S 865-061
(11)
Remove the DO-NOT-CLOSE tags and close these circuit breakers:
(a) P6 Main Power Distribution Panel
1) 6D33 PROBE HEAT AUX PITOT R
2) 6E01 PRIM T/E FLAP CONT AC
3) 6E02 PRIM T/E FLAP CONT DC
TASK 34-11-00-795-161
7. The Captain's Static System Leak Test (Full-Range)
__________________________________________________
A. Standard Tools and Equipment
(1) Pneumatic Test Set
(a) Vacuum source, 10 to 30 inches of mercury (absolute)
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(2)
Gages
(a) Static system test gage - required to indicate 10 to 30 inches of mercury (absolute) with accuracy of |0.1 (readable to |0.01) inch of mercury or |200 (readable to |20) feet.
(3)
Flow restrictors, control valves, cutoff valves, and pressure tape as required.
B. References
(1) 34-11-01/601, Pitot-Static Probe
C. Access
(1) Location Zone
115 Area Between Nose Gear Well and Fuselage, LH
116 Area Between Nose Gear Well and Fuselage, RH
117 Electrical and Electronics Compartment, LH
D. Procedure
S 865-271
WARNING: MAKE SURE THAT YOU DO NOT APPLY ELECTRICAL POWER TO THE FLIGHT
_______ CONTROLS. FLIGHT CONTROL SURFACES CAN MOVE AUTOMATICALLY WHEN YOU PRESSURIZE THE PITOT-STATIC SYSTEM. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
CAUTION: MAKE SURE THAT YOU DO NOT APPLY ELECTRICAL POWER TO THE
_______ PITOT-STATIC PROBE HEATERS. YOU CAN CAUSE DAMAGE TO THE PITOT-STATIC PROBES.
(1) Open these circuit breakers and attach DO-NOT-CLOSE tags:
(a) P6 Main Power Distribution Panel
1) 6E01 PRIM T/E FLAP CONT AC
2) 6E02 PRIM T/E FLAP CONT DC
3) 6D30 PROBE HEAT PITOT L
4) 6D33 PROBE HEAT AUX PITOT R
S 865-163
CAUTION:_______DISCONNECT THE AIR DATA COMPUTER FROM THE STATIC SYSTEM. YOU CAN CAUSE DAMAGE TO THE AIR DATA COMPUTER.
(2) Disconnect the captain's static system from the L-ADC.
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S 865-531
WARNING:_______ MAKE SURE THAT THE PROBE HEAT IS NOT ON. YOU CAN CAUSE INJURY
TO PERSONS.
CAUTION:_______ DO NOT EXTEND THE SEALS INTO THE STATIC PORTS. YOU CAN CAUSE
DAMAGE TO THE SURFACE IN THE AREA WHEN YOU REMOVE THE SEALS.
(3) Seal these locations with vinyl adhesive tape:
(a)
The forward static ports (S1) in the upper left pitot-static probe
(b)
The aft static ports (S2) in the lower right pitot-static probe.
S 865-165
(4) Connect the pneumatic test set to the captain's static system test fitting.
(a)
Connect the static (vacuum) source in the pneumatic test unit through the static control valve to the static cutoff valve.
(b)
Connect the quick-disconnect test fitting of the captain's static system to the static cutoff valve through the test gage and flow restrictor.
NOTE: You will find the test fitting on the left side of the
____ airplane above the pitot-static system drains at STA
400.
(c) Open the static cutoff valve.
S 865-166
CAUTION: DISCONNECT THE LEFT AIR DATA COMPUTER FROM THE STATIC SYSTEM.
_______ YOU CAN CAUSE DAMAGE TO THE AIR DATA COMPUTER.
(5) Do a leak test of the captain's static system (full-range).
(a) Apply pressure to the captain's static system equivalent to 25,000 |200 feet of altitude (11.10 |0.10 in. Hg absolute).
CAUTION: HOLD THE VACUUM, AS AN ALTERNATIVE, BEHIND THE CUTOFF
_______ VALVE DURING THE CUTOFF TIME. YOU CAN CAUSE DAMAGE TO THE EQUIPMENT WHEN YOU OPEN THE CUTOFF VALVE WITHOUT THE VACUUM.
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本文链接地址：747-400 AMM 飞机维护手册 导航 NAVIGATION 1(46)
