(b)
The airplane lands short of the prepared surface.
(c)
The airplane makes a landing that involves the blowing of two or more tires.
(d)
The airplane skids on the runway to make you think that damage of the airplane issuspected.
D. When the conditional inspection tells you to examine a component or area, look for the
following conditions (replace or repair components, if necessary):
(1)
Cracks
(2)
Creases or cracks in the skin or web
(3)
Skin wrinkling that crosses a line of fasteners
(4)
Pulled apart structure
(5)
Loose paint (paint flakes)
(6)
Twisted parts (distortion)
(7)
Bent components
(8)
Fastener holes that have become larger or longer
(9)
Loose fasteners
(10)
Fasteners pulled out or missing
(11)
Delaminations
(12)
Misalignment
(13)
Interference
(14)
Other signs of damage
E. Examinations are visual with minimum disassembly (without component removal) unless stated otherwise.
500
May 01/01 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 5-51-51 Page 201
2. Phase I Inspection
A. Main Landing Gear Areas
(1)
After an off-runway excursion, do the following steps:
(a)
Do a through washing of the gear with wheels and brakes removed.
(b)
All wheel/tire assemblies should be replaced when evidence of possible contamination from water, dirt, or mud in the wheel bearings exists.
(c)
All gear wheel speed transducers should be removed and inspected.
(d)
The gear must be cleaned of debris, especially under the axle sleeves and inbearings, then thoroughly lubricate before returning to service.
(e)
Ensure brakes operate, AMM 32-41-41, page 601.
(2)
Examine the main landing gear areas as follows:
(a)
Examine the main landing gear wheels and tires for damage or cracks.
1) If any of the main landing gear wheels are removed because of a blown tire, dothe steps that follow (Ref AMM 5-51-251):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 fromtire/wheel fragments
(b)
Check for wheel misalignment.
(c)
Examine the main landing gear shock-strut at the top and bottom ends for signs ofhydraulic fluid leakage.
NOTE: A small quantity of hydraulic fluid on the inner cylinder is satisfactory.
(d)
Examine the main landing gear doors and linkage for distortion, cracks, or othertypes of damage.
(e)
Examine the main gear trunnion, trunnion link, and shock strut top end for cracks, distortion, or other signs of damage.
(f)
Examine the main gear drag brace, side brace, attach fittings, and joints for distortion or cracks. 1) Inspect the downlock link assembly and downlock, 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 sidebrace assembly.
(g)
Examine the inside diameter of the drag brace fuse pins (Fig. 201, Sheet 2) and outboard end of the main landing gear beam for distortion (Fig. 201, Sheet 1). Disassembly of structure is limited to gain access to inner diameter of pins for thisinspection. Inspection of the outboard end of the main landing gear beam will be limited to external visual, unless Phase II inspections are required.
(h)
Examine the landing gear beam-to-rear-spar: 1) Attachment fittings (Fig. 201, Sheet 3) 2) Upper and lower wing skin panels around the spar attachment fittings, for the
main gear support beam and forward trunnion.
(i)
Examine the landing gear forward trunnion-to-rear-spar attach structure
(j)
Examine the landing gear aft trunnion-to-landing-gear-beam attachment. Do not remove grease seals that are present (Fig. 201, Sheet 5).
(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. 201, Sheet 3). Damage at this location indicates the trunnion link should be removed for inspection of theforward trunnion fuse bolt (Fig. 201, sheet 4). 1) Forward and aft attach bolt inspections – loosen nuts and turn or tap the bolts
inboard or outboard to ensure bolts are free to move, and are not deformed or crank shafted. 中國航空網 www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：737 AMM 飛機維護手冊 時間限制 TIME LIMITS(16)
