(2)
Make sure the ends of the hydraulic tubes are clean and serviceable.
S 164-014
(3)
If there is leakage of the fluid, identify the fluid and clean the area (AMM 12-25-01/301).
(4)
Apply the assembly lube to the threads of the hydraulic fittings.
S 214-013
S 644-015
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747-400 MAINTENANCE MANUAL
S 424-016
(5)
Install the hydraulic fuse:
(a)
Put the hydraulic fuse in its position between the hydraulic tubes.
(b)
Tighten the two nuts to connect the hydraulic fuse to the hydraulic tubes.
S 434-017
(6)
Install the support clamps on the hydraulic tubes.
S 614-018
(7)
Fill the hydraulic reserviors if it is necessary (AMM 12-12-01/301).
S 714-019
(8)
Do the operational test of the hydraulic fuse.
TASK 32-41-77-714-020
4. Hydraulic Fuse Operational Test________________________________
A. References
(1)
AMM 09-11-00/201, Towing
(2)
AMM 24-22-00/201, Manual Control
(3)
AMM 29-11-00/201, Main Hydraulic Supply System
B.
Access
(1)
Location Zone
135 Wing Landing Gear Well, LH
136 Wing Landing Gear Well, RH
C.
Procedure
S 864-021
(1)
Supply electrical power (AMM 24-22-00/201).
(2)
Pressurize hydraulic system No. 4 (AMM 29-11-00/201).
S 714-023
(3)
Do the steps that follow to do a test of the Brake Source Selector Valve Fuse.
(a)
Push the captain's brake pedals to the stops and hold them. 1) Make sure there are no leaks at the hydraulic fuse.
(b)
Release the brake pedals.
(4)
Remove the pressure from hydraulic system No. 4 (AMM 29-11-00/201).
S 864-022
S 864-024
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(5) S 784-027Pressurize hydraulic system No. 1 (AMM 29-11-00/201).
(6) S 734-028Do the steps that follow to do a test of the Accumlator Isolation Valve Fuse. (a) Push the captain's brake pedals to the stops and hold them. 1) Make sure there are no leaks at the hydraulic fuse. (b) Release the brake pedals.
(7) S 864-029Remove the pressure from hydraulic system No. 1 if it is not necessary (AMM 29-11-00/201).
(8) S 864-025Remove electrical power if it is not necessary (AMM 24-22-00/201).
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747-400 MAINTENANCE MANUAL
BRAKE CONTROL SYSTEM - DESCRIPTION AND OPERATION
________________________________________________
1. General_______
A. The brake control system supplies antiskid protection, automatic braking, and brake torque control for use during landing, takeoff and taxiing of the airplane. It also supplies arming logic for the body gear steering system. The antiskid system prevents skids by releasing brake pressure applied to any wheel that approaches a skid condition. The automatic braking system supplies braking at a constant deceleration rate without manual input from the flight crew. The brake torque control system monitors torque of the brake during operation and releases brake pressure before the torque increases to more than the maximum safe limit.
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