PRIMARY LOCK SWITCHES_____________________  BIT___  BIT STATUS__________  DESCRIPTION___________
 R BODY GR STRNG LEFT  26  1  LOCKED
 R BODY GR STRNG RIGHT  27  1  LOCKED
 L BODY GR STRNG RIGHT  28  1  LOCKED
 L BODY GR STRNG LEFT  29  1  LOCKED

 (e)  
Turn the Captain's tiller for a left turn (CCW) until the nose wheel angle shown on the steering collar decal is 23.75 to 24 degrees.

 (f)  
Make sure these bits for label 273 are as follows:

 (g)  
Push the NEXT PAGE button and go to page 2.

 (h)  
Make sure these bits for label 271 are as follows:

 ALTERNATE LOCK SWITCHES_______________________  BIT___  BIT STATUS__________  DESCRIPTION___________
 R BODY GR STRNG LEFT  26  1  LOCKED
 R BODY GR STRNG RIGHT  27  0  UNLOCKED
 L BODY GR STRNG RIGHT  28  0  UNLOCKED
 L BODY GR STRNG LEFT  29  1  LOCKED

 PRIMARY LOCK SWITCHES_____________________ BIT __________ DESCRIPTION
___ BIT STATUS ___________ R BODY GR STRNG LEFT 26 1 LOCKED R BODY GR STRNG RIGHT 27 0 UNLOCKED L BODY GR STRNG RIGHT 28 0 UNLOCKED L BODY GR STRNG LEFT 29 1 LOCKED
 S 744-035
 (19)
 With the steering tiller in the centered position, do the BITE test steps that follow:

 (a)  
Put the Captain's tiller to the neutral position.

 (b)  
Make sure these bits for label 273 are as follows:

 (c)  
Push the PREVIOUS PAGE button and go to page 1.

 (d)
Make sure these bits for label 271 are as follows:

 ALTERNATE LOCK SWITCHES_______________________  BIT___  BIT STATUS__________  DESCRIPTION___________
 R BODY GR STRNG LEFT  26  1  LOCKED
 R BODY GR STRNG RIGHT  27  1  LOCKED
 L BODY GR STRNG RIGHT  28  1  LOCKED
 L BODY GR STRNG LEFT  29  1  LOCKED

 PRIMARY LOCK SWITCHES_____________________  BIT___  BIT STATUS__________  DESCRIPTION___________
 R BODY GR STRNG LEFT  26  1  LOCKED
 R BODY GR STRNG RIGHT  27  1  LOCKED
 L BODY GR STRNG RIGHT  28  1  LOCKED
 L BODY GR STRNG LEFT  29  1  LOCKED

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 32-53-01
 ALL  ú
 ú  01  Page 409
 ú  Oct 10/91 

BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 F. Put the Airplane in Its Usual Condition
 S 414-036
 (1)  
Connect the torsion links for the nose landing gear at the apex (AMM 32-21-03/201).

 S 414-037

 (2)  
Connect the steering actuators for the body landing gear to the torsion link (AMM 32-53-11/201).

 S 864-038

 (3)  
Remove the pressure from the No. 1 hydraulic system
 (AMM 29-11-00/201).

 S 864-039

 (4)  
Remove electrical power if it is not necessary (AMM 24-22-00/201).

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 32-53-01
 ALL  ú ú 01 Page 410 ú Oct 10/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 BODY GEAR STEERING ELECTRONIC CONTROL UNIT - REMOVAL/INSTALLATION
_________________________________________________________________
 1. General
_______
 A. This procedure has two tasks:
 (1)  
Removal of the electronic control unit of the body gear steering

 (2)  
Installation of the electronic control unit of the body gear steering.

 TASK 32-53-03-004-001
 2. Body Gear Steering Electronic Control Unit Removal
__________________________________________________
 A. References
 (1)  
AMM 09-11-00/201, Towing

 (2)  
AMM 32-00-30/201, Landing Gear Door Locks
　
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 起落架 LANDING GEAR 8(71)