AD 2004-20-14 Airworthiness Directives; Airbus Model A300 B4 Series Airplanes and Model A300 B4-600, A300 B4-600R, and A300 F4-600R (Collectively Called A300-600) Series Airplanes

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

All Model A300 B4-600, B4-600R, and F4-600R (collectively called A300-600) series airplanes; and all Model A300 B4 series airplanes; certificated in any category.

Required as indicated, unless accomplished previously. To detect and correct cracking of the splice fitting at fuselage frame (FR) 47, which could result in reduced structural integrity of the airplane, accomplish the following: Repetitive Inspections (a) For airplanes defined in Airbus Service Bulletin A300-53-0350, Revision 02, dated November 12, 2002: Do a high frequency eddy current (HFEC) inspection to detect cracking of the splice fitting at fuselage FR 47 between stringers 24 and 26 (left- and right-hand sides), at the applicable times specified in paragraph (a)(1) or (a)(2) of this AD. Repeat the inspection thereafter at the earlier of the flight-cycle/flight-hour intervals specified in the applicable column in Table 2 of Figure 1 and Sheet 1 of the Accomplishment Instructions of the service bulletin. Do the inspections in accordance with the service bulletin, excluding Appendix 01. (1) For airplanes that have accumulated 20,000 or more total flight cycles as of the effective date of this AD: Do the initial inspection at the later of the times specified in paragraphs (a)(1)(i) and (a)(1)(ii) of this AD: (i) At the earlier of the flight-cycle/flight-hour intervals after the effective date of this AD, as specified in the applicable column in Table 1 of Figure 1 and Sheet 1 of the Accomplishment Instructions of the service bulletin. (ii) Within 750 flight cycles or 1,500 flight hours after the effective date of this AD, whichever is first. (2) For airplanes that have accumulated fewer than 20,000 total flight cycles as of the effective date of this AD: Do the initial inspection at the later of the times specified in paragraphs (a)(2)(i) and (a)(2)(ii) of this AD. (i) At the earlier of the flight-cycle/flight-hour intervals after the effective date of this AD, as specified in the applicable column in Table 1 of Figure 1 and Sheet 1 of the Accomplishment Instructions of the service bulletin. (ii) Within 1,800 flight cycles or 3,000 flight hours after the effective date of this AD, whichever is first. (b) For airplanes defined in Airbus Service Bulletin A300-53-6123, Revision 02, dated November 12, 2002: Do the HFEC inspection required by paragraph (a) of this AD at the applicable times specified in paragraph (b)(1) or (b)(2) of this AD. Repeat the inspection thereafter at the earlier of the flight-cycle/flight-hour intervals specified in the applicable column in Table 2 of Figure 1 and Sheet 1 of the Accomplishment Instructions of the service bulletin. Do the inspections in accordance with the service bulletin, excluding Appendix 01. (1) For airplanes that have accumulated 10,000 or more total flight cycles as of the effective date of this AD: Do the initial inspection within 750 flight cycles or 1,900 flight hours after the effective date of this AD, whichever is first. (2) For airplanes that have accumulated fewer than 10,000 total flight cycles as of the effective date of this AD: Do the initial inspection at the later of the times specified in paragraphs (b)(2)(i) and (b)(2)(ii) of this AD. (i) At the earlier of the flight-cycle/flight-hour intervals after the effective date of this AD, as specified in the applicable column in Table 1 of Figure 1 and Sheet 1 of the Accomplishment Instructions of the service bulletin. (ii) Within 1,500 flight cycles or 3,800 flight hours after the effective date of this AD, whichever is first. Repair (c) Repair any cracking found during any inspection required by this AD before further flight, in accordance with Airbus Service Bulletin A300-53-0350 or A300-53-6123, both Revision 02, both excluding Appendix 01, both dated November 12, 2002; as applicable. Where the service bulletins specify to contact Airbus in case of certain crack findings, this AD requires that a repair be accomplished before further flight in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent). Credit for Previous Issues of Airbus Service Bulletin (d) Accomplishment of the actions before the effective date of this AD in accordance with Airbus Service Bulletin A300-53-0350 or A300-53-6123, Revision 01, dated December 18, 2001; is considered acceptable for compliance with the corresponding actions specified in this AD. Alternative Methods of Compliance (e) In accordance with 14 CFR 39.19, the Manager, International Branch, ANM-116, is authorized to approve alternative methods of compliance for this AD. Incorporation by Reference (f) Unless otherwise specified in this AD, the actions shall be done in accordance with Airbus Service Bulletin A300-53-0350, Revision 02, excluding Appendix 01, dated November 12, 2002; and Airbus Service Bulletin A300-53-6123, Revision 02, excluding Appendix 01, dated November 12, 2002; as applicable. 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, 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 National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Note 1: The subject of this AD is addressed in French airworthiness directive 2002-184(B), dated April 3, 2002. Effective Date (g) This amendment becomes effective on November 17, 2004. Issued in Renton, Washington, on September 30, 2004. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-22564 Filed 10-12-04; 8:45 am] BILLING CODE 4910-13-P