(2)
AMM 36-00-00/201, Pneumatic System
(3)
AMM 54-62-00/201, Nacelle Strut Access Panels
(4)
IPC 29-11-41, Fig. 1
B.
Access
(1)
Location Zone
454 System 1 - Strut Aft Fairing
484 System 4 - Strut Aft Fairing
(2)
Access Panel 454A Trailing Edge Fairing Door, LH - System 1 484A Trailing Edge Fairing Door, LH - System 4
C.
Procedure
S 014-002
(1) Open the left fairing door on the trailing edge of the strut (AMM 54-62-00/201).
S 864-003
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.
(2)
Release the pressure in the pneumatic system (AMM 36-00-00/201).
(3)
Release the pressure in the hydraulic system (AMM 29-11-00/201).
S 864-004
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
29-11-25
ALL ú ú 01 Page 401 ú Feb 18/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
ENGINE NACELLE STRUT
ELECTRICAL COMPONENT ASSEMBLY
SEE B
SEE A
TURBINE DRIVE
SEE C
GEARCASE
AFT LOOKING FORWARD
A
Electrical Component Assembly Installation
Figure 401 (Sheet 1)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
29-11-25
ALL ú ú 01 Page 402 ú Oct 10/92
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
RECEPTACLE
ELECTRICAL COMPONENT ASSEMBLY
ALIGNMENT PIN
CYLINDER
PORT TUBE
PACKING JAMNUT ELBOW
FWD FILTER PORT TUBE SUPPLY
B
HYDRAULIC HOSEELECTRICAL CONNECTOR CAPTIVE SCREW
CAPTIVE WASHER NUT
BOLT WASHER SPACER FWD
(2 LOCATIONS)
C
Electrical Component Assembly Installation Figure 401 (Sheet 2)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
29-11-25
ALL ú ú 01 Page 403 ú Feb 10/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
S 864-005
(4)
Open this circuit breaker for the applicable system:
(a)
P7 Overhead Circuit Breaker Panel
1) 7J1 HYDRAULICS DEMAND 1
2) 7F1 HYDRAULICS DEMAND 4
S 024-034
(5)
Remove the electrical component assembly:
(a)
Disconnect the electrical connector from the electrical component assembly.
(b)
Disconnect the cylinder port tube from the electrical component assembly.
CAUTION: MAKE SURE YOU CAREFULLY DISCONNECT THE SUPPLY PORT TUBE.
_______ THE FILTER IN THE TUBE CAN FALL OUT OF THE TUBE WHEN YOU DISCONNECT IT. THIS CAN CAUSE DAMAGE TO THE FILTER.
(c)
Disconnect the supply port tube from the electrical component assembly.
(d)
Disconnect the hydraulic hose from the electrical component assembly.
(e)
Remove the two bolts, the washers, and the spacers from the lower bracket of the electrical component assembly.
(f)
Remove the captive washer nut from below the upper bracket.
(g)
Lift the electrical component assembly until the alignment pin and the captive screw are free of the gearcase.
(h)
Remove the electrical component assembly from the turbine drive.
NOTE: Do not remove the alignment pin from the gearcase.
____
(i) Remove the two jam nuts, the elbows, and the packings from the cylinder and supply ports. 1) Discard the packings.
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護手冊 液壓 HYDRAULIC 2(50)
