(2)  
Move captain's right pedal until forward quadrant stop is contacted. Measure rudder travel. Required movement is 21.82 +0.80 inches.

D.  Restore Airplane to Normal
(1)  
Remove systems A, B and standby hydraulic power (Ref 27-21-0).

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

(3)  
Close all access doors and install access panels.

501 
27-21-141 Page 504  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Nov 1/74 

G09319 G09462
501  Rudder Travel and Index Plate 
Nov 01/74  Figure 502 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-21-141 Page 505 

Rudder Forward Quadrant Installation  500 
27-21-141Page 506   Figure 503 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 15/73 

STANDBY RUDDER ACTUATOR - INSPECTION/CHECK
1.  General
A.  This data consists of illustrations, wear limits charts and instructions on measuring wear limits. 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.  Standby Rudder Actuator Wear Limits
C36893
500  Standby Rudder Actuator Wear Limits 
Feb 20/94  Figure 601 (Sheet 1)  27-21-141 
Page 601 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

INDEX NO.  PART NAME  DIM.  DESIGN LIMITS  WEAR LIMTS  REPLACE WORN PART  REPAIR WORN PART  REPAIR INSTR. 
DIAMETER  ALLOWED WEAR DIM.  MAX DIAM CLEAR-ANCE
MIN  MAX 
1  ROD END  ID  0.2495  0.2500  0.2530  0.0035  X 
BOLT  OD  0.2485  0.2495  0.2481  X 
2  CLEVIS  ID  0.2500  0.2505  0.2535  0.0040  X  1 
BOLT  OD  0.2485  0.2495  0.2481  X 
3  ROD END  ID  0.6245  0.6250  0.6280  0.0040  X 
BOLT  OD  0.6230  0.6240  0.6190  X 
4  CLEVIS  ID  0.6250  0.6265  0.6305  0.0065  X  2 
BOLT  OD  0.6230  0.6240  0.6190  X 
5  ROD BEARING  ID  0.5620  0.5625  0.5655  0.0040  X 
BOLT  OD  0.5605  0.5615  0.5665  X 
6  CLEVIS  ID  0.5620  0.5625  0.5655  0.0040  X  3 
BOLT  OD  0.5605  0.5615  0.5665  X 

OBTAIN BUSHING. BORE HOLE TO ATTAIN -0.0010 TO 0.0000 INCH INTERFERENCE FIT (0.3754 INCH MAXIMUM). REAM BUSHING TO 0.2500/0.2505 INCH DIAMETER.
REPLACE WORN BUSHING
REPLACE WORN BUSHING (SEE SECTION A-A). SHRINK FIT INSTALLATION (REF OVERHAUL MANUAL, 20-50-03). IF SPECIAL STEEL WEAR PLATE IS INSTALLED UNDER UPPER BUSHING FLANGE, REPLACE WITH NEW STEEL WEAR PLATE APPLIED WITH SEALANT BMS 5-95.
Standby Rudder Actuator Wear Limits  501 
27-21-141  Figure 601 (Sheet 2)  May 15/80 
Page 602 
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A. Standard Tools and Equipment
(1)
 Micrometer

(2)
Vernier Caliper

(3)
 Feeler gages

B. Procedure
(1)
Measure the two clearances, X1 and X2, shown in Fig. 601, View B.

(a)
Calculate the difference in clearance.

NOTE: X1-X2 = Difference in clearance.

(b)
If the difference in clearance is less than 0.015 inch, replace the rod bearing housing.

(2)
Remove the standby rudder actuator (Ref 27-21-141 R/I).

(3)
Measure the parts of the standby rudder actuator for worn areas.

(4)
Compare the dimensions that you measured with the permitted dimensions shown in Fig.

601.

(5)
Replace or repair the parts that are not in the tolerance.

(6)
Install the standby rudder actuator (Ref 27-21-141 R/I).

500 
May 01/98  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-21-141 Page 603 
　
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