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 B.  The rudder control system is pedal operated by the captain or the first officer (Fig. 1). Pedal movement rotates the forward quadrants, which are cable connected to the aft quadrant. Rotation of the aft quadrant moves a control rod connected to a torque tube. Rotation of the torque tube moves a crank connected to the rudder power control unit linkage (Fig. 2). This admits hydraulic fluid to the actuating cylinder, which moves the rudder.
 C.  Rudder trim is initiated by the rudder trim knob located on the aisle stand (Fig. 3). The rudder trim knob activates arming and control switches which direct electrical input to the rudder trim actuator motor. Rotating the trim knob arms the trim motor circuit and selects either the extend mode for left rudder trim or the retract mode for right trim. Extension or retraction of the trim actuator jackscrew causes the feel unit frames to rotate. This moves linkages which rotate the torque tube, causing rudder power control unit input.
 D.  Rudder feel is provided by a rudder feel unit. The feel unit is connected to the rudder control torque tube, which connects through linkage and cables to the rudder pedals (Fig. 4).
 E.  The rudder is fully power operated through the entire travel. The rudder power control unit is hydraulically operated by hydraulic systems A and B simultaneously. The A and B systems can be independently activated by switches located on the overhead panel. Either of the A and B switches can be used to activate the standby hydraulic system and supply pressure to the standby actuator. The standby hydraulic system is automatically activated in the event of the loss of the A or B hydraulic system on takeoff.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
RUDDER
STANDBY RUDDER SEE B
ACTUATOR RUDDER
RUDDER AFT POWER UNIT
CONTROL QUADRANT
FEEL AND CENTERING
MECHANISM RUDDER TRIM ACTUATOR
RUDDER TRIM KNOB
STANDBY RUDDER ACTUATOR
SHUTOFF VALVE
RA RB
RUDDER CONTROL CABLES
SEE A
RUDDER PEDAL ADJUSTMENT  FORWARD RIGGING  AFT RIGGING PIN HOLE 
CRANK  PIN HOLE  FORWARD 
QUADRANT 
BUSROD 
RUDDER PEDAL  (TO FIRST 
ADJUSTMENT  OFFICER'S 
SHAFT  PEDALS) 

CAPTAIN'S RUDDER PEDALS
PUSHROD TO NOSE WHEEL STEERING
BRAKE PUSHROD (TYPICAL)
RIGGING PIN HOLE
(R-1 ON CAPTAIN'S PEDAL ARM,
R-2 ON FIRST OFFICER'S PEDAL ARM)

A
Rudder Control System Component Location Figure 1 (Sheet 1)
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

737-300/400/500
MAINTENANCE MANUAL

STANDBY RUDDER ACTUATOR
STANDBY INPUT ROD
EXTERNAL SUMMING LEVER
TRIM AND
FEEL ROD
RIG PIN
INPUT LINK INPUT CRANK RUDDER POWER UNIT
INPUT ROD
TORQUE TUBE
CONTROL ROD
LOWER CRANK (BELL CRANK)
FEEL AND CENTERING
MECHANISM CRANK
FEEL AND CENTERING
MECHANISM FWD
RUDDER TRIM
ACTUATOR

RB  RUDDER AFT
CONTROL QUADRANT

RA  B
Rudder Control System Component Location
Figure 1 (Sheet 2)

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
 F.  To maintain system B hydraulic pressure to the elevator system in case of a rudder system hydraulic leak, the system B pressure line to the rudder PCU has a fuse (not on all airplanes) located in the aft stabilizer compartment, and the system B return line from the rudder has a check valve (not on all airplanes) located in the space above the stabilizer center section.
　
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