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34-11-0 Page 206 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Jun 20/85
PITOT STATIC SYSTEM -ADJUSTMENT/TEST
EFFECTIVITY
GJ ALL EXCEPT B-2524
1. Pitot Static System Test
A. General
(1)
Make sure that the ATC transponders are not in an altitude reporting mode.
WARNING: MAKE SURE THAT THE ATC TRANSPONDERS ARE NOT IN AN ALTITUDE REPORTING MODE WHEN YOU SIMULATE ALTITUDE. IF YOU DO NOT, YOU CAN ACCIDENTALLY CAUSE FALSE TCAS TARGETS.
(2)
The low-range leakage test should be performed when a connection in the pitot static system has been broken to permit the replacement of instrument, hoses or tubing. Quick disconnects, when reconnected, do not require a leak check. A visual check of the quick disconnect for full mating and to assure connection is locked and in the sealed position is required. If after an apparent satisfactory low-range test, the behavior of the instruments is still such as to suggest leakage, a full-range test should be performed.
(3)
The full-range test must be performed after flushing procedure or each major airframe overhaul. Flushing before every system leakage check is not normally required. Both flushing to remove foreign matter and system leakage checks may be carried out at the same time when deemed necessary.
CAUTION: THE FOLLOWING STEPS ARE REQUIRED TO PREVENT INSTRUMENT DAMAGE, AND TO ENSURE VALID READINGS.
(4)
Any application or release of vacuum or pressure should be made at a rate of climb or descent less than 5000 feet per minute for the static system and 300 knots per minute for the pitot system. (Appropriate gage saver restrictors should be used.)
(5)
Pressure in pitot lines should always be greater than, or equal to pressure in static lines. Differential pressure should never exceed 10.00 inches of mercury.
(6)
The absolute pressure applied to the static system should never exceed the ambient absolute pressure when any instrument is connected to the static system.
(7)
The captain's, first officer's and alternate static systems must be exposed to the same absolute pressure conditions simultaneously during any leakage test unless otherwise instructed.
B. Equipment and Materials
(1)
Dry air pressure source - 0-5 inches of mercury
(2)
Vacuum source - 0-20 inches of mercury
(3)
Adapters
(a) Static Port Test Adapter Assembly - F72823-23, or F72823-40
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Feb 20/93 34-11-0 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
T53515
Pitot Static System Test Connections 599
34-11-0 Figure 501 Sep 20/82
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(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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Feb 20/85 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-11-0 Page 503
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