(2)
Normal and Alternate Brake System - Operational Test
(3)
Gear Retract Brake System - Operational Test
(4)
Hydraulic Brake System - Adjustment
(5)
Hydraulic Brake System - System Test
B.
The Alternate Source Selector Valve - Operational Test, the Normal and Alternate Brake System - Operation Test, and the Gear Retract Brake System - Operational Test make up the Hydraulic Brake System -Operational Test.
C.
You must adjust the brake linkage and cables after you complete these operations:
-
If you replaced the control quadrant for the brake metering valve
-
If you replaced the brake cables.
D.
The brake system is adjusted with the brakes in the off position.
E.
When the adjustment is completed, all rig pins must move freely through the rig pin holes.
F.
The cables must be adjusted when the cable tensions are not in the tolerance band shown (|10 lbs) (Fig. 501).
G.
To do the cable adjustment, these conditions must be obeyed:
-
The temperature of the airplane must be |5 degrees F of the ambient temperature
-
The temperature must be stable for one hour before the cable adjustments are made.
H.
You must do servicing on hydraulic system No. 1, 2, and 4 before you do a brake system test.
I.
To make sure the brakes are adjusted correctly, you must do a full brake
system test.
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32-41-00
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
TASK 32-41-00-715-124
2. Alternate Source Selector Valve - Operational Test__________________________________________________
A. General
(1)
There must not be unusual noise in the hydraulic lines or in the brake valves during the operational test.
B.
References
(1)
AMM 09-11-00/201, Towing
(2)
AMM 12-15-09/301, Brake Hydraulic Accumulator
(3)
AMM 12-15-11/301, Hydraulic Pressure Surge Accumulator
(4)
AMM 24-22-00/201, Manual Control
(5)
AMM 29-11-00/201, Main Hydrualic Supply System
(6)
AMM 32-00-30/201, Landing Gear Ground Locks
C.
Access
(1)
Location Zones
221 Control Cabin, LH
222 Control Cabin, RH
735 Wing Landing Gear - Left
745 Wing Landing Gear - Right
755 Body Landing Gear - Left
765 Body Landing Gear - Right
D.
Preconditions
S 865-178
(1)
These conditions are necesssary for this task:
(a)
Electrical power is available (AMM 24-22-00/201).
(b)
The brake hydraulic accumulator precharge pressure is correct (AMM 12-15-09/301).
(c)
The surge accumulators precharge pressure is correct (AMM 12-15-11/301).
(d)
The hydraulic systems are serviceable (AMM 29-11-00/201).
(e)
If you do not use the hydraulic service cart to pressurize hydraulic system #2, you must operate the engine to power the engine-driven pump for hydraulic system #2, and you must operate the demand pump (ACMP or ADP) for hydraulic system #2 (AMM 29-11-00/201).
(f)
The Integrated Display System (IDS) is serviceable (AMM 31-61-00/501).
E.
Prepare for the Test
S 495-090
(1) Make sure the ground locks are installed in all landing gear (AMM 09-11-00/201).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
S 495-173
WARNING:_______ YOU MUST CAREFULLY DO THE STEPS IN THE TASK BELOW TO INSTALL
THE DOOR LOCKS ON THE LANDING GEAR DOORS. THE DOORS CAN CLOSE
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