AD 2000-12-11 Airworthiness Directives; Airbus Model A300-600 Series Airplanes

Models named: A300-600 series. Read the applicability below — it usually turns on serial or part numbers too.

Model A300-600 series airplanes, certificated in any category, on which Airbus Modification 10161 has not been installed in production. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise 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 (c) 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.

Required as indicated, unless accomplished previously. To prevent fatigue cracks in the bolt holes of the wing spars, which could result in reduced structural integrity of a wing spar, accomplish the following: Ultrasonic Inspections (a) Perform an ultrasonic inspection to detect fatigue cracking of the bolt holes inboard and outboard of rib 9 on the bottom booms of the front and rear wing spars, in accordance with Airbus Service Bulletin A300-57-6037, dated August 1, 1994, or Revision 1, dated August 31, 1995, at the applicable time specified in paragraph (a)(1) or (a)(2) of this AD. Repeat the inspection thereafter at intervals not to exceed 4,800 flight cycles or 11,000 flight hours, whichever occurs first. (1) For airplanes on which Airbus Modification 8842 (reference Airbus Service Bulletin A300-57-6039) has not been installed: Inspect at the earlier of the times specified by paragraphs (a)(1)(i) and (a)(1)(ii) of this AD. (i) Prior to the accumulation of 17,000 total flight cycles, or within 2,000 flight cycles after May 10, 1995 (the effective date of AD 95-07-05, amendment 39-9187), whichever occurs later. (ii) Prior to the accumulation of 39,000 total flight hours. (2) For airplanes on which Airbus Modification 8842 has been installed: Inspect at the earlier of the times specified by paragraphs (a)(2)(i) and (a)(2)(ii) of this AD. (i) Within 17,000 flight cycles after accomplishment of Airbus Modification 8842, or within 2,000 flight cycles after May 10, 1995, whichever occurs later. (ii) Within 39,000 flight hours after accomplishment of Airbus Modification 8842. Corrective Action (b) If any crack is found, prior to further flight, repair in accordance with Airbus Service Bulletin A300-57-6037, dated August 1, 1994, or Revision 1, dated August 31, 1995. Thereafter, perform the repetitive inspections required by paragraph (a) of this AD. Alternative Methods of Compliance (c) 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, International Branch, ANM-116, 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, International Branch, ANM-116. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. Special Flight Permits (d) Special flight permits may be issued in accordance with §§ 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. Incorporation by Reference (e) The actions shall be done in accordance with Airbus Service Bulletin A300-57-6037, dated August 1, 1994; or Airbus Service Bulletin A300-57-6037, Revision 1, dated August 31, 1995, as applicable. Airbus Service Bulletin A300-57-6037, Revision 1, dated August 31, 1995, contains the following list of effective pages:   Page No. Revision level shown on page Date shown on page 1, 2, 4-6 1 August 31, 1995. 3, 7-17 Original August 1, 1994. (1) The incorporation by reference of Airbus Service Bulletin A300-57-6037, Revision 1, dated August 31, 1995, is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) The incorporation by reference of Airbus Service Bulletin A300-57-6037, dated August 1, 1994, was approved previously by the Director of the Federal Register as of May 10, 1995 (60 FR 17990, April 10, 1995). (3) 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. Note 3: The subject of this AD is addressed in French airworthiness directive 94-208-169(B)R2, dated October 8, 1997. (f) This amendment becomes effective on July 24, 2000. Issued in Renton, Washington, on June 9, 2000. Donald L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 00-15186 Filed 6-16-00; 8:45 am] BILLING CODE 4910-13-U