(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) Visually inspect for fitting distortion or damage (Fig. 201, Sheet 3).
5-51-51 May 01/01 Page 202
(m) Examine main gear torsion links including the upper and lower joints for damage ordistortion. Ensure the apex joint is secure and tight and there is no shimmy damperleakage or damage to the shimmy damper shaft.
B. Nose Landing Gear Areas
(1)
After an off-runway excursion, do the following steps:
(a)
Do a through washing of gear with wheels removed.
(b)
The gear must be cleaned of debris, especially under axle sleeves and in bearings, and thoroughly lubricated before returning to service.
(c)
All wheel/tire assemblies should be replaced when evidence of possible contamination from water, dirt, or mud in the wheel bearings exists.
(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 wellat body station 294.5.
(b)
Examine the nose landing gear outer-cylinder at the trunnion-fitting area and the drag brace and linkage. 1) Look for cracks, paint that has flaked, and bent parts. 2) Look for fasteners that have pulled out, or are missing.
(c)
Examine the landing gear wheels and tires for damage or cracks. 1) If any landing gear wheels are removed because of a blown tire, do the following steps (Ref AMM 05-51-54):
a) Examine the nose wheel structure for cracks.
b) Examine the nose wheel bearings for smooth operation (no roughness).
(d)
Check for wheel misalignment.
(e)
Examine the nose 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.
(f)
Examine the nose landing gear outer cylinder for distortion, cracks, paint that hasflaked, or other types of damage.
(g)
Examine bolted connections, specifically trunnions (attaching upper end of outercylinder and upper end of upper drag brace), and both upper and lower drag bracesegments, attach lugs, and pins.
(h)
Examine lock links, torsion links, and torsion link joints including the apex joint. Ensure all joints including nuts, retaining pins, and cotter pins are secure.
C. Fuselage
(1)
Examine the upper and lower fuselage skin panels forward and aft of the wing for buckles, wrinkles, or damage.
NOTE: Permanent wrinkles frequently occur on the lower side of the fuselage skins aft ofSTA 727.
(2)
If you found wrinkles on the skin panels and you did not know they were there before, make an internal inspection.
NOTE: If the wrinkles were there before, make a careful inspection of the wrinkles forcracks.
(3)
Examine the keel beam chords, stiffeners, webs and splices at station 663 thru 727A fordistortion, buckled, or damaged panels and loose fasteners.
(a) Make sure the fasteners are installed in the correct positions.
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May 01/01 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 5-51-51 Page 203
D. Wing
(1)
Examine the strut-to-wing fairing panels on the upper and lower nacelle for buckling, cracks, and loose fasteners.
(a) Make sure the fasteners are installed in the correct positions.
(2)
Examine the wing leading edge fairing for displacement, fastener hole elongation, or tear-out, skin cracks, and loose fasteners.
(a) Make sure the fasteners are installed in the correct positions.
3. Phase II Examination
A. Examine the Airplane Structure
(1)
Lift the airplane on jacks at the wing and fuselage jack points (Ref 07-11-11).
(2)
Retract and then extend the main and nose landing gear with the normal system(Ref 32-32-00 and Ref 32-33-00) to make sure there is no interference, misalignment, ordistortion.
(3)
Retract and then extend the main and nose landing gear with alternate manual system(Ref 32-34-00 and Ref 32-35-00) to make sure there is no interference, misalignment, ordistortion.
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