2001-06-10: Center Section of Fuselage

2001-06-10 AIRBUS INDUSTRIE: Amendment 39-12157. Docket 2000-NM-105-AD. Applicability: All Model A300 B4-601, A300 B4-603, A300 B4-620, A300 B4-605R, A300 B4-622R, and A300 F4-605R 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 request approval for an alternative method of compliance in accordance with paragraph (e) 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. Compliance: Required as indicated, unless accomplished previously. To prevent cracking of the center section of the fuselage, which could result in rupture of the frame foot and reduced structural integrity of the airplane, accomplish the following: High Frequency Eddy Current (HFEC) or Rototest Inspection (a) Perform a HFEC or rototest inspection to detect cracking in the area surrounding the frame feet attachment holes between fuselage frames (FR) 41 and FR46 from stringers 24 to 28, left- and right-hand sides, in accordance with Airbus Service Bulletin A300-53-6122, dated February 9, 2000, at the time specified in paragraph (a)(1) or (a)(2), as applicable. (1) For airplanes on which Task 53-15-54 in Maintenance Review Board Document (MRBD), Revision 3, dated April 1998, has NOT been accomplished as of the effective date of this AD: Perform the inspection at the later of the times specified in paragraphs (a)(1)(i) and (a)(1)(ii) of this AD. (i) Prior to the accumulation of thetotal flight-cycle or flight-hour threshold, whichever occurs first, specified in paragraph 1.E. ("Compliance") of the service bulletin; or (ii) Within the applicable grace period specified in paragraph 1.E. ("Compliance") of the service bulletin. (2) For airplanes on which Task 53-15-54 in Maintenance Review Board Document (MRBD), Revision 3, dated April 1998, has been accomplished as of the effective date of this AD: Perform the next repetitive inspection at the later of the times specified in paragraphs (a)(2)(i) and (a)(2)(ii) of this AD. (i) Within the flight-cycle or flight-hour interval, whichever occurs first, specified in paragraph 1.E. ("Compliance") of the service bulletin, following the latest inspection accomplished in accordance with the MRBD; or (ii) Within the grace period specified in paragraph 1.E. ("Compliance") of the service bulletin. (b) For airplanes on which no cracking is detected during the inspection required by paragraph (a) of this AD, prior to further flight, install new fasteners as applicable, in accordance with Airbus Service Bulletin A300-53-6122, dated February 9, 2000; and repeat the inspection required by paragraph (a) of this AD thereafter at intervals not to exceed the applicable intervals specified in paragraph 1.E. ("Compliance") of the service bulletin. Corrective Actions (c) For airplanes on which cracking is detected during any inspection required by this AD: Prior to further flight, except as required by paragraph (d) of this AD, accomplish corrective actions (e.g., performing rotating probe inspections, reaming out cracks, cold working fastener holes, and installing oversized fasteners) in accordance with Airbus Service Bulletin A300-53-6122, dated February 9, 2000. Repeat the inspection required by paragraph (a) of this AD thereafter at intervals not to exceed the applicable intervals specified in paragraph 1.E. ("Compliance") of the service bulletin. (d) If crackingis detected during any inspection required by this AD, and the service bulletin specifies to contact the manufacturer for an appropriate corrective action: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction G n rale de l'Aviation Civile (DGAC) (or its delegated agent). Alternative Methods of Compliance (e) 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. 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 (f) 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. Incorporation by Reference (g) Except as required by paragraph (d) of this AD, the actions must be done in accordance with Airbus Service Bulletin A300-53-6122, dated February 9, 2000. 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. Note 3: The subject of this AD is addressed in French airworthiness directive 2000-060-303(B) R1, dated July 12, 2000. Effective Date (h) This amendment becomes effective on May 7, 2001.