C. Procedure
S 042-014
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 leading edge slat system (AMM 27-81-00/201).
S 042-009
(2)
Do the deactivation procedure for the trailing edge flap system (AMM 27-51-00/201).
(3)
Do the visual examinations of the areas that follow:
S 212-010
NOTE: When you examine the honeycomb panels, look at the two sides
____ for cracks, delaminations, soft spots and core damage.
(a) The nose radome.
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(b)
The wings, for signs of hail damage to the areas that follow: 1) All horizontal surfaces. 2) Leading edges. 3) Trailing edges. 4) Panels.
(c)
The flight control surfaces.
(d)
The leading edge fairings on the horizontal stabilizer.
(e)
The leading edge fairings on the vertical stabilizer.
(f)
The external fuselage structure.
1) If signs of hail damage to the external fuselage structure is found, refer to SRM 51-10-00 for the aerodynamic smoothness and investigation and clean-up of damage.
2) Refer to SRM 51-10-00 for the aerodynamic smoothness and investigation and clean-up of damage.
(g)
The flight compartment windows, for signs of hail damage as follows: 1) Cracks. 2) Displacement of the outer window. 3) Other types of window damage.
(h)
The forward fuselage section above the flight compartment windows and the radome.
(i)
The wing tip fairings and navigation lights.
(j)
The passenger and cargo dooors.
(k)
The nacelle strut.
(l)
The nose landing gear doors.
(m)
The main landing gear doors.
(n)
The passener compartment windows for signs of hail damage as follows: 1) Cracks. 2) Displacement of the outer window. 3) Crazing. 4) Other types of window damage.
(o)
Examine the nose cowl and the engine for signs of foreign object damage.
S 222-011
(4)
The allowable damage shown in the Structural Repair Manual is to be used to define the limits of damage within each component. (SRM 51-10-00).
S 442-012
(5)
Do the reactivation procedure for the leading edge slat system. (AMM 27-81-00/201).
S 442-013
(6)
Do the reactivation procedure for the trailing edge flap system (AMM 27-51-00/201).
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APU TURBINE WHEEL SEPARATION (CONDITIONAL INSPECTION) -
_______________________________________________________ MAINTENANCE PRACTICES
_____________________
1. General_______
A. This procedure contains an inspection procedure for the airplane after there is an APU separation.
B. When there is a turbine wheel separation, the pieces can be contained within the APU, or the pieces can make a hole in the APU and cause damage to the shroud and other components.
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