AD 2009-01-09 Airworthiness Directives; Airbus Model A310 Series Airplanes

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

This AD applies to Airbus Model A310 series airplanes, certificated in any category, except those airplanes modified in-service in accordance with Airbus Service Bulletin A310-53-2119, dated October 25, 2005; or Revision 01, dated February 27, 2007.

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 2000-26-14 Inspections and Corrective Actions (f) Perform a detailed inspection to detect cracks propagating from the fastener holes that attach the left- and right-hand pick-up angles at frame 40 to the wing lower skin and fuselage panel, at the time specified in paragraph (g), (h), (i), (j), or (k) of this AD, as applicable. Perform the actions in accordance with Figure 2, Sheet 1, “Synoptic Chart,” of Airbus Service Bulletin A310-53A2111, Revision 01, dated June 21, 2000, except as provided by paragraph (l) of this AD. (1) If no cracking is found during the inspection required by paragraph (f) of this AD, repeat the detailed inspection thereafter at the interval specified in paragraph (f)(1)(i) or (f)(1)(ii) of this AD, as applicable, except as provided by paragraph (n) of this AD. (i) For Model A310-200 series airplanes: Except as provided by paragraph (i) of this AD, repeat the inspection thereafter at intervals not to exceed 1,000 flight cycles or 2,600 flight hours, whichever occurs first. (ii) For Model A310-300 series airplanes: Except as provided by paragraphs (i) of this AD, repeat the inspection thereafter at intervals not to exceed 850 flight cycles or 2,800 flight hours, whichever occurs first. (2) If any cracking is found during the inspection required by paragraph (f) of this AD, prior to further flight, perform applicable corrective actions (including repair (drilling and reaming a crack stop hole in the pick-up angle, performing a Rototest inspection and repetitive detailed inspections at the time specified in the service bulletin, and replacing the pick-up angle with a new angle at the time specified in the service bulletin, except as provided by paragraph (o) of this AD); or immediate replacement of any cracked angle with a new angle). Perform the actions and repetitive inspections in accordance with Figure 2, Sheet 1, “Synoptic Chart,” of Airbus Service Bulletin A310-53A2111, Revision 01, dated June 21, 2000, except as provided by paragraph (l) of this AD. Note 1: Accomplishment of the actions required by paragraph (f) of this AD in accordance with Airbus Service Bulletin A310-53A2111, dated April 21, 2000, is considered to be acceptable for compliance with the requirements of that paragraph. Compliance Times (g) For Model A310-200 series airplanes: Except as provided by paragraphs (i), (j), and (k) of this AD, perform the initial inspection at the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD. (1) Prior to the accumulation of 7,900 total flight cycles or 23,600 total flight hours, whichever occurs first. (2) Within 700 flight cycles or 1,200 flight hours after February 9, 2001 (the effective date of AD 2000-26-14), whichever occurs first. (h) For Model A310-300 series airplanes: Except as provided by paragraphs (i), (j), and (k) of this AD, perform the initial inspection required by paragraph (f) of this AD at the later of the times specified in paragraphs (h)(1) and (h)(2) of this AD. (1) Prior to the accumulation of 6,700 total flight cycles or 24,700 total flight hours, whichever occurs first. (2) Within 700 flight cycles or 1,200 flight hours after February 9, 2001, whichever occurs first. (i) For airplanes that have accumulated more than 18,000 total flight cycles or 53,000 total flight hours as of February 9, 2001: Perform the initial inspection required by paragraph (f) of this AD within 350 flight cycles or 600 flight hours after February 9, 2001, whichever occurs first. Repeat the inspection thereafter at intervals not to exceed 350 flight cycles or 600 flight hours, whichever occurs first. (j) For airplanes having manufacturer's serial number 0162 through 0326 inclusive, on which Airbus Service Bulletin A310-53-2014 has been accomplished prior to February 9, 2001: The initial inspection threshold may be counted from the date of accomplishment of Airbus Service Bulletin A310-53-2014. (k) For airplanes on which a pick-up angle has been replaced: For that pick-up angle only, the initial inspection threshold may be counted from the date of installation of the new pick-up angle. Note 2: For the purposes of this AD, a detailed inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.” New Requirements of This AD New Revisions of Service Bulletin (l) As of the effective date of this AD, use only the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310-53-2111, Revision 03, dated May 21, 2007, to do the inspections and corrective actions required by paragraph (f) of this AD; except where Figure 2 Sheet 2 of Airbus Mandatory Service Bulletin A310-53-2111, Revision 03, dated May 21, 2007, specifies actions for crack length of “<54 mm (2.126 in.)” and “<69 mm (2.716 in.),” this AD requires the corresponding actions for crack lengths less than or equal to those measurements. (m) Inspections and applicable corrective actions done before the effective date of this AD in accordance with Airbus Mandatory Service Bulletin A310-53-2111, Revision 02, dated October 25, 2005, are acceptable for compliance with the requirements of paragraph (f) of this AD. Revised Repetitive Intervals for Detailed Inspections (n) As of the effective date of this AD, repeat the detailed inspections for no crack findings required by paragraph (f)(1)(i), (f)(1)(ii), or (i) of this AD, as applicable, at the applicable times specified in Table 1 of this AD, until the modification specified in paragraph (p) of this AD is done. Table 1—Revised Repetitive Intervals for Certain Detailed Inspections         For model— Repeat the inspection at the later of the following times— And thereafter at intervals not to exceed— (1) A310-200 series airplanes Within 950 flight cycles or 1,900 flight hours since the last inspection required by paragraph (f)(1)(i) or (i) of this AD, whichever occurs first Within 50 flight cycles or 250 flight hours after the effective date of this AD, whichever occurs first 950 flight cycles or 1,900 flight hours, whichever occurs first. (2) A310-300 series airplanes (short range) Within 900 flight cycles or 2,550 flight hours since the last inspection required by paragraph (f)(1)(ii) or (i) of this AD, whichever occurs first Within 50 flight cycles or 250 flight hours after the effective date of this AD, whichever occurs first 900 flight cycles or 2,550 flight hours, whichever occurs first. (3) A310-300 series airplanes (long range) Within 800 flight cycles or 4,000 flight hours since the last inspection required by paragraph (f)(1)(ii) or (i) of this AD, whichever occurs first Within 50 flight cycles or 250 flight hours after the effective date of this AD, whichever occurs first 800 flight cycles or 4,000 flight hours, whichever occurs first. Revised Threshold for Replacing the Pick-Up Angles (o) As of the effective date of this AD, do the replacement of the pick-up angle required by paragraph (f)(2) of this AD, at the applicable time specified in Table 2 of this AD. Table 2—Revised Thresholds for Replacing Pick-Up Angles       For model— Replace at the earlier of the following times— (1) A310-200 series airplanes At the time specified in paragraph (f)(2) of this AD for replacing the pick-up angle Within 1,500 flight cycles or 3,000 flight hours since the last detailed inspection, or within 30 days after the effective date of this AD, whichever occurs later. (2) A310-300 series airplanes (short range) At the time specified in paragraph (f)(2) of this AD for replacing the pick-up angle Within 1,600 flight cycles or 4,600 flight hours since the last detailed inspection, or within 30 days after the effective date of this AD, whichever occurs later. (3) A310-300 series airplanes (long range) At the time specified in paragraph (f)(2) of this AD for replacing the pick-up angle Within 1,400 flight cycles or 7,200 flight hours since the last detailed inspection, or within 30 days after the effective date of this AD, whichever occurs later. Optional Terminating Modification (p) Remove the existing pick-up angles and install a reinforced doubler between frames (FR) FR40 and FR41, and perform applicable related investigative and corrective actions by accomplishing all the applicable actions specified in the Accomplishment Instructions of Airbus Service Bulletin A310-53-2119, Revision 01, dated February 27, 2007; except as provided by paragraph (q) of this AD. Accomplishing these actions ends the repetitive inspections required by this AD. (q) If any crack is detected and Airbus Service Bulletin A310-53-2119, Revision 01, dated February 27, 2007, specifies to contact Airbus: Before further flight, repair the crack 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). (r) Actions done before the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-53-2119, dated October 25, 2005, are acceptable for compliance with the corresponding requirements of paragraph (p) of this AD. Alternative Methods of Compliance (AMOCs) (s) 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: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-2125; 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 (t) EASA airworthiness directive 2007-0184, dated July 3, 2007, also addresses the subject of this AD. Material Incorporated by Reference (u) You must use the service information identified in Table 3 of this AD to do the actions required by this AD, unless the AD specifies otherwise. If you do the optional terminating modification provided in this AD, you must use Airbus Service Bulletin A310-53-2119, Revision 01, including Appendix 01, dated February 27, 2007, to do the optional terminating modification. Table 3—Material Incorporated by Reference for Actions required by This AD Service bulletin Revision level Date Airbus Service Bulletin A310-53A2111, including Appendix 01 01 June 21, 2000. Airbus Mandatory Service Bulletin A310-53-2111, including Appendix 01 03 May 21, 2007. (1) The Director of the Federal Register approved the incorporation by reference of the service information identified in Table 4 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51. Table 4—New Material Incorporated by Reference Service bulletin Revision level Date Airbus Mandatory Service Bulletin A310-53-2111, including Appendix 01 03 May 21, 2007. A310-53-2119, including Appendix 01 01 February 27, 2007. (2) The Director of the Federal Register previously approved the incorporation by reference of Airbus Service Bulletin A310-53A2111, Revision 01, including Appendix 1, dated June 21, 2000, on February 9, 2001 (66 FR 1031, January 5, 2001). (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. E9-3765 Filed 2-25-09; 8:45 am] BILLING CODE 4910-13-P

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 prevent reduced structural integrity of the airplane due to fatigue damage and consequent cracking of the pick-up angles at frame 40.