G08305
Rudder Forward Quadrant Installation  500 
27-21-91Page 506   Figure 503 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 15/73 

C.  Test Rudder Travel (Fig. 501)
(1)  
Position flight control switch B to OFF, leave flight control switch A in ON position.

(2)  
Move captain's left pedal until forward quadrant stop is contacted. Measure rudder travel. Check that rudder travel is 21.82 +0.80 inches.

(3)  
Move captain's right pedal until forward quadrant stop is contacted. Measure rudder travel. Check that rudder travel is 21.82 +0.80 inches.

(4)  
Position flight control switch A to OFF, and flight control switch B to ON.

(5)  
Repeat steps (2) and (3).

D.  Do a test of the secondary slide on the dual servo valve of the rudder power control unit: 
(1)  
Supply the rudder hydraulic power systems A and B (Ref 27-21-0/201).

(2)  
Slowly push the captain's left pedal forward until it touches the stop then release.

(3)  
As fast as possible, push the captain's right pedal forward. The right pedal should move smoothly forward until it touches the stop.

(a)  If the right pedal moves in the opposite direction of the applied force, replace the rudder power control unit (Ref 27-21-91/401).

(4)  
Release the right pedal.

(5)  
Slowly push the captain's right pedal forward until it touches the stop then release.

(6)  
As fast as possible, push the captain's left pedal forward. The left pedal should move smoothly forward until it touches the stop.

(a)  If the left pedal moves in the opposite direction of the applied force, replace the rudder power control unit (Ref 27-21-91/401).

(7)  
Release the left pedal.

(8)  
Slowly push the first officer's left pedal forward until it touches the stop then release.

(9)  
As fast as possible, push the first officer's right pedal forward. The right pedal should move smoothly forward until it touches the stop.

(a)  If the right pedal moves in the opposite direction of the applied force, replace the rudder power control unit (Ref 27-21-91/401).

(10)
Release the right pedal.

(11)
Slowly push the first officer's right pedal forward until it touches the stop then release.

(12)
As fast as possible, push the first officer's left pedal forward. The left pedal should move smoothly forward until it touches the stop.

(a)  If the left pedal moves in the opposite direction of the applied force, replace the rudder power control unit (Ref 27-21-91/401).

(13)
Release the left pedal.

E.  Restore airplane to normal.
(1)  
Remove rudder systems A and B hydraulic power (Ref 27-21-0).

(2)  
Connect pushrod to nose wheel steering, if disconnected.

(3)  
Close access doors and install access panels.

501 
Apr 01/97  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-21-91 Page 507 

RUDDER POWER CONTROL UNIT - INSPECTION/CHECK
EFFECTIVITY

AIRPLANES PRE-SB 27-1252
1.  General
A.  This data consists of illustrations and wear limits charts. There will be no procedure given in this section for gaining access to, or removing and replacing the component after inspection for wear. Refer to component removal/installation for this information.
2.  Rudder Power Control Unit Wear Limits

G08343
503  Rudder Power Control Unit Wear Limits 
May 01/03  Figure 601 (Sheet 1)  27-21-91 
Page 601 

BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

G08356 G44606
Rudder Power Control Unit Wear Limits  500 
27-21-91 Page 602  Figure 601 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 15/68 

501  Rudder Power Control Unit Wear Limits 
May 01/76  Figure 601 (Sheet 3) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-21-91 Page 603 

RUDDER POWER CONTROL UNIT - REMOVAL/INSTALLATION
EFFECTIVITY
AIRPLANES POST-SB 27-1252
1.  General
A.  The rudder power control unit (PCU) is located in the lower area of the vertical fin (Fig. 401).
B.  Replaceable components of the rudder power control unit include three solenoid valves, two transfer valves, two position transducers and four filters.
　
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