NOTE: Leave the ALTN FLAPS arming switch in the ARM position and
____ the flap control lever in the 10 unit detent for the remainder of hydraulic system No. 1 check.
 I. Empennage Hydraulic Control System - Internal Leakage Check
 S 866-026
 (1)  
Put the system No. 1 TAIL FLT CONTROL SHUTOFF switch in the OFF position.

 S 976-027

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

 flow No. 4. Flow No. 4__________GPM
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 29-11-00
 ALL  ú ú 01 Page 624 ú Feb 10/92
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 747-400 MAINTENANCE MANUAL
 (3)  S 976-028Subtract flow No. 4 from flow No. 3 and write this flow as flow No. 4A. Flow No. 3__________GPM Flow No. 4__________GPM Flow No. 4A__________GPM
 NOTE:____ Flow No. 4A is the null leakage for the power packages of the left inboard and outboard elevators and the control package for the upper rudder.
 (4)  S 866-029Put the system No. 1 TAIL FLT CONTROL SHUTOFF switch in the ON position.
 (5)  S 866-030Put the control column in the full forward position.
 (6)  S 976-031Let the flow become stable for one minute and write this flow as flow No. 5. Flow No. 5__________GPM
 (7)  S 866-032Put the control column in the neutral position.
 (8)  S 976-033Subtract flow No. 5 from flow No. 3 and write this flow as flow No. 5A. Flow No. 3__________GPM Flow No. 5__________GPM Flow No. 5A__________GPM
 NOTE:____ Flow No. 5A is the null leakage for the power packages for the left inboard and outboard elevators.
 (9)  S 976-034Subtract flow No. 5A from flow No. 4A and write this flow as flow No. 5B. Flow No. 4A__________GPM Flow No. 5A__________GPM Flow No. 5B__________GPM
 NOTE:____ Flow No. 5B is the null leakage for the control package for the upper rudder.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 29-11-00
 ALL  ú ú 01 Page 625 ú Oct 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 J. Lateral Hydraulic Control System - Internal Leakage Check
 S 866-035
 (1)  
Put the system No. 1 WING FLT CONTROL SHUTOFF switch in the OFF position.

 S 976-036

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

 flow No. 6. Flow No. 6__________GPM
 S 976-037
 (3) Subtract flow No. 6 from flow No. 3 and write this flow as flow
 No. 6A. Flow No. 3__________GPM Flow No. 6__________GPM
 Flow No. 6A__________GPM
 NOTE: Flow No. 6A is the null leakage for the left
____ central-lateral control package and the power packages for the left inboard and outboard ailerons.
 S 866-038
 (4)  
Put the system No. 1 WING FLT CONTROL SHUTOFF switch in the ON position.

 S 866-039

 (5)  
Turn the control wheel fully counterclockwise.

 S 976-040

 (6)
Let the flow become stable for one minute and write this flow as

 flow No. 7. Flow No. 7__________GPM
 S 866-041
 (7)  
Put the control wheel in the neutral position.

 S 976-042

 (8)
Subtract flow No. 7 from flow No. 3 and write this flow as flow

 No. 7A. Flow No. 3__________GPM Flow No. 7__________GPM
 Flow No. 7A__________GPM
 NOTE: Flow No. 7A is the null leakage for the left central-lateral
____ control package and the power package for the left inboard aileron.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 29-11-00
 ALL  ú ú 01 Page 626 ú Oct 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護手冊 液壓 HYDRAULIC 1(55)