29-11-00
ALL ú ú 01 Page 634 ú Feb 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
S 866-437
(3)
Let the flight controls stay in the center position.
S 976-076
(4)
Let the flow become stable for 3 minutes and write this flow as flow
No. 1. Flow No. 1__________GPM
If the internal leakage of system No. 2 (Flow No. 1) is more than 5 GPM, you must complete the remainder of this test.
NOTE: If the gross internal leakage for either of the inboard
____ systems (2 or 3) exceeds 3 GPM the other inboard system must not exceed 3 GPM. Maximum gross internal leakage for a inboard system (2 or 3) is 5 GPM.
G. Hydraulic System No. 2 - Pressure Module Check
S 796-077
(1)
If the hydraulic service cart is used as a pressure source, monitor the HYD PUMPS DEMAND PRESS and HYD PUMPS ENGINE PRESS lights on the P5 overhead panel. If the demand pump is used as a pressure source, monitor the HYD PUMPS ENGINE PRESS light. If any of the lights that are monitored go off, replace the applicable check valve in the pressure module (AMM 29-11-23/201).
S 796-078
(2)
Carefully feel the return line between the pressure module and the reservoir.
(a)
If the return line is hot, replace the pressure relief valve in the pressure module (AMM 29-11-23/201).
H.
Empennage Hydraulic Control System - Internal Leakage Check
S 866-079
(1)
Put the system No. 2 TAIL FLT CONTROL SHUTOFF switch in the OFF position.
S 866-080
(2)
Put the system No. 2 WING FLT CONTROL SHUTOFF switch in the OFF position.
S 976-081
(3)
Let the flow become stable for 1 minute and write this flow as flow
No. 2. Flow No. 2__________GPM
NOTE: Flow No. 2 is the null leakage for the stabilizer pitch trim
____
and the elevator feel computer.
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29-11-00
ALL ú ú 01 Page 635 ú Jun 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
S 866-082
(4) Put the system No. 2 STAB TRIM switch in the CUTOUT position.
S 976-083
(5) Let the flow become stable for 1 minute and write this flow as flow
No. 3.
Flow No. 3__________GPM
NOTE:____ Flow No. 3 is the null leakage for the elevator feel
computer.
S 976-084
(6) Subtract flow No. 3 from flow No. 2 and write this flow as flow
No. 3A. Flow No. 2__________GPM Flow No. 3__________GPM
Flow No. 3A__________GPM
NOTE: Flow No. 3A is the null leakage for the stabilizer
____ pitch trim.
S 866-085
(7)
Put the system No. 2 STAB TRIM switch in the ON position.
S 866-086
(8)
Put the system No. 2 WING FLT CONTROL SHUTOFF switch in the ON position.
S 976-087
(9)
Let the flow become stable for 1 minute and write this flow as flow
No. 4. Flow No. 4__________GPM
S 976-088
(10) Subtract flow No. 4 from flow No. 1 and write this flow as flow
No. 4A. Flow No. 1__________GPM Flow No. 4__________GPM
Flow No. 4A__________GPM
NOTE: Flow No. 4A is the null leakage of the power packages of the
____ left inboard-elevator and the lower rudder.
S 866-089
(11) Put the system No. 2 TAIL FLT CONTROL SHUTOFF switch in the ON position.
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29-11-00
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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