B. Pressurize Leading Edge Flaps and Slats Hydraulic Systems A and B
(1)
Connect electrical power to airplane.
(2)
Set parking brake and install ground lock assembly in nose gear.
(3)
Position GRD INTERCONNECT switch on forward overhead panel to OPEN.
(4)
Position No. 1 or 2 system B HYD PUMPS switches on forward overhead panel to ON to pressurize hydraulic system A and B.
C. Restore Airplane to Normal
NOTE: Perform the following steps after completing the 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 from airplane.
(4)
Remove ground lock assembly.
4. Leading Edge Flaps and Slats Hydraulic Systems A, B and Standby Depressurization
A. General
(1) Leading edge flaps and slats receive pressure through hydraulic systems A and B, and through the standby hydraulic system. All three hydraulic systems must be depressurized before maintenance is performed on leading edge components.
B. Depressurize Leading Edge Flaps and Slats Hydraulic Systems A, B and Standby
(1)
Open FLAP VALVES circuit breaker on P6 circuit breaker panel.
(2)
Ensure ALTERNATE FLAPS switch on forward overhead panel is OFF.
(3)
Ensure No. 1 and 2 system B HYD PUMPS switches on forward overhead panel are OFF.
(4)
Ensure GRD INTERCONNECT switch on forward overhead panel is positioned at CLOSE.
(5)
To dissipate remaining hydraulic power, cycle rudder pedals until rudder stops moving. Position FLT CONTROLS A switch to STBY RUD and cycle rudder again. Position FLT CONTROLS A and B switches to OFF.
(6)
If any hydraulic connections are to be disturbed, depressurize system A and standby hydraulic reservoirs (Ref 29-09-300).
(7)
Install lock on standby hydraulic module as follows (Fig. 201).
(a)
Disconnect electrical connector from leading edge devices shutoff valve at standby hydraulic module, located on aft bulkhead of main wheel well.
(b)
Manually move override lever at leading edge devices shutoff valve to position 2.
(c)
Install lock on shutoff valve and insert attaching lockpin.
C. Restore Airplane to Normal
NOTE: Perform the following steps after completing the system maintenance requiring depressurization.
(1)
Remove lock from standby hydraulic module shutoff valve and reconnect electrical connector.
(2)
Close FLAP VALVES circuit breaker.
(3)
Return FLT CONTROLS A and B switches to ON.
500
27-81-0 Page 202 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Sep 20/82
G41204
500 Hydraulic Module Lock Installation
Feb 15/69 Figure 201 27-81-0
Page 203
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
5. Leading Edge Flap And Slat Locks Application
A. Install leading edge flap and slat locks to prevent retraction of leading edge flaps and slats as follows:
(1)
Provide system A hydraulic power (par. 3).
(2)
Position flap control lever to 40-degree detent to fully extend leading edge devices.
(3)
Install leading edge flap and slat locks on extended leading edge flap and slat actuators.
WARNING: INSTALL LEADING EDGE FLAP AND SLAT LOCKS TO PREVENT INADVERTENT OPERATION OF LEADING EDGE FLAPS AND SLATS. FLAPS AND SLATS ARE FAST ACTING AND CAN CAUSE SERIOUS INJURY TO PERSONNEL.
(4)
Depressurize hydraulic system A (par. 4).
B. Remove leading edge flap and slat locks as follows:
(1)
Remove leading edge flap and slat locks from leading edge flap and slat actuators.
WARNING: LEADING EDGE FLAPS AND SLATS ARE FAST ACTING AND CAN CAUSE SERIOUS INJURY TO PERSONNEL. 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(151)
