2009-11-12: Wing root

2009-11-12 Airbus: Amendment 39-15922. Docket No. FAA-2008-1201; Directorate Identifier 2008-NM-007-AD. Effective Date (a) This AD becomes effective August 25, 2009. Affected ADs (b) This AD supersedes AD 2004-14-06. Applicability (c) This AD applies to Airbus Model A310 series airplanes, certificated in any category, on which Airbus Modifications 8888 and 8889 have not been accomplished. Unsafe Condition (d) This AD results from mandatory continuing airworthiness information originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. We are issuing this AD to detect and correct fatigue cracks and corrosion around and under the chafing plates of the wing root, which could result in reduced structural integrity of the airplane. Compliance (e) 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 2004-14-06 Repetitive Inspections and Corrective Actions (f) Except as provided by paragraphs (g), (k), and (l) of this AD: Within 4 years since date of manufacture, or within 12 months after June 3, 1998 (the effective date of AD 98-09-20, amendment 39- 10501), whichever occurs later, perform an inspection to detect discrepancies around and under the chafing plates of the wing root, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-53-2069, Revision 06, dated May 22, 2007; Revision 05, dated November 12, 2002; Revision 04, dated November 8, 2000; Revision 03, dated October 28, 1997; Revision 2, dated September 23, 1996; or Revision 1, dated September 19, 1995. If any discrepancy is found, prior to further flight, accomplish follow-on corrective actions (i.e., removal of corrosion, corrosion protection, high frequency eddy current inspection, x-ray inspection), as applicable, in accordance with the applicable service bulletin. Repeat the inspections thereafter at the intervals specified in the applicable service bulletin. After August 13, 2004 (the effective date of AD 2004-14-06), repeat the inspections thereafter at the intervals specified in Airbus Service Bulletin A310-53-2069, Revision 04, dated November 8, 2000; Airbus Service Bulletin A310-53-2069, Revision 05, dated November 12, 2002; or Airbus Service Bulletin A310-53-2069, Revision 06, dated May 22, 2007. (g) If any discrepancy is found during any inspection required by paragraph (f) of this AD, and Airbus Service Bulletin A310-53- 2069, Revision 06, dated May 22, 2007; Revision 05, dated November 12, 2002; Revision 04, dated November 8, 2000; Revision 03, dated October 28, 1997; Revision 2, dated September 23, 1996; or Revision 1, dated September 19, 1995; as applicable; specifies to contact Airbus for appropriate action: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. Where differences in the compliance times or corrective actions exist between the service bulletin and this AD, the AD prevails. Optional Terminating Action (h) Except as provided by paragraph (i) of this AD: Accomplishment of the replacement of the stainless steel chafing plates with new chafing plates made of aluminum alloy, in accordance with Airbus Service Bulletin A310-53-2070, Revision 02, dated November 8, 2000; or the original issue, dated October 3, 1994; constitutes terminating action for the repetitive inspections required by paragraph (f) of this AD. Actions done in accordance with Airbus Service Bulletin A310-53-2070, Revision 1, dated September 23, 1996, are acceptable for compliance with actions required by this AD. Continuation of Repetitive Inspections (i) Except as provided by paragraphs (k) and (l) of this AD: Within 30 days after August 13, 2004, do a review of the airplane maintenance records todetermine if any corrosion was detected and reworked on the left and/or right side of frame 39, stringer 35, during the accomplishment of any corrective action or repair specified in paragraphs (f) or (g) of this AD. If any corrective action or repair has been accomplished in this area, perform an inspection for fatigue cracking of frame 39, stringer 35, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-53-2069, Revision 06, dated May 22, 2007; Revision 05, dated November 12, 2002; or Revision 04, dated November 8, 2000. Do the initial inspection at the threshold specified in Figure 1 of the service bulletin, or within 30 days after August 13, 2004, whichever is later. Repeat the inspection thereafter at the intervals specified in Figure 1 of the service bulletin. If any discrepancy is found, prior to further flight, accomplish the applicable follow-on corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-53-2069, Revision 06, dated May 22, 2007; Revision 05, dated November 12, 2002; or Revision 04, dated November 8, 2000. Submission of Information Not Required (j) Although the service bulletins specified in Table 1 of this AD specify to submit information to the manufacturer, this AD does not include such a requirement. Table 1--No Reporting Requirement for These Service Bulletins Airbus Service Bulletin Revision Dated A310-53-2069 1 September 19, 1995 A310-53-2069 2 September 23, 1996 A310-53-2069 03 October 28, 1997 A310-53-2069 04 November 8, 2000 A310-53-2069 05 November 12, 2002 A310-53-2069 06 May 22, 2007 A310-53-2070 Original October 3, 1994 A310-53-2070 1 September 23, 1996 A310-53-2070 02 November 8, 2000 New Actions Required by This AD New Service Bulletin Revision (k) As of the effective date of this AD, use only the Accomplishment Instructions of Airbus Service Bulletin A310-53-2069, Revision 06, dated May 22, 2007, to do the inspections and corrective actions required by paragraphs (f) and (i) of this AD. Repetitive Inspections at Frame 39, Stringer 35 at Reduced Intervals (l) As of the effective date of this AD, if any corrosion is found at frame 39, stringer 35, during any inspection required by this AD, do the repetitive inspections required by paragraphs (f) and (i) of this AD, as applicable, at the earlier of the times specified in paragraphs (l)(1) and (l)(2) of this AD. Repeat the inspections thereafter at intervals specified in Figure 1, Sheets 4 and 5, of Airbus Service Bulletin A310-53-2069, Revision 06, dated May 22, 2007, except as provided by paragraph (m) of this AD. (1) At the next specified repeat interval specified in paragraph (f) of this AD. (2) At the later of the times specified in paragraphs (l)(2)(i) and (l)(2)(ii) of this AD, except as provided by paragraph (m) of this AD. (i) At the applicable threshold specified in Figure 1, Sheets 4 and 5,of Airbus Service Bulletin A310-53-2069, Revision 06, dated May 22, 2007. (ii) Within 900 flight cycles or 1,800 flight hours after the effective date of this AD, whichever occurs first. (m) Where Figure 1, Sheets 4 and 5, of Airbus Service Bulletin A310-53-2069, Revision 06, dated May 22, 2007, specifies to contact Airbus, do the inspections at threshold and repeat intervals approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). Alternative Methods of Compliance (AMOCs) (n) The Manager, International Branch, ANM-116, Transport Airplane Directorate, 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 (o) European Aviation Safety Agency (EASA) Airworthiness Directive 2007-0292, dated November 27, 2007, also addresses the subject of this AD. Material Incorporated by Reference (p) You must use Airbus Service Bulletin A310-53-2069, Revision 06, dated May 22, 2007, as applicable, to do the actions required by this AD, unless the AD specifies otherwise. If you accomplish the optional terminating action specified in this AD, you must use the service bulletins specified in Table 2 of this AD, as applicable, unless the AD specifies otherwise. Table 2--Material Incorporated by Reference for Optional Actions Specified in This AD Airbus Service Bulletin Revision Dated A310-53-2070 02 November 8, 2000A310-53-2070 Original October 3, 1994 Airbus Service Bulletin A310-53-2070, Revision 02, dated November 8, 2000, contains the following effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1-13, 15-16, 21-22 02 November 8, 2000 14, 17-18 1 September 23, 1996 19-20 Original October 3, 1994 (1) The Director of the Federal Register approved the incorporation by reference of the service information contained in Table 3 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51. Table 3--New Material Incorporated by Reference Airbus Service Bulletin Revision Dated A310-53-2069 06 May 22, 2007 A310-53-2070 02 November 8, 2000 (2) The Director of the Federal Register previously approved the incorporation by reference of Airbus Service Bulletin A310-53- 2070, dated October 3, 1994, on June 3, 1998 (63 FR 23377, April 29, 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: [email protected]; Internet http://www.airbus.com. (4) You may review copies of the service information 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 that is incorporated by reference 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.