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时间:2011-04-16 09:58来源:蓝天飞行翻译 作者:航空
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
TEST NO. 5 - OIL SYSTEM STATIC LEAK TEST
________________________________________
 (2)  
Access Panels
 415 Left Thrust Reverser Half - Engine 1
 416 Right Thrust Reverser Half - Engine 1
 425 Left Thrust Reverser Half - Engine 2
 426 Right Thrust Reverser Half - Engine 2
 435 Left Thrust Reverser Half - Engine 3
 436 Right Thrust Reverser Half - Engine 3
 445 Left Thrust Reverser Half - Engine 4
 446 Right Thrust Reverser Half - Engine 4


 G.
Procedure


 S 015-059-N00
 (1)  If it is not done, open the thrust reverser with the steps that follow:
 (a)  Open the fan cowl panel (AMM 71-11-04/201).
 WARNING: DO THE THRUST REVERSER DEACTIVATION PROCEDURE TO PREVENT
_______ THE OPERATION OF THE THRUST REVERSER. THE ACCIDENTAL OPERATION OF THE THRUST REVERSER CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.
 (b)  
Do this procedure: Thrust Reverser Deactivation for Ground Maintenance (AMM 78-31-00/201).

 (c)  
Open the core cowl panel (AMM 71-11-06/201).


 WARNING: OBEY THE INSTRUCTIONS IN AMM 78-31-00/201 WHEN YOU OPEN
_______ THE THRUST REVERSERS. IF YOU DO NOT OBEY THE INSTRUCTIONS, INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR.
 (d)  Open the thrust reverser (AMM 78-31-00/201).
 S 485-061-N00
 (2)  
Use the hose clamp to attach the tube end of the PWA 85700 adapter into the end of the deoiler outlet tube (Fig. 504, View A).

 (3)
Attach the plug end of the adapter to an external air supply.


 S 485-062-N00
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 71-00-00
 ALL  ú ú N04 Page 531 ú Oct 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / PW4000 SERIES /747-400 / ENGINES /MAINTENANCE MANUAL ////////////////////////
SEE  A 
DRAIN 
COLLECTOR  OIL TANK 
SEE  B  (REF) 

DEOILER
OUTLET TUBE
FWD
OIL TANK SCUPPER DRAIN (REF)
A
DRAIN FOR THE AIR/OIL
THERMAL RELIEF HEAT EXCHANGER VALVE
VENT FOR THE IDG AND 2.5 BLEED VALVE ACTUATOR
STRUT DRAIN
OIL SEAL DRAIN FOR DRAIN FOR THE FUEL
THE STARTER DRIVE PUMP DRIVE OIL SEAL
OIL SEAL DRAIN DRAIN FOR THE FUEL/OIL COOLER, BYPASS
FOR THE EEC VALVE OF THE FUEL/OIL COOLER, AND THEOIL SEALALTERNATOR DRIVE FUEL/OIL HEAT EXCHANGER OF THE IDGDRAIN FOR THE IDG DRIVE DRAIN FOR THE AIR SHUTOFF VALVE OF
OIL SEAL DRAIN THE TCC, ACTUATOR OF THE VARIABLE
FOR THE HYDRAULIC STATOR VANE, AND THE VALVE FOR THE
PUMP DRIVE AIR/OIL HEAT EXCHANGER OF THE IDGFWD
DRAIN COLLECTOR B
Oil System Static Leak Test Port Locations Figure 504
G58760
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
 71-00-00
 ALL  ú ú N04 Page 532 ú Jun 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
TEST NO. 5 - OIL SYSTEM STATIC LEAK TEST
________________________________________
 S 865-058-N00
 CAUTION: DO NOT SUPPLY MORE THAN 10 PSIG (68.9 KPA) PRESSURE OR 325°F
_______ (163°C) TEMPERATURE AIR IN THE GEARBOX. DO NOT MOTOR THE ENGINE DURING THIS TEST. IF YOU MOTOR THE ENGINE WHILE THE OIL SYSTEM IS PRESSURIZED, OIL CONTAMINATION OF THE COMPRESSORS AND GASPATH CAN OCCUR.
 (4)  Supply and keep the clean, dry air supply at a regulated pressure of 7-10 psi (48.3-68.9 kPa) in the gearbox.
 NOTE: A pressure of less than 7 psig (48 kPa) is not sufficient to
____
 give accurate results.

 (a)  
Make sure the air pressure is 7-10 psig (48-68.9 kPa).

 (b)  
Make sure the air temperature is less than 325°F (163°C).


 S 795-064-N00
 (5)  Use the leak check or soap and water solution to examine for leaks at these locations:
 (a)  
All gearbox pad seals without the overboard drains.

 (b)  
All connections to the deoiler.


 
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