S 866-293
(4)
Push the R HYD PUMPS ELEC switch on the hydraulic control panel on the P5 panel to ON.
S 216-294
(5)
Make sure the PRESS light for the right ACMP on the P5 panel is off.
S 816-295
(6)
If the PRESS light is on, repair the pressure indication circuit for the right system and again do the two steps above.
S 866-296
(7)
Push the R HYD PUMPS ELEC switch on hydraulic control panel on the P5 panel to OFF.
S 866-297
(8)
Remove the pressure from the right hydraulic system (AMM
29-11-00/201).
I.
Put the Airplane Back to Its Usual Condition
S 416-298
(1)
Close the access door, 197KL, for the central hydraulic service center (AMM 06-41-00/201).
S 416-301
(2)
Close the access panels, 434AL and 444AL, for the hydraulic bay in the aft strut (AMM 06-43-00/201).
S 416-302
WARNING:_______USE THE PROCEDURE AMM 32-00-15 TO REMOVE THE DOOR LOCKS. THE DOORS OPEN AND CLOSE QUICKLY AND CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
(3) Remove the door locks from the landing gear doors and close the door (AMM 32-00-15/201).
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29-11-00
ALL ú ú 08 Page 680 ú May 28/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757 MAINTENANCE MANUAL
S 866-300
(4) Remove electrical power if it is not necessary (AMM 24-22-00).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
29-11-00
ALL ú ú 06 Page 680A ú Dec 20/94
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757 MAINTENANCE MANUAL
TASK 29-11-00-706-474
12. Full Hydraulic System Internal Leakage Check and Isolation of Components with_____________________________________________________________________________ High Leakage.____________
A. General
(1)
If the system leakage is more than the approved leakage rates, you must find and replace the components with too much leakage. The tests must be done with the airplane in a landing configuration.
(2)
The approved total system null leakage limit is 4.5 GPM for the left and right systems and 4.0 GPM for the center system. If the null leakage is more than the allowable limits, replace components until the leakage is less than the limits.
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本文鏈接地址：757 AMM 飛機維護手冊 液壓 CHAPTER 29 - HYDRAULIC POWER 1(144)
