747-400 MAINTENANCE MANUAL
WORN PART REPAIRABLE. CHROME PLATE TO 0.020 THICKNESS AND GRIND TO DESIGN LIMITS.
DISTANCE BETWEEN SHOULDERS OF HOUSING ASSEMBLY.
DISTANCE OVER SHOULDERS OF OUTER RACE.
ZERO CLEARANCE WHEN BEARING RETAINING NUT INSTALLED.
WORN PART REPAIRABLE. CHROME PLATE TO 0.010 THICKNESS AND GRIND TO DESIGN LIMITS.
DISTANCE BETWEEN HEAD AND SHOULDER OF BOLT PLUS POSSIBLE ONE-SIXTH TURN BACKOFF OF NUT.
WIDTH OVER OUTER FLANGES OF BUSHINGS IN TRUNNION FORK.
WORN PART REPAIRABLE. CHROME PLATE TO 0.010 UNDER HEAD OF BOLT AND GRIND TO DESIGN DIMENSIONS.
PLATING TO RUN OUT FROM 2.45 DIAMETER TO 2.33 DIAMETER.
GAP BETWEEN FLANGES OF BUSHINGS IN TRUNNION FORK.
WIDTH OVER OUTER FLANGES OF BUSHINGS IN SHOCK STRUT OUTER CYLINDER.
REPLACE WORN PARTS OR SHIM UNDER FLANGES OF BUSHINGS (0.015 MAXIMUM EACH).
GAP BETWEEN FLANGES OF BUSHINGS IN SHOCK STRUT OUTER CYLINDER.
WIDTH OVER FLANGES OF BUSHINGS IN TRUNNION FORK.
GAP BETWEEN FLANGES OF BUSHINGS IN TRUNNION FORK.
WIDTH OVER OUTER FLANGES OF BUSHINGS IN SHOCK STRUT OUTER CYLINDER.
LIMITS SHOWN MAY BE EXCEEDED PROVIDED MAXIMUM CLEARANCE IS NOT EXCEEDED.
Wing Gear Trunnion Fork Wear Limits
Figure 601 (Sheet 4)

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 ALL  ú ú 01 Page 605 ú Feb 10/89
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 WING GEAR TRUCK POSITIONING ACTUATOR - REMOVAL/INSTALLATION
___________________________________________________________
 1.  General_______
 A.  This procedure has two tasks:
 (1)  
The removal of the truck positioning actuator for the wing landing gear (referred to as the truck positioning actuator).

 (2)  
The installation of the truck positioning actuator.

 B.  
The truck positioning actuator is attached to the airplane at two location. The head end of the actuator is attached to the shock strut. And the rod end of the actuator is attached to the bellcrank. The removal and the installation procedure for the two actuators is the same.

 TASK 32-11-20-004-001
 2.  Wing Gear Truck Positioning Actuator Removal (Fig. 401)___________________________________________
 A.  References
 (1)  
AMM 09-11-00/201, Towing

 (2)  
AMM 29-11-00/201, Main Hydraulic Supply System

 (3)  
AMM 32-00-30/201, Landing Gear Door Locks

 (4)  
AIPC 32-11-02 Fig. 2

 (5)  
AIPC 32-11-20 Fig. 1

 (6)  
AIPC 32-11-21 Fig. 1

 B.  
Access

 (1)  
Location Zone
 735 Wing Landing Gear, LH
 745 Wing Landing Gear, RH

 C.  
Procedure

 S 224-034
 CAUTION: MAKE SURE THAT YOU DO NOT MOVE OR DAMAGE THE WING GEAR TRUCK
_______ SENSORS OR TARGET BRACKET. IF THE TARGET BRACKET OR SENSORS ARE MOVED, THEN THE AIRPLANE SYSTEMS MAY NOT RECOGNIZE AN IN-AIR CONDITION.
 (1)  If the sensor or target bracket is moved or damaged, then do the task to measure the wing landing gear truck sensor clearance (AMM 32-61-22/201).
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 ALL  ú ú 01 Page 401 ú Feb 18/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

SHOCK STRUT
SEE A
BOLT
BLEED SEE B VALVE
PIN END CAP
SPACER
ACTUATOR HEAD END 1
A
ACTUATOR
ROD END

1
SEE C

SPACER
PIN
BELLCRANK END CAP BOLT
INDEX
SEALANT MARKS
LUBE FITTING
COTTER PIN FWD
B
LAMINATED SHIM
C
1 LUBRICATE PER AMM 12-21-01/301 FIGURE 313
AFTER INSTALLATION
Truck Positioning Actuator Installation for the Wing Landing Gear
Figure 401

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