S 866-168
 (11)
 Put the system No. 3 TAIL FLT CONTROL SHUTOFF switch in the ON position.

 (12)
 Put the control column in the full forward position.

 S 866-169
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 29-11-00
 ALL  ú ú 01 Page 651 ú Oct 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 S 976-170
 (13) Let this flow become stable for 1 minute and write this flow as flow
 No. 5. Flow No. 5__________GPM
 S 866-171
 (14)
 Put the control column in the neutral position.

 S 976-172

 (15)
 Subtract flow No. 5 from flow No. 1 and write this flow as flow

 No. 5A. Flow No. 1__________GPM Flow No. 5__________GPM
 Flow No. 5A__________GPM
 NOTE: Flow No. 5A is the null leakage of the power package for the
____
 right inboard elevator.

 S 976-173
 (16) Subtract 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 of the control package for
____
 the upper rudder.

 I. Lateral Hydraulic Control System - Internal Leakage Check
 S 866-174
 (1)  
Put the system No. 3 WING FLT CONTROL SHUTOFF switch in the OFF position.

 S 976-175

 (2)  
Let this flow become stable for 1 minute and write this flow as flow

 No. 6. Flow No. 6__________GPM
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 29-11-00
 ALL  ú ú 01 Page 652 ú Oct 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

 S 976-176
 (3)  Subtract flow No. 6 from flow No. 1 and write this flow as flow
 No. 6A. Flow No. 1__________GPM Flow No. 6__________GPM
 Flow No. 6A__________GPM
 NOTE: Flow No. 6A is the null leakage of these controls:
____
 -
the right central-lateral control package.

 -
the power package for left inboard aileron.

 -
the power package for the right outboard aileron.

 -internal leakage other than the null leakage of the control valves in spoiler packages 1, 4, 9, and 12.
 S 866-177
 (4)  
Put the system No. 3 WING FLT CONTROL SHUTOFF switch in the ON position.

 S 486-178

 (5)  
Install the control wheel adapter and protractor.

 S 866-179

 (6)  
Turn the control wheel counterclockwise 30 to 40 degrees.

 S 976-180

 (7)  
Let the flow become stable for one minute and write this flow as

 flow No. 7. Flow No. 7__________GPM
 S 866-181
 (8)  
Turn the control wheel to a position 60 to 70 degrees counterclockwise of neutral.

 S 976-182

 (9)  
Let the flow become stable for one minute and write this flow as

 flow No. 8. Flow No. 8__________GPM
 S 866-183
 (10) Put the control wheel in the neutral position.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 29-11-00
 ALL  ú ú 01 Page 653 ú Oct 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

 S 976-184
 (11) Subtract flow No. 8 from flow No. 7 and write this flow as flow No. 8A.
 Flow No. 7__________GPM
 Flow No. 8__________GPM
 Flow No. 8A__________GPM
 NOTE:____ Flow No. 8A is the null leakage of the power package for the
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機(jī)維護(hù)手冊(cè) 液壓 HYDRAULIC 1(66)