oil. 3) Connect the tube tee nut (28) to the forward tee connection
of the drain tube. 4) Connect the tube nut to the union (34). 5) Lubricate the threads of the screw (31) with engine oil. 6) Attach the clamp (30) on the drain tube with the screw
(31), nut (32), and washer (33). a) Tighten the screw. 7) Tighten the tube nuts for the drain tube (28).
(o)
Attach the drain hose (13) to the top union (14) on the actuator (7). 1) Tighten the tube nut.
(p)
Lubricate the threads of the lower adapter (9) on the actuator
(7) with the antigalling compound.
(q)
Connect the servo fuel supply tube (10) to the lower adapter
(9) on the actuator (7). 1) Tighten the tube nut to 225-250 pound-inches (25.4-28.2 newton-meters).
2) Safety the tube nut with lockwire or safety cable and safety cable ferrule.
(r)
Lubricate the threads of the center adapter (12) with the antigalling compound.
(s)
Connect the servo fuel return tube (11) to the center adapter (12) on the actuator (7). 1) Tighten the tube nut to 200-225 pound-inches (22.6-25.4
newton-meters). 2) Safety the tube nut with lockwire or safety cable and safety cable ferrule.
H. Return the Aircraft to Its Usual Condition.
S 414-055-N00
WARNING: OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU CLOSE THE
_______ THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
(1) Close the right thrust reverser (AMM 78-31-00/201).
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S 414-049-N00
(2) Close the right core cowl panel (AMM 71-11-06/201).
S 414-050-N00
(3) Close the right fan cowl panel (AMM 71-11-04/201).
S 444-051-N00
(4) Do the activation procedure for the thrust reverser (AMM 78-31-00/201).
S 864-038-N00
(5) For the applicable engine, remove the DO-NOT-CLOSE tags and close these circuit breakers as follows:
(a) P6 Main Power Distribution Panel 1) 6G1 FUEL SHUTOFF VALVE ENG 1 2) 6G15 SCU ALT PWR ENG 1 3) 6G23 ENG SCU 1 4) 6G2 FUEL SHUTOFF VALVE ENG 2 5) 6G16 SCU ALT PWR ENG 2 6) 6G24 ENG SCU 2 7) 6G3 FUEL SHUTOFF VALVE ENG 3 8) 6G17 SCU ALT PWR ENG 3 9) 6G25 ENG SCU 3 10) 6G4 FUEL SHUTOFF VALVE ENG 4 11) 6G18 SCU ALT PWR ENG 4 12) 6G26 ENG SCU 4
S 864-039-N00
(6) Remove the DO-NOT-OPERATE tag from the FUEL CONTROL switch.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
COMPRESSOR BLEED CONTROL SYSTEM - DESCRIPTION AND OPERATION
___________________________________________________________
1. General
_______
A. The stability of the compressor is improved during starting, transient, and reverse thrust operation by bleeding air off from the 4th-stage of the low pressure compressor (LPC) and the 9th-stage of the high pressure compressor (HPC) to the fan airstream.
B. The compressor bleed control system includes the 2.5 and 2.9 bleed systems.
C. The 2.5 bleed system includes the 2.5 bleed valve and the 2.5 bleed valve actuator.
D. The 2.9 bleed system includes two 2.9 bleed valves, a 2.9 bleed valve solenoid, and a stability bleed pneumatic relay valve.
2. 2.5 Bleed Valve
_______________
A. The 2.5 bleed valve is a 360 degree, translating ring type valve.
B. The 2.5 bleed valve is found in the fan exit case and is moved by the cam and roller linkage of the 2.5 bleed valve actuator.
C. The 2.5 bleed valve, when opened, vents 4th-stage compressor airflow through 14 bleed ducts, found circumferentially around the fan exit inner case, into the fan airstream. When the valve is opened, it also functions as a dirt separator by diverting dirt-laden air from the HPC.
D. The fully open valve also permits borescope access to the 4th-stage compressor blades through the 14 bleed ducts.
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