Perform Functional Test - Pitot System Plumbing. (Refer to ) (m) Install wing tip. (Refer to 57-0) All Page 7 5 Dec 04
MODEL SR0 TYPICAL INSTALLATION 6 5 5 8 INSTRUMENT PANEL 9 7 6 5 3 4 7 5 0 5 7 6 8 6 7 0 4 5 FUSELAGE 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 005 thru 336, 337 thru 4 w/o PFD before SB X-34-. SR0_MM34_08E Figure Pitot-Static System - Serials 005 thru 336, 337 thru 4 w/o PFD before SBX-34- (Sheet of 9) Page 8 5 Dec 04 Serials 005 thru 336, 337 thru 4 w/o PFD before SBX-34-
MODEL SR0 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 7. Nylon Union Tee 8. Altimeter 9. Air Speed Indicator. Altitude Transducer. PFD INSTRUMENT PANEL 5 3 4 7 8 CENTER CONSOLE 7 7 7 7 7 4 5 7 6 9 8 3 9 0 6 3 NOTE Serials 337 thru 4: Tie down on forward location. Serials 43 & subs: Grommet on forward location. Serials 337 thru 4 w/ PFD, 43 thru 63, 634 thru 638 before SB X-34-. SR0_MM34_70D Figure Pitot-Static System - Serials 337 thru 4 w/ PFD, 43 thru 638 before SBX-34- (Sheet of 9) Serials 337 thru 4 w/ PFD, 43 thru 638 before SBX-34- Page 9 5 Dec 04
MODEL SR0 Serials 633, 639 thru 705 before SB X-34-. INSTRUMENT PANEL 3 7 8 7 CENTER CONSOLE 9 5 4 6 7 Serials 706 thru thru 877, 879 thru 885, Serials 005 thru 705 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 633, 639 thru 877, 879 thru 885.. PFD 3. Static Line Sump SR0_MM34_34C Page 0 5 Dec 04 Figure Pitot-Static System - Serials 639 thru 885 (Sheet 3 of 9) Serials 639 thru 885
MODEL SR0 INSTRUMENT PANEL 3 8 CENTER CONSOLE 5 7 7 7 7 7 6 0 9 3 7 8 7 7 6 5 4 7 Serials 886 thru 05, 06 & subs w/o Perspective Avionics. 3 4 3 LEGEND. Pitot Tube. Static Tube 3. Grommet 4. Plug 5. Fitting 6. Tie Down 7. Cable Tie 8. Drain Tube 0. Bushing. Tee 3. Fitting (pipe to flare) 4. Static Port 5. Static Line 7. Nylon Union Tee 8. Altimeter 9. Air Speed Indicator. Altitude Transducer. PFD 3. Static Line Sump SR0_MM34_747A Figure Pitot-Static System - Serials 886 thru 05, 06 & subs w/o Perspective Avionics (Sheet 4 of 9) Serials 886 thru 05, 06 & subs w/o Perspective Avionics Page 5 Dec 04
MODEL SR0 7 6 Serials 06 thru w/ Perspective Avionics. 4 4 7 3 6 8 CENTER CONSOLE 5 7 7 9 3 0 3 4 3 6 7 7 7 NOTE Optional dual ADC installation shown. Tee is positioned at LH CAPS enclosure and centered between rivet holes. 7 4 8 5 6 7 Serials 06 & subs w/ Perspective Avionics and 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 0. Bushing. Tee 3. Fitting (pipe to flare) 4. Static Port 5. Static Line 7. Nylon Union Tee 8. Altimeter 9. Air Speed Indicator 3. Static Line Sump 4. Air Data Computer SR0_MM34_8D Figure Pitot-Static System - Serials 06 & subs w/ Perspective Avionics and w/o MD30 (Sheet 5 of 9) Page 5 Dec 04 Serials 06 & subs w/ Perspective Avionics and w/o MD30
MODEL SR0 ADC # 0 0 ADC # CENTER CONSOLE 9 6 7 5 9 47 3 7 6 0 5 4 9 6 9 7 9 NOTE Optional dual ADC installation shown. Tee is positioned at LH CAPS enclosure and centered between rivet holes. 7 4 8 5 6 9 Serials 73 & subs 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 4. Static Port 9. Static Line Sump 0. Air Data Computer 47. MD30 Standby Attitude Module SR0_MM34_3676 Figure Pitot-Static System - Serials 73 & subs w/ MD30 Standby Attitude Module (Sheet 6 of 9) Serials 73 & subs w/ MD30 Standby Attitude Module Page 3 5 Dec 04
MODEL SR0 3 30 9 5 8 6 7 7 6 3 7 Serials 06 & subs w/ Perspective Avionics. 30 8 CONSOLE ASSEMBLY 5 3 PANEL LIGHTS WIRE HARNESS 6 6 6 7 6 5 8 30 9 7 LED ANGLE BRACKET 7 6 6 3 CONSOLE ASSEMBLY Serials 005 thru 705 before SB X-34-. Serials 706 thru 05, 06 & subs w/o Perspective Avionics. Serials 005 thru 705 after SB X-34-. LEGEND. Static Tube 7. Nylon Union Tee 5. Alternate Static Source Valve 6. Screw 7. Knob 8. Adel Clamp 9. Washer 30. Nut 3. Plug 3. Spiral Wrap SR0_MM34_084G Page 4 5 Dec 04 Figure Pitot-Static System (Sheet 7 of 9) All
MODEL SR0 SKYWATCH DIFFERENTIAL PRESSURE SWITCH 7 7 33 37 7 33 37 7 Serials 005 thru 05 w/ SKYWATCH, 06 & subs w/ SKYWATCH, w/o Perspective Avionics. 37 33 # HOUR METER DIFFERENTIAL PRESSURE SWITCH Serials 005 thru 63, 634 thru 638, after SB X-3-0. 37 33 # HOUR METER DIFFERENTIAL PRESSURE SWITCH 38 Serials 005 thru 336, 337 thru 4 w/o PFD. TO DRAIN 34 39 34 7 34 34 7 34 37 Serials 639 thru 05, 06 & subs w/o Perspective Avionics. 33 36 34 35 34 Serials 337 thru 4 w/ PFD, 43 thru 05, 06 & subs w/o Perspective Avionics. 36 34 TO ALT STATIC SOURCE LEGEND. Pitot Line. Static Line 7. Nylon Union Tee 33. Spring Clip 34. Hose Clamp 35. Nylon Coupling 36. Tubing 37. Hose 38. Mounting Tray 39. Altitude Encoder SR0_MM34_083G All Figure Pitot-Static System (Sheet 8 of 9) Page 5 5 Dec 04
MODEL SR0 40 CONDUIT 44 GROUND STRAP 6 4 6 4 46 4 6 3 30 WING RIB 30 7 3 30 7 WING SKIN 7 7 7 43 43 44 45 45 Serials 878, 886 & subs. Serials 005 thru 877, 879 thru 885. LEGEND. Pitot Line. Elbow 6. Nylon Insert 7. Screw 30. Washer 3. Nut 40. Backing Plate 4. Tygon Tubing 4. Female Tube Connector 43. Bracket, Pitot Mast 44. Extension Tube 45. Pitot Mast 46. Pipe to Flare Fitting SR0_MM34_748A Page 6 5 Dec 04 Figure Pitot-Static System (Sheet 9 of 9) All
MODEL SR0 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 SR0_MM34_374 All Figure Inspection/Check - Pitot Mast Page 7 5 Dec 04
MODEL SR0 G. Vertical Speed Indicator (VSI) - Serials 005 thru 336, 337 thru 4 w/o PFD (See Figure 34-03) () 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 System Plumbing. (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 8 5 Dec 04 Serials 005 thru 336, 337 thru 4 w/o PFD
MODEL SR0 TO ALTERNATE STATIC SOURCE TO ALTIMETER 4 3 INSTRUMENT PANEL 5 6 LEGEND. Vertical Speed Indicator. Tee Connector 3. Static Line 4. Connector 5. Washer 6. Screw Figure 3 VSI Installation - Serials 005 thru 336, 337 thru 4 w/o PFD Serials 005 thru 336, 337 thru 4 w/o PFD Serials 005 thru 336, 337 thru 4 w/o PFD. SR0_MM34_76C Page 9 5 Dec 04
MODEL SR0 H. Altimeter - Serials 005 thru 336, 337 thru 4 w/o PFD (See Figure 4) () 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 System Plumbing. (Refer to ) (f) Perform Functional Test - Static System Plumbing. (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 30 5 Dec 04 (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 005 thru 336, 337 thru 4 w/o PFD
MODEL SR0 (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 005 thru 336, 337 thru 4 w/o PFD Page 3 5 Dec 04
MODEL SR0 I. Altimeter - Serials 337 thru 4 w/ PFD, 43 & subs w/o MD30 Standby Attitude Module (See Figure 4) () 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 System Plumbing. (Refer to ) (f) Perform Functional Test - Static System Plumbing. (Refer to ) (g) Perform Functional Test - Altimeter. (Refer to ) (h) Serials 005 thru 05, 06 & subs w/o Perspective Avionics: 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) Serials 005 thru 05, 06 & subs w/o Perspective Avionics: On GNS 430, rotate [C] knob clockwise for COM/GPS power and volume. (c) Serials 06 & subs w/ Perspective Avionics: On audio control panel, select COM audio selector button. (d) Using COM, listen to ATIS. Obtain current altimeter barometric pressure setting. (e) Set barometric pressure in altimeter window. (f) Verify correct altitude is indicated. (g) 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. Page 3 5 Dec 04 Serials 337 thru 4 w/ PFD, 43 & subs w/o MD30 Standby Attitude Module