747-400
MAINTENANCE MANUAL
YOU CAN REPAIR THIS PART. REFER TO THE OVERHAUL MANUAL FOR REPAIR INSTRUCTIONS GET A REPLACEMENT BUSHING. INSTALL THE BUSHING IN THE TRUNNION CLEVIS WITH AN INTERFERENCE FIT
OF 0.0008 TO 0.0029 INCH (AMM 20-11-01/401). MACHINE THE BUSHING INNER DIAMETER TO THE CORRECT DIMENSIONS WITH A 63 MICROINCH SURFACE FINISH. DO NOT MACHINE THE FLANGE SURFACES ON BUSHINGS WHICH ARE MACHINED BEFORE INSTALLATION. IF THE
BUSHINGS ARE NOT MACHINED BEFORE INSTALLATION, YOU MUST MACHINE THE FLANGE SURFACES TO THE CORRECT DIMENSIONS. IF YOU CHANGE THE BUSHING SHAPE FOR REPAIR, YOU MUST ALSO MACHINE THE FLANGE SURFACES TO THE CORRECT DIMENSIONS. THE FLANGE SURFACES MUST HAVE A 63 MICROINCH SURFACE FINISH.
THIS IS THE DISTANCE BETWEEN THE INNER EDGES OF THE TWO BUSHINGS ON THE TRUNNION CLEVIS.
THIS IS THE WIDTH OF THE ACTUATOR BEARING.
YOU MUST REPLACE THE ACTUATOR (AMM 32-34-01/401).
THIS IS THE DISTANCE BETWEEN THE BOLT HEAD AND THE BOLT EDGE PLUS A 1/6 TURN TO LOOSEN THE NUT.
THIS IS THE DISTANCE BETWEEN THE OUTER FLANGE SURFACES OF THE BUSHINGS IN THE TRUNNION CLEVIS.
THIS IS FOR A TRUNNION CLEVIS WITH A DISTANCE OF 3.620 INCHES BETWEEN ITS OUTER SIDES.
THIS INFORMATION IS NOT AVAILABLE NOW.
THIS IS THE DISTANCE BETWEEN THE OUTER FLANGE SURFACES OF THE BUSHINGS IN THE SUPPORT FITTING.
THIS IS THE DISTANCE BETWEEN THE OUTER FLANGE SURFACES OF THE BUSHINGS IN THE OUTER CYLINDER.
GET A REPLACEMENT BUSHING. DRILL A 0.4688 TO 0.4728-INCH DIAMETER HOLE IN THE BUSHING HALVES.
THIS HOLE MUST ALIGN WITH THE KEY IN THE SUPPORT FITTING AND THE SUPPORT FITTING CAP. MAKE SURE
THE KEY IS 0.005 TO 0.010 INCHES BELOW THE INNER DIAMETER OF THE BUSHING. YOU CAN FILE THE KEY
IF NECESSARY. REFER TO AMM 20-11-01/401 WHEN YOU INSTALL THE BUSHING HALVES. DO NOT PUT PRIMER
IN THE GREASE HOLES. MARK THE BUSHINGS AS LEFT OR RIGHT AND MARK THE BUSHING HALVES AS UPPER OR
LOWER.
THIS IS THE DISTANCE BETWEEN THE INBOARD SURFACES OF THE TWO TRUNNION PINS.
THE MEASURED LIMIT CAN BE MORE THAN THE PERMITTED LIMIT IF THE MEASURED CLEARANCE IS NOT MORE
THAN THE MAXIMUM CLEARANCE.
THIS IS THE DISTANCE BETWEEN INNER FLANGE SURFACE OF THE BUSHINGS IN THE SUPPORT FITTING.
Wear Limits For the Nose Landing Gear
Figure 601 (Sheet 3)
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
C22794
A
747-400 MAINTENANCE MANUAL
B. Procedure
S 206-010
(1)
Do an external inspection of the components on the nose landing gear.
(a)
Examine the shock strut, the drag strut, the drag braces, and the tripod braces for corrosion and damage.
(b)
Examine all of the pin connections on the nose landing gear for corrosion and damage.
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32-21-01
ALL ú ú 01 Page 606 ú Oct 10/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
NOSE LANDING GEAR SHOCK STRUT - MAINTENANCE PRACTICES
_____________________________________________________
1. General_______
A. This procedure has two tasks:
(1)
An inspection for seal leaks
(2)
Inspection for scraper rings and replacement of scraper rings with optional split scraper rings.
B.
This procedure introduces on optional split scraper ring which can be used to replace the damaged scraper ring on the gear without the removal of the gear or disassembly of the gear. Also, this procedure has two quick checks to examine the scraper ring without the removal of the gear or disassembly of the gear.
TASK 32-21-02-202-019
2. Nose Landing Gear Shock Strut Seal Leak Inspection__________________________________________________
A. General
(1) This task gives the instructions to make sure a shock strut is serviceable when you find fluid leakage on the inner cylinder.
NOTE: During the initial landing cycles of a new landing gear, thin
____ dark olive-green streaks on the shock strut frequently occur. This condition is okay. The petrolatum and grease that we use during shock strut assembly cause these streaks. These streaks will stop after more landing cycles occur. These streaks are different from the red color streaks that are the indication of strut fluid leakage.
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