83-23-02 R1: Flap Hinges Attach Brackets

83-23-02 R1 SIAI-MARCHETTI: Amendment 39-4850. Applies to all Model S.205-18/F, S.205-20/F, S.205-18/R, S.205-20/R, S.205-22/R, S.208 and S.208-A (all serial numbers) series airplanes certificated in any category. Compliance: Required as indicated, unless previously accomplished within the last 50 hours time-in-service. To preclude the malfunction of the flap system, accomplish the following: (a) Before further flight and thereafter at intervals not to exceed 50 hours time-in- service from the last inspection, remove inspection panel Part Number (P/N) 205-3-022-17 and visually inspect, using a light and mirror, the rear side of each wing rear spar around the attachment holes of the flap hinges attach brackets, P/N 205-3-010-01, P/N 205-3-010-02, P/N 205-3-010-03 and P/N 205-3-010-04, in accordance with the INSTRUCTIONS FOR INSPECTION described in SIAI-Marchetti Service Bulletin 205B57, R.A.I. approved December 6, 1983. (1) If no cracks are found or if the cracks do not exceed any of the criteria listed below, reinspect per paragraph (a) every 50 hours time-in-service. (i) Four (4) cracked holes on any one wing rear spar, or (ii) a single crack extending more than 15 mm. (19/32 in.) from the center of a flap hinge attachment hole, or (iii) two (2) cracked holes at a single flap hinge attachment location. (2) If cracks are found that exceed the limits stated in paragraph (a) (1) of this AD, and if no one single crack extends more than 20 mm. (25/32 in.) from the center of a flap hinge attachment hole, prior to further flight modify the rear spar on both wings in accordance with the INSTRUCTIONS FOR MODIFICATION described in SIAI-Marchetti Service Bulletin 205B57, R.A.I. approved December 6, 1983. (3) If any one single crack extends more than 20 mm. (25/32 in.) from the center of a flap hinge attachment hole, prior to further flight contact the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium, for appropriate corrective action to be accomplished before the airplane is returned to service. (b) The interval between repetitive inspections required by paragraph (a) of this AD may be increased to 100 hours time-in-service upon incorporation of the modification described in SIAI-Marchetti Service Bulletin 205B57. (c) The intervals between the repetitive inspections, required by this AD, may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where the inspection, as specified by this AD, may be accomplished. (e) An equivalent means of compliance with this AD may be used, if approved by the Manager, Aircraft Certification Staff, AEU-100, FAA, c/o American Embassy, Brussels, Belgium. This amendment becomes effective on April 30, 1984, to all persons except those to whom it has already been made effective by priority letter from the FAA dated November 10, 1983.