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 A.  The standby rudder actuator shutoff valve is located on the aft bulkhead of the main wheel well (Fig. 8). The unit is mounted on the standby system modular unit by four bolts. The valve is electrically operated from a 28-Volt DC source, and consists of a motor spool sleeve and cartridge. The cartridge containing the spool and sleeve fits into a cavity in the modular package. The electric motor is splined to a cam which converts rotary motor action into linear spool travel in the sleeve. The valve is equipped with a manual override lever and position indicator. The manual override allows the valve to be positioned with electrical power off. The valve is off when the lever is in position 1, and on when the lever is in position 2.
 12. Standby Rudder Actuator_______________________
 A.  The standby rudder actuator (Fig. 7) positions the rudder when hydraulic system A and B are not available. The actuator consists of a bypass valve, control valve, and the actuating cylinder. Standby hydraulic power for the standby actuator is controlled by system A and B switches on the overhead flight controls panel or by activation of the automatic standby function.
 B.  Hydraulic pressure supplied from the standby system operates the actuator. Rotation of the input crank will position the control valve to port fluid to the actuating cylinder.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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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