AD 2004-15-07 Airworthiness Directives; Airbus Model A310 Series Airplanes

Models named: A310 series. Read the applicability below — it usually turns on serial or part numbers too.

Model A310 series airplanes, certificated in any category; on which Airbus Modification 12525 has not been done during production.

Required as indicated, unless accomplished previously. To prevent fatigue cracking of the area around the fasteners of the landing plate of the aileron access doors and the bottom skin panel of the wings, which could result in reduced structural integrity of the wings, accomplish the following: Repetitive Inspections (a) For airplanes on which Airbus Modification 5106 (Airbus Service Bulletin A310-57-2004, Revision 2, dated March 5, 1990) has not been done as of the effective date of this AD: Within 2,000 flight cycles after the effective date of this AD, or within 3,000 flight cycles after the last inspection done per paragraph (k) of AD 98-26-01, amendment 39-10942 (63 FR 69179, December 16, 1998), whichever is first; do a high frequency eddy current (HFEC) inspection for cracking of the area around the fasteners of the landing plate of the wing bottom skin panel No. 2 of the left and right wings. Do the inspection per the Accomplishment Instructions of Airbus Service Bulletin A310-57-2082, dated June 11, 2002. If no cracking is found, repeat the inspection thereafter at intervals not to exceed 1,900 flight cycles, until accomplishment of the terminating action specified in paragraph (d) of this AD. (b) For airplanes on which Airbus Modification 5106 has been done as of the effective date of this AD: Do the HFEC inspection required by paragraph (a) of this AD at the applicable time specified in paragraph (b)(1), (b)(2), (b)(3), or (b)(4) of this AD. If no cracking is found, repeat the inspection thereafter at intervals not to exceed 1,900 flight cycles, until accomplishment of the terminating action specified in paragraph (d) of this AD. (1) For airplanes that have accumulated fewer than 17,000 total flight cycles since the date of issuance of the original Airworthiness Certificate or the date of issuance of the original Export Certificate of Airworthiness, whichever is first, as of the effective date of this AD: Inspect prior to the accumulation of 18,000 total flight cycles. (2) For airplanes that have accumulated 17,000 or more total flight cycles, but fewer than 19,001 total flight cycles since the date of issuance of the original Airworthiness Certificate or the date of issuance of the original Export Certificate of Airworthiness, whichever is first, as of the effective date of this AD: Inspect within 2,000 flight cycles after the effective date of this AD. (3) For airplanes that have accumulated 19,001 or more total flight cycles, but fewer than 21,001 total flight cycles since the date of issuance of the original Airworthiness Certificate or the date of issuance of the original Export Certificate of Airworthiness, whichever is first, as of the effective date of this AD: Inspect with 1,200 flight cycles after the effective date of this AD. (4) For airplanes that have accumulated 21,001 or more total flight cycles since the date of issuance of the original Airworthiness Certificate or the date of issuance of the original Export Certificate of Airworthiness, whichever is first, as of the effective date of this AD: Inspect within 500 flight cycles after the effective date of this AD. Corrective Action (c) If any cracking is found during any inspection required by paragraph (a) or (b) of this AD: Before further flight, do the actions required by either paragraph (c)(1) or (c)(2) of this AD. (1) Do a permanent repair of the area by doing the applicable corrective actions per the Accomplishment Instruction of Airbus Service Bulletin A310-57-2082, dated June 11, 2002. Accomplishment of the permanent repair terminates the repetitive inspections required by this AD for the repaired area only. (2) Do the terminating action specified in paragraph (d) of this AD. Optional Terminating Action (d) Modification of the landing plate of the aileron access doors of the wing bottom skin panel No. 2 of the left and right wings by doing all the actions, per the Accomplishment Instructions of Airbus Service Bulletin A310-57-2081, dated June 11, 2002, terminates the requirements of this AD. Where the service bulletin specifies contacting the manufacturer for disposition of certain repair conditions that may be associated with the modification procedure, this AD requires that the repair be done per a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Direction Ge ne rale de l'Aviation Civile, or its delegated agent. 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 A310-57-2082, dated June 11, 2002. The optional terminating action, if accomplished, shall be done in accordance with Airbus Service Bulletin A310-57-2081, dated June 11, 2002. 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 2003-242(B), dated June 25, 2003. Effective Date (g) This amendment becomes effective on August 31, 2004. Issued in Renton, Washington, on July 9, 2004. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-16675 Filed 7-26-04; 8:45 am] BILLING CODE 4910-13-P