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 the forward connection. 3) Loosen the two checknuts on the vernier control rod. 4) Adjust the length of the vernier control rod assembly:
 NOTE: Increase the length of the rod assembly to move the
____ rudder right. Decrease the length of the rod assembly to move the rudder left.
 a)  Turn the sleeve and the rod end together to adjust the rod assembly length.
 NOTE: One-half of a turn is approximately equal 1/2
____ inch of rudder movement at the trailing edge.
 5) Connect the vernier control rod to the center crank. a) Tighten the outer bolt (or larger nut) to 45-60 pound-inches.
 CAUTION: DO NOT TIGHTEN THE LARGE NUT AFTER YOU TIGHTEN
_______ THE SMALL NUT. MOVEMENT OF THE LARGE NUT CAN CAUSE THE SMALL NUT TO COME LOOSE.
 b) Tighten the small nut to 12-15 pound-inches.
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A

737-300/400/500
MAINTENANCE MANUAL

TORQUE TUBE
SEE A
STANDBY RUDDER ACTUATOR
RIG PIN R-5 
CONTROL UNIT POWER LEVER EXTERNAL SUMMING 
ROD VERNIER CONTROL 
TORQUE TUBE 
FWD 

TORQUE TUBE A Rudder Power Control Unit Adjustment Figure 502
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
 6) Move the FLT CONTROL A and B switches to ON. 7) Turn the sleeve of the vernier control rod until the rudder aligns with the tab. 8) Tighten the two checknuts on the vernier control rod.
 NOTE: Make sure the total number of threads that you can
____ see on the sleeve and the rod end is not more than 27 turns.
 S 085-006
 (5)  
Remove the rig pin R-5.

 S 725-007

 (6)  
Do the functional test of the rudder PCU.

 S 415-008

 (7)  
Install the access panels 9512 and 9514.

 TASK 27-21-91-725-009
 3. Rudder Power Control Unit Functional Test
_________________________________________
 A. References
 (1)  
22-12-00/501, Yaw Damper System

 (2)  
27-21-00/201, Rudder Control System

 (3)  
32-00-01/201, Ground Lock Assemblies

 B.
Access

 (1)  
Location Zone
 101, 102 Control Cabin
 706 Vertical Stabilizer

 C.
Prepare for the Functional Test

 S 485-010
 (1)  Install the lockout pin for the nose gear steering
 (AMM 32-00-01/201).

 NOTE: It is not necessary to disconnect the steering if the
____ airplane is on jacks and the nose landing gear is fully extended.
 S 865-011
 (2)  
Supply hydraulic power system A and B to the rudder system. (AMM 27-21-00/201).

 (3)  
Make sure there are no leaks at the hydraulic lines on the PCU.

 (4)  
Set the rudder trim to zero units of trim (Fig. 503).

 S 795-012
 S 865-013
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
RUDDER TRIM
INDICATOR

PEDAL ASSEMBLY
SEE A
FORWARD RIG PIN HOLE (R-3 ON THE CAPTAIN'S QUADRANT R-4 ON THE FIRST OFFICER'S QUADRANT)
ADJUSTMENT
AFT RIG PIN CRANK FOR THE
HOLE (R-3) RUDDER PEDALS
FORWARD QUADRANT
ADJUSTMENT BUSROD (TO THESHAFT
FIRST OFFICER'S PEDALS)
CAPTAIN'S RUDDER PEDALS
PUSHROD TO THE NOSE WHEEL STEERING
RIG PIN HOLE
(R-1 ON THE CAPTAIN'S PEDAL ARM,

BRAKE R-2 ON THE FIRST OFFICER'S PEDAL ARM)
　
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