97-16-06: Inspect Forward Fitting Of Frame 47

97-16-06 AIRBUS INDUSTRIE: Amendment 39-10097. Docket 95-NM-228-AD. Applicability: All Model A300-600 series airplanes, certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (f) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent fatigue crackingon the forward fitting of frame 47 at the level of the last fastener of the external angle fitting, which could result in reduced structural integrity of the airframe, accomplish the following: (a) Perform a rotating probe inspection to detect cracks of the attachment holes H and I in accordance with Airbus Service Bulletin A300-57-6049, dated September 9, 1994, at the applicable time specified in paragraph (a)(1) or (a)(2) of this AD. (1) For airplanes on which Airbus Modification 10454 (reference Airbus Service Bulletin A300-57-6050) has not been installed: Inspect prior to the accumulation of 13,800 total landings, or within 750 landings after the effective date of this AD, whichever occurs later. (2) For airplanes on which Airbus Modification 10454 (reference Airbus Service Bulletin A300-57-6050) or Airbus Modification 10155 has been installed: Inspect prior to the accumulation of 18,700 total landings, or within 750 landings after the effective date of this AD, whichever occurs later. (b) If no crack is found, prior to further flight, install a new fastener in accordance with Airbus Service Bulletin A300-57-6049, dated September 9, 1994. Repeat the rotating probe inspection thereafter at intervals not to exceed 5,600 landings. (c) If any crack in hole I is found to be greater than 0.196 inches in length and/or depth, prior to further flight, repair it in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (d) If any crack in hole H is found to be greater than .062 inches in length, prior to further flight, repair it in accordance with a method approved by the Manager, Standardization Branch, ANM-113. (e) If any crack in hole H or hole I is found to be less than or equal to the limits specified in paragraphs (c) and (d) of this AD, prior to further flight, repair it in accordance with Airbus Service Bulletin A300-57-6049, dated September 9, 1994. (f) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (g) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (h) The inspection, installation, and certain repair shall be done in accordance with Airbus Service Bulletin A300-57-6049, dated September 9, 1994. This incorporationby reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (i) This amendment becomes effective on September 5, 1997.