G07111
Rudder Pedal Assemblies Installation  531 
27-21-31 Page 402  Figure 401 (Sheet 1) B
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 Feb 15/73 

G07116 G07153
500  Rudder Pedal Assemblies Installation 
May 15/68  Figure 401 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-21-31 Page 403 

Rudder Pedal Assemblies Installation  531 
27-21-31 Page 404  Figure 401 (Sheet 3) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 01/99 

C.  Coat support shaft with corrosion preventive compound and install with head inboard. Install shaft support bracket fasteners before tightening shaft nut.
NOTE:  Use one or more washers at both ends of shaft to ensure that no shaft threads are in bellcrank bearing.
D.  Install shaft support bracket to structure as follows:
(1)  
Position solid or laminated shim (3, figure 401) or both as required between underside of bracket and mating structure at forward end mounting holes. With radius fillers (2) in place per figure 401 install two bolts (1), and secure with washers (4) and nuts (5).

(2)  
At aft end of bracket place radius fillers (2), (3), and (4) in position and install two bolts (2) with washers (4) and nuts (5).

E.  Tighten support shaft nut to 200-300 pound-inches torque. Install cotter pin.
F.  Insert rigging pins R-3 and R-4 through forward rigging pin holes of both forward quadrants.
G.  Set rudder pedal adjustment at midtravel position.
H.  Insert rigging pins R-1 and R-2 through rudder pedal arms.
I.  Attach quadrant pushrods to rudder pedal arms. Adjust if necessary. Torque nuts and install cotter pins.
J.  Airplanes with retainers; install retainers on pedal arms.
K.  Attach brake pushrods to bellcrank. Tighten nuts and install cotter pins. Adjust and test brake system (Ref 32-43-0).
L.  Position upper rudder pedal cover to heel rest and install bolts (Fig. 402).
M.  Remove riggings pins R-1 and R-2 from pedal arms, and R-3 and R-4 from rudder forward quadrants.
N.  Provide rudder systems A and B hydraulic power (Ref 27-21-0).
O.  Test rudder pedal limit travel.
(1)  
Set rudder trim knob to zero and use pedal adjustment crank to locate pedals at midposition.

(2)  
Move pedal adjustment to full forward, then move left pedal forward until stop at forward quadrant is contacted and hold in that position. Measure total forward travel of left pedal from midposition of pedal adjustment. Total forward travel shall be 6.86 inches minimum. Measure at pedal pivot point.

May 01/99 27-21-31 Page 405 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

(3)  
Repeat steps (1) and (2) with right pedal.

(4)  
Use pedal adjustment crank to move pedals to midposition.

(5)  
Move pedal adjustment to full aft then move left pedal forward until stop at forward quadrant is contacted and hold in that position. Measure total at travel of right pedal from midposition of pedal adjustment. Total aft travel shall be 6.89 inches minimum. Measure at pedal pivot point.

(6)  
Repeat steps (4) and (5) moving right pedal forward and measuring total aft travel of left pedal.

P.  Restore airplane to normal hydraulic configuration (Ref 27-21-0).
Q.  Replace access panels, and close lower nose compartment door.

G07158
Upper Rudder Pedal Cover Installation  500 
27-21-31  Figure 402  May 01/99 
Page 406 
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RUDDER PEDAL ASSEMBLIES - INSPECTION/CHECK
1.  General
A.  The rudder control quadrant push rods installed under the control cabin floor between the Captain's and First Officer's rudder pedals and the forward cable quadrants can be deformed due to compressive overload. The following provides a check for allowable inservice deformation limits to determine if replacement is required. Corrosion may also result.
　
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