(b) Pitot static probe adapter - P/N PSS22300-3-4-4, Allen Aircraft Radio Inc., 2050 Touhy Avenue, Elk Grove Village, Illinois 60007.
(4) Gages
(a)
Pitot system gage - 0 to 5 inches of mercury with accuracy of + 0.16 (readable to + 0.03) inches of mercury or + 5 (readable to + 1) knots.
(b)
Static system gage - 0 to 20 inches of mercury with accuracy of 0.10 (readable to + 0.01) inch mercury or + 200 (readable to + 20) feet.
C. Prepare to Test Pitot Static System
(1)
The autopilot system should be off during this test.
(2)
Tests should be run with drain caps connected to drain fittings.
NOTE: To test poppet valves in drains, run test with drain caps off drain fittings. Leakage test must then be rerun with drain caps connected.
(3)
Pitot static probe heaters are to remain off during this test.
(4)
Open FLAP LOAD RELIEF circuit breaker on P6 panel.
WARNING: FAILURE TO OPEN TE FLAP LOAD RELIEF CIRCUIT BREAKER MAY RESULT IN FLAP MOVEMENT AND INJURY TO PERSONNEL.
(5)
Connect test equipment (Fig. 501) as follows:
(a)
Connect static probe adapters and cutoff valves to those static systems to be tested. Connect an external altimeter or pressure indicator between static cutoff valve and airplane system.
(b)
Connect static control valve between cutoff valves and static test unit.
(c)
Connect pitot probe adapters and cutoff valves to those pitot systems to be tested. Connect an external airspeed indicator or pressure indicator between the appropriate cutoff valve and the airplane system.
(d)
Connect pitot control valve between cutoff valves and pitot test unit.
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D. Test Pitot Systems
(1) Test captain's pitot system for leakage, observing the cautions in steps A.(3) and A.(4) above.
NOTE: Accuracy of reading and recording pressure should be + 0.03 inches of mercury or + 1 knot.
(a)
Temporarily seal pressure chamber drain hole in captain's pitot static probe (upper left probe). Connect air pressure supply to pitot static probe (pitot pressure portion).
(b)
For low-range leakage test: 1) Apply pressure of 250 knots on captain's airspeed/mach indicator or test indicator.
2) After system has stabilized, cut off pressure between airplane system and pressure source. Read and record airspeed/mach indicator or test indicator reading.
3) Wait 1 minute. Check that pressure does not decrease more than 2.5 knots.
(c) For full-range leakage test: 1) Apply pressure of 4.53 (+ 0.16) inches of mercury (gage) or 300 (+ 5) knots on captain's airspeed/mach indicator or pressure indicator. 2) After system has stabilized, cut off pressure between airplane system and pressure source. Read and record airspeed/mach indicator or test indicator.
3) Wait 1 minute. Pressure should not decrease more than 0.16 inches of mercury or 5 knots of airspeed.
(2)
Test first officer's pitot system for leakage.
(a) Repeat steps D.(l)(a) through (c) above on the upper right pitot static probe.
(3)
Test auxiliary No. 1 or No. 2 pitot system for leakage.
(a) Repeat steps D.(l)(a) through (c) on lower right probe (No. 1 system) or lower left probe (No. 2 system).
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E. Test Static Systems
(1)
Temporarily seal all static ports to which test adapters have not been applied. Method of sealing should not extend into static ports or deform or alter surface in the area when seals are removed.
(2)
Place captain's and first officer's static source selector valves in NORMAL position.
CAUTION: PITOT PRESSURE SHOULD ALWAYS EQUAL OR EXCEED STATIC LINE PRESSURE AND DIFFERENCE (DIFFERENTIAL PRESSURE) SHOULD NOT EXCEED 10.00 INCHES OF MERCURY. DIFFERENTIAL PRESSURE DESCRIBED ABOVE SHOULD NOT FALL BELOW ZERO.
NOTE: Accuracy of reading and recording vacuum pressure or altimeter should be +
0.01 inches of mercury or + 20 feet of altitude respectively.
(3) Test captain's static system for leakage observing cautions in steps A.(3) through A.(6).
(a)
Place all static cutoff valves in open position.
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