737 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 1(15)

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4.  Rudder Control
A.  The hydraulically-powered rudder is controlled by the captain's and first officer's rudder pedals. (See figure 2.) The rudder pedals are bussed together and are adjustable fore and aft by use of pedal adjustment cranks. The pedals provide input to the rudder power control unit through the rudder control system. The power control unit moves the rudder with hydraulic power from both hydraulic systems A and B. Rudder hydraulic supplies are controlled by the flight controls shutoff valve in the flight controls hydraulic modular packages. (See figure 4.) Switches for these valves are on the pilots' overhead panel. (See figure 5.) In the event of hydraulic system A or B failure, the standby hydraulic system will drive a rudder standby power unit to move the rudder. Control of the standby hydraulic system power is by a shutoff valve on the standby modular package. The flight controls switches on the pilots' overhead panel control this valve. These switches also provide control for pressurizing the standby hydraulic system.
B.  Rudder trim is accomplished by rotating the rudder trim control wheel (figure 2) which is located on the control stand. Motion from the trim wheel shifts rudder control system neutral providing trim correction by positioning the rudder.
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5.  Lift Devices
A.  The lift devices consist of two pairs of triple slotted trailing edge flaps, three pairs of leading edge slats and two pairs of leading edge flaps. Fore and aft movement of the flap control lever, on the control stand, is transmitted by the flap control system to the flap control valve in the main wheel well. The flap control valve directs power from hydraulic system A to actuate the flap power unit. The rotary motion of the flap power unit is transmitted by the flap drive system to retract or extend the trailing edge flaps. The trailing edge flaps can be located at intermediate angles depending on the positions of the flap control lever. In the event of hydraulic system failure, the trailing edge flaps may be operated electrically. In this case, control of the flaps is accomplished by two switches on the pilot's overhead panel (Fig. 5). One switch arms the electric flap drive system and the other switch activates the system to extend or retract the flaps. The trailing edge flap system is protected from excessive airloads by a flap load limiter system. The load limiter system automatically retracts the flaps from 40 to 30 units at airspeeds in excess of 152 to 162 knots.
B.  The leading edge slats are located outboard of the engines and extend forward from the wing leading edge. The leading edge flaps are located inboard of the engines and extend by rotating downward from the lower surface of the wing leading edge. Motion of the trailing edge flap drive system actuates the leading edge flap and slat control valve. This valve directs hydraulic system A power to drive the leading edge flap and slat actuators. In the event of hydraulic system A failure, the leading edge flaps and slats will be driven to the extended position using power from the standby hydraulic system. In this case the leading edge flaps and slats extend when the electric flap drive system is armed and the control switch is placed in the down position.
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531  Flight Controls System Hydraulic Schematic 
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FLIGHT CONTROLS MODULE (P5-3) - REMOVAL/INSTALLATION
1. General
A.  The P5-3 Module is on the pilot's overhead panel.  It contains the lights and switches used by the primary and auxiliary flight control system hydraulic supply valve.
B.  This procedure has these task:
(1)  
A removal of the P5-3 Module

(2)  
An installation of the P5-3 Module.
　
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