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Flight Environmental Systems CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22 FLIGHT ENVIRONMENTAL SYSTEMS 1. DESCRIPTION This section covers that portion of the system which senses environmental conditions and uses the data to influence navigation of the airplane. This includes pitot-static, Vertical Speed Indicator (VSI), altimeter, air- speed indicator, and Outside Air Temperature (OAT) gage/clock. (See Figure 34-001) The pitot system utilizes an “L” shaped mast with integral pitot tube and heater located on the LH wing just inboard of the wing tip to sense impact or ram air pressure. The pitot mast utilizes an electrical heating ele- ment to prevent ice from blocking ram air. Pitot heat is controlled by a switch located in the center of the bolster switch panel. An amber PITOT HEAT light on the annunciation panel will illuminate if the PITOT HEAT switch is set to ON position and the pitot heater is not using power. The pitot heat system operates on 28 VDC supplied through the 7.5-amp PITOT HEAT/COOLING FAN cir- cuit breaker on the Non-Essential Bus. The PITOT HEAT warning light operates on 28 VDC supplied through the 2-amp ANNUN circuit breaker on the Essential Bus. The normal static system utilizes two ports, a static source water trap, an alternate static source selector valve, and the necessary plumbing to provide static air pressure sensing for the airspeed indicator, vertical speed indicator, altimeter, altitude encoder, and altitude transducer. Serials 0435 thru 0820 w/ PFD, 0821 & subs: The primary flight display (PFD) receives static air pressure data through the static system. The normal static ports are located on the LH and RH sides of the fuselage behind the aft cabin bulkhead. The static line runs from these ports to a tee connector mounted on the aft cabin bulkhead to a water trap located directly forward of the pitot system water trap. Serials 0002 thru 2036, 2038 thru 2042 after SB 2X-34-22, 2037, 2043 & subs: A static line sump mounted directly to the ports provides increased resistance against forced water intrusion. The alternate static source valve, located on the lower LH side of the console, provides an alternate source of static air pressure from inside the cabin in the event the normal static sources are plugged. Note: The alternate static source is to be used when the normal system is inoperative or malfunc- tioning. When alternate static air is used, instrument readings will vary from normal readings due to static air being obtained from the cabin. Refer to the Pilot’s Operating Handbook for flight operation using alternate static air. Serials 0002 thru 0434, 0435 thru 0820 w/o PFD: The Outside Air Temperature (OAT) gage/clock is located in the upper LH portion of the pilot’s instrument panel. The OAT gage is integral to the clock. The clock provides Universal Time (UT), Local Time (LT), Flight Time (FT) with alarm, Elapsed Time (ET), Out- side Air Temperature in °C or °F, and Voltmeter functions. All features and functions are selectable from control buttons on the clock face. The clock receives the OAT signal from a temperature sensor installed immediately forward of the pilots door. The clock operates on 28 VDC supplied through a 5-amp fuse con- nected to the airplane primary bus in the Master Control Unit (MCU). A replaceable AA battery is installed to provide up to three years battery back up. Serials 0435 thru 0820 w/ PFD, 0821 & subs: The PFD receives an OAT signal from a temperature sensor integral to the magnetometer installed in the RH wing. Serials 0002 thru 1601, 1603 thru 1643, 1645 thru 1662 w/ EMax Engine Monitoring: The Multifunction Display (MFD) receives an OAT signal from a temperature sensor installed immediately forward of the co- pilot’s door. Serials 1602, 1644, 1663 & subs: The MFD receives an OAT signal from a temperature sensor integral to the magnetometer installed in the RH wing. EFFECTIVITY: All 34-10 Page 1 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22 The Vertical Speed Indicator (VSI) measures the rate of change in static pressure when the airplane is climbing or descending. By means of a pointer, it indicates the rate of descent or ascent of the airplane in feet per minute. Serials 0002 thru 0434, 0435 thru 0820 w/o PFD: The VSI is located in the lower RH portion of the pilot’s instrument panel. A zero adjust screw is located on the front of the VSI in the lower LH corner to allow for pointer adjustment. Serials 0435 thru 0820 w/ PFD, 0821 & subs: The VSI is on the PFD with no standby indicator. The airspeed indicator is a differential air pressure gage which measures the difference between ram air pressure and static air pressure to indicate the speed of the airplane. An adjustment knob allows the pilot to correlate outside air temperature with pressure altitude, thereby allowing the airspeed indicator to show both true and indicated airspeeds. A moveable pointer and a fixed dial with the 0 index at the 12 o’clock position indicates airspeed. Range of the instrument is 0 to 220 knots. Serials 0002 thru 0434, 0435 thru 0820 w/o PFD: The airspeed indicator is located in the upper LH portion of the pilot’s instrument panel. Serials 0435 thru 0820 w/ PFD, 0821 & subs: The primary airspeed indicator is on the PFD. The standby airspeed indicator is located in the LH bolster panel. The altimeter converts static pressure into a visual indication of airplane altitude above sea level. Pointers on the instrument dial indicate altitude in increments of 100, 1000, and 10,000 feet, with a range of -1000 to 20,000 feet. Serials 0002 thru 0434, 0435 thru 0820 w/o PFD: The altimeter is located in the upper mid portion of the instrument panel. Serials 0435 thru 0820 w/ PFD, 0821 & subs: The primary altimeter is on the PFD. The standby altimeter is located in the LH bolster panel. EFFECTIVITY: 34-10 All Page 2 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22 2. TROUBLESHOOTING Trouble - Pitot-Static Probable Cause Remedy Erroneous altimeter or vertical Leaks in static and/or pitot line. Check lines for leaks. Perform speed indication. System Test - Static Plumbing System. (Refer to 34-10) Check lines for leaks. Perform System Test - Pitot Plumbing Sys- tem. (Refer to 34-10) Incorrect or sluggish response on Leaks or obstruction in static line. Repair or replace line. Remove all three pitot-static instruments. obstruction. Pitot tube does not heat or melt PITOT HEAT switch is set to OFF Set PITOT HEAT switch to ON ice. position. position. Pitot tube does not heat or melt Circuit breaker out. Reset circuit breaker. ice. Pitot Light ON. Break in wiring. Test and repair wiring. Insufficient current. Check current drain of element. Heating element burned out. Replace element. Low or sluggish airspeed indica- Pitot tube deformed. Repair or replace damaged com- tion. Normal altimeter and vertical Leak or obstruction in pitot line. ponent. speed indication. Trouble - Vertical Speed Ind. Probable Cause Remedy Pointer indicates erroneous data. Moisture in static traps and/or Check traps and sump for mois- sump. ture. Blow out lines. Moisture in static line. Check lines for moisture. Perform System Test - Static Plumbing System. (Refer to 34-10) Pointer does not set on zero. Leaking or ruptured diaphragm. Substitute known-good indicator and check reading. Replace or repair instrument. Pointer fails to respond. Obstruction in static line. Check line for obstruction. Blow out lines. (Refer to 34-10) Pointer oscillates or fails to Leaks in static line. Check line for obstruction. Blow respond. out lines. (Refer to 34-10) Defective instrument. Replace or repair instrument. Excessive vibration caused by Tighten mounting screws. loose mounting screws. EFFECTIVITY: All 34-10 Page 3 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22 Trouble - Altimeter Probable Cause Remedy Pointer indicates erroneous data. Moisture in static traps and/or Check traps and sump for mois- sump. ture. Blow out lines. Moisture in static line. Check lines for moisture. Perform System Test - Static Plumbing System. (Refer to 34-10) Cracked or loose cover glass. Excessive vibration caused by Tighten mounting screws. loose mounting screws. High reading. Static system leak. Inspect static system. (Refer to 34-10) Excess scale error. Improper calibration adjustment. Replace instrument. Excessive pointer oscillation. Defective instrument. Replace or repair instrument. Difficult to rotate setting knob. Wrong or lack of lubrication. Replace or repair instrument. Trouble - Airspeed Indicator Probable Cause Remedy Pointer fails to respond or indi- Leak in instrument case. Replace or repair instrument. cates improperly. Obstruction in pitot line. Check line for obstruction. Blow out lines. (Refer to 34-10) Incorrect indication or pointer Alternate static source valve open. Close for normal operation. oscillates. Moisture in static traps and/or Check traps and sump for mois- sump. ture. Blow out lines. Moisture in static line. Check lines for moisture. Perform System Test - Static Plumbing System. (Refer to 34-10) Leak in pitot or static lines. Repair or replace damaged lines. Tighten connections. Leaking or ruptured diaphragm. Substitute known-good indicator and check reading. Replace or repair instrument. Pointer vibrates. Excessive vibration caused by Tighten mounting screws. loose mounting screws. Excessive pitot tube vibration. Tighten clamps and connections. EFFECTIVITY: 34-10 All Page 4 15 Apr 2007 CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22 3. MAINTENANCE PRACTICES A. Pitot Tube Assembly (See Figure 34-101) (1) Removal - Pitot Tube Assembly (a) Set BAT 1, BAT 2, and AVIONICS switches to OFF positions. (b) Pull PITOT HEAT circuit breaker. (c) Remove left wing tip. (Refer to 57-20) (d) Identify and disconnect pitot line at low point on connector projecting from top of pitot bracket.
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