(b)

(c)

(d)

(e)

(f)

(g)

(h)

(i)

(j)

A
737-300/400/500MAINTENANCE MANUAL
Examine the main landing gear wheels and tires for damage or cracks. 1) If any main landing gear wheels are removed because of a
 blown tire, do the steps that follow (AMM 05-51-54/201):
 a) Examine the wheel structure for cracks.
 b) Examine the brake assembly for damage.
 c) Examine the wheel bearings for smooth operation (no

 roughness). d) Examine airplane structure including control surfaces
 for damage from tire/wheel fragments.Check for wheel misalignment.Examine the main landing gear shock strut at the top and bottom ends for signs of hydraulic fluid leakage.
 NOTE: A small quantity of hydraulic fluid on the inner
____ cylinder is satisfactory.
Examine the main landing gear doors and linkage for distortion,
 cracks or other types of damage.
Examine the main gear trunnion, trunnion link, and shock strut
 top end for cracks, distortion, or other signs of damage.
Examine the main gear drag brace, side brace, attach fittings
 and joints for distortion or cracks.
 1) Inspect the downlock link assembly and downlock, and the

 uplock support structure and body frame structure at the intersection of the inboard end of the reaction link and the upper end of the side brace assembly.
Examine the inside diameter of the fuse pins of the drag brace and outboard end of the main landing gear beam for distortion (Fig. 201 and 202). Disassembly of structure is limited to gain access to inner diameter of pins for this inspection. Inspection of outboard end of main landing gear beam attach bolt will be limited to external visual unless Phase II inspections are required.Examine the landing gear beam-to-rear-spar: 1) Attachment fittings (Fig. 203). 2) Upper and lower wing skin panels around the spar attachment
 fittiings for the main gear support beam and the forward
 trunnion of the gear.Examine the landing gear forward trunnion-to-rear-spar attach structure.Examine the landing gear aft trunnion-to-landing-gear-beam attachment. Do not remove grease seals that are present (Fig. 205).
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 05-51-51
 ALL  ú ú 01 Page 208 ú Nov 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 (k)  
Examine the main landing gear beam to rear spar stabilizing link for damage of the link, or crank shafting of the forward and aft attach bolts (Fig. 203). Damage at this location indicates that the trunnion link should be removed for inspection of the forward trunnion fuse bolt (Fig. 204). 1) Forward and aft attach bolt inspections - loosen nuts and

 then turn or tap the bolts inboard or outboard to ensure bolts are free to move, and are not deformed or crank-shafted.

 (l)  
Examine the main landing gear beam-to-body attachment (side-of-body support link). 1) Examine body bulkheads common to the support link,

 including the fuselage skin adjacent to the body bulkheads
 that support the inboard end of the main landing gear beam
 and side brace.
 a) Inspect for fitting distortion or damage (Fig. 203).

 (m)  
Examine main gear torsion lnks including the upper and lower joints for damage or distortions. Ensure the apex joint is secure and tight and there is no shimmy damper leakage or damage to the shimmy damper shaft.

 B. Nose Landing Gear Areas
 S 212-023
 (1)  If the following inspections are being done after an off-runway excursion, do the steps that follow:
 (a)  
Do a thorough washing of gear with wheels removed.

 (b)  
The gear must be cleaned of debris, especially under axle sleeves and in bearings, and then thoroughly relubricated before return to service.

 (c)  
All wheel/tire assemblies should be replaced when possible contamination of wheel bearings from water, dirt or mud.

 S 212-024
 (2)  Examine the nose landing gear areas as follows:
 (a)  
Examine the nose wheel well for buckled skin, paint that has flaked, and for cracks. 1) Look for fasteners that have pulled out, or are not in the

 web of the nose wheel well. 2) Look carefully in the area near the outer cylinder trunnion attach points, and the drag-strut support fittings. 3) Do an exterior examination of the fuselage skin and frame just aft of wheel well at body station 294.5.
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737-300 400 500 AMM 飛機維護手冊 TIME LIMITS/MAINTENANCE CHE(49)