G07069
Rudder Removal/Installation Sling  5D1 
27-21-12  Figure 402  Feb 20/87 
Page 406 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

I.  Coat hinge bolts with corrosion preventive compound.
5.  Install Rudder (Fig. 401)
A.  Install and tighten hinge bolts at rudder hinges No. 1, 7, 3, and 6, in that order (Ref 27-21-22 R/I).
B.  Install bonding jumper at hinge No. 3.
C.  Before incorporation of SB 51-1011, install bonding jumper at hinge No. 7. Apply sealant to jumper ends and fasteners.
D.  After incorporation of SB 51-1011, install bonding jumper at station 227.57. Apply sealant to jumper ends and fasteners.
E.  Install bearing bar and two attach bolts in hinge No. 2. Do not tighten attach bolts. Install rudder hinge bolt. Do not tighten rudder hinge bolt. Tighten bearing bar attach bolts (Ref 27-21-22 R/I). Shim hinge to control gap between rudder hinge segment and bearing bar. Tighten hinge bolt.
F.  Use the milliohmmeter to make sure there is a maximum of 0.01 ohms between the rudder and the vertical fin.
G.  Remove rudder sling (Fig. 402).
H.  Install vertical fin hinge segments and bearing bars at rudder hinges No. 4 and 5. Do not tighten attach bolts.
I.  Install and tighten hinge bolts at hinges No. 4 and 5, then tighten vertical fin hinge segments and bearing bar attach bolts (Ref 27-21-22 R/I). 
6.  Restore Airplane to Normal (Fig. 401)
A.  Install vertical fin trailing edge seal segments covering rudder hinge locations No. 4 and 5.
B.  Check rudder hinge friction and rudder limit travel.
(1)  
If rudder power control unit is installed in fin, disconnect forward end. Move forward end right and forward so that power unit will clear rudder clevis during friction and travel checks.

(2)  
Check that all seals clear rudder nose and balance weights. Make this check with rudder deflected 5 to 8 degrees to left and to right of faired position.

CAUTION:  WHEN MOVING RUDDER SURFACE BY EXTERNAL FORCE ALWAYS USE LOADING BLOCK TO PREVENT DAMAGE TO RUDDER. APPLY EXTERNAL FORCE APPROXIMATELY 46.9 INCHES FROM RUDDER HINGE LINE BETWEEN RUDDER STATIONS 13.33 AND 31.65. DO NOT EXCEED A LOAD OF 50 POUNDS ON RUDDER AT ANY TIME.

(3)  
Use rudder loading block to slowly move rudder by hand through full travel left and right. If any sign of binding, rough spots, or excessive friction at any point of travel, correct condition and repeat check.

(4)  
Measure maximum force required to move rudder slowly left from neutral until rudder stops.

(5)  
Measure maximum force required to move rudder slowly right from neutral until rudder stops.

(6)  
If force in step (4) or (5) is greater than 25 pounds, bearing friction is excessive. Correct condition and repeat from step (2) on.

(7)  
Move rudder left and right full travel and measure travel. Required travel left and right is

23.17 +0.30 inches from neutral.
5D1 
Apr 01/97  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-21-12 Page 407 

C.  Connect rudder power control unit to fin and to rudder (Ref 27-21-91 R/I).
D.  Connect standby actuator to rudder (Ref 27-21-141 R/I).
E.  Install input rod between input crank and torque tube.
F.  Check that fin to rudder mismatch at each rib location (14 places)along each surface does not exceed allowable tolerances.
G.  Adjust fin trailing edge seals then tighten down seal retainers.
H.  Adjust fin to balance weight seals then tighten down seal retainers.
I.  Restore airplane to normal hydraulic configuration (Ref 27-21-0, MP).
J.  Test rudder hinge and power control unit bearing play, and rudder travel (Ref 27-21-0, Test Rudder Hinge and Power Control Unit Bearing Play, and Test Rudder Travel).
K.  Replace all access panels, close access doors, and install fairings.
5D1 
27-21-12 Page 408  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 20/87 

RUDDER - INSPECTION/CHECK
EFFECTIVITY
Airplanes with Graphite/Composite Rudder
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 Wear Limits (Fig. 601)
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

 Rudder Wear Limits  500 
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 2(20)