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
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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).
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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
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本文链接地址：747-400 AMM 飞机维护手册 起落架 LANDING GEAR 8(71)
