H. Loosen all fin trailing edge seals and push seals to maximum forward position.
I. Position rudder to fin using rudder sling. Use guy ropes to keep rudder from striking structure.
J. Coat hinge pivot bolts with corrosion preventive compound.
5. Install Rudder (Fig. 401)
A. Install and tighten hinge pivot bolts at rudder hinges No. 1, 7, 2, 3, and 6, in that order (Ref 27-21-21 R/I).
B. Install bonding jumpers at hinges No. 2 and 7.
C. Tighten rudder hinge segment internal-wrenching attach bolts at rudder hinges No. 2, 3, 6, and 7 (Ref 27-21-21 R/I).
D. Use the milliohmmeter to make sure there is a maximum of 0.01 ohms between the rudder and the vertical fin.
E. Remove rudder sling assembly (Fig. 402).
F. Install fin hinge segments and rudder hinge segments at rudder hinge locations No. 4 and 5. Do not tighten attach bolts.
G. Install and tighten hinge pivot bolts at rudder hinges No. 4 and 5, then tighten fin hinge segment and rudder hinge segment attach bolts (Ref 27-21-21 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 (Section A-A, Fig. 401). 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 (Fig. 401, details D and E). Make this check with the rudder deflected 5 to 8 degrees to left and to right of faired position.
(3)
Use rudder loading block to slowly move rudder by hand through full travel left and right. If there is any sign of binding, rough spots, or excessive friction at any point of travel, correct the condition and repeat check.
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.
(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 too high. Correct this condition and repeat from step (2) on.
(7)
Move rudder left and right full travel and measure travel. Minimum required travel left and right is 23.17 inches from neutral.
500
Apr 01/97 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-11 Page 407
C. Reconnect rudder power control unit to fin and to rudder (AMM 27-21-91/401).
D. Connect standby actuator to rudder (AMM 27-21-141/401).
E. Check that fin to rudder mismatch at each rib location (14 places) along each surface does not exceed allowable tolerances (Fig. 401, Detail E).
F. Adjust fin trailing edge seals per Detail E of Fig. 401, then tighten down seal retainers.
G. Adjust fin to balance weight seals per detail D of Fig. 401, then tighten down seal retainers.
H. Restore airplane to normal hydraulic configuration (AMM 27-21-0/201).
I. Test rudder hinge and power control unit bearing play, and rudder travel. Refer to 27-21-0, Test Rudder Hinge and Power Control Unit Bearing Play, and Test Rudder Travel.
J. Replace all access panels, close access doors, and install fairings.
500
27-21-11 Page 408 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/01
RUDDER - INSPECTION/CHECK
EFFECTIVITY
Airplanes With Aluminum/Fiberglass 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
G42359
500 Rudder Wear Limits
Jun 20/90 Figure 601 (Sheet 1) 27-21-11
Page 601
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
G08906
Rudder Wear Limits 501
27-21-11 Page 602 Figure 601 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Nov 15/76
