AD 95-18-08

95-18-08 AIRBUS INDUSTRIE: Amendment 39-9355. Docket 95-NM-03-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 use the authority provided in paragraph (b) 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 reduced structural integrity of the wing, accomplish the following:

(a) Prior to the accumulation of 24,000 total flight cycles since date of manufacture of the airplane, or within 750 flight cycles after the effective date of the AD, whichever occurs later, perform a detailed visual inspection to detect cracks in the bottom skin of the wing in the area of the cut out for the pylon rear attachment fitting, in accordance with Airbus Service Bulletin A300-57-6028, Revision 3, dated September 13, 1994. Repeat the inspection thereafter at intervals not to exceed 9,000 flight cycles. If any crack is detected, prior to further flight, repair the wing bottom skin in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.

(b) An alternative method of complianceor 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.

(c) 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.

(d) The inspection shall be done in accordance with Airbus Service Bulletin A300- 57-6028, Revision 3, dated September 13, 1994, which contains the specified effective pages:

Page Number Revision Level Shown on Page Date Shown on Page 1-6 3 September 13, 1994 7-9 2 February 22, 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.

(e) This amendment becomes effective on October 16, 1995.