AD 2003-06-04 Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes; and A300 B4-600, B4-600R, and F4-600R (Collectively Called A300-600) Series Airplanes

Models named: A300 B2, B4 series. Read the applicability below — it usually turns on serial or part numbers too.

All Model A300 B2 and B4 series airplanes; and all Model A300 B4-600, B4-600R, and F4-600R (collectively called 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 request approval for an alternative method of compliance in accordance with paragraph (f)(1) 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 detect and correct fatigue cracking of the upper radius of the forward fitting of fuselage frame 47, which could result in propagation of the cracking to the rear fitting and reduced structural integrity of frame 47, accomplish the following: Model A300-600: Inspection (a) For Model A300-600 series airplanes: At the earlier of the times specified by paragraphs (a)(1) and (a)(2) of this AD, perform an eddy current inspection to detect cracking of the upper radius of the left and right forward fitting of frame 47, in accordance with Airbus Service Bulletin A300-53-6029, Revision 02, dated November 7, 1994; or Revision 05, dated April 11, 2001. After the effective date of this AD, only Revision 05 of the service bulletin may be used. Accomplishment of an inspection before the effective date of this AD in accordance with Airbus Service Bulletin A300-53-6029, Revision 03, dated October 7, 1997, or Revision 04, dated October 25, 1999, is acceptable for compliance with the initial inspection requirements of paragraph (a) of this AD. (1) Before the accumulation of 17,300 total flight cycles, or within one year after October 16, 1996 (the effective date of AD 96-18-18, amendment 39-9744), whichever occurs later. (2) At the later of the times specified by paragraphs (a)(2)(i) and (a)(2)(ii) of this AD. (i) Before the accumulation of 10,000 total flight cycles or 26,000 total flight hours, whichever occurs first. (ii) Within 750 flight cycles or 1,900 flight hours, whichever occurs first after the effective date of this AD. Model A300-600: Follow-On Inspections (b) For Model A300-600 series airplanes on which no cracking is found during any inspection required by paragraph (a) of this AD: (1) If the initial inspection was accomplished before the effective date of this AD, repeat the inspection at the later of the times specified in paragraphs (b)(1)(i) and (b)(1)(ii) of this AD. Thereafter, repeat the inspection at least every 6,100 flight cycles or 15,600 flight hours, whichever occurs first. (i) Reinspect within 6,100 flight cycles after the initial inspection. (ii) Reinspect within 750 flight cycles or 1,900 flight hours, whichever occurs first after the effective date of this AD. (2) If the initial inspection was not accomplished before the effective date of this AD, repeat the inspection thereafter at least every 6,100 flight cycles or 15,600 flight hours, whichever occurs first. Model A300-600: Corrective Action (c) For Model A300-600 series airplanes on which any cracking is found during any inspection required by this AD: Before further flight, contact the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated representative); for instructions regarding repair or for an applicable reinspection interval in accordance with Airbus Service Bulletin A300-52-6029, Revision 05, dated April 11, 2001. Repair and/or reinspection accomplished before the effective date of this AD in accordance with a method approved by the Manager, International Branch, ANM-116, is acceptable for compliance with the requirements of paragraph (c) of this AD. Model A300 B2 and B4: Inspection and Follow-On Actions (d) For Model A300 B2 and B4 series airplanes: At the applicable time specified in paragraph (d)(1), (d)(2), or (d)(3) of this AD, perform repetitive eddy current inspections to detect cracking of the upper radius of the forward fitting of frame 47, left and right sides, per Airbus Service Bulletin A300-53-0246, Revision 03, dated April 11, 2001. If any cracking is found: Before further flight, contact the Manager, International Branch, ANM-116, or the DGAC (or its delegated representative), for instructions regarding repair, or for an applicable reinspection interval in accordance with the service bulletin. This requirement terminates the corresponding inspection requirement of the A300 Supplemental Structural Inspection Document (SSID) for Model A300 B2 and B4 series airplanes. That SSID is mandated by AD 96-13-11, amendment 39-9679. (1) For Model A300 B2 series airplanes: Perform the initial inspection at the later of the times specified by paragraphs (d)(1)(i) and (d)(1)(ii) of this AD. Repeat the inspection thereafter at least every 10,400 flight cycles or 13,300 flight hours, whichever occurs first. (i) Before the accumulation of 16,500 total flight cycles or 21,000 total flight hours, whichever occurs first. (ii) Within 1,000 flight cycles or 1,300 flight hours after the effective date of this AD, whichever occurs first. (2) For Model A300 B4-100 series airplanes: Perform the initial inspection at the later of the times specified by paragraphs (d)(2)(i) and (d)(2)(ii) of this AD. Repeat the inspection thereafter at least every 8,500 flight cycles or 16,400 flight hours, whichever occurs first. (i) Before the accumulation of 10,300 total flight cycles or 19,800 total flight hours, whichever occurs first. (ii) Within 750 flight cycles or 1,500 flight hours after the effective date of this AD, whichever occurs first. (3) For Model A300 B4-200 series airplanes: Perform the initial inspection at the later of the times specified by paragraphs (d)(3)(i) and (d)(3)(ii) of this AD. Repeat the inspection thereafter at least every 7,000 flight cycles or 13,600 flight hours, whichever occurs first. (i) Before the accumulation of 11,000 total flight cycles or 21,200 total flight hours, whichever occurs first. (ii) Within 750 flight cycles or 1,500 flight hours after the effective date of this AD, whichever occurs first. Reporting Requirement (e) At the applicable time specified in paragraph (e)(1) or (e)(2) of this AD: Submit a report of all results of each inspection required by paragraphs (a), (b), and (d) of this AD to Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, Attention Jacques Leborgne, fax 33-5-61-93-36-14. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane. Information collection requirements contained in this AD have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq. ) and have been assigned OMB Control Number 2120-0056. (1) For airplanes on which the inspection is accomplished after the effective date of this AD: Submit the report within 30 days after performing the inspection. (2) For airplanes on which the inspection has been accomplished before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. Alternative Methods of Compliance (f)(1) 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. (2) Alternative methods of compliance, approved previously in accordance with AD 96-18-18, amendment 39-9744, and AD 96-13-11, amendment 39-9679, are approved as alternative methods of compliance with the requirements of paragraphs (c) and (d) of this AD. 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 (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. Incorporation by Reference (h) Except as otherwise required by this AD, the actions must be done in accordance with Airbus Service Bulletin A300-53-0246, Revision 03, including Appendix 01, dated April 11, 2001; Airbus Service Bulletin A300-53-6029, Revision 05, including Appendix 01, dated April 11, 2001; and Airbus Service Bulletin A300-53-6029, Revision 02, dated November 7, 1994. (1) The incorporation by reference of Airbus Service Bulletin A300-53-6029, Revision 05, including Appendix 01, dated April 11, 2001; and Airbus Service Bulletin A300-53-0246, Revision 03, including Appendix 01, dated April 11, 2001; 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 A300-53-6029, Revision 02, dated November 7, 1994, was approved previously by the Director of the Federal Register, as of October 16, 1996 (61 FR 47808, September 11, 1996). (3) Copies of these service bulletins may be obtained from Jacques Leborgne, Airbus Industrie Customer Service Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; fax (+33) 5 61 93 36 14. 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 2001-355(B), dated August 8, 2001. Effective Date (i) This amendment becomes effective on May 1, 2003. Issued in Renton, Washington, on March 18, 2003. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 03-6995 Filed 3-26-03; 8:45 am] BILLING CODE 4910-13-P