95-24-04: Rear Spar Web

95-24-04 AIRBUS INDUSTRIE: Amendment 39-9436. Docket 95-NM-04-AD. Applicability: All Model A300 and 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 use the authority provided in paragraph (f) 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 request should 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 fatigue-related cracking in the rear spar web of the wings, which could result in reduced structural integrity of the wing, accomplish the following: (a) For Model A300 B2 series airplanes: Prior to the accumulation of 18,000 total flight cycles or within 1,400 flight cycles after the effective date of this AD, whichever occurs later, perform a high frequency eddy current (HFEC) inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300-57-0213, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles. (b) For Model A300 B4-103, and B4-2C series airplanes: Prior to the accumulation of 19,000 total flight cycles or within 1,400 flight cycles after the effective date of this AD, whichever occurs later, perform an HFEC inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300-57-0213, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 6,000 flight cycles. (c) For Model A300 B4-200 series airplanes: Prior to the accumulation of 17,000 total flight cycles or within 1,400 flight cycles after the effective date of this AD, whichever occurs later, perform an HFEC inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300-57-0213, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles. (d) For Model A300-600 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, and F4-605R series airplanes: Prior to the accumulation of 21,600 flight cycles, perform an HFEC inspection to detect cracks at the aft spar web of the wings, in accordance with Airbus Service Bulletin A300-57-6059, dated August 12, 1994. Repeat the inspection thereafter at intervals not to exceed 5,700 flight cycles. (e) If any crack is detected during any inspection required by this AD, prior to further flight, repair the crack in accordance with Airbus Service Bulletin A300-57-0213, dated August 12, 1994, or Airbus Service Bulletin A300-57-6059, dated August 12, 1994, as applicable; or in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (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. 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 fromthe 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 inspections and repair shall be done in accordance with Airbus Service Bulletin A300-57-0213, dated August 12, 1994, or Airbus Service Bulletin A300-57-6059, dated August 12, 1994, as applicable. 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. (i) This amendment becomes effective on December 27, 1995.