(c)
Nose landing gear for shock strut servicing abnormalities, such as loss of fluid or difficulty in maintaining normal pressure.
(d)
If examination per (b) and (c) give indication of damage, or if overweight landing is combined with high impact on the nose gear, remove inner cylinder and examine for distortion and cracks. Examine orifice support tube, without removing, for distortion and cracks.
(e)
If examination per (b) and (c) give no indication of damage, inner cylinder and orifice support tube examination should be made at the first convenient opportunity following report of overweight landing.
(f)
Main landing gear outer and inner cylinder lugs and main gear torsion links for cracks and visible surface distortion.
(g)
Main gear drag and side strut linkage for distortion or cracks.
(h)
Shock strut walking beam fitting and shock strut aft trunnion support fitting for cracks.
(i)
Main gear actuator walking beam and linkage fittings for distortion, cracks, nick, gauges and pulled or missing fasteners.
(j)
Main gear outer cylinder to trunnion link attach bolt, trunnion link fittings for cracks. Remove bolt, examine holes and bushing for elongation.
(k)
Main landing gear shock strut for fluid level. If fluid level is ten pints low or more, remove inner cylinder and examine for distortion or cracks. Examine orifice support tube, without removing, for obvious cracks (Refer to Chapter 32, Landing Gear for relevant steps pertaining to removal of main gear inner cylinder.
(l)
Nose and main landing gear wheel well cavities for evidence of fuel or other fluid leaks in region of landing gears.
(3)
Fuselage:
(a)
Lower fuselage structure for skin buckling, flaking paint, cracks, and pulled or missing fasteners. In particular examine area below body crease and from station 727 to 100 inches aft.
(b)
Wing to fuselage joints at stations 540 and 664 for distortion, flaking paint, cracks and pulled or missing fasteners.
(c)
Upper fuselage structure between S-6 LH and S-6 RH at station 540, 664 and 727 for buckling, distortion, flaking paint, cracks and pulled or missing fasteners.
(d)
Bulkheads at body stations 294.5 and 360, fuselage structure immediately outboard of nose wheel well for buckling, flaking paint, cracks and pulled or missing fasteners.
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NOTE: This examination can be performed on the forward side through access holes in nose wheel well side walls. Examine aft side of bulkhead at station
294.5 from the electronics compartment.
(e)
Nose landing gear wheel well for buckling, flaking paint, cracks, and pulled or missing fasteners in web of nose wheel well particularly in vicinity of trunnion support fittings.
(f)
Keel beam chords, stiffeners, webs and splices at station 540 thru 727A for distortion, buckled or damaged panels and pulled or missing fasteners.
(g)
Fuselage exterior surface for evidence of fuel or other fluid leaks.
(h)
DELETED
(i)
Permanent wrinkles often occur on lower side fuselage skins aft of STA 727. Interior inspection is required if such wrinkles are found and not know to be pre-existing. If the wrinkles were pre-existing they must be closely inspected for cracks.
(4)
Wings:
(a)
Wings, nacelles, engine-to-wing fairing for evidence of fuel or other fluid leaks.
(b)
Wing ribs along aft side of rear spar, WBL 92.5 and 114.0 for cracks.
(c)
Upper and lower trailing edge panels and structure with particular attention to main landing gear beam area.
(d)
Inboard and outboard trailing edge flaps, flap tracks, drive screws, linkages and fairings for sheared rivets and structure damage.
(e)
Inboard and outboard spoilers for sheared rivets and structure damage.
(f)
Outboard trailing edge flap track bolts for crank shafting when flaps have been in contact with ground.
(g)
Inboard trailing edge flap track bolts for crank shafting when flaps have been in contact with ground.
(5)
Nacelles:
(a) Conduct dragged engine nacelle inspection (Ref 5-51-61).
(6)
Flight Controls for freedom of movement, and specified cable tension.
(7)
Check rigging of nose landing gear steering mechanism (Ref Chapter 32, Landing Gear).
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