AD 2005-25-19 Airworthiness Directives; Airbus Model A300 B2 Series Airplanes, Model A300 B4 Series Airplanes, Model A310-200 Series Airplanes, Model A310-300 Series Airplanes; and Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)

Models named: A300 B2-1A, B2-1C, B2K-3C, B2-203, A300 B4-2C, B4-103, B4-203, A300 B4-601, B4-603, B4-620. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes; Model A300 B4-2C, B4-103, and B4-203 airplanes; Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R and F4-622R airplanes; Model A300 C4-605R Variant F airplanes; Model A310-203, -204, -221, and -222 airplanes; and Model A310-304, -322, -324, and -325 airplanes; certificated in any category; except for airplanes on which Airbus Modification 12662 has been done in production.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspections (f) At the applicable initial inspection threshold specified in Table 1 of this AD or within the applicable grace period specified in Table 2 of this AD, whichever occurs later: Do an eddy current inspection for cracks of the stiffener fittings of the fuselage at FR 12A, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-53-0365, Revision 01 (for Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes, and Model A300 B4-2C, B4-103, and B4-203 airplanes); Airbus Service Bulletin A300-53-6138, Revision 01 (for Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes, Model A300 B4-605R and B4-622R airplanes, Model A300 F4-605R and F4-622R airplanes, and Model A300 C4-605R Variant F airplanes); or Airbus Service Bulletin A310-53-2117, Revision 01 (for Model A310-203, -204, -221, and -222 airplanes, and Model A310-304, -322, -324, and -325 airplanes); all dated April 4, 2005; as applicable. Repeat the inspection thereafter at intervals not to exceed the applicable compliance time specified in Table 1 of this AD until the actions specified in paragraph (h) of this AD are done. Table 1.—Compliance Times for Initial and Repetitive Inspections For airplanes identified as— Do the initial inspection prior to the accumulation of— And repeat at intervals not to exceed— Configuration 01 in Airbus Service Bulletin A300-53-0365, Revision 01, dated April 4, 2005 19,300 total flight cycles 11,450 flight cycles. Configuration 02 in Airbus Service Bulletin A300-53-0365, Revision 01, dated April 4, 2005 15,500 total flight cycles 9,200 flight cycles. Configuration 01 in Airbus Service Bulletin A300-53-6138, Revision 01, dated April 4, 2005 19,300 total flight cycles 11,450 flight cycles. Configuration 02 in Airbus Service Bulletin A300-53-6138, Revision 01, dated April 4, 2005 17,600 total flight cycles 11,450 flight cycles. Configuration 03 in Airbus Service Bulletin A300-53-6138, Revision 01, dated April 4, 2005 12,700 total flight cycles 8,000 flight cycles. Configuration 04 in Airbus Service Bulletin A300-53-6138, Revision 01, dated April 4, 2005 10,200 total flight cycles 6,400 flight cycles. Configuration 01 in Airbus Service Bulletin A310-53-2117, Revision 01, dated April 4, 2005 19,300 total flight cycles 11,450 flight cycles. Configuration 02 in Airbus Service Bulletin A310-53-2117, Revision 01, dated April 4, 2005 17,600 total flight cycles 11,450 flight cycles. Configuration 03 in Airbus Service Bulletin A310-53-2117, Revision 01, dated April 4, 2005 12,700 total flight cycles 8,000 flight cycles. Table 2.—Grace Period for the Initial Inspection For Airbus Model— Grace period is— A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes Within 2,500 flight cycles after the effective date of this AD. A300 B4-2C, B4-103, and B4-203 airplanes; A300 B4-601, B4-603, B4-620, and B4-622 airplanes; A300 B4-605R and B4-622R airplanes; A300 F4-605R and F4-622R airplanes; A300 C4-605R Variant F airplanes; A310-203, -204, -221, and -222 airplanes; and A310-304, -322, -324, and -325 airplanes Within 2,000 flight cycles after the effective date of this AD. Corrective Action (g) If any cracking is found during any inspection required by paragraph (f) of this AD, before further flight, do the replacement and installation specified in paragraph (h) of this AD. Terminating Action (h) Replacing the existing fitting on FR12A with a FR12A crossbeam and installing a new web between FR12A and FR13 at stringer 26 in accordance with Airbus Service Bulletin A300-53-0364, Revision 02, dated September 24, 2004 (for Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes, and Model A300 B4-2C, B4-103, and B4-203 airplanes); Airbus Service Bulletin A300-53-6137, Revision 03, dated April 4, 2005 (for Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes, Model A300 B4-605R and B4-622R airplanes, Model A300 F4-605R and F4-622R airplanes, and Model A300 C4-605R Variant F airplanes); or Airbus Service Bulletin A310-53-2116, Revision 02, dated September 24, 2004 (for Model A310-203, -204, -221, and -222 airplanes, and Model A310-304, -322, -324, and -325 airplanes); as applicable; and except as required by paragraph (i) of this AD; constitutes terminating action for the requirements of this AD. (i) Where the service bulletins specify to contact the manufacturer for certain information, before further flight, do the terminating action according to a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the DGAC (or its delegated agent). Actions Accomplished According to Previous Issue of Service Bulletin (j) Actions accomplished before the effective date of this AD according to the Airbus service bulletins specified in Table 3 of this AD are considered acceptable for compliance with the corresponding actions specified in this AD. Table 3.—Previous Issues of Service Bulletins Airbus Service Bulletin Revision level Date A300-53-0364 Original December 1, 2003. A300-53-0364 01 May 5, 2004. A300-53-0365 Original December 1, 2003. A300-53-6137 Original December 1, 2003. A300-53-6137 01 May 5, 2004. A300-53-6137 02 September 24, 2004. A300-53-6138 Original December 1, 2003. A310-53-2116 Original December 1, 2003. A310-53-2116 01 May 5, 2004. A310-53-2117 Original December 1, 2003. No Reporting Required (k) Although the service bulletins referenced in this AD specify to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (l)(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 (m) French airworthiness directive F-2005-084, dated May 25, 2005, also addresses the subject of this AD. Material Incorporated by Reference (n) You must use the service information listed in Table 4 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Jacques Leborgne, Airbus Customer Service Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, fax (+33) 5 61 93 36 14, for service information identified in this AD for Airbus Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes; and Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this AD for Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Airbus Model A300 B4-605R and B4-622R airplanes; Airbus Model A300 F4-605R and F4-622R airplanes; Airbus Model A300 C4-605R Variant F airplanes; Model A310-203, -204, -221, and -222 airplanes; and Airbus Model A310-304, -322, -324, and -325 airplanes. 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. Table 4.—Material Incorporated by Reference Airbus Service Bulletin Revision level Date A300-53-0364 02 September 24, 2004. A300-53-0365, excluding Appendix 01 01 April 4, 2005. A300-53-6137 03 April 4, 2005. A300-53-6138, excluding Appendix 01 01 April 4, 2005. A310-53-2116 02 September 24, 2004. A310-53-2117, excluding Appendix 01 01 April 4, 2005. Issued in Renton, Washington, on December 2, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-23900 Filed 12-13-05; 8:45 am] BILLING CODE 4910-13-P

This AD results from reports of cracks on the upper attachment fitting of the stiffener fitting at frame (FR) 12A. We are issuing this AD to prevent failure of the stiffener fittings, which could result in the reduced structural integrity of the floor and rods around FR12A.