3)  Rotate the fuse pin. If the fuse pin is free to rotate, no damage exists.

 (c)  
Fuse pin partial removal and binding inspection, method number 3. 1) Remove the load from the joint that has the fuse pin to be

 inspected. 2) Access the fuse pin that is to be inspected. a) Remove all strut panels and doors, and open the nacelle cowlings (AMM 54-52-01/601).
 3)  Pull the fuse pin out 0.5 inches (0.127 mm). If the fuse pin is free to slide in and out of the lugs, no damage exists.
 C.  Examine the Airplane Structure
 S 042-044
 WARNING: DO THE DEACTIVATION PROCEDURE FOR THE TRAILING EDGE FLAP
_______ ACTUATION SYSTEMS. FLAP ACTUATION SYSTEMS MUST NOT BE OPERATED DURING THIS INSPECTION. FAILURE TO OBEY THIS WARNING CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
 (1)  Do the deactivation procedure for the trailing edge flap system (AMM 27-51-00/501).
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 S 042-045
 WARNING:_______ DO THE DEACTIVATION PROCEDURE FOR THE LEADING EDGE FLAP
 ACTUATION SYSTEMS.  FLAP ACTUATION SYSTEMS MUST NOT BE OPERATED
 DURING THIS INSPECTION.  FAILURE TO OBEY THIS WARNING CAN CAUSE

 INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
 (2)  
Do the deactivation procedure for the leading edge flap system (AMM 27-81-00/501).

 S 212-046

 (3)  
Do the inspections that follow:

 (a)  Examine the external surface of the lower chords and webs in the keel beam between body stations 1000 and 1480.
 NOTE: A vertically bent web of the keel beam is
____ satisfactory.
 (b)  
Examine the external surface of the fuselage above the wing, aft of station 1319.

 (c)  
Examine the external surface of the lower body between stations 1480 and 2007.

 (d)  
Examine all of the external surface of the fuselage between body stations 2007 and 2598.

 (e)  
If external damage was found in the last four steps, do the step that follows: 1) Examine all of the adjacent internal primary structure in

 the areas you can get access to.
 S 212-048
 (4)  Examine the external surfaces around the top and bottom wing-to-body attachment.
 NOTE: This includes the wing-to-body fairing, and the pressure web
____ of the canted rear spar.
 (a)  If you see external damage, examine the areas that follow: 1) The body-to-wing joints at body stations 1000 and 1241.
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 2) The landing gear beam-to-body joint at body station 1350. 3) The overwing longeron splice at body stations 1000 and 1241. 4) The drag splice fitting on the underwing at body station 1000. 5) The skin splice on the upperwing at wing buttock line
 128.5.
 S 492-049
 WARNING:_______ DO NOT GO INTO THE WING LEADING EDGE AREAS BEFORE YOU INSTALL
 THE SAFETY LOCKS.  THE LEADING EDGE FLAPS WILL RETRACT IN 7
 SECONDS.  PUT LOCKS ON ALL LEADING EDGE FLAPS THAT ARE
 EXTENDED.  THIS WILL PREVENT INJURY TO PERSONS FROM ACCIDENTAL

 FLAP OPERATION.
 (5)  
Put safety locks on the leading edge flaps (AMM 27-81-00/201).

 S 212-050

 (6)  
Examine the external surfaces of the wing at the skin splices and the upper surface of the trailing edge.

 (a)  If external damage is found, do the step that follows:
 1)  Examine all of the internal primary structure in the damaged area that you can get access to.
 S 212-051
 (7)  
Examine the wing control surfaces and attachments at wing front and rear spars.

 S 212-047

 (8)  
Do the inspections that follow:

 (a)  Examine all of the internal structure you can get access to in the fuselage, aft of the rear pressure bulkhead (body station 2360). 1) Examine the fuselage bulkheads at body stations 2360, 2484,
　
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