737 AMM 飞机维护手册 液压 HYDRAULIC POWER(39)

曝光台 注意防骗 网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者

HYDRAULIC SYSTEM A - MAINTENANCE PRACTICES
1.  General
A.  The maintenance practices included in this section (201-299 page block) are general maintenance instructions that do not definitely fall within a specific category. Other maintenance instructions, such as Servicing, Removal/Installation, Adjustment/Test, etc. are provided in the applicable page blocks.
B.  To pressurize hydraulic system A, three methods can be used: hydraulic test stand, system B using electric motor-driven pumps, or system A engine-driven hydraulic pump.
C.  Pressurizing the hydraulic system will supply hydraulic power to the flight control module, flaps, slats, ground spoilers, landing gear module, and inboard brakes.
D.  When maintenance being performed on system A affects the return side of the hydraulic system, the system A hydraulic reservoir will have to be depressurized.
E.  Should fluid spill on airplane, decontaminate (Ref Chapter 12, Cleaning and Washing).
2.  Pressurize Hydraulic System A
WARNING:  CHECK THAT PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF ALL FLIGHT CONTROL SURFACES AND NOSE GEAR BEFORE TURNING HYDRAULIC POWER ON. ISOLATE OR TAG SYSTEMS NOT BEING TESTED TO PREVENT INJURY TO PERSONNEL OR DAMAGE TO AIRPLANE.
A.  Equipment and Materials
(1)  
Hydraulic test stand - 0 to 3000 psi, with Hydraulic Fluid BMS 3-11

(2)  
Ground Lock Assembly - F72735

B.  Pressurize Hydraulic System A (Hydraulic Test Stand)
(1)  
Install ground lock assembly in nose gear.

(2)  
Open air conditioning duct access panel on right side of airplane.

(3)  
Connect hydraulic test stand to hydraulic ground power modular unit.

(4)  
Open ground interconnect valve.

(a)  
If airplane is on ground and electrical power is available check that parking brake is set and position ground interconnect switch on forward overhead panel to OPEN.

(b)  
If electrical power is not available or airplane is on jacks, disconnect the ground interconnect valve electrical connector and open valve using manual override lever.

 

500 
May 1/76  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  29-11-0 Page 201 

CAUTION:  VALVE MOTOR BURNOUT MAY OCCUR IF THE GROUND INTERCONNECT VALVE IS MANUALLY POSITIONED WHILE ELECTRICAL POWER IS APPLIED TO THE VALVE.  TO PREVENT THIS, ENSURE THAT THE VALVE ELECTRIC CONNECTOR IS DISCONNECTED, AND SUITABLY TAGGED.
(5)  
Operate hydraulic test stand to pressurize system until requirements are complete.

(6)  
Close ground interconnect valve.

(7)  
Disconnect test stand from module and install dust caps.

(8)  
Close access panel.

(9)  
Remove ground lock from nose gear if maintenance is complete.

C.  Pressurize Hydraulic System A (System B Electric Motor-Driven Pump)
CAUTION:  DO NOT OPERATE SYSTEM B PUMPS MORE THAN 2 MINUTES UNLESS THE NO. 2 FUEL TANK CONTAINS AT LEAST 1675 LBS/760 KG OF FUEL. IF PUMPS ARE OPERATED 2 MINUTES WITHOUT FUEL IN TANK, ALLOW RESERVOIR TO RETURN TO AMBIENT TEMPERATURE BEFORE RESUMING TEST.
NOTE:  With the A system reservoir not pressurized and the system B pump operating at near maximum, the system A reservoir fluid level may rise faster than the system B reservoir fluid level. This condition is possible because with the system A reservoir not pressurized, the balance line is not large enough to handle maximum system B pump output. This condition can be corrected by pressurizing the hydraulic reservoirs (Ref 29-09-300, Maintenance Practices).
(1)  
Install ground lock assembly in nose gear.

(2)  
Connect electrical power to airplane and close system B pump circuit breakers.

(3)  
Check that parking brake is set.

(4)  
Open ground interconnect valve.

(a)  
If airplane is on ground check that parking brake is set and position ground interconnect switch on forward overhead panel to OPEN.

(b)  
If airplane is on jacks, disconnect the ground interconnect valve electrical connector and open valve using manual override lever.

 

500 
29-11-0 Page 202  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Oct 20/84 

CAUTION:  VALVE MOTOR BURNOUT MAY OCCUR IF THE GROUND INTERCONNECT VALVE IS MANUALLY POSITIONED WHILE ELECTRICAL POWER IS APPLIED TO THE VALVE. TO PREVENT THIS, ENSURE THAT THE VALVE ELECTRIC CONNECTOR IS DISCONNECTED, AND SUITABLY TAGGED.
(5)  
Operate system B pump (Ref 29-12-0 MP).

(6)  
Check that system A hydraulic pressure stabilizes between 2800 and 3200 psi.
　
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737 AMM 飞机维护手册 液压 HYDRAULIC POWER(39)