13. CLAMP
PNEUMATIC DUCT
12. BOLT
11. WASHER
10.  MOUNTING
BRACKET

4. CLAMP
8. BOLT
6. WASHER
9. SPACER
7. NUT
4. CLAMP
3.  PRESSURIZATION HOSE
5.
 BOLT

FOR THE HYDRAULIC
6.
 WASHER

RESERVOIR
7.
 NUT

FWD
A
Air-Driven Pump Turbine Drive Installation for System 1 with Auxiliary Pump and System 4 Figure 402 (Sheet 1)
A03272
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 29-11-08
 ALL  ú ú 02 Page 406 ú Feb 10/92
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

ENGINE NACELLE STRUT
SEE  B 
A  A  (7 LOCATIONS) 16. SCREWS CASCADE 15. TURBINE EXHAUST 
CONNECTOR 14. ELECTRICAL 
DRIVE 2. TURBINE 
21. WASHER (3 QTY) (2 LOCATIONS) 20. NUT 22. BOLT 

10.  MOUNTING BRACKET
B
24. BOLT RIGHT SIDE
MOUNTING FLANGE
NUTPLATE
AFT STRUT BULKHEAD
NUTPLATE
LEFT SIDE MOUNTING FLANGE
25.
 BUSHING

26.
 BOLT

FWD
TURBINE DRIVE FORWARD MOUNTS
C
SEE C
17.
SUPPORT ROD
(2 LOCATIONS)

18.
 BOLT

19.
 WASHER
(4 LOCATIONS)

AIR-DRIVEN
PUMP

CASCADE
SEAL

CASCADE
TURBINE DRIVE EXHAUST FLANGE
A-A
Air-Driven Pump Turbine Drive Installation
for System 1 with Auxiliary Hydraulic Pump and System 4
Figure 402 (Sheet 2)

A03187
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 29-11-08
 ALL  ú ú 01 Page 407 ú Feb 10/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

 (2)  
Access Panels
 454A Trailing Edge Fairing Doors - System 1
 484A Trailing Edge Fairing Doors - System 4

 C.
Procedure

 S 014-019
 (1)  
Open the fairing doors on the trailing edge of the strut
 (AMM 54-62-00/201).

 S 864-020

 (2)  
Supply electrical power (AMM 24-22-00/201).

 S 864-114

 (3)  
Put these switches, on the P5 panel, in the OFF position:

 (a)  
HYD DEMAND 1 for system 1

 (b)  
HYD DEMAND 4 for system 4.

 S 864-022
 WARNING: MAKE SURE YOU RELEASE THE PNEUMATIC SYSTEM PRESSURE BEFORE YOU
_______ OPEN THE HYDRAULIC SYSTEM. THE PNEUMATIC SYSTEM PRESSURIZES THE HYDRAULIC RESERVOIR. HYDRAULIC FLUID THAT HAS PRESSURE CAN CAUSE INJURY TO PERSONS.
 (4)
Release the pressure in the pneumatic system (AMM 36-00-00/201).

 S 864-023

 (5)
Release the pressure in the hydraulic system (AMM 29-11-00/201).

 S 864-115

 (6)  
Open the circuit breaker, for the applicable system, and install a DO-NOT-CLOSE tag:

 (a)  
P7 Overhead Circuit Breaker Panel
 1) 7J1 HYDRAULICS DEMAND 1 for system 1
 2) 7F1 HYDRAULICS DEMAND 4 for system 4.

 S 014-025
 (7)  
Remove the ADP (AMM 29-11-17/401).

 (8)  
Remove the auxiliary hydraulic pump (AMM 29-21-01/401).

 S 024-094

 (9)  
Remove the turbine drive (2):

 (a)  
Disconnect the electrical connector (14), for the applicable system, from the electrical component receptacle: 1) DM647A for system 1 2) DM874A for system 4

 S 014-026
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 29-11-08
 ALL  ú ú 01 Page 408 ú Jun 18/01
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護(hù)手冊 液壓 HYDRAULIC 1(117)