AD 2006-19-02 Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)

Models named: A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, C4-605R Variant F. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes, certificated in any category, except those on which Airbus Modification 8683 has been done.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Restatement of the Requirements of AD 97-14-02 (f) Prior to the accumulation of 14,100 total flight cycles, or within 12 months after August 4, 1997 (the effective date of AD 97-14-02), whichever occurs later, conduct an eddy current inspection to detect cracking of the fuselage outer skin at frames 28A and 30A above stringer 30, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6045, dated March 21, 1995, as revised by Change Notice No. O.A., dated June 1, 1995; or Airbus Service Bulletin A300-53-6045, Revision 03, dated October 28, 2004. After the effective date of this AD, only Revision 03 may be used. After the effective date of this AD, the initial eddy current inspection and all applicable repairs required by this paragraph must be done before doing the reinforcement specified in paragraph (g) of this AD. (1) If no cracking is found, repeat the eddy current inspection thereafter at intervals not to exceed 4,500 flight cycles. (2) If any cracking is found that is within the limits specified in the service bulletin: Prior to further flight do the actions in paragraph (f)(2)(i) or (f)(2)(ii) of this AD. After the effective date of this AD, only Airbus Service Bulletin A300-53-6045, Revision 03, dated October 28, 2004, may be used for the repair specified in paragraph (f)(2)(i) of this AD; and the reinforcement option specified in paragraph (f)(2)(ii) of this AD is not allowed in accordance with this paragraph. (i) Repair in accordance with paragraph 2.D. of the Accomplishment Instructions of Airbus Service Bulletin A300-53-6045, dated March 21, 1995, as revised by Change Notice No. O.A., dated June 1, 1995; or paragraph 3.C. of the Accomplishment Instructions of Airbus Service Bulletin A300-53-6045, Revision 03, dated October 28, 2004. After the repair, repeat the eddy current inspection thereafter at intervals not to exceed 4,500 flight cycles. (ii) Reinforce the structure at frames 28 and 29, and at frames 30 and 31, between stringers 29 and 30, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6037, dated March 21, 1995; or Airbus Service Bulletin A300-53-6037, Revision 02, dated October 28, 2004. Such reinforcement constitutes terminating action for the repetitive inspections required by this AD. (3) If any cracking is found that is outside the limits specified in the service bulletin: Prior to further flight, reinforce the structure at frames 28 and 29, and at frames 30 and 31, between stringers 29 and 30, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6037, dated March 21, 1995; or Airbus Service Bulletin A300-53-6037, Revision 02, dated October 28, 2004. After the effective date of this AD, only Revision 02 may be used. Such reinforcement constitutes terminating action for the repetitive inspections required by this AD. (g) Within 5 years after August 4, 1997: Reinforce the structure at frames 28 and 29, and at frames 30 and 31, between stringers 29 and 30, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6037, dated March 21, 1995; or Airbus Service Bulletin A300-53-6037, Revision 02, dated October 28, 2004. After the effective date of this AD, only Revision 02 may be used. Such reinforcement constitutes terminating action for the repetitive inspections required by this AD. After the effective date of this AD, the initial eddy current inspection and all applicable repairs required by paragraph (f) of this AD must be done before doing the reinforcement. New Requirements of This AD Inspection and Corrective Action (h) For airplanes that meet the conditions of both paragraphs (h)(1) and (h)(2) of this AD: Within 2,400 flight cycles or 18 months after the effective date of this AD, whichever occurs first, conduct an eddy current inspection to detect cracking of the fuselage outer skin at frames 28A and 30A above stringer 30, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-6045, Revision 03, dated October 28, 2004. If no cracking is found: No further action is required by this paragraph. If any cracking is found: Before further flight, repair the cracking using a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent). (1) Airplanes that were reinforced before the effective date of this AD in accordance with any service bulletin specified in Table 1 of this AD. Table 1.—Reinforcement Service Bulletins Airbus service bulletin Revision level Date A300-53-6037 Original March 21, 1995.   1 February 3, 1999.   02 October 28, 2004. (2) Airplanes that were not inspected and repaired in accordance with any service bulletin specified in Table 2 of this AD. Table 2.—Inspection and Repair Service Bulletins Airbus service bulletin Revision level Date A300-53-6045 Original March 21, 1995.   01 August 25, 1997.   02 May 2, 1999.   03 October 28, 2004. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (j) French airworthiness directive F-2005-002, dated January 5, 2005, also addresses the subject of this AD. Material Incorporated by Reference (k) You must use the service information identified in Table 3 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. Table 3.—Material Incorporated by Reference Airbus service bulletin Revision level Date A300-53-6037 Original March 21, 1995. A300-53-6037 02 October 28, 2004. A300-53-6045 03 October 28, 2004. A300-53-6045, as revised by Change Notice No. O.A., dated June 1, 1995 Original March 21, 1995. (1) The Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A300-53-6037, Revision 02, dated October 28, 2004; and Airbus Service Bulletin A300-53-6045, Revision 03, dated October 28, 2004; in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On August 4, 1997 (62 FR 35072, June 30, 1997), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A300-53-6045, dated March 21, 1995, as revised by Change Notice No. O.A., dated June 1, 1995; and Airbus Service Bulletin A300-53-6037, dated March 21, 1995. (3) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Renton, Washington, on September 1, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-14942 Filed 9-11-06; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report that the previously required actions were not sufficient to correct cracking before the structural reinforcement was installed. We are issuing this AD to prevent fatigue cracking of the outer skin of the fuselage at certain frames, which could result in reduced structural integrity, and consequent rapid decompression of the airplane.