*[1] Defines the maximum allowable differences between electric altimeters.
*[2] Defines the maximum allowable differences between the electric and pneumatic altimeters.
*[3] In proceeding from test point to test point, the captain’s and first officer’s electric vertical speed
indicators should not differ more than 150 feet. *[4] Maximum allowable differences between mach indicators in 0.012 mach. *[5] Maximum allowable differences between airspeed indicators is 3 knots.
Scale Error Test Chart 5C8
34-12-01Page 508 Figure 503 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/93
5) Ensure static source selector valve on captain's static system is in NORMAL position and that altimeter warning flags are not in view.
6) Apply pressure to airplane pitot static systems to point 1 in Fig. 503. Check that altimeter, vertical speed and mach/airspeed readings are within tolerance shown. Use head correction as necessary.
7) Repeat step 6) for test points 2 thru 4 of Fig. 503.
(4)
Test Air Data Pressure Instrument System for Leakage
(a)
Perform leakage test on each pitot static system: captain's, first officer's, and auxiliary. Apply vacuum of 22,500 +200 feet altitude to static system and pressure of 300 knots equivalent airspeed to pitot system. Check that leakage rate does not exceed 400 feet per minute and 5 knots per minute respectively.
(b)
Reconnect cabin altimeter and differential pressure indicator to auxiliary static pressure system.
(5)
Restore Air Data Pressure Instrument and Pitot Static Systems to Normal
(a)
Remove external hoses and static port seals, ensuring that no deposit or roughness exists in or about static ports.
(b)
Ensure that flight recorder is returned to normal operating configuration.
(c)
If no longer required, remove electrical power from airplane.
567
Jun 20/90 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-12-01 Page 509
AIR DATA COMPUTER-REMOVAL/INSTALLATION
1. Remove Air Data Computer
CAUTION: TO AVOID COMPUTER DAMAGE, PITOT AND STATIC SYSTEM PRESSURES MUST BE AT AMBIENT BEFORE PROCEEDING.
TO AVOID ELECTRIC FLIGHT RECORDER DAMAGE, FLIGHT RECORDER CIRCUIT BREAKERS MUST BE OPENED BEFORE PROCEEDING.
A. Open air data computer circuit breakers on panel P6 or P18.
B. Disconnect pitot and static pneumatic hoses from front panel.
C. Loosen cam-lock handles and remove computer.
2. Install Air Data Computer
A. Insert computer into case being careful to avoid stress and/or damage to electrical connectors on rear chassis panel.
B. Tighten cam-lock handles.
CAUTION: TO AVOID COMPUTER DAMAGE, PITOT AND STATIC SYSTEM PRESSURES MUST BE AT AMBIENT BEFORE PROCEEDING.
C. Connect pitot and static system pneumatic hoses to front panel.
D. Close air data computer circuit breakers on panel P6 or P18.
E. Make sure the hose connections are locked in the sealed position.
3. Test Air Data Computer
A. Provide electrical power.
B. The following steps list all self-tests. Perform those steps for self-test readout available.
NOTE: TEST VALID WHEN LIT light should come on and remain on while push-to-test switch is pressed. Switch must be held for approximately one-half minute for the FUNCTION switch position to allow instruments to stabilize. For other switch positions, light should come on in approximately two seconds.
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