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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
STANDBY ACTUATOR SEE A
FIN STRUCTURE
STANDBY ACTUATOR SEE B
TORQUE
TUBE
INPUT ROD
INDEX MARKS
INPUT CRANK FWD
RUDDER
A
INPUT CRANK SHAFT
CONTROL VALVE R
BYPASS VALVE
(PRESSURE ON P
CONDITION)
RUDDER
FIN ATTACH ATTACH POINT POINT
INPUT CRANK
B
Rudder Standby Actuator
Figure 7
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
13. Operation_________
A. The rudder control system is operated by two sets of pedals, one for each pilot. Pedal movement is transmitted to forward quadrants and jackshafts by rods. The two forward quadrants are interconnected by a bus rod. Cables transmit forward quadrant motion to the aft quadrant located in the vertical fin. Rotation of the aft quadrant in turn causes rotation of the rudder control torque tube.
B. The rudder control torque tube, when rotated, provides simultaneous input to the rudder power control unit, the standby rudder actuator, and to the rudder feel and centering mechanism. In normal operation, the power control unit is powered by hydraulic systems A and B (Fig. 9). Control input to the power unit occurs when a torque tube-mounted crank rotates. The crank is connected by a rod to the input linkage of the power unit. As the input linkage moves, the control valve opens and ports hydraulic fluid to the actuator cylinder. The actuating piston then moves and causes rudder deflection. Nominal rudder travel is 26 degrees in both directions.
STANDBY RUDDER ACTUATOR SHUTOFF VALVE
Figure 8
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
FLT CONTROL STANDBY STANDBY A B HYD
MODULAR
LOW RUDDER
QUANTITY PACKAGE
STDBY STDBY RUD RUD LOW
STANDBY
PRESSURE
OFF OFF
POWER
M
A ON B ON UNIT
ALTERNATE FLAPS OFF
UP PRESSURE LOW LOW
PRESSURE OFF
SPOILER
AB
DOWNARM
TO STANDBY OFF OFF RESERVOIR
FEEL DIFF PRESS ON ON
SPEED TRIM
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