(a)  
The rudder moves approximately 3 degrees trailing edge right

 (b)  
The rudder moves approximately 3 degrees trailing edge left

 (c)  
The rudder goes back to its neutral position

 S 736-008
 (7)  
If the rudder does not move correctly, do the "Yaw Damper Summing Lever - Inspection" task.

 D.
Put the Airplane Back to Its Usual Condition

 S 866-009
 (1)  Remove the power from the left, right, and center hydraulic systems (Ref 29-11-00/201).
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757 MAINTENANCE MANUAL
 S 866-010
 (2)  Remove electrical power if it is not necessary (Ref 24-22-00/201).
 TASK 27-21-17-736-011
 3.  Yaw Damper Summing Lever - Inspection_____________________________________
 A. Equipment
 (1)  
Rig Pins From Set B20003-XX (Ref 20-10-24/201):

 (a)  
R9 - P/N B20003-54

 B.
References

 (1)  
06-42-00/201, Empennage Access Doors and Panels

 (2)  
20-10-24/201, Rig Pins

 C.
Access

 (1)  
Location Zone 324 Vertical Stabilizer, Rear Spar to Trailing Edge

 (2)  
Access Panel
 324BL Yaw Damper Summing Linkage

 D.
Yaw Damper Summing Lever - Inspection

 S 016-012
 (1)  
Open access panel 324BL to get access to the yaw damper summing lever (Ref 06-42-00/201).

 S 226-013

 (2)  
Examine the clevis that mates with the servo summing link for cracks or other defects.

 S 216-023

 (3)  
AIRPLANES WITH SHEAR PIN; Make sure you can easily install and remove rig pin R9 in the inspection hole that goes thru the yaw damper shear pin.

 S 036-015

 (4)  
If you find cracks or cannot install rig pin R9, replace the yaw damper summing lever (Ref 27-21-17/401).

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757 MAINTENANCE MANUAL
 S 226-022
 (5)  
AIRPLANES WITH SHEAR RIVETS; Make sure you can easily install and remove rig pin R9 in the inspection hole that is located below the yaw damper shear rivets.

 S 036-021

 (6)  
If you find cracks or cannot install rig pin R9, replace the shear rivets.

 E.
Put the Airplane Back to Its Usual Condition

 S 416-016
 (1)  Close the access panel, 324BL (Ref 06-42-00/201).
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 RUDDER THERMAL COMPENSATING LINKAGE - REMOVAL/INSTALLATION
__________________________________________________________
 1.  General_______
 A.  This procedure contains the removal and installation tasks for the rudder thermal compensating linkage and its components.
 NOTE: Before this procedure is done, make sure the airplane is
____ stable at ambient air temperature 10 degrees F ( 5.5 degrees C). Before adjustments or adjustment checks are made, maker sure the temperature has been stable for at least one hour.
 (1) You will have to use six rivets for this task (NAS1398D-2).
 TASK 27-21-19-024-001
 2.  Rudder Thermal Compensating Linkage and Its Components - Removal________________________________________________________________
　
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