AD 2009-01-08 Airworthiness Directives; Airbus Model A300, A310, and A300-600 Series Airplanes

This AD applies to Airbus airplanes identified in Table 1 of this AD, certificated in any category. Table 1—Applicability Model— As identified in Airbus Mandatory Service Bulletin— (1) A300 series airplanes A300-57-0232, Revision 02, dated February 21, 2000. (2) A310 series airplanes A310-57-2075, Revision 03, dated December 1, 2006. (3) A300-600 series airplanes A300-57-6079, Revision 04, dated February 21, 2000.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Requirements of AD 98-16-11: Repetitive Detailed Inspections at Reduced Thresholds and Repeat Intervals for Certain Airplanes (f) At the applicable time specified in paragraph (f)(1) or (f)(2) of this AD: Perform a detailed inspection to detect cracks in the pylon thrust and sideload fitting of the wing, in accordance with Airbus Service Bulletin A300-57-0232, Revision 01 (for Model A300 series airplanes); A310-57-2075, Revision 01 (for Model A310 series airplanes); or A300-57-6079, Revision 02 (for Model A300-600 series airplanes); all dated January 12, 1998; as applicable; except as provided by paragraph (h) of this AD. (1) For Model A300 and A300-600 series airplanes: Inspect prior to the accumulation of 2,800 total flight cycles, or within 18 months after September 4, 1998 (the effective date AD 98-16-11), whichever occurs later, and thereafter at intervals not to exceed 2,800 flight cycles. (2) For Model A310 series airplanes: Inspect at the earlier of the times specified in paragraph (f)(2)(i) and (f)(2)(ii) of this AD. Repeat thereafter at the applicable intervals specified in Table 3 of this AD. (i) Prior to the accumulation of 2,800 total flight cycles, or within 18 months after September 4, 1998, whichever occurs later. (ii) At the applicable time specified in Table 2 of this AD. Table 2—Reduced Inspection Thresholds for Model A310 Series Airplanes Model Compliance time (whichever occurs later) Threshold Grace period A310-200 series airplanes. Before the accumulation of 1,500 total flight cycles or 3,000 total flight hours since first flight, whichever occurs first Within 800 flight cycles or 1,600 flight hours after the effective date of this AD, whichever occurs first. A310-300 series airplanes (short range) Before the accumulation of 1,300 total flight cycles or 3,800 total flight hours since first flight, whichever occurs first Within 800 flight cycles or 1,600 flight hours after the effective date of this AD, whichever occurs first. A310-300 series airplanes (long range) Before the accumulation of 800 total flight cycles or 4,000 total flight hours since first flight, whichever occurs first Within 800 flight cycles or 1,600 flight hours after the effective date of this AD, whichever occurs first. Table 3—Reduced Repeat Intervals for Model A310 Series Airplanes For Model— Repeat the detailed inspection at the later of— And, thereafter at intervals not to exceed— A310-200 series airplanes. Within 1,500 flight cycles or 3,000 flight hours since the last detailed inspection, whichever occurs first; or within 800 flight cycles or 1,600 flight hours after the effective date of this AD, whichever occurs first 1,500 flight cycles or 3,000 flight hours, whichever occurs first. A310-300 series airplanes (short range) Within 1,300 flight cycles or 3,800 flight hours since the last detailed inspection, whichever occurs first; or within 800 flight cycles or 1,600 flight hours after the effective date of this AD, whichever occurs first 1,300 flight cycles or 3,800 flight hours, whichever occurs first. A310-300 series airplanes (long range) Within 800 flight cycles or 4,000 flight hours since the last detailed inspection, whichever occurs first; or within 800 flight cycles or 1,600 flight hours after the effective date of this AD, whichever occurs first 800 flight cycles or 4,000 flight hours, whichever occurs first. Corrective Action (g) If any crack is detected during any inspection required by paragraph (f) of this AD, prior to further flight, replace the pylon thrust and sideload fitting with a new fitting in accordance with Airbus Service Bulletin A300-57-0232, Revision 01 (for Model A300 series airplanes); A310-57-2075, Revision 01 (for Model A310 series airplanes); or A300-57-6079, Revision 02 (for Model A300-600 series airplanes); all dated January 12, 1998; as applicable; except as provided by paragraphs (h) and (j) of this AD. New Actions Required by This AD: New Service Information (h) For all airplanes: As of the effective date of this AD, use only the Accomplishment Instructions of the applicable service bulletin specified in Table 4 of this AD to do the repetitive detailed inspections required by paragraph (f) of this AD and the replacement required by paragraph (g) of this AD. Table 4—New Service Bulletins Airbus mandatory Service Bulletin— For model— (1) A300-57-0232, Revision 02, dated February 21, 2000 A300 series airplanes. (2) A300-57-6079, Revision 04, dated February 21, 2000 A300-600 series airplanes. (3) A310-57-2075, Revision 03, dated December 1, 2006 A310 series airplanes. (i) Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A300-57-6079, Revision 02, dated January 12, 1998, or Revision 03, dated October 25, 1999 (for Model A300-600 series airplanes); A310-57-2075, Revision 01, dated January 12, 1998, or Revision 02, dated February 21, 2000 (for Model A310 series airplanes); or A300-57-0232, Revision 01, dated January 12, 1998 (for Model A300 series airplanes); are acceptable for compliance with the corresponding requirements of this AD. Optional Approval Method (j) Repairing the pylon thrust and sideload fitting of the wing, using a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA), or its delegated agent, is acceptable for compliance with the replacement required by paragraph (g) of this AD. Alternative Methods of Compliance (AMOCs) (k) The Manager, International Branch, ANM-116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1138; fax (425) 227-1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Related Information (l) EASA airworthiness directive 2007-0243, dated September 4, 2007, also addresses the subject of this AD. Material Incorporated by Reference (m) You must use service bulletins identified in Table 5 of this AD to do the actions required by this AD, as applicable, unless the AD specifies otherwise. Table 5—All Material Incorporated by Reference Airbus service information Revision Date Airbus Mandatory Service Bulletin A300-57-0232 02 February 21, 2000. Airbus Mandatory Service Bulletin A300-57-6079 04 February 21, 2000. Airbus Mandatory Service Bulletin A310-57-2075 03 December 1, 2006. Airbus Service Bulletin A300-57-0232 01 January 12, 1998. Airbus Service Bulletin A300-57-6079 02 January 12, 1998. Airbus Service Bulletin A310-57-2075 01 January 12, 1998. (1) The Director of the Federal Register approved the incorporation by reference of the service bulletins identified in Table 6 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Table 6—New Material Incorporated by Reference Airbus mandatory Service Bulletin— Revision— Dated— A300-57-0232 02 February 21, 2000. A300-57-6079 04 February 21, 2000. A310-57-2075 03 December 1, 2006. (2) On September 4, 1998 (63 FR 40816, July 31, 1998) the Director of the Federal Register approved the incorporation by reference of the service bulletins identified in Table 7 of this AD. Table 7—Material Previously Incorporated by Reference Airbus Service Bulletin— Revision— Dated— A300-57-0232 01 January 12, 1998. A310-57-2075 01 January 12, 1998. A300-57-6079 02 January 12, 1998. (3) For service information identified in this AD, contact Airbus SAS—EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: account.airworth- eas@airbus.com ; Internet http://www.airbus.com. (4) You may review copies of the service information that is incorporated by reference at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221 or 425-227-1152. (5) You may also review copies of the service information 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 . Issued in Renton, Washington, on December 18, 2008. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9-3276 Filed 2-19-09; 8:45 am] BILLING CODE 4910-13-P

This AD results from issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. We are issuing this AD to detect and correct cracks in the pylon thrust and sideload fitting of the wing, which could result in reduced structural integrity of the airplane.