B.  Prepare for Adjustment
(1)  
Supply power to the standby hydraulic system (Ref 27-21-0 MP).

(2)  
Move the rudder pedals through ten cycles to flush and bleed the standby rudder actuator.

(3)  
Remove power from the standby hydraulic system (Ref 27-21-0 MP).

(4)  
Provide rudder systems A and B hydraulic power (Ref 27-21-0 MP).

(5)  
Remove access panel on left side of vertical stabilizer to gain access to rudder standby actuator.

(6)  
Check that rudder trim is set at zero units of trim.

(7)  
Jiggle feel and centering unit input arm (trim and feel rod) to ensure that system is centered.

(8)  
Insert rigging pin R-5 in centering unit output crank. Rigging pin shall enter easily without movement of output crank.

C.  Adjust Standby Rudder Actuator (Fig. 501).
(1)  Check alignment of index mark on standby actuator valve input crank and center mark on actuator body.
(a)  
If marks align, proceed to step (4).

(b)  
If marks do not align and misalignment is less than 0.02 inch, proceed to step (2).

(c)  
If marks do not align and misalignment is more than 0.02 inch, proceed to step (3).

500 
May 01/99  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-21-141 Page 501 

E04138
Standby Rudder Actuator Adjustment  500 
27-21-141  Figure 501  Feb 20/94 
Page 502 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

(2)  
Adjust control rod (fine adjustment) as follows:

(a)  
Loosen both checknuts on rod assembly and back them off a few turns.

(b)  
Turn tube until index marks align. One full turn at tube moves index mark approximately 0.006 inch.

(c)  
Tighten both checknuts.

(d)  
Proceed to step (4).

(3)  
Adjust control rod (coarse adjustment) as follows:

(a)  
Position flight control switches A and B to OFF.

CAUTION: HYDRAULIC POWER MUST BE OFF FOR THIS PROCEDURE.

(b)  
Loosen both checknuts on rod assembly.

(c)  
Remove bolt connecting aft end of rod to actuator.

(d)  
Turn aft rod end and tube together and/or aft rod end alone in the same direction. Half a turn of one rod end moves index mark approximately 0.015 inch.

(e)  
Install clevis bolt at aft end of rod.

(f)  
Position flight control switches A and B to ON.

(g)  
Repeat fine adjustment starting at step 1.B.(3).

(4)  
Check for minimum thread engagement on rod. Rod end threads must be visible through inspection holes in tube at both ends.

(5)  
Remove rigging pin R-5.

(6)  
Test standby actuator per paragraph 2.

2.  Standby Rudder Actuator Test
A.  Prepare for Test
(1)  
Disconnect pushrod to nose wheel steering. (See figure 503.)

NOTE:  Nose gear steering need not be disconnected if airplane is jacked so that nose gear is fully extended.

(2)  
Provide rudder systems A and B hydraulic power. Refer to 27-21-0.

(3)  
Check that rudder trim knob is at neutral position.

(4)  
Check that rudder is at neutral.

(5)  
Position flight control switches A and B to OFF, then position flight control switch A or B to STDBY RUD.

(6)  
Check that there is no leakage at standby actuator hydraulic connections.

500 
Feb 15/73  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-21-141 Page 503 

B.  Test Standby Rudder Actuator Deadband
(1)  
By hand, push hard on rudder to the right, then slowly ease off load.

(2)  
With hands off rudder, measure rudder position in inches to the right.

(3)  
By hand, push hard on rudder to the left, then slowly ease off load.

(4)  
With hands off rudder, measure rudder position in inches to the left.

(5)  
Calculate difference between (2) and (4). If difference is greater than 0.2 inch, the standby actuator input control rod must be adjusted again.

C.  Test rudder travel (Fig. 502).
(1)  
Move captain's left pedal until forward quadrant stop is contacted. Measure rudder travel. Required movement is 21.82 +0.80 inches (Fig. 502).
　
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