S 866-015
 (1)  Pressurize hydraulic systems No. 1 and No. 4 to 3000 psig.
 S 866-483
 WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE LE AND TE
_______ FLAPS AND FLAP DRIVE MECHANISMS BEFORE YOU MOVE THE FLAP CONTROL LEVER. WITH HYDRAULIC POWER REMOVED, THE FLAPS WILL MOVE AUTOMATICALLY BY ELECTRICAL POWER WHEN YOU MOVE THE FLAP CONTROL LEVER.
 (2)  
Operate the flight controls through four or five cycles.

 S 866-431

 (3)  
Operate the inboard flaps through 3 full cycles.

 S 866-432

 (4)  
Leave the flight controls in the center position and the flap control handle in the "0" detent position.

 S 976-017

 (5)  
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. 1 (Flow No. 1) is more than 5 GPM, you must complete the remainder of this test.
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 29-11-00
 ALL  ú ú 01 Page 622 ú Feb 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

 G. Hydraulic System No. 1 - Pressure Module Check
 S 796-428
 (1)  
Examine the system No. 1 auxiliary pump for mechanical vibration and noise. (This is an indication of flow or pump rotation).

 S 426-433

 (2)  
If there is a sign of flow to the auxiliary pump through its pressure hose, replace the check valve for the auxiliary pump in the pressure module (AMM 29-11-23/201).

 S 796-018

 (3)  
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.

 (a)  
If a light goes off, replace the applicable check valve in the pressure module (AMM 29-11-23/201).

 S 216-666
 (4)  
If the demand pump is used as a pressure source, monitor the HYD PUMPS ENGINE PRESS light.

 (a)  
If the light goes off, replace the applicable check valve in the pressure module (AMM 29-11-23/201).

 S 796-019
 (5)  
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.
Inboard Trailing-Edge Flap-Control System - Internal Leakage Check

 S 866-020
 (1)  
Put the ALTN FLAPS arming switch in the ARM position.

 S 976-021

 (2)
Let the flow become stable for one minute and write this flow as

 flow No. 2. Flow No. 2__________GPM
 S 976-022
 (3) Subtract flow No. 2 from flow No. 1 and write this flow as flow
 No. 2A. Flow No. 1__________GPM Flow No. 2__________GPM
 Flow No. 2A__________GPM
 NOTE: Flow No. 2A is the null leakage of the motor for the inboard
____
 trailing edge flap.

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 29-11-00
 ALL  ú ú 01 Page 623 ú Oct 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 S 866-429
 WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE LE AND TE
_______ FLAPS AND FLAP DRIVE MECHANISMS BEFORE YOU MOVE THE FLAP CONTROL LEVER. WITH HYDRAULIC POWER REMOVED, THE FLAPS WILL MOVE AUTOMATICALLY BY ELECTRICAL POWER WHEN YOU MOVE THE FLAP CONTROL LEVER.
 (4)  
Put the handle for the trailing-edge flap control in the 10 unit detent.

 S 976-024

 (5)
Let this flow become stable for one minute and write this flow as

 flow No. 3. Flow No. 3__________GPM
 S 976-025
 (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 of the control valve for the
　
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