(b)
Lift the nose of the airplane with jacks (Ref 7-11-1).
(c)
If you found tire damage in Phase 1, do the steps that follow.
1) Remove and examine the wheel structure.
2) Examine the axle.
(d)
Examine all structural components of the nose landing gear and carefully examine the components that follow: 1) Shock strut 2) Torsion links 3) Drag strut 4) Lock links 5) Drag brace link 6) The attach nut of the orifice support tube (signs of fluid leakage).
(e)
Examine the wheel well area and carefully examine the parts that follow:
1) Web (the left and right side walls)
2) Aft bulkhead
3) Trunnion attachments
4) Drag strut attachments
(f)
Examine the wheel well bulkheads and fuselage outboard of nose wheel well at (Body Stations 294.5 and 360).
NOTE: You can do this inspection on the forward side through the access holes in the sidewalls of the nose wheel well. Examine the aft side of the bulkhead at Body Station 294.5 from the electronics compartment.
(g)
If one or more of the conditions that follow occurred; remove, disassemble, and examine all parts of the shock strut (Ref 32-21-11). 1) The shock strut pressures were sufficiently low to cause damage. 2) The hydraulic fluid levels were sufficiently low to cause damage. 3) You found damage to one or more of the parts during your inspection of the
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landing gear.
NOTE: Do not remove the orifice support tube to examine it.
(h)
Make sure that steering system is adjusted and operates correctly (Ref 32-51-0).
(i)
Make sure the nose landing gear retracts and extends correctly (Ref 32-33-0).
(j)
Lower the nose of the airplane from the jacks (Ref 7-11-11).
(3) Fuselage Inspection
NOTE: If you find external damage to the fuselage, always examine the adjacent internal structure.
(a)
Examine the lower fuselage structure.
NOTE: Examine carefully in the area below the body crease from Body Station 727 to 100 inches aft.
(b)
Examine carefully these components (Body Stations 540 through 727A):
1) Keel beam chords
2) Stiffeners
3) Webs and splices
(c)
Also examine carefully the top of the fuselage between S-6 left and S-6 right (Body Stations 540, 664, and 727).
(d)
Examine the upper and lower fuselage skin panels forward and aft of the wing.
NOTE: Permanent wrinkles frequently occur on the lower side of the fuselage skins aft of Body Station 727. An internal inspection is necessary if you found wrinkles that were not there before the landing. Examine the wrinkles carefully for cracks.
(e)
Examine the wing-to-fuselage joints (Body Stations 540 and 664).
(f)
Examine the fuselage skin joints above the landing gear beam.
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ICE OR SNOW CONDITION – CONDITIONAL INSPECTION
1. Ice or Snow Condition
A. Whenever Icing or Snow Conditions Exist, Prior to Flight:
(1) Examine for the following:
(a)
Fuselage, wings, control surfaces, balance panel areas and hinge points for ice and snow. If snow or ice exists, refer to 12-50--, Cold Weather Maintenance.
(b)
Engine inlet cowl for ice and snow, secondary inlet doors for freedom of movement, and the first stage compressor for freedom of rotation (Ref 71-09-111, Maintenance Practices).
(c)
Light coatings of frost up to 1/8-inch thick on lower wing surfaces only are permissible; however, all control surfaces, tab surfaces and balance panel cavities, wing leading edge slats, and wing upper surface must be completely free of snow or ice before takeoff (Ref 12-50-0, Cold Weather Operation).
(d)
If thrust reversers have been operated, check actuator locks for ice entrapment.
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TOILET OVER-SERVICING – MAINTENANCE PRACTICES (CONDITIONAL INSPECTION)
1. General
A. This procedure supplies the tasks that follow:
(1)
Toilet over-servicing conditional inspection (forward toilet).
(2)
Toilet over-servicing conditional cleaning (forward toilet).
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