(a) Make sure the fasteners are installed in the correct positions.
(4)
Examine the bulkheads at body stations 294.5 and 360 and the fuselage structure immediately outboard of the nose wheel well for buckling, flaking paint, cracks, and loose fasteners.
NOTE: You can examine the forward side if you use the access holes in the sidewalls ofthe nose wheel well. You can examine the aft side of the bulkhead at station
294.5 from the electronics compartment.
(a) Make sure the fasteners are installed in the correct positions.
(5)
Examine the wheel well of the nose landing gear for buckling, flaking paint, cracks, and loose paint.
(a) Make sure the fasteners are installed in the correct positions.
(6)
Make sure there are no loose fasteners in the web of the nose wheel well near the trunnion support fittings.
(a) Make sure the fasteners are installed in the correct positions.
(7)
Examine the keel beam chords, stiffeners, webs, and splices at station 540 thru 727A fordistortion, buckled or damaged panels and loose fasteners.
(a) Make sure the fasteners are installed in the correct positions.
(8)
Examine the trunnion support fitting at body station 706 for the main landing gear forcracks and bolt distortion.
(a) Make sure the fasteners are installed in the correct positions.
(9)
If you find wrinkles frequently occur on the lower side of the fuselage skin aft of STA 727. If the wrinkles were there before, you must make a careful inspection for cracks.
F. Wings
(1)
Examine the wings, nacelles, and upper and lower nacelle strut-to-wing fairing for fuel orother fluid leaks.
(2)
Examine the wing ribs along the aft side of the rear spar, WBL 92.5 and 114.0 for cracks.
(3)
Examine the upper and lower trailing edge panels and the airplane structure for damage.
NOTE: Make sure you examine the area near the main landing gear beam carefully.
(4)
Examine the inboard and out board trailing edge flaps, flap tracks, drive screws, linkagesand fairings for sheared rivets and structure damage.
(5)
Examine the flap track bolts on the outboard trailing edge flap for crankshafting when the flaps touch the ground.
(6)
Examine the flap track bolts on the inboard trailing edge flap for crankshafting when the flaps touch the ground.
(7)
Do the task to make and inspection of the engine after a hard landing (Ref 71-00-00, I/C).
(8)
Do an inspection of the forward and aft engine mounts on the engine (Ref 71-20-00).
(9)
Do an inspection of the aft flange on the turbine frame.
(10)
Do the task to inspect the engine nacelle when it touched the ground (Ref 5-51-62).
(11)
Examine the flight controls to make sure the movement of travel is free and the cable tension is satisfactory.
(12)
Do a check of the rigging for the steering mechanism of the nose landing gear (Ref 32-51-00).
500
5-51-51 Page 210 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/01
500
May 01/01 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 5-51-51 Page 211
ENGINE SEIZURE/ENGINE SURGE/UNCONTAINED FAILURES - MAINTENANCE PRACTICES (CONDITIONAL INSPECTION)
1. General
A. Engine Malfunction Conditions
When an engine malfunctions, a structural inspection is necessary if:
–
Unusually high engine loads (high torque) occurred and;
–
The engine must be removed for repairs.
Malfunctions which require structural inspections are:
–
Engine blade fractures that caused high vibrations or compressor surges.
–
Rotors, disks, airseals that turn, spacers, or shafts that fractured.
–
A malfunction that will not allow the fan or compressor to turn easily.
B. Inspection
(1)
The inspection is divided into two phases (Phase 1 and Phase 2).
(2)
Do the Phase 1 inspection before the next flight.
(3)
Do the Phase 2 inspection if:
–
Unusually high engine loads (high torque) were possible, and;
–
The engine must be removed for repairs.
NOTE: If you do not find damage during the Phase 1 inspection, the Phase 2 inspection is not necessary.
C. Repairs and Replacements
(1)
When this procedure tells you to "examine" a part, remove (if necessary) and look for these conditions:
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737 AMM 飞机维护手册 时间限制 TIME LIMITS(19)
