AD 93-23-07 SUPERSEDED

93-23-07 AIRBUS INDUSTRIE: Amendment 39-8741. Docket 92-NM-44-AD.

Applicability: All Model A300-600 series airplanes, certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent reduced structural integrity of the center spar section of the wing, accomplish the following:

(a) For those airplanes on which the modification described in Airbus Repair Drawing R571-40588 has not been accomplished: Perform high frequency eddy current (HFEC) inspections to detect cracks in the center spar sealing angles adjacent to Rib 8, in accordance with Airbus Industrie Service Bulletin No. A300-57-6027, dated October 8, 1991, at the times specified in paragraph (a)(1), (a)(2), or (a)(3) of this AD, as applicable:

(1) For airplanes that have accumulated less than 12,000 total landings as of the effective date of this AD: Prior to the accumulation of 12,000 total landings or within 2,000 landings after the effective date ofthis AD, whichever occurs later; and thereafter at intervals not to exceed 6,000 landings.

(2) For airplanes that have accumulated 12,000 total landings or more, but less than 14,000 total landings as of the effective date of this AD: Prior to the accumulation of 14,000 total landings or within 2,000 landings after the effective date of this AD, whichever occurs later; and thereafter at intervals not to exceed 6,000 landings.

(3) For airplanes that have accumulated 14,000 total landings or more as of the effective date of this AD: Prior to the accumulation of 500 landings after the effective date of this AD; and thereafter at intervals not to exceed 6,000 landings.

(b) For those airplanes on which the average flight time differs from 2.1 hours by more than 10 percent: For purposes of complying with this AD, the initial inspection thresholds and the repetitive inspection intervals specified in paragraph (a) of this AD must be multiplied by an adjustment factor obtained from the formula listed in paragraph 1.C.(3) of Airbus Industrie Service Bulletin A300-57-6027, dated October 8, 1991.

(c) For those airplanes on which the modification described in Airbus Repair Drawing R571-40588 has been accomplished: Prior to the accumulation of 15,000 landings after accomplishing the modification, or within 500 landings after the effective date of this AD, whichever occurs later; and thereafter at intervals not to exceed 6,000 landings, perform a HFEC inspection to detect cracks in the center spar sealing angles adjacent to Rib 8, in accordance with Airbus Industrie Service Bulletin No. A300-57-6027, dated October 8, 1991.

(d) If any crack is found in the center spar sealing angles, including cracking entirely through the sealing angle, as a result of the inspections required by paragraph (a), (b), or (e) of this AD, prior to further flight, replace the pair of sealing angles on the affected wing and cold work the attachment holes, in accordance with Airbus Repair Drawing R571-40589; and perform the repetitive inspections required by paragraph (c) of this AD.

(e) If any sealing angle is found to be cracked through entirely as a result of the inspections required by paragraph (a) or (c) of this AD, prior to further flight, perform additional inspections to detect cracks in the adjacent butt strap and skin panel, in accordance with paragraph 2.B.(5) of Airbus Industrie Service Bulletin No. A300-57-6027, dated October 8, 1991. If any crack is found in the adjacent butt strap and skin panel, prior to further flight, repair it in accordance with Airbus Repair Drawing R571-40611.

(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 commentsand then send it to the Manager, Standardization Branch, ANM-113.

NOTE: 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 FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.

(h) The inspections shall be done in accordance with Airbus Industrie Service Bulletin No. A300-57-6027, including Appendix 1, dated October 8, 1991. 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 January 5, 1994.