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(9)
Drain for the Air/Oil Heat Exchanger Valve and the Actuator for the
2.5 Bleed Valve
(a) The section of the drain for the air/oil heat exchanger valve and the actuator for the 2.5 bleed valve has a fitting with a cap. This fitting is used as a fluid trap to isolate the source of the leakage.
B.
The rear drain system includes the drains that follow.
(1)
Oil Tank Scupper Drain
(a) This drain goes out through the lower side of the left core cowl panel.
C.
Vents
(1)
The thermal relief vent for the IDG lets air out to the rear of the main drain collector.
D.
Drain Collector
(1)
All ends of the drains are attached to a drain collector which is attached to the bottom of the main gearbox. The drain fluids then go out of an overboard drain line through the main overboard drain port in the right thrust reverser.
(2)
Two tubes for the overboard drain fluid collector, with a drain valve on each overboard drain line, are used as a fluid trap to find if leakage has occured in the forward drain system. The forward collector collects leakage from the strut and the rear connector collects leakage from the engine.
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ENGINE VENTS AND DRAINS - MAINTENANCE PRACTICES
_______________________________________________
1. General
_______
A. This procedure gives the instructions to clean the engine drain lines. You can do this task when you get access to the drain line during the other maintenance procedure.
B. Refer to AMM 54-53-00/201 to make the strut drain lines clear.
C. You can get an access to the engine drain lines when you open the thrust reversers.
D. For this procedure, the component, accessory drive pad, or the drain shroud (where a drain line starts) will be referred to as a source.
TASK 71-71-00-102-001-N00
2. Clean the Engine Drain Lines (Fig. 201)
____________________________
A. Standard Tools and Equipment
(1)
Regulated air pressure supply, hose and nozzle
(2)
Plugs for 3/8, 1/2, and 3/4 inch drain lines
B.
References
(1)
AMM 71-11-04/201, Fan Cowl Panels
(2)
AMM 71-11-06/201, Core Cowl Panels
(3)
AMM 78-31-00/201, Thrust Reverser System
C.
Access
(1)
Location Zone
412 Engine 1
422 Engine 2
432 Engine 3
442 Engine 4
(2)
Access Panel
415 and 416 Thrust Reverser Half - Engine 1
425 and 426 Thrust Reverser Half - Engine 2
435 and 436 Thrust Reverser Half - Engine 3
445 and 446 Thrust Reverser Half - Engine 4
D.
Procedure
(1)
Open the fan cowl panels (AMM 71-11-04/201).
S 012-011-N00
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////////////////////////A / PW4000 SERIES /747-400 / ENGINES/MAINTENANCE MANUAL ////////////////////////
S 042-012-N00
WARNING:_______ DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT THE
OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF
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本文鏈接地址：747-400 AMM 飛機維護手冊 動力裝置 POWER PLANT 2(117)
