AD 2010-22-03 Airworthiness Directives; Airbus Model A310 Series Airplanes

Models named: A310-203, -204, -221, -222, -304, -322, -324, -325. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to all Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes, certificated in any category.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Restatement of Certain Requirements of AD 2006-09-05 Modification (g) For all airplanes except those that are modified by Airbus Modifications 06672S6812, 06673S6813, and 07387S7974 in production: Within 60 months after June 7, 2006 (the effective date of AD 2006-09-05), modify the holes in the internal angle and tee fitting and do all applicable related investigative and corrective actions by accomplishing all the actions specified in the Accomplishment Instructions of Airbus Service Bulletin A310-57-2035, Revision 08, dated September 19, 2005; or Airbus Mandatory Service Bulletin A310-57-2035, Revision 10, dated March 25, 2008; except as required by paragraph (h) of this AD. Do all applicable related investigative and corrective actions before further flight. As of the effective date of this AD, use only Airbus Mandatory Service Bulletin A310-57-2035, Revision 10, dated March 25, 2008. Contact the FAA (h) Where the service information specified in Table 1 of this AD specifies to contact the manufacturer if certain cracks are found, before further flight, repair those conditions according to a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent); or EASA (or its delegated agent). Table 1—Service Information Document Revision Date Airbus Mandatory Service Bulletin A310-57-2035 10 March 25, 2008. Airbus Service Bulletin A310-57-2035 08 September 19, 2005. Actions Accomplished According to Previous Issues of Airbus Service Bulletin A310-57-2035 (i) Actions accomplished before June 7, 2006, in accordance with the service information specified in Table 2 of this AD, are considered acceptable for compliance with the corresponding actions specified in paragraph (g) of this AD. Table 2—Previous Issues of Service Bulletin A310-57-2035 Document Revision Date Airbus Service Bulletin A310-57-2035 1 October 13, 1989. Airbus Service Bulletin A310-57-2035 2 February 26, 1990. Airbus Service Bulletin A310-57-2035 3 May 23, 1990. Airbus Service Bulletin A310-57-2035 4 April 15, 1992. Airbus Service Bulletin A310-57-2035 5 May 27, 1992. Airbus Service Bulletin A310-57-2035 6 March 8, 1994. Airbus Service Bulletin A310-57-2035 7 April 17, 1996. New Requirements of This AD—Revised Compliance Times for Inspections Required by AD 2006-09-05 Initial and Repetitive Inspections of the Rear Spar Internal Angle (j) For airplanes on which an inspection of the rear spar internal angle has not been done in accordance with Airbus Service Bulletin A310-57-2047 as of the effective date of this AD: At the later of the times specified in paragraphs (j)(1) and (j)(2) of this AD, do a rotating probe inspection for any crack of the rear spar internal angle located in the center wing box and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57-2047, Revision 08, dated July 2, 2009; except as required by paragraphs (n) and (o) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection thereafter at the applicable time specified in Table 4 of this AD. Certain compliance times are applicable to short range use, average flight time (AFT) equal to or less than 4 hours, or long range use, AFT exceeding 4 hours. Note 1: To establish the AFT, divide the accumulated flight time (counted from the take-off up to the landing) by the number of accumulated flight cycles. This gives the average flight time per flight cycle. (1) Within the applicable time specified in Table 3 of this AD. (2) Within the applicable time specified in paragraph (j)(2)(i), (j)(2)(ii), or (j)(2)(iii) of this AD: (i) For A310-203, -204, -221, and -222 airplanes: Within 700 flight cycles or 1,500 flight hours after the effective date of this AD, whichever occurs first. (ii) For A310-304, -322, -324, and -325 short range airplanes: Within 700 flight cycles or 1,900 flight hours after the effective date of this AD, whichever occurs first. (iii) For A310-304, -322, -324, and -325 long range airplanes: Within 500 flight cycles or 2,500 flight hours after the effective date of this AD, whichever occurs first. Table 3—Initial Inspection Internal Angle       Model and configuration Compliance time (whichever occurs first) A310-203, -204, -221, and -222 airplanes on which Mod 6672S6812 and Mod 7387S7974 are not done Before the accumulation of 9,200 total flight cycles Before the accumulation of 18,500 total flight hours. A310-203, -204, -221, and -222 airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in production Before the accumulation of 19,800 total flight cycles Before the accumulation of 39,600 total flight hours. A310-203, -204, -221, and -222 airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in accordance with Airbus Service Bulletin A310-57-2035 and before the accumulation of 6,200 total flight cycles and 12,500 total flight hours Within 19,800 flight cycles after the effective date of this AD Within 39,600 flight hours after the effective date of this AD. A310-203, -204, -221, and -222 airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in accordance with Airbus Service Bulletin A310-57-2035 and are not done before the accumulation of 6,200 total flight cycles and 12,500 total flight hours Within 8,200 flight cycles after the effective date of this AD Within 16,400 flight hours after the effective date of this AD. A310-304, -322, -324, and -325 short range airplanes on which Mod 6672S6812 and Mod 7387S7974 are not done Before the accumulation of 7,500 total flight cycles Before the accumulation of 21,100 total flight hours. A310-304, -322, -324, and -325 long range airplanes on which Mod 6672S6812 and Mod 7387S7974 are not done Before the accumulation of 5,300 total flight cycles Before the accumulation of 26,900 total flight hours. A310-304, -322, -324, and -325 short range airplanes on which Mod 6672S6812 and Mod 7387S7974 are done Before the accumulation of 15,900 total flight cycles Before the accumulation of 44,700 total flight hours. A310-304, -322, -324, and -325 long range airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in production Before the accumulation of 11,300 total flight cycles Before the accumulation of 56,900 total flight hours. A310-304, -322, -324, and -325 short range airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in accordance with Airbus Service Bulletin A310-57-2035 and before the accumulation of 4,700 total flight cycles and 13,100 total flight hours Within 15,900 flight cycles after the effective date of this AD Within 44,700 flight hours after the effective date of this AD. A310-304, -322, -324, and -325 short range airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in accordance with Airbus Service Bulletin A310-57-2035 and not done before the accumulation of 4,700 total flight cycles and 13,100 total flight hours Within 8,500 flight cycles after the effective date of this AD Within 23,800 flight hours after the effective date of this AD. A310-304, -322, -324, and -325 long range airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in accordance with Airbus Service Bulletin A310-57-2035 before the accumulation of 3,300 total flight cycles and 16,700 total flight hours Within 11,300 flight cycles after the effective date of this AD Within 56,900 flight hours after the effective date of this AD. A310-304, -322, -324, and -325 long range airplanes on which Mod 6672S6812 and Mod 7387S7974 are done in accordance with Airbus Service Bulletin A310-57-2035 and not done before the accumulation of 3,300 total flight cycles and 16,700 total flight hours Within 6,000 flight cycles after the effective date of this AD Within 30,300 flight hours after the effective date of this AD. Table 4—Repetitive Intervals Model and configuration Interval (not to exceed) A310-203, -204, -221, and -222 airplanes Within 7,200 flight cycles or 14,400 flight hours, whichever occurs first. A310-304, -322, -324, and -325 short range airplanes Within 6,800 flight cycles or 19,100 flight hours, whichever occurs first. A310-304, -322, -324, and -325 long range airplanes Within 4,800 flight cycles or 24,300 flight hours, whichever occurs first. (k) For airplanes on which an inspection of the rear spar internal angle has been done in accordance with Airbus Service Bulletin A310-57-2047 as of the effective date of this AD: At the applicable time specified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD, do a rotating probe inspection for any crack of the rear spar internal angle located in the center wing box and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57-2047, Revision 08, dated July 2, 2009; except as required by paragraphs (n) and (o) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection thereafter at the applicable time specified in Table 4 of this AD. Certain compliance times are applicable to short range use, AFT equal to or less than 4 hours, or long range use, AFT exceeding 4 hours. (1) For A310-203, -204, -221, and -222 airplanes: At the earlier of the times specified in paragraphs (k)(1)(i) and (k)(1)(ii) of this AD. (i) Within 7,940 flight cycles or 15,880 flight hours after the most recent inspection, whichever occurs first. (ii) At the later of the times specified in paragraphs (k)(1)(ii)(A) and (k)(1)(ii)(B) of this AD. (A) Within the applicable interval specified in Table 4 of this AD. (B) Within 740 flight cycles or 1,480 flight hours after the effective date of this AD, whichever occurs first. (2) For A310-304, -322, -324, and -325 short range airplanes: At the later of the times specified in paragraphs (k)(2)(i) and (k)(2)(ii) of this AD. (i) Within the applicable interval specified in Table 4 of this AD. (ii) Within 700 flight cycles or 1,900 flight hours after the effective date of this AD, whichever occurs first. (3) For A310-304, -322, -324, and -325 long range airplanes: At the later of the times specified in paragraphs (k)(3)(i) and (k)(3)(ii) of this AD. (i) Within the applicable interval specified in Table 4 of this AD. (ii) Within 500 flight cycles or 2,500 flight hours after the effective date of this AD, whichever occurs first. Initial and Repetitive Inspections of the Tee Fitting (l) For airplanes on which an inspection of the left and right sides of the tee fitting has not been done in accordance with Airbus Service Bulletin A310-57-2047 as of the effective date of this AD: At the later of the times specified in paragraphs (l)(1) and (l)(2) of this AD, do a rotating probe inspection for any crack of the left and right sides of the tee fitting, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57-2047, Revision 08, dated July 2, 2009; except as required by paragraphs (n) and (o) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection thereafter at the applicable time specified in Table 6 of this AD. Certain compliance times are applicable to short range use, AFT equal to or less than 4 hours, or long range use, AFT exceeding 4 hours. (1) Within the applicable time specified in Table 5 of this AD. (2) Within the applicable time in paragraph (l)(2)(i), (l)(2)(ii), or (l)(2)(iii) of this AD. (i) For A310-203, -204, -221, and -222 airplanes: Within 800 flight cycles or 1,600 flight hours, whichever occurs first. (ii) For A310-304, -322, -324, and -325 short range airplanes: Within 800 flight cycles or 2,200 flight hours, whichever occurs first. (iii) For A310-304, -322, -324, and -325 long range airplanes: Within 600 flight cycles or 3,100 flight hours, whichever occurs first. Table 5—Initial Inspection Tee Fitting       Model and configuration Compliance time (whichever occurs first) A310-203, -204, -221, and -222 airplanes on which Mod 6673S6813 is not done Before the accumulation of 14,300 flight cycles Within 28,700 flight hours after the effective date of this AD. A310-203, -204, -221, and -222 airplanes on which Mod 6673S6813 is done in production Before the accumulation of 17,500 total flight cycles Before the accumulation of 35,000 total flight hours. A310-203, -204, -221, and -222 airplanes on which Mod 6673S6813 is done in accordance with Airbus Service Bulletin A310-57-2035 and before the accumulation of 8,100 total flight cycles and 16,200 total flight hours Within 17,500 flight cycles after the effective date of this AD Within 35,000 flight hours after the effective date of this AD. A310-203, -204, -221, and -222 airplanes on which Mod 6673S6813 is done in accordance with Airbus Service Bulletin A310-57-2035 and not before the accumulation of 8,100 total flight cycles and 16,200 total flight hours Within 9,600 flight cycles after the effective date of this AD Within 19,200 flight hours after the effective date of this AD. A310-304, -322, -324, and -325 short range airplanes on which Mod 6673S6813 is not done Within 10,800 flight cycles after the effective date of this AD Within 30,400 flight hours after the effective date of this AD. A310-304, -322, -324, and -325 long range airplanes on which Mod 6673S6813 is not done Before the accumulation of 8,500 total flight cycles Before the accumulation of 42,800 total flight hours. A310-304, -322, -324, and -325 short range airplanes on which Mod 6673S6813 is done in production Before the accumulation of 13,100 total flight cycles Before the accumulation of 36,700 total flight hours. A310-304, -322, -324, and -325 long range airplanes on which Mod 6673S6813 is done in production Before the accumulation of 10,300 total flight cycles Before the accumulation of 51,600 total flight hours. A310-304, -322, -324, and -325 short range airplanes on which Mod 6673S6813 is done in accordance with Airbus Service Bulletin A310-57-2035 and before the accumulation of 5,800 total flight cycles and 16,400 total flight hours Within 13,100 flight cycles after the effective date of this AD Within 36,700 flight hours after the effective date of this AD. A310-304, -322, -324, and -325 short range airplanes on which Mod 6673S6813 is done in accordance with Airbus Service Bulletin A310-57-2035 and not before the accumulation of 5,800 total flight cycles and 16,400 total flight hours Within 7,400 flight cycles after the effective date of this AD Within 20,900 flight hours after the effective date of this AD. A310-304, -322, -324, and -325 long range airplanes on which Mod 6673S6813 is done in accordance with Airbus Service Bulletin A310-57-2035 and before the accumulation of 4,600 total flight cycles and 23,100 total flight hours Within 10,300 flight cycles after the effective date of this AD Within 51,600 flight hours after the effective date of this AD. A310-304, -322, -324, and -325 long range airplanes on which Mod 6673S6813 is done in accordance with Airbus Service Bulletin A310-57-2035 and not before the accumulation of 4,600 total flight cycles and 23,100 total flight hours Within 6,000 flight cycles after the effective date of this AD Within 30,300 flight hours after the effective date of this AD. Table 6—Repetitive Intervals Model and configuration Interval (not to exceed) A310-203, -204, -221, and -222 airplanes 9,100 flight cycles or 18,300 flight hours, whichever occurs first. A310-304, -322, -324, and -325 short range airplanes 7,300 flight cycles or 20,400 flight hours, whichever occurs first. A310-304, -322, -324, and -325 long range airplanes 5,900 flight cycles or 29,600 flight hours, whichever occurs first. (m) For airplanes on which an inspection of the rear left and right sides of the tee fitting has been done in accordance with Airbus Service Bulletin A310-57-2047 as of the effective date of this AD: At the applicable time specified in paragraphs (m)(1) or (m)(2) of this AD, do a rotating probe inspection for any crack of the left and right sides of the tee fitting, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57-2047, Revision 08, dated July 2, 2009; except as required by paragraphs (n) and (o) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection thereafter at the applicable time specified in Table 6 of this AD. Certain compliance times are applicable to short range use, AFT equal to or less than 4 hours, or long range use, AFT exceeding 4 hours. (1) For A310-203, -204, -221, and -222 airplanes: At the earlier of the times specified in paragraphs (m)(1)(i) and (m)(1)(ii) of this AD. (i) Within 10,800 flight cycles or 17,400 flight hours after the most recent inspection, whichever occurs first. (ii) At the later of the times specified in paragraphs (m)(1)(ii)(A) and (m)(1)(ii)(B) of this AD. (A) Within the applicable interval specified in Table 6 of this AD. (B) Within 700 flight cycles or 1,500 flight hours after the effective date of this AD, whichever occurs first. (2) For A310-304, -322, -324, and - 325 airplanes: At the later of the times specified in paragraphs (m)(2)(i) and (m)(2)(ii) of this AD. (i) Within the applicable interval specified in Table 6 of this AD. (ii) Within 700 flight cycles or 1,900 flight hours after the effective date of this AD, whichever occurs first. Contact the FAA (n) Where Airbus Service Bulletin A310-57-2047, Revision 08, dated July 2, 2009, specifies to contact the manufacturer if certain cracks are found, before further flight, repair those conditions according to a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA (or its delegated agent). No Reporting Required (o) Although Airbus Service Bulletin A310-57-2047, Revision 08, dated July 2, 2009, specifies to submit certain information to the manufacturer, this AD does not include that requirement. (p) Actions accomplished before the effective date of this AD in accordance with Airbus Mandatory Service Bulletin A310-57-2035, Revision 09, dated September 27, 2007, are considered acceptable for compliance with the corresponding actions specified in paragraph (g) of this AD. (q) Actions accomplished before the effective date of this AD in accordance with the service information specified in Table 7 of this AD, are considered acceptable for compliance with the corresponding actions specified in paragraphs (j) through (m) of this AD. Table 7—Previous Issues of Airbus Service Bulletin A310-57-2047 Document Revision Date Airbus Service Bulletin A310-57-2047 03 November 26, 1997. Airbus Service Bulletin A310-57-2047 04 March 5, 1999. Airbus Service Bulletin A310-57-2047 05 August 3, 2000. Airbus Service Bulletin A310-57-2047 06 July 13, 2004. Airbus Service Bulletin A310-57-2047 07 March 14, 2008. Related AD (r) Accomplishing a rotating probe inspection of the rear spar internal angle and the tee fitting in accordance with Airbus Service Bulletin A310-57-2047, Revision 08, dated July 2, 2009, or a service bulletin listed in Table 7 of this AD, terminates the requirements specified in paragraph (o) of AD 98-26-01. FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows: Although the MCAI or service information tells you to contact the manufacturer for repair information, paragraph (n) of this AD requires that you contact the FAA or EASA (or its delegated agent) instead. Although the MCAI or service information tells you to submit information to the manufacturer, paragraph (o) of this AD specifies that such submittal is not required. Other FAA AD Provisions (s) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): 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: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2125; fax (425) 227-1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (2) AMOCs approved previously in accordance with AD 2006-09-05, Amendment 39-14575, are approved as AMOCs for the corresponding provisions of this AD. (3) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. Related Information (t) Refer to MCAI EASA Airworthiness Directive 2008-0187, dated October 10, 2008; Airbus Service Bulletin A310-57-2047, Revision 08, dated July 2, 2009; and Airbus Mandatory Service Bulletin A310-57-2035, Revision 10, dated March 25, 2008; for related information. Material Incorporated by Reference (u) You must use Airbus Mandatory Service Bulletin A310-57-2035, Revision 10, dated March 25, 2008; and Airbus Service Bulletin A310-57-2047, Revision 08, dated July 2, 2009; as applicable; to do the actions required by this AD, unless the AD specifies otherwise. Airbus Service Bulletin A310-57-2047 contains the following effective pages:   Page No. Revision level shown on page Date shown on page 1-7a, 26, 86, 88 08 July 2, 2009. 7b-21, 26, 29-31, 33, 35, 38, 39, 44, 45, 95, 96 07 March 14, 2008. 22-25, 37 06 July 13, 2004. 27, 28, 36, 47-56, 61-74 Original February 26, 1991. 32, 34, 40-43, 59-60, 81-85, 87, 89-94 04 March 5, 1999. 46, 75-80 05 August 3, 2000. 57, 58 2 January 22, 1997. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) 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 . (3) 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. (4) 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. Issued in Renton, Washington, on October 13, 2010. John Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010-26659 Filed 10-28-10; 8:45 am] BILLING CODE 4910-13-P