95-20-02: Rear Spar

95-20-02 AIRBUS INDUSTRIE: Amendment 39-9380. Docket 94-NM-56-AD. Applicability: Model A300-600 series airplanes; having manufacturer's serial numbers (MSN) 252 through 553 inclusive; and on which Airbus Industrie Production Modification No. 07601 has not been accomplished prior to delivery; 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 use the authority provided in paragraph (d) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a requestshould include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent degradation of the structural integrity of the airframe due to cracks in the rear spar, accomplish the following: NOTE 2: Accomplishment of the inspections and repair of cracking in accordance with Airbus Industrie Service Bulletin A300-57-6017, dated November 22, 1993, prior to the effective date of this AD, is acceptable for compliance with the applicable action specified in this amendment. (a) Perform a high frequency eddy current (HFEC) rototest inspection to detect cracks in certain bolt holes where the main landing gear (MLG) forward pick-up fitting and MLG rib 5 aft are attached to the rear spar, in accordance with Airbus Industrie Service Bulletin A300- 57-6017, Revision 1, (includes Appendix 1), dated July 25, 1994. NOTE 3: This service bulletin also references Airbus Industrie Service Bulletin A300- 57-6020, dated November 22, 1993, as an additional source of service information. (1) For airplanes that have accumulated 17,300 total landings or less as of the effective date of this AD: Inspect prior to the accumulation of 17,300 total landings, or within 1,500 landings after the effective date of this AD, whichever occurs later. (2) For airplanes that have accumulated 17,301 or more total landings, but less than 19,300 total landings as of the effective date of this AD: Inspect within 1,500 landings after the effective date of this AD. (3) For airplanes that have accumulated 19,300 or more total landings as of the effective date of this AD: Inspect within 750 landings after the effective date of this AD. (b) If no crack is found during the inspection required by paragraph (a) of this AD, repeat that inspection thereafter at the time specified in either paragraph (b)(1) or (b)(2) of this AD, as applicable. (1) For airplanes on which Airbus Industrie Modification 07716 (as described in Airbus Industrie Service Bulletin A300-57-6020) has not been accomplished, inspect at the time specified in paragraph (b)(1)(i) or (b)(1)(ii) of this AD, as applicable. (i) For airplanes having MSN 465 through 553 inclusive: Repeat the inspection at intervals not to exceed 13,000 landings. (ii) For airplanes having MSN 252 through 464 inclusive: Repeat the inspection at intervals not to exceed 8,400 landings. (2) For airplanes on which Airbus Industrie Modification 07716 has been accomplished, inspect at the time specified in either paragraph (b)(2)(i) or (b)(2)(ii) of this AD, as applicable. (i) For airplanes having MSN 465 through 553 inclusive: Repeat the inspection at intervals not to exceed 11,800 landings. (ii) For airplanes having MSN 252through 464 inclusive: Repeat the inspection within 10,700 landings following the initial inspection required by paragraph (a) of this AD, and thereafter at intervals not to exceed 7,500 landings. (c) If any crack is found during the inspection required by either paragraph (a) or (b) of this AD, prior to further flight, accomplish the requirements of either paragraph (c)(1) or (c)(2) of this AD, as applicable. (1) For airplanes on which Airbus Industrie Modification 07716 has not been accomplished: Oversize the bolt hole by 1/32 inch and repeat the HFEC inspection required by paragraph (a) of this AD, in accordance with Airbus Service Bulletin 300-57-6017, Revision 1, dated July 25, 1994. After accomplishing the oversizing and HFEC inspection, repeat the inspection as required by paragraph (b) of this AD at the applicable schedule specified in that paragraph. (i) If no cracking is detected, install the second oversize bolt in accordance with the service bulletin.(ii) If any cracking is detected, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (2) For airplanes on which Airbus Industrie Modification 07716 has been accomplished: Repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113. After repair, repeat the inspections as required by paragraph (b) of this AD at the applicable schedule specified in that paragraph. (d) 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. 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 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (e) 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. (f) The inspections and installation shall be done in accordance with Airbus Industrie Service Bulletin A300-57-6017, Revision 1, (includes Appendix 1), dated July 25, 1994. This incorporation by 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. (g) This amendment becomes effective on November 9, 1995.