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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 main power control unit is powered by hydraulic systems A and B (Fig. 9).  Control input to the main power control 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.
C.  If hydraulic systems A and B are not available to power the rudder, then standby power may be turned on, and the rudder operated with the standby actuator.  Rudder pedal input positions a servovalve in the standby actuator which ports fluid to the actuating piston.  Movement of the piston closes off the ports when the desired rudder travel is reached.
D.  In addition to operating the rudder power unit and the standby actuator, the torque tube moves the centering cam in the feel and centering mechanism.  When the camshaft is rotated it displaces the spring-loaded cam follower.
E.  If rudder trim is adjusted with the power control unit depressurized, the drag of the unpowered rudder system will allow the system to remain out of center.  This will force the rudder feel and centering mechanism cam follower out of the cam detent.  Then when hydraulic power is applied, the rudder pedals and rudder will rapidly move to the newly trimmed position.
500 
May 01/03  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-21-1 Page 19 

RUDDER AND RUDDER TRIM CONTROL SYSTEM - ADJUSTMENT/TEST
EFFECTIVITY
AIRPLANES POST-SB 27-1252
1.  Rudder and Rudder Trim Control System Adjustment
A.  General
(1)  
The rudder system is rigged to synchronize the components of the system.  This is accomplished by adjusting all components and cables to neutral position, from forward to aft of the airplane, then adjusting the rudder to neutral position.  Five rudder system rigging pins are needed to adjust the system; four in the nose section, and one in the tail section.

NOTE:  If rudder trim is adjusted with the power control unit depressurized, the drag of the unpowered rudder system will allow the system to remain out of center.  This will force the rudder feel and centering mechanism cam follower out of the cam detent.  Then when hydraulic power is applied, the rudder trim control knob and rudder will rapidly move to the newly trimmed position.

(2)  
The rudder trim system is rigged by adjusting components to neutral position, and synchronizing adjustments from forward to aft.  One tail section rigging pin, common to the rudder control system, is needed to adjust the system.

CAUTION:  RUDDER, ELEVATOR AND AILERONS ARE FULLY POWERED SYSTEMS. ALL THREE SYSTEMS ARE POWERED SIMULTANEOUSLY.  CHECK TO ENSURE THAT PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF ALL CONTROL SURFACES BEFORE TURNING POWER ON.

(3)  
If an out-of-trim condition exists, refer to AMM 27-09-400, Adjustment/Test.

(4)  
The rudder and rudder trim control system is properly adjusted when the individual components are adjusted to meet the following conditions: (See Fig. 501 for rigging pin locations and cable tension requirements.)

(a)  Rudder Forward Quadrants
1)  With rudder pedals positioned to neutral with pedal adjustment crank, and using trim knob, and with rigging pin R-5 installed through feel and centering unit output crank, rudder forward quadrants shall be positioned so that rigging pins R-3 and R-4 fit through forward rigging pin holes in quadrants. If not, quadrants may be adjusted per par. 1.C.(2).
May 01/03 27-21-1 Page 501
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

W28823
Rudder Control System Adjustment  500 
27-21-1  Figure 501  May 01/03 
Page 502 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

(b) 
 Rudder Pedals

1)  With rigging pins R-3 and R-4 in place, rigging pins R-1 and R-2 shall fit through rigging pin holes on pedal arm assembly. If both pins cannot be installed, tension rods and cables may be adjusted per paragraph 1.C.(3).

(c)  
Rudder Trim Actuator

1)  With rigging pin R-5 installed (system should be centered and rigging pin should fit freely), cotter pin hole on right side of actuator shall fall within paint mark on housing. Dimension from upper end of actuator drum extension to end of actuator screw shall be 1.92 (+0.03/-0.02) inches. If either of these conditions is not met, actuator may be adjusted per paragraph 1.C.(4).
　
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