(2)
Intermittent system B pump operation is limited to five starts of any one pump in a 5-minute period. Following the fifth start, run pump for at least 5 minutes or turn pump off for a minimum of 30 minutes.
C. The following procedure covers pressurization of hydraulic systems B and A through operation of electrical-driven hydraulic system B pumps only. Pressurization of hydraulic systems A through operation of engine-driven hydraulic system A power is not covered.
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2. Spoiler Hydraulic System A and B Pressurization
A. Equipment and Materials
(1) Lock Assembly - Ground, F72735
B. Provide spoiler system A and B hydraulic pressure.
(1)
Connect electrical power to airplane.
(2)
Ensure that SPOILER SHUTOFF VALVES circuit breaker on P6 circuit breaker panel is closed.
(3)
Set parking brake and install ground lock assembly in nose gear.
(4)
Position GRD INTERCONNECT switch on forward overhead panel to OPEN.
(5)
Position No. 1 or No. 2 system B HYD PUMPS switches on forward overhead panel to ON.
(6)
Position SPOILER A and B switches on forward overhead panel to ON.
NOTE: To pressurize system A or system B separately, select system by appropriate positioning of SPOILER A and B switches.
C. Restore Airplane to Normal
NOTE: Perform the following steps after completing flight spoiler system maintenance that required pressurization.
(1)
Position No. 1 and 2 system B HYD PUMPS switches to OFF.
(2)
Position GRD INTERCONNECT switch to CLOSE.
(3)
Remove electrical power.
(4)
Remove ground lock assembly.
3. Spoiler Hydraulic System A and B Depressurization
A. Equipment and Materials
(1) Lock Assembly - F80049-1 (2 required)
B. Depressurize spoiler hydraulic systems A and B.
(1)
Position SPOILER A and B switches on the forward overhead panel to OFF.
(2)
Open all flight control circuit breakers on P6 circuit breaker panel.
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G29410
500 Hydraulic Module Lock Installation
Feb 15/73 Figure 201 27-61-0
Page 203
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(3)
Position No. 1 and 2 system B HYD PUMPS switches on forward overhead panel to OFF.
(4)
Position GRD INTERCONNECT switch on forward overhead panel to CLOSE.
(5)
To dissipate one remaining hydraulic power, cycle captain's control wheel.
(6)
If any hydraulic connections are to be disturbed, depressurize hydraulic system A and system B reservoirs. Refer to 29-09-300, Hydraulic Reservoir Pressurization System -Maintenance Practices.
(7)
Install hydraulic module locks. (See figure 201.)
(a)
Disconnect electrical connector from spoiler shutoff valve at system A flight controls hydraulic module in left wheel well.
(b)
Disconnect electrical connector from spoiler shutoff valve at system B flight controls hydraulic module in right wheel well.
(c)
Manually place override lever at both spoiler shutoff valves in position 2.
(d)
Install lock on each spoiler shutoff valve and insert attaching lockpins.
C. Restore Airplane to Normal
NOTE: Perform the following steps after completing spoiler system maintenance that required depressurization.
(1)
Remove locks from system A and B flight control hydraulic module shutoff valves and reconnect electrical connectors.
(2) 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 飞行操纵 FLIGHT CONTROLS 3(88)
