(6)  
SSM 28-31-01

 (7)  
WDM 28-31-12

 C.
Access

 (1)  
Location Zones 571 Rear Spar to Landing Gear Support Beam, Left 671 Rear Spar to Landing Gear Support Beam, Right

 D.
Procedure

 S 864-033
 (1)  
Make sure the manual override handle on the actuator (1) is in the closed position.

 S 424-034

 (2)  
Engage the shaft in the actuator with the adapter plate to put the actuator (1) in its position on the rear spar.

 S 434-035

 (3)  
Install the screws (3) and washers (4) (four locations) that attach the actuator (1) to the index plate.

 (4)  
Install lockwire on the screws (3).

 S 434-073
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 28-31-04
 ALL  ú ú 01 Page 409 ú Feb 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 S 284-074
 CAUTION: MAKE SURE THE MANUAL OVERRIDE LEVER DOES NOT TOUCH THE LOCKWIRE
_______ ON THE ADAPTER PLATE AND INDEX PLATE. IF THERE IS NO CLEARANCE, THE VALVE WILL NOT OPERATE CORRECTLY AND COULD CAUSE DAMAGE TO THE ACTUATOR MOTOR.
 (5)  
Make sure there is sufficient clearance between the manual override lever and the lockwire on the adapter plate and index plate.

 S 434-037

 (6)
Install the screw (8), washers (6), and nut (5) that attach the bonding jumper (7) to the actuator (1) (AMM 20-11-15/401).

 S 434-038

 (7)  
Connect the electrical connector (2) to the actuator (1).

 NOTE: Refer to this table for the equipment numbers.
____
 ~................................................................. | | Equipment Number | | Location ............................ | | Valve | Connector | ................................................................... | No. 2 Main Tank | V442 | DV442 | ................................................................... | No. 3 Main Tank | V443 | DV443 | 2......................................…...........…..............1
 S 764-039
 (8)  
Make sure the bonding resistance between the actuator (1) and the airplane structure is not more than 0.0025 ohm (AMM 20-22-01/601).

 E.
Put the Airplane Back to the Usual Condition.

 S 864-058
 (1)
Remove the DO-NOT-CLOSE tags and close these circuit breakers:

 (a)  
On the main power distribution panel, P6:
 1) 6E17, CTR R & MAIN 2 JTSN VLV
 2) 6F17, CTR L & MAIN 3 JTSN VLV

 S 094-044
 WARNING: USE THE PROCEDURE IN AMM 32-00-30/201 TO REMOVE THE DOOR LOCKS.
_______ THE DOORS OPEN AND CLOSE QUICKLY AND CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
 (2)  Remove the wing and body gear door locks (AMM 32-00-30/201).
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 28-31-04
 ALL  ú ú 01 Page 410 ú Feb 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 S 714-091
 (3)  Do this procedure: Ground Test - Fuel Jettison Transfer Valve (AMM 28-31-00/501).
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 28-31-04
 ALL  ú ú 01 Page 411 ú Feb 10/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 FUEL JETTISON NOZZLE VALVE ACTUATOR - REMOVAL/INSTALLATION
__________________________________________________________
 1.  General_______
 A.  This procedure contains instructions for the removal and installation of the actuator (V49, V56) for the fuel jettison nozzle valve.
 B.  The actuator is found in the wingtip dry bay, immediately outboard of the wing surge tank, installed on the jettison nozzle valve body.
　
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 燃油 FUEL 4(48)