AD 2011-10-17 Airworthiness Directives; Airbus Model A300 and A310 Series Airplanes, and Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)

Models named: A300 B2-1A, B2-1C, B4-2C, B2K-3C, B4-103, B2-203, B4-203, A310-203, -204, -221. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to all Airbus model airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category. (1) Model A300 B2-1A, B2-1C, B4-2C, B2K-3C, B4-103, B2-203, and B4-203 airplanes. (2) Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes. (3) Models A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, and F4-622R airplanes, and Model A300 C4-605R Variant F airplanes. Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (t)(1) of this AD. The request should include a description of changes to the required inspections that will ensure the continued damage tolerance of the affected structure. The FAA has provided guidance for this determination in Advisory Circular (AC) 25-1529-1.

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 2007-04-11 (g) Within one year after August 9, 1996 (the effective date of AD 96-13-11), replace the revision of the maintenance program with the inspections, inspection intervals, repairs, and replacements defined in Airbus Industrie A300 Supplemental Structural Inspection Document, Revision 2, dated June 1994. Accomplish the actions specified in the service bulletins identified in Section 6, “SB Reference List,″ in Airbus Industrie A300 Supplemental Structural Inspection Document, Revision 2, dated June 1994, at the times specified in those service bulletins. The actions are to be accomplished in accordance with those service bulletins. Accomplishing the initial ALI tasks required by paragraph (s) of this AD terminates the actions required by this paragraph. (1) For airplanes that have exceeded the threshold specified in any of the service bulletins identified in Section 6, “SB Reference List,″ in Airbus Industrie A300 Supplemental Structural Inspection Document, Revision 2, dated June 1994: Accomplish the actions specified in those service bulletins within the grace period specified in those service bulletins. The grace period is to be measured from August 9, 1996. (2) For airplanes that have exceeded the threshold specified in any of the service bulletins identified in Section 6, “SB Reference List,″ in Airbus Industrie A300 Supplemental Structural Inspection Document, Revision 2, dated June 1994, and a grace period is not specified in that service bulletin: Accomplish the actions specified in that service bulletin within 1,500 flight cycles after August 9, 1996. Revision of the Maintenance Inspection Program (h) For airplanes identified in paragraph (c)(1) of this AD: Within 12 months after April 3, 2007 (the effective date of AD 2007-04-11), replace the revision of the maintenance program required by paragraph (g) of this AD with the supplemental structural inspections, inspection intervals, and repairs defined in Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, as revised by Airbus A300 Temporary Revision (TR) 3.1, dated April 2006. Accomplish the actions specified in Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, as revised by Airbus A300 TR 3.1, dated April 2006, at the times specified in that ALI, except as provided by paragraph (i) of this AD. The actions must be accomplished in accordance with Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, as revised by Airbus A300 TR 3.1, dated April 2006. Accomplishing the initial ALI tasks required by paragraph (s) of this AD terminates the actions required by this paragraph. (i) For airplanes identified in paragraph (c)(1) of this AD that have exceeded the threshold or intervals specified in the Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, for the application tolerance on the first interval for new and revised requirements and have exceeded 50 percent of the intervals specified in sections D and E of Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September 2005: Do the actions within 6 months after April 3, 2007. Corrective Actions (j) Damaged, cracked, or corroded structure detected during any inspection done in accordance with the Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, must be repaired, before further flight, in accordance with Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, as revised by Airbus A300 TR 3.1, dated April 2006, except as provided by paragraph (k) of this AD; or other data meeting the certification basis of the airplane which is approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or by the European Aviation Safety Agency (EASA) (or its delegated agent). (k) Where the Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, specifies contacting Airbus for appropriate action: Before further flight, repair the damaged, cracked, or corroded structure using a method approved by either the Manager, International Branch, ANM-116; or the EASA (or its delegated agent). No Fleet Sampling (l) Although Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, specifies to do a “Sampling Concept″ in section B, this AD prohibits the use of such a sampling program and requires all affected airplanes of the fleet to be inspected. No Reporting (m) Although Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, specifies to submit certain information to the manufacturer, this AD does not include that requirement. Restatement of Requirements of AD 2007-20-03

For airplanes identified in paragraph (c)(3) of this AD: Within 3 months after October 31, 2007 (the effective date AD 2007-20-03), revise the ALS of the Instructions for Continued Airworthiness to incorporate Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006. The tolerance (grace period) for compliance (specified in paragraph 2 of Section B—Program Rules) with Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006, is within 2,000 flight cycles after October 31, 2007, provided that none of the following is exceeded. Accomplishing the initial ALI tasks required by paragraph (s) of this AD terminates the actions required by this paragraph. (1) Thresholds or intervals in the operator's current approved maintenance schedule that are taken from a previous ALI issue, if existing, and are higher than or equal to those given in Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006. (2) 8 months after October 31, 2007. (3) 50 percent of the intervals given in Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006. (4) Any application tolerance given in the task description of Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006. Restatement of Requirements of AD 2007-25-02 Revision of the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA) (o) For airplanes identified in paragraph (c)(2) of this AD: Within 3 months after January 14, 2008 (the effective date of AD 2007-25-02), do the actions specified in paragraphs (o)(1) and (o)(2) of this AD. Accomplishing the initial ALI tasks required by paragraph (s) of this AD terminates the actions required by this paragraph. (1) Revise the ALS of the ICA to incorporate the structural inspections and inspection intervals defined in Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006 (approved by the EASA on May 31, 2006). Accomplish the actions specified in Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006, at the times specified in Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006, except as provided by paragraph (p) of this AD. Thereafter, except as provided by paragraphs (o)(2) and (t)(1) of this AD, no alternative structural inspection intervals may be approved. The actions specified in Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006, must be accomplished in accordance with Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006. (2) Revise the ALS of the ICA to incorporate the new and revised structural inspections and inspection intervals defined in Airbus Temporary Revision (TR) 6.1, dated November 2006 (approved by the EASA on December 12, 2006), to Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006. Thereafter, except as provided by paragraph (t)(1) of this AD, no alternative structural inspection intervals may be approved. Exception to Issue 6 of the ALI (p) The tolerance (grace period) for compliance with Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006, is within 1,500 flight cycles after January 14, 2008, provided that none of the following is exceeded. (1) Thresholds or intervals in the operator's current approved maintenance schedule that are taken from a previous ALI issue, if existing, and are higher than or equal to those given in Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006. (2) 18 months after January 14, 2008. (3) 50 percent of the intervals given in Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006. (4) Any application tolerance specified in Section D of Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006. Corrective Actions (q) Damaged, cracked, or corroded structure detected during any inspection done in accordance with Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006, must be repaired, before further flight, in accordance with Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006; or in accordance with other data meeting the certification basis of the airplane that has been approved by either the Manager, International Branch, ANM-116, or the EASA (or its delegated agent). Where Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006, specifies to contact Airbus for appropriate action: Before further flight, repair the damaged, cracked, or corroded structure using a method approved by either the Manager, International Branch, ANM-116, or the EASA (or its delegated agent). Reporting Requirement (r) If any damage that exceeds the allowable limits specified in Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006, is detected during any inspection required by this AD: At the applicable time specified in paragraph (r)(1) or (r)(2) of this AD, submit a report of the finding to Airbus, Customer Service Directorate, Attn: Department Manager Maintenance Engineering, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; e-mail: sched.maint@airbus.com. The report must include the ALI task reference, airplane serial number, the number of flight cycles and flight hours on the airplane, identification of the affected structure, location and description of the finding including its size and orientation, and the circumstance of detection and inspection method used. (1) If the inspection was done after January 14, 2008: Submit the report within 30 days after the inspection. (2) If the inspection was accomplished prior to January 14, 2008: Submit the report within 30 days after January 14, 2008. New Requirements of This AD Revision of the ALS of the Instructions for ICA (s) Within 3 months after the effective date of this AD: Revise the maintenance program to incorporate the structural inspections and inspection intervals defined in the applicable ALI document listed in Table 1 of this AD. Thereafter, except as provided by paragraph (t)(1) of this AD, no alternative structural inspections and inspection intervals may be approved. The actions must be accomplished in accordance with the applicable issue of the ALI. The initial ALI tasks must be done at the times specified in the applicable ALI document listed in Table 1 of this AD. Accomplishing the applicable initial ALI tasks constitutes terminating action for the requirements of paragraphs (g) through (r) of this AD for that airplane only. Table 1—Airworthiness Limitations Items Document Model Document Issue Date A300 Airbus A300 Airworthiness Limitation Items Document AI/SE-M2/95A.1308/07 4 June 2008. A310 Airbus A310 Airworthiness Limitation Items Document AI/SE-M2/95A.1309/07 7 June 2008. A300-600 Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.1310/07 12 June 2008. FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows: Where the MCAI includes a compliance time of “from the effective date of this AD,″ we have determined that a compliance time of “within 3 months after the effective date of this AD″ is appropriate. The manufacturer and EASA agree with this difference in compliance time. Other FAA AD Provisions (t) 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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-2125; fax (425) 227-1149. Information may be e-mailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. AMOCs approved previously in accordance with AD 2007-04-11, Amendment 39-14943; AD 2007-20-03, Amendment 39-15213; and AD 2007-25-02, Amendment 39-15283; as applicable; are approved as AMOCs for the corresponding provisions of this AD. (2) 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. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200. Related Information (u) Refer to MCAI EASA Airworthiness Directive 2009-0155, dated July 17, 2009; Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006; Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.1310/07, Issue 12, dated June 2008; Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, as revised by Airbus A300 Temporary Revision 3.1, dated April 2006; Airbus A300 Airworthiness Limitation Items Document AI/SE-M2/95A.1308/07, Issue 4, dated June 2008; Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006; Airbus Temporary Revision 6.1, dated November 2006; Airbus A310 Airworthiness Limitation Items Document, AI/SE-M2/95A.1309/07, Issue 7, dated June 2008; and Airbus Industrie A300 Structural Inspection Document, Revision 2, dated June 1994; for related information. Material Incorporated by Reference (v) You must use the service information contained in Table 2 of this AD to do the actions required by this AD, as applicable, unless the AD specifies otherwise. Table 2—All Material Incorporated by Reference Document Issue/revision Date Airbus A300 Airworthiness Limitation Items Document AI/SE-M2/95A.1308/07 4 June 2008. Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, as revised by Airbus A300 TR 3.1, dated April 2006 3 September 2005. Airbus A300 Airworthiness Limitation Items, Document SEM2/95A.1090/05, Temporary Revision 3.1, including attachment, dated April 2006, and including attachments dated September 2005 Original April 2006. Airbus Temporary Revision 6.1, including pages 1 and 2 of Section D and page 1 of Section E, dated November 2006, to Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006 Original November 2006. Airbus A310 Airworthiness Limitation Items Document AI/SE-M2/95A.1309/07 7 June 2008. Airbus A310 Airworthiness Limitations Items Document AI/SE-M2/95A.0263/06 6 April 2006. Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.1310/07 12 June 2008. Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06 11 April 2006. Airbus Industrie A300 Structural Inspection Document 2 June 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 Document Issue Date Airbus A300 Airworthiness Limitation Items Document AI/SE-M2/95A.1308/07 4 June 2008. Airbus A310 Airworthiness Limitation Items Document AI/SE-M2/95A.1309/07 7 June 2008. Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.1310/07 12 June 2008. (2) The Director of the Federal Register previously approved the incorporation by reference of Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006; and Airbus Temporary Revision 6.1, including pages 1 and 2 of Section D and page 1 of Section E, dated November 2006, to Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006; on January 14, 2008 (72 FR 69612, December 10, 2007). (3) The Director of the Federal Register previously approved the incorporation by reference of Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006, on October 31, 2007 (72 FR 54536, September 26, 2007). (4) The Director of the Federal Register previously approved the incorporation by reference of Airbus A300 Airworthiness Limitations Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, as revised by Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Temporary Revision 3.1, including attachment, dated April 2006, and including attachments, dated September 2005, on April 3, 2007 (72 FR 8604, February 27, 2007). (5) The Director of the Federal Register previously approved the incorporation by reference of Airbus Industrie A300 Supplemental Structural Inspection Document, Revision 2, dated June 1994, on August 9, 1996 (61 FR 35122, July 5, 1996). (6) 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. (7) 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. (8) 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 May 2, 2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011-11333 Filed 5-12-11; 8:45 am] BILLING CODE 4910-13-P