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C. Rudder pedal adjustment crank and crank handle stops are installed to prevent the rudder pedal adjustment screw from being backdriven by heavy foot pressure simultaneously applied to both rudder pedals. The crank incorporates a spring-loaded pin within the knob. The stops are incorporated into the crank housing bearing retainer. Rotation of the crank handle is prevented in either direction beyond the stop blocks, by contact of the spring-loaded pin that protrudes from the crank handle. To permit crank rotation for rudder pedal adjustment, the knob must be pulled aft so the pin clears the stops.
Rudder Aft Control Quadrant
___________________________
A. The rudder aft control quadrant (Fig. 2) transmits the motion of the rudder control cables to the dual path torque tube. The assembly consists of a quadrant bolted to a shaft. The shaft is mounted horizontally in the vertical stabilizer.
B. Rotation of the quadrant pushes or pulls the quadrant input rod attached
to a crank on the rudder control torque tube.Rudder Control Torque Tube
__________________________
A. The rudder control torque tube provides a dual load path for rudder control linkage inputs. The torque tube (Fig. 2) consists primarily of two aluminum tubes bonded and swaged together. A dual-load-path plug forms each end of the torque tube and is double riveted in place. The torque tube is mounted on two bearings retained by two nuts installed on each dual plug. The tube is mounted in a vertical position in the vertical fin. Three cranks are bolted to the tube. The lower crank is connected to the input rod from the aft control quadrant and to the feel and centering mechanism. The center crank is connected to the main rudder power control unit linkage. The upper crank is connected to the standby power unit control linkage. The cranks are of dual construction with the two halves bonded and riveted together.
B. Rudder pedal input causes the torque tube and cranks to rotate. This provides input to the rudder power unit, the feel and centering unit, and the standby actuator.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500
MAINTENANCE MANUAL
Rudder Trim Control System Schematic
Figure 3
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ALL ú ú 01 Page 7 ú Jul 15/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500
MAINTENANCE MANUAL
TORQUE TUBE
SEE B
RUDDER FEEL AND CENTERING UNIT
RUDDER AFT CONTROL QUADRANT
SEE A
SEE D
RUDDER
TRIM KNOB
SEE D
CONTROL STAND
AIRPLANES WITHOUT EFIS
RUDDER TRIM KNOB
A
CONTROL
STAND
AIRPLANES WITH EFIS A Rudder Trim and Feel System Figure 4 (Sheet 1)
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
LOWER CRANK (BELLCRANK)
SUPPORT SUPPORT SHAFT TRIM AND SHAFT BEARING FEEL ROD
CONTROL ROD
FWD
FEEL AND TORQUE TUBE CENTERING CRANK
FIXED
RIGGING
END
PIN HOLE
CLEVIS
FRAME
RUDDER TRIM
ACTUATOR
SEE C
ARM AND ROLLER
SPRING FRAMECAM
SUPPORT SHAFT BEARING
B
ELECTRICAL INDICATOR
CONNECTOR MARKS
RUDDER TRIM
OUTPUT INDICATOR
CLEVIS
RUDDER TRIM 15105 0 51015
LEFT RIGHT
AILERON
NOSE LEFT
NOSE RIGHT
FIXED END
R CLEVIS
U LEFT
D WING WING RIGHT
D DOWN
E R
RUDDER TRIM
ACTUATOR
DOWN
RUDDER TRIM KNOB
C D
Rudder Trim and Feel System
Figure 4 (Sheet 2)
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