(2)
Examine horizontal clearance of main gear forward trunnion bearing.
(a)
Clamp dial indicator to rear spar structure near forward trunnion bearing in a position to measure horizontal clearance.
(b)
Raise main gear inner cylinder with axle jack until shock strut is approximately 1 inch from fully compressed.
(c)
Insert wood 2 x 4 between wheel and shock strut in a horizontal position.
(d)
Twist gear to take up all clearance in one direction. Set dial indicator in contact with trunnion as near as possible to forward trunnion bearing.
(e)
Set dial indicator to zero.
(f)
Rock gear torsionally by levering 2 x 4.
(g)
Read bearing clearance on dial indicator. If clearance is greater than 0.030 inch for shrink fit bearing assemblies, or 0.050 inch for threaded bearing assemblies, check wear limits per Fig. 601 and replace parts as necessary.
32-11-101 Aug 01/94
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E. Restore Airplane to Normal
(1)Remove dial indicator setup.
(2)Remove wood 2 x 4.
(3)Remove axle jack.
(4)Lower airplane and remove jacks.
(5)Service shock strut. Refer to Main Landing Gear Shock Strut Servicing, Chapter 12.
3. Main Gear Forward Trunnion Bearing Assembly Wear Limits
A. General
(1) The following data consists of an illustration and a wear limit chart. There will be no procedure given in the section for gaining access to, or removing and installing the component after inspection for wear. Refer to the specific component removal/installation for this information.
B. Main Gear Forward Trunnion Bearing Assembly Wear Limits (See figure 601.)
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Main Gear Forward Trunnion Bearing Assembly Wear Limits 500
32-11-101 Figure 601 Aug 01/94
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MAIN GEAR AXLE -APPROVED REPAIRS
1. General
A. On airplanes on which heavy braking has generated enough heat to melt the cadmium plating on the axle brake flanges, the cadmium plating may be removed to inspect base metal for heat damage. If the damage falls within given limits, the flanges may be reworked and given an inorganic protective coating.
B. Repairs to axle sleeves consists of blending out scratches, scoring and galling within limits given below. Rework on axle sleeves must be given an anticorrosive treatment. Alodine or Primer.
2. Equipment and Materials
A. Fluorescent magnetic inspection equipment
B. Abrasive Paper or Cloth-Aluminum Oxide 150-Finer or Silicon Carbide 180-Finer
C. Grease - MIL-G-25760
D. Axle Sleeve Puller -F80126-9
3. Repair Main Gear Axle
A. If installed, remove lockbolt, retaining sleeve and axle (Fig. 801).
B. Remove sleeve from axle with axle sleeve puller - F80126-9. If necessary, sleeve may be heated up to approximately 200oF.
C. Remove the Ti-Cad plating by hand sanding or by filing. Do not use power tools.
NOTE: Maximum mismatch is 0.003 inch.
D. Check flanges for evidence of cadmium embrittlement cracks by fluorescent magnetic examination technique.
NOTE: The axle may continue in service with cracks emanating from any four of the twelve fastener holes and progressing toward or to the outer periphery of the flange.
E. If cracks are found, continue to remove plating and base metal until cracks blend out.
CAUTION: DO NOT REMOVE MORE THAN 0.003 INCH OF BASE METAL.
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F. Apply inorganic protective coating. Refer to Chapter 51, Heat, Weather, and Oil Resistant Inorganic Protective Coating.
G. Apply a generous coating of grease on axle lands and install sleeve by chilling axle and heating sleeve. Refer to 737 Overhaul Manual.
NOTE: Do not remove excessive grease from inside diameter of axle sleeve after installation.
H. If lockbolt is installed, align bolt holes in axle and sleeve and install lockbolt. (See figure 801.)
I. Check diameter of bearing supports after sleeve installation. The outer diameter of small bearing support must not exceed 3.2813 inches, and outer diameter of large bearing support must not exceed 3.375 inches. (See figure 801.)
Axle Sleeves Installation 500 中國航空網 m.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：737 AMM 飛機維護手冊 起落架 LANDING GEAR(49)
