71-71-00
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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S 412-016-N00
(10)
Close the core cowl panels (AMM 71-11-06/201).
S 412-017-N00
(11)
Close the fan cowl panels (AMM 71-11-04/201).
S 442-018-N00
(12)
Do the activation procedure for the thrust reversers (AMM 78-31-00/201).
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71-71-00
ALL ú ú N01 Page 206 ú Jun 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
ENGINE VENTS AND DRAINS - INSPECTION/CHECK
__________________________________________
1. General
_______
A. This procedure has two tasks. One task is to examine the engine drains for leakage. The other task is to examine the strut drains for heavy deposits.
B. There are nine fittings with caps on them in the front drain system. These fittings are used as fluid traps. These fluid traps are used to isolate the sources of the leakage when fluids drain into the drain collector. This procedure has the leakage limits and the steps to correct a leakage that is not in the specified limits.
C. The engine drains are in two locations on the engine:
(1)
There is a group of drains at the drain collector on the bottom, center of the engine below the gearbox.
(2)
There is one drain on the aft, center of the engine.
D.
The fluid traps on the drains help you find the component that has the leakage. A schematic shows where the traps are located.
E.
After you find which component leaks, you will run the engine to find how much leakage there is. The leakage will drain into the drain collector and then into the fluid collector for the engine drain. This tube holds approximately 10 cc of fluid. The maximum permitted leakage for a component is 1.0 cc/min. The fluid collector tube holds sufficient fluid to do this check.
TASK 71-71-00-206-001-N00
2. Examine the Engine Vents and Drains
___________________________________
A. References
(1)
AMM 24-11-01/401, Integrated Drive Generator
(2)
AMM 24-11-15/401, IDG Air/Oil Heat Exchanger Valve
(3)
AMM 29-11-00/601, Main Hydraulic Supply Systems
(4)
AMM 29-11-05/401, Engine Driven Pump
(5)
AMM 71-11-04/201, Fan Cowl Panel
(6)
AMM 71-11-06/201, Core Cowl Panel
(7)
AMM 72-61-06/401, Accessory Drive Seals
(8)
AMM 73-11-01/401, Fuel Pump
(9)
AMM 73-11-03/401, Fuel Pressurizing and Drain (P & D) Valve
(10)
AMM 73-21-08/401, Electronic Engine Control (EEC) Generator
(11)
AMM 75-31-02/401, Stator Vane Actuator
(12)
AMM 75-32-01/401, 2.5 Bleed Valve Actuator
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71-71-00
ALL ú ú N01 Page 601 ú Jun 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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(13)
AMM 78-31-00/201, Thrust Reverser System
(14)
AMM 79-21-01/401, Engine Fuel/Oil Cooler
(15)
AMM 80-11-01/401, Pneumatic Starter
B.
Access
(1) 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：747-400 AMM 飞机维护手册 动力装置 POWER PLANT 2(119)
