(2)
AMM 27-11-00/001, Aileron and Aileron Trim Control System
(3)
AMM 27-21-00/001, Rudder and Rudder Trim Control System
(4)
AMM 27-31-00/001, Elevator and Tab Control System
(5)
AMM 27-51-00/201, Trailing Edge Flap System
(6)
AMM 27-61-00/001, Spoiler Control System
(7)
AMM 27-81-00/201, Leading Edge Flap and Slat Control System
B. Procedure
S 862-001
WARNING: DO THE DEACTIVATION PROCEDURE FOR THE FLAP/SLAT ACTUATION
_______ SYSTEMS. INJURY TO A PERSON OR DAMAGE TO EQUIPMENT CAN OCCUR IF THE FLAPS/SLATS MOVE. FLAP/SLAT ACTUATION SYSTEMS MUST NOT BE OPERATED DURING THIS INSPECTION. FAILURE TO OBEY CAN CAUSE INJURY TO PERSONS.
(1)
Do the deactivation procedure for the trailing edge flap system (AMM 27-51-00/201).
S 862-002
(2)
Do the deactivation procedure for the leading edge slat system (AMM 27-81-00/201).
S 212-003
(3)
Do the examinations that follow:
(a) Examine the external surface of the fuselage for distortion, paint that has flaked, and for cracks. Also look for fasteners that have pulled out or are not there. 1) Examine these areas carefully:
a) The keel beam between stations 540 and 727 b) The area above the wing aft of station 639
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c) The bottom fuselage between stations 727 and 927 d) The fuselage between station 927 and 1088.
2) If you find any damage, examine the internal structure in that area. a) Look for distortion, buckling, cracks, paint that has
flaked, unsatisfactory fasteners and fasteners that are not there.
NOTE: Small distortions or buckling in the keel beam
____
are satisfactory.
(b) Examine all of the internal structure of the fuselage, section 48 that you can get access to. Look at the structure from the rear pressure bulkhead to the aft end of the airplane. Look for distortions, paint that has flaked, and cracks. Also look for fasteners that have pulled out or are not there. 1) Examine these areas carefully:
a) The aft fuselage bulkheads b) The fin attach fittings c) The stabilizer attach fittings (Stations 1016, 1088 and
1156) d) The horizontal stabilizer center section e) The stabilizer hinge fittings f) The terminal fittings for the front and rear spar of
the horizontal stabilizer g) The stabilizer jackscrew-mechanism mount fittings and support structure 2) Look at the jackscrew and hinges for signs of binding.
(c) Examine the external surfaces around the top and bottom wing-to-body attachment. This includes the wing to body fairing, and the rear spar web. Look for distortion, cracks, badly chafed areas, and fasteners that have pulled out or are not there. 1) If you see external damage, examine the body-to-wing
joints, and the landing gear beam-to-body joints. Also examine the upper-wing skin splice for distortion, paint that has flaked, cracks, and for fasteners that have pulled out or are not there.
WARNING: DO NOT ENTER THE WING LEADING EDGE AND TRAILING EDGE AREAS
_______ BEFORE YOU INSTALL SAFETY LOCKS. THE LEADING EDGE SLAT AND TRAILING EDGE FLAP SAFETY LOCK PROCEDURES ARE FOUND IN AMM 27-81-00 AND AMM 27-51-00. THIS WILL PREVENT INJURY TO PERSONS FROM ACCIDENTAL FLAP/SLAT OPERATION.
(d) Examine the external surfaces of the wing at the skin splices. Look for misalignment and for rivets that have pulled out or are not there. 1) Examine the external surface of the top of the wing
trailing edge for buckles in the skin.
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