..........................................................................
| SYS | LEFT INBOARD | | ELEVATOR FEEL | LOWER RUDDER |
| 2 | ELEVATOR PCP | ---| COMPUTER OR | PCP OR BRAKE |
| *[2] | | | FEEL ACTUATOR | ANTISKID |
| | | | | SHUTTLE |
| | | | | VALVES *[3] |
..........................................................................
| SYS | UPPER RUDDER | ELEVATOR FEEL | | RIGHT INBOARD |
| 3 | PCP | COMPUTER OR | ---| ELEVATOR PCP |
| *[2] | | FEEL ACTUATOR | | |
..........................................................................
| SYS | BRAKE | LOWER RUDDER | RIGHT INBOARD | |
| 4 | ANTISKID | PCP OR BRAKE | ELEVATOR PCP | ---|
| *[2] | SHUTTLE | ANTISKID | | |
| | VALVES *[3] | SHUTTLE | | |
| | | VALVES *[3] | | |
2........…...............…...............…...............…...............1
*[1] The system must not be pressurized.
*[2] The system must be pressurized.
*[3] For the brake antiskid shuttle valves, brake operation or a large
difference in the reservoir pressures is necessary for movement of the fluid between the systems.
S 796-712
(6)
To check the Alternate Brake Return Check Valve as a possible source of fluid transfer from System 1 to System 2, do the following steps:
(a)
Close the System 1 and 2 flight control shutoff valves.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
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747-400 MAINTENANCE MANUAL
(b)
Depressurize System 4 (AMM 29-11-00/201).
(c)
Pressurize System 1 (AMM 29-11-00/201).
(d)
Depressurize System 2 (AMM 29-11-00/201).
(e)
Apply and hold the brakes.
(f)
Pressurize System 4 (AMM 29-11-00/201).
NOTE: This moves the number 1 Source Select Valve to the
____
isolated position.
(g)
Release the brakes.
(h)
Depressurize System 4 (AMM 29-11-00/201).
NOTE: This moves the number 1 source select valve to the
____ open position. Flight controls may be cycled to speed the reduction of System 4 pressure.
(i)
Repeat steps c-g for approximately 10 times and monitor System 1 and System 2 fluid quantities for fluid transfer.
E.
Put the airplane back to its usual condition.
S 866-695
(1)
Find the switches for the FLT CONTROL HYD POWER on the pilot's overhead maintenance panel, P461.
(a)
Make sure the WING switches, for the hydraulic systems No. 1, 2, 3, and 4, are in the NORM position.
(b)
Make sure the TAIL switches, for the hydraulic systems No. 1, 2, 3, and 4, are in the NORM position.
S 866-696
(2)
Remove the hydraulic power if it is not necessary
(AMM 29-11-00/201).
S 866-697
(3)
Remove the 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
MAIN HYDRAULIC SYSTEM RESERVOIR - REMOVAL/INSTALLATION
______________________________________________________
1. General_______
A. This procedure contains the tasks to remove and install the hydraulic system reservoir. It also contains a task to visually inspect the reservoir support beams for cracks.
B. To remove the hydraulic reservoir, you must release the pressure in the pneumatic and the hydraulic systems.
C. Before you remove the hydraulic reservoir, you must remove the diagonal brace.
D. The hydraulic reservoir is on the aft side of the strut torque box. You can get access to the reservoir through the fairing doors on the trailing edge of the strut.
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