NOTE:  If any external damage is observed, the elevator spar web should be examined for distortion, flaking paint, cracks and pulled or missing fasteners.

(d)  
Deleted.

(e)  
Deleted.

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NOTE:  If any unusual handling conditions are observed, check all flight controls for force requirements and cable tensions. (Refer to applicable sections of Chapter 27, FLIGHT CONTROLS.)
C.  Exceeding Design Speed
(1)  The maximum design speed of the airplane for normal flight operation is the Maximum Operating Speed as defined in Section 1, "LIMITATIONS" of the airplane Flight Manual. An aural warning horn activates at this speed condition. If the airplane exceeds the Maximum Operating Speed by 20 knots or more, a structural examination is required.
3.  Examine Airplane Structure
A.  General
(1)  If severe buffeting or excessive flight load factors occur as a result of turbulence, excessive speeds or unusual maneuvers, the inspections defined in steps B thru P must be performed.
B.  Fuselage exterior surface for distortion, flaking paint, cracks and pulled or missing rivets. Particular attention should be paid to the keel beam lower chords and webs between body stations 540 and 727, the area above the wing aft of station 639, the lower body between stations 727 and 927, and the whole area between stations 927 and 1088.
NOTE:  If any exterior damage is observed, examine all accessible internal primary structure in affected area for distortion or buckling, cracks, flaking paint and pulled or missing fasteners.
Wrinkles in keel beam vertical web are considered normal. Permanent wrinkles often occur in the lower side fuselage skins aft of Sta. 727. Interior inspection is required if such wrinkles are found and not known to be pre-existing. If wrinkles were pre-existing, they must be closely inspected for cracks.
C.  Accessible interior structure in fuselage, aft of rear pressure bulkhead, for distortion, cracks, flaking paint and pulled or missing fasteners. Check the following: Fuselage bulkheads and fin and stabilizer attachment fittings at body stations 1016, 1088, and 1156; horizontal stabilizer center section hinge fittings; horizontal stabilizer front and rear spar terminal fittings; and stabilizer jackscrew mechanism mount fittings and support structure. Check jackscrew and hinges for evidence of binding.
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D.  Exterior surface around top and bottom of wing root area, including wing to body fairing, for distortion, cracks and pulled or missing fasteners.
NOTE:  If any exterior damage is observed, the body to wing joints at body stations 540 and 664 and the upper wing skin splice at BL 70.85 must be examined for distortion, flaking paint, cracks and pulled or missing fasteners.
E.  Wing exterior surfaces, checking particularly at skin splices for misalignment and pulled or missing rivets, and along trailing edge upper surface for skin buckles.
NOTE:  If any exterior damage is observed, all accessible internal primary structure in the affected area must be examined for distortion, buckling, cracks, flaking paint and pulled or missing fasteners.
F.  Wing control surfaces for cracks, pulled or missing rivets and for evidence of binding.
G.  Horizontal stabilizer exterior surface for evidence of buckling, checking particularly at skin splices for cracking, yielding and pulled or missing fasteners.
NOTE:  If any exterior damage is observed, the spars and all accessible internal primary structure in the affected area must be examined for distortion or buckling, cracks, flaking paint and pulled or missing fasteners.
H.  Elevator and tab external surfaces for cracks, pulled or missing fasteners, and hinge bearings and actuator bearings for evidence of binding.
NOTE:  If any external damage is observed, the elevator spar web should be examined for distortion, flaking paint, cracks and pulled or missing fasteners.
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I.  Fin and rudder in same manner as horizontal stabilizer and elevator in par. G. and H.
J.  Flight controls for freedom of movement.
NOTE:  If any unusual handling conditions are observed, check all flight controls for force requirements and cable tensions. (Refer to applicable sections of Chapter 27, FLIGHT CONTROLS.)
K.  Engine-to-wing fairing panels and lower surface of engine cowlings for buckling, cracks, pulled or missing fasteners, or any unusual external condition.
　
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