FUSELAGE INSPECTION

TM 1-1520-238-23 2-36 Change 7 2.11. FUSELAGE INSPECTION d. Check nontransparent barrier armor assembly for cracks, tears, punctures, debonding, and delaminat- ing. e. Check structural attachment points for wear caused by movement. None allowed. 2.11.4. Transmission Deck a. Check for corrosion, holes, cracks, tears, and loose or missing fasteners. b. Check catwalk for corrosion, cracks, loose or missing fasteners, and condition of anti-skid coating. c. Check structural attachment points for wear caused by movement. None allowed. d. Check rotor support mast support base and transmission rotor support strut assemblies for damage or corrosion. e. Check aft equipment bay area. (1) Open access doors L200, L325, R200, T250L, T250R, T290L, and T290R (para 2.2). (2) Identify any leak source and repair. (3) Clean area if fluid or dirt has accumulated in sufficient quantity to form pools, puddles, or excessive deposits (para 1.41). NOTE Spraying/misting is evidenced by a film of oil covering a general area. Film may be on upper or lower surfaces of an area. In general, oil leakage shall be kept to a minimum, if not completely stopped. (4) Clean area if excessive oil/fuel is detected and source is unknown (para 1.47). Then conduct a 15 MINUTE ground run. Immediately check for leaks. Any fuel leaks must be repaired prior to aircraft operation. Any oil leak, static or dynamic, causing pooling/puddling or spraying/misting must be repaired prior to next flight. (5) Secure access doors L200, L325, R200, T250L, T250R, T290L, and T290R (para 2.2). 2.11.5. General (Fittings, Casting, Forging) NOTE �Nicks, scratches, and gouges which do not develop into cracks are generally acceptable if sharp edges can be blended and damage does not interfere with operational characteristics of affected components. If blending is required, remove minimal material to smooth off sharp edges. �Cracks are generally not acceptable. Use approved nondestructive testing methods to determine if cracks exist. END OF TASK