FLAP SYSTEM B POWER PRESSURE UNIT
CONDITION: FLAPS EXTENDED RETURN
Flight Controls System Hydraulic Schematic Figure 5 (Sheet 2)
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A 737-300/400/500MAINTENANCE MANUAL
NO. 2 LEFT WING NO. 1 LEFT WING
NO. 5 RIGHT WING NO. 4 RIGHT WING
NO. 1 LEFT WING NO. 3 LEFT WING NO. 2 LEFT WING
NO. 6 RIGHT WING NO. 4 RIGHT WING NO. 3 RIGHT WING
LE FLAP
ACTUATORS
LE SLAT
ACTUATORS
SEE D TO AUTOSLAT COMPUTER 2 TO AUTOSLAT COMPUTER 1
PRESSURE SYSTEM B
INTERMEDIATE EXTENSION
FULL EXTENSION
STANDBY PRESSURE SOLENOID 1 SOLENOID 2
RETURN 4 WAY VALVE 3 WAY VALVE
AUTOSLAT CONTROL VALVE
LE DEVICES
LE STANDBY CONTROL VALVE
DRIVE SHUTOFF
VALVE
FLOW FUSE
LIMITING
VALVE
8 9
FLight Controls System Hydraulic Schematic
Figure 5 (Sheet 3)
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A 737-300/400/500MAINTENANCE MANUAL
FLT CONTROL STANDBY A B HYD
Flight Control System Hydraulic Schematic
Figure 5 (Sheet 4)
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T81685
A
737-300/400/500MAINTENANCE MANUAL
C. Flight spoilers and ground spoilers are located on the upper surface of the wing. Two flight spoilers are outboard of each nacelle. Two ground spoilers are outboard of the flight spoilers, and one ground spoiler is inboard of each nacelle. The flight spoilers are hydraulically actuated in response to inputs from the aileron control system. The flight spoilers raise on the wing with up aileron and remain faired on the wing with down aileron. Flight spoiler motion is in proportion to aileron movement. One spoiler actuator hydraulically positions each flight spoiler panel. Hydraulic system A provides power for spoilers 3 and 6. Hydraulic system B provides power for spoilers 2 and 7. The flight spoilers may be deactivated by the spoiler shutoff valves in the flight controls hydraulic modular packages (Fig. 4). These valves are controlled by spoiler system A and B switches on the pilots' overhead panel (Fig. 5). All flight spoilers may also be used as speed brakes by aft movement of the speed brake control lever (Fig. 2). The speed brake control lever actuates the spoiler control system to cause all the flight spoiler panels to raise in unison. The flight spoilers will still respond to aileron inputs when being used as speed brakes. With speed brakes on and the airplane on the ground, hydraulic system A will power the ground spoilers 0, 1, 4, 5, 8, and 9 to full up position.
3. Pitch Control System____________________
A. The elevators provide primary response of the airplane in pitch control. Fore and aft movement of the captain's and first officer's control columns (Fig. 2) is transmitted through the elevator control system to the control valves of the two elevator power control units. These power control units are supplied with hydraulic power, one from system A and the other from system B. Elevator hydraulic supplies are controlled by the flight controls shutoff valve in each flight controls hydraulic modular package (Fig. 4). Switches for these valves are located on the pilots' overhead panel (Fig. 5). The power control units are interchangeable with the aileron power control units and are located in the empennage aft of the stabilizer rear spar. These power control units drive the elevator through pushrods and a torque tube. Balance panels and tabs aerodynamically reduce the forces required for elevator movement. In the event of hydraulic failure, motion of the pilots' control columns mechanically positions the elevators. Also, the elevator balance tabs reduce the forces required to operate the elevator.
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本文鏈接地址：737-300 400 500 AMM 飛機(jī)維護(hù)手冊(cè) 飛行操縱 FLIGHT CONTROLS 1(12)
