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), 27875-27880 [2011-11333]

Download as PDF Federal Register / Vol. 76, No. 93 / Friday, May 13, 2011 / Rules and Regulations (1) Within the next 10 hours time-inservice (TIS) after May 31, 2011 (the effective date of this AD) or within the next 10 days after May 31, 2011 (the effective date of this AD), whichever occurs first, cut off the rubber flap of the two flapper valves near frame 36, inspect the flapper valves, and do the functional test of the valves and fuselage drainage holes following Part A of PIAGGIO AERO INDUSTRIES S.p.A. Service Bulletin (Mandatory) N.: 80–0330, dated April 21, 2011. (2) If in the inspection and functional test required in paragraph (f)(1) of this AD the valves and drain holes are found to not drain properly, before further flight, take corrective action following Part A of PIAGGIO AERO INDUSTRIES S.p.A. Service Bulletin (Mandatory) N.: 80–0330, dated April 21, 2011. (3) Within the next 165 hours TIS after May 31, 2011 (the effective date of this AD) or within the next 90 days after May 31, 2011 (the effective date of this AD), whichever occurs first, add drain holes on keel beam webs connecting the lateral bays to the center bays following Part B of PIAGGIO AERO INDUSTRIES S.p.A. Service Bulletin (Mandatory) N.: 80–0330, dated April 21, 2011; or PIAGGIO AERO INDUSTRIES S.p.A. Service Bulletin (Mandatory) N.: 80–0291, dated November 29, 2010. (4) Within 10 days after complying with the actions required in paragraphs (f)(1), (f)(2), and (f)(3) of this AD or within 10 days after May 31, 2011 (the effective date of this AD), whichever occurs later, report the results (including no findings) using the Confirmation Slip attached to PIAGGIO AERO INDUSTRIES S.p.A. Service Bulletin (Mandatory) N.: 80–0330, dated April 21, 2011. Send the report to Piaggio at one of the addresses (facsimile, email) referenced in the Related Information section, paragraph (i)(2) of this AD. FAA AD Differences WReier-Aviles on DSKGBLS3C1PROD with RULES Note: This AD differs from the MCAI and/ or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, 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: Mike Kiesov, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4144; fax: (816) 329– 4090. 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. (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 VerDate Mar<15>2010 15:13 May 12, 2011 Jkt 223001 27875 to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For the reporting requirement in this AD, 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. Issued in Kansas City, Missouri, on May 4, 2011. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. Related Information AGENCY: (h) Refer to EASA AD No.: 2011–0074–E, dated April 22, 2011; PIAGGIO AERO INDUSTRIES S.p.A. Service Bulletin (Mandatory) N.: 80–0330, dated April 21, 2011; and PIAGGIO AERO INDUSTRIES S.p.A. Service Bulletin (Mandatory) N.: 80– 0291, dated November 29, 2010 for related information. SUMMARY: Material Incorporated by Reference (i) You must use PIAGGIO AERO INDUSTRIES S.p.A. Service Bulletin (Mandatory) N.: 80–0330, dated April 21, 2011; and PIAGGIO AERO INDUSTRIES S.p.A. Service Bulletin (Mandatory) N.: 80– 0291, dated November 29, 2010, to do the actions required by this AD, unless the AD specifies otherwise. (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 Piaggio Aero Industries S.p.A–Airworthiness Office; Via Luigi Cibrario, 4—16154 Genova—Italy; telephone: +39 010 6481353; fax: +39 010 6481881; E-mail: airworthiness@piaggioaero.it. (3) You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. (4) You may also review copies of the service information incorporated by reference for this AD 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: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 [FR Doc. 2011–11330 Filed 5–12–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0030; Directorate Identifier 2009–NM–183–AD; Amendment 39–16698; AD 2011–10–17] RIN 2120–AA64 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) Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. We are superseding three existing airworthiness directives (ADs) that apply to the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: The airworthiness limitations applicable to the Damage Tolerant Airworthiness Limitation Items (DT ALI) are currently listed in Airbus ALI Documents, which are referenced in the A300, A310, and A300–600 Airworthiness Limitations Section (ALS) Part 2. Airbus has recently revised the ALI Documents, which have been approved by the European Aviation Safety Agency (EASA). * * * * * The actions contained in these revised documents, which introduce more restrictive maintenance requirements and/or airworthiness limitations, have been identified as mandatory actions for continued airworthiness. * * * The unsafe condition is fatigue cracking, damage, or corrosion in principal structural elements, which could result in reduced structural integrity of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective June 17, 2011. The Director of the Federal Register approved the incorporation by reference E:\FR\FM\13MYR1.SGM 13MYR1 27876 Federal Register / Vol. 76, No. 93 / Friday, May 13, 2011 / Rules and Regulations of certain publications listed in this AD as of June 17, 2011. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of January 14, 2008 (72 FR 69612, December 10, 2007). The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of October 31, 2007 (72 FR 54536, September 26, 2007). The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of April 3, 2007 (72 FR 8604, February 27, 2007). The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of August 9, 1996 (61 FR 35122, July 5, 1996). ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: 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. SUPPLEMENTARY INFORMATION: WReier-Aviles on DSKGBLS3C1PROD with RULES Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on January 25, 2011 (76 FR 4260), and proposed to supersede AD 2007–04–11, Amendment 39–14943 (72 FR 8604, February 27, 2007); AD 2007– 20–03, Amendment 39–15213 (72 FR 54536, September 26, 2007); and AD 2007–25–02, Amendment 39–15283 (72 FR 69612, December 10, 2007). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: The airworthiness limitations applicable to the Damage Tolerant Airworthiness Limitation Items (DT ALI) are currently listed in Airbus ALI Documents, which are referenced in the A300, A310, and A300–600 Airworthiness Limitations Section (ALS) Part 2. Airbus has recently revised the ALI Documents, which have been approved by the European Aviation Safety Agency (EASA). —Airbus A300 ALI Document issue 04. —Airbus A310 ALI Document issue 07 and —Airbus A300–600 ALI Document issue 12 VerDate Mar<15>2010 15:13 May 12, 2011 Jkt 223001 The actions contained in these revised documents, which introduce more restrictive maintenance requirements and/or airworthiness limitations, have been identified as mandatory actions for continued airworthiness. EASA issued ADs 2006–0071, 2006–0260, and 2006–0374 [which correspond to FAA ADs 2007–04–11, 2007– 25–02, and 2007–20–03] to require compliance with the maintenance requirements and associated airworthiness limitations defined in previous issues of these Airbus ALI documents. For the reason described above, [the] EASA AD supersedes existing ADs 2006–0071, 2006–0260, and 2006–0374 and requires an update to the approved aircraft maintenance programme and compliance with the maintenance requirements and associated airworthiness limitations defined in the Airbus ALI Documents listed above. The actions that are required by AD 2007–04–11, AD 2007–20–03, and AD 2007–25–02, and retained in this proposed AD, take about 1 work hour per product. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of those actions on U.S. operators to be $85 per product. We estimate that it will take about 1 work-hour per product to comply with the new basic requirements of this AD. The average labor rate is $85 per workhour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $17,510, or $85 per product. The unsafe condition is fatigue cracking, damage, or corrosion in principal structural elements, which could result in reduced structural integrity of the airplane. The required actions include revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness to incorporate new and revised structural inspections and inspection intervals. You may obtain further information by examining the MCAI in the AD docket. Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,″ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.″ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance We estimate that this AD will affect about 206 products of U.S. registry. PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 Authority for This Rulemaking Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this AD: 1. Is not a ‘‘significant regulatory action″ under Executive Order 12866; 2. Is not a ‘‘significant rule″ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. E:\FR\FM\13MYR1.SGM 13MYR1 Federal Register / Vol. 76, No. 93 / Friday, May 13, 2011 / Rules and Regulations Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–14943 (72 FR 8604, February 27, 2007); Amendment 39–15213 (72 FR 54536, September 26, 2007); and Amendment 39–15283 (72 FR 69612, December 10, 2007); and adding the following new AD: ■ 2011–10–17 Airbus: Amendment 39–16698. Docket No. FAA–2011–0030; Directorate Identifier 2009–NM–183–AD. Effective Date (a) This airworthiness directive (AD) becomes effective June 17, 2011. WReier-Aviles on DSKGBLS3C1PROD with RULES Affected ADs (b) This AD supersedes AD 2007–04–11, Amendment 39–14943; AD 2007–20–03, Amendment 39–15213; and AD 2007–25–02, Amendment 39–15283. Applicability (c) 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 VerDate Mar<15>2010 15:13 May 12, 2011 Jkt 223001 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. Subject (d) Air Transport Association (ATA) of America Codes 52: Doors; 53: Fuselage; 54: Nacelles/pylons; 55: Stabilizers; 57: Wings; and 71: Powerplant (for Model A300–600 only). Reason (e) The mandatory continuing airworthiness information (MCAI) states: The airworthiness limitations applicable to the Damage Tolerant Airworthiness Limitation Items (DT ALI) are currently listed in Airbus ALI Documents, which are referenced in the A300, A310, and A300–600 Airworthiness Limitations Section (ALS) Part 2. Airbus has recently revised the ALI Documents, which have been approved by the European Aviation Safety Agency (EASA). * * * * * The actions contained in these revised documents, which introduce more restrictive maintenance requirements and/or airworthiness limitations, have been identified as mandatory actions for continued airworthiness. * * * The unsafe condition is fatigue cracking, damage, or corrosion in principal structural elements, which could result in reduced structural integrity of the airplane. Compliance (f) 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. PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 27877 (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, E:\FR\FM\13MYR1.SGM 13MYR1 27878 Federal Register / Vol. 76, No. 93 / Friday, May 13, 2011 / Rules and Regulations 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. WReier-Aviles on DSKGBLS3C1PROD with RULES Restatement of Requirements of AD 2007– 20–03 Actions and Compliance (n) 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. VerDate Mar<15>2010 15:13 May 12, 2011 Jkt 223001 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. PO 00000 Frm 00032 Fmt 4700 Sfmt 4700 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. E:\FR\FM\13MYR1.SGM 13MYR1 27879 Federal Register / Vol. 76, No. 93 / Friday, May 13, 2011 / Rules and Regulations TABLE 1—AIRWORTHINESS LIMITATIONS ITEMS DOCUMENT Model Document A300 ................................................... Airbus A300 Airworthiness Limitation Items Document AI/SE–M2/ 95A.1308/07. Airbus A310 Airworthiness Limitation Items Document AI/SE–M2/ 95A.1309/07. Airbus A300–600 Airworthiness Limitation Items Document AI/SE–M2/ 95A.1310/07. A310 ................................................... A300–600 ........................................... 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/ Issue 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 FAAapproved 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 Date 4 June 2008. 7 June 2008. 12 June 2008. 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 WReier-Aviles on DSKGBLS3C1PROD with RULES Document Issue/revision Airbus A300 Airworthiness Limitation Items Document AI/SE–M2/95A.1308/07 ............................. Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, as revised by Airbus A300 TR 3.1, dated April 2006. 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. 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. Airbus A310 Airworthiness Limitation Items Document AI/SE-M2/95A.1309/07 .............................. Airbus A310 Airworthiness Limitations Items Document AI/SE-M2/95A.0263/06 ............................ Airbus A300–600 Airworthiness Limitation Items Document AI/SE-M2/95A.1310/07 ...................... Airbus A300–600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06 ...................... Airbus Industrie A300 Structural Inspection Document .................................................................... 4 .................................. 3 .................................. June 2008. September 2005. Original ........................ April 2006. Original ........................ November 2006. 7 .................................. 6 .................................. 12 ................................ 11 ................................ 2 .................................. June 2008. April 2006. June 2008. April 2006. June 1994. (1) The Director of the Federal Register approved the incorporation by reference of the service information contained in Table 3 VerDate Mar<15>2010 15:13 May 12, 2011 Jkt 223001 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51. PO 00000 Frm 00033 Fmt 4700 Sfmt 4700 E:\FR\FM\13MYR1.SGM 13MYR1 Date 27880 Federal Register / Vol. 76, No. 93 / Friday, May 13, 2011 / Rules and Regulations TABLE 3—NEW MATERIAL INCORPORATED BY REFERENCE Document Issue WReier-Aviles on DSKGBLS3C1PROD with RULES Airbus A300 Airworthiness Limitation Items Document AI/SE–M2/95A.1308/07 ................................................................. Airbus A310 Airworthiness Limitation Items Document AI/SE–M2/95A.1309/07 ................................................................. Airbus A300–600 Airworthiness Limitation Items Document AI/SE–M2/95A.1310/07 ......................................................... (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.airwortheas@airbus.com; Internet https:// 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: https://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 VerDate Mar<15>2010 15:13 May 12, 2011 Jkt 223001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 RIN 2120–AA64 Airworthiness Directives; DASSAULT AVIATION Model MYSTERE–FALCON 50 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding an existing airworthiness directive (AD) that applies to the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: SUMMARY: ` On two occurrences on Mystere-Falcon 50 aeroplanes in service, it was detected that two pipes of the emergency brake system #2 located near the nose landing gear bearing were swapped. The swapping of these two pipes implies that when the Left Hand (LH) brake pedal is depressed, the Right Hand (RH) brake unit is activated, and conversely, when the RH brake pedal is depressed, the LH brake unit is actuated. This constitutes an unsafe condition, which may go unnoticed as the condition is latent until the emergency brake system #2 is used. This condition, if not corrected, could ultimately lead to a runway excursion of the aeroplane. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective June 17, 2011. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 9, 2010 (75 FR 71530, November 24, 2010). ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Frm 00034 Fmt 4700 June 2008. June 2008. June 2008. Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1137; fax (425) 227–1149. FOR FURTHER INFORMATION CONTACT: [Docket No. FAA–2011–0042; Directorate Identifier 2010–NM–267–AD; Amendment 39–16695; AD 2011–10–14] PO 00000 4 7 12 Date Sfmt 4700 SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on February 16, 2011 (76 FR 8919), and proposed to supersede AD 2010–24–08, Amendment 39–16527 (75 FR 71530, November 24, 2010). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: In AD 2010–24–08, we pointed out that the corresponding EASA AD, AD 2010–0208–E, dated October 12, 2010, requires painting the pipes end of the emergency brake system number 2 and related unions within 7 months after the effective date of that AD. We explained that AD 2010–24–08 did not require that action, and that we might consider additional rulemaking to require this action in the future. We have determined that further rulemaking is indeed necessary to require that action, and this AD follows from that determination. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. E:\FR\FM\13MYR1.SGM 13MYR1

Agencies

[Federal Register Volume 76, Number 93 (Friday, May 13, 2011)]
[Rules and Regulations]
[Pages 27875-27880]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-11333]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0030; Directorate Identifier 2009-NM-183-AD; 
Amendment 39-16698; AD 2011-10-17]
RIN 2120-AA64


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)

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are superseding three existing airworthiness directives 
(ADs) that apply to the products listed above. This AD results from 
mandatory continuing airworthiness information (MCAI) originated by an 
aviation authority of another country to identify and correct an unsafe 
condition on an aviation product. The MCAI describes the unsafe 
condition as:

    The airworthiness limitations applicable to the Damage Tolerant 
Airworthiness Limitation Items (DT ALI) are currently listed in 
Airbus ALI Documents, which are referenced in the A300, A310, and 
A300-600 Airworthiness Limitations Section (ALS) Part 2. Airbus has 
recently revised the ALI Documents, which have been approved by the 
European Aviation Safety Agency (EASA).
* * * * *
    The actions contained in these revised documents, which 
introduce more restrictive maintenance requirements and/or 
airworthiness limitations, have been identified as mandatory actions 
for continued airworthiness. * * *

    The unsafe condition is fatigue cracking, damage, or corrosion in 
principal structural elements, which could result in reduced structural 
integrity of the airplane. We are issuing this AD to require actions to 
correct the unsafe condition on these products.

DATES: This AD becomes effective June 17, 2011.
    The Director of the Federal Register approved the incorporation by 
reference

[[Page 27876]]

of certain publications listed in this AD as of June 17, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of January 
14, 2008 (72 FR 69612, December 10, 2007).
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
October 31, 2007 (72 FR 54536, September 26, 2007).
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of April 
3, 2007 (72 FR 8604, February 27, 2007).
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of August 
9, 1996 (61 FR 35122, July 5, 1996).

ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: 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.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on January 25, 2011 (76 
FR 4260), and proposed to supersede AD 2007-04-11, Amendment 39-14943 
(72 FR 8604, February 27, 2007); AD 2007-20-03, Amendment 39-15213 (72 
FR 54536, September 26, 2007); and AD 2007-25-02, Amendment 39-15283 
(72 FR 69612, December 10, 2007). That NPRM proposed to correct an 
unsafe condition for the specified products. The MCAI states:

    The airworthiness limitations applicable to the Damage Tolerant 
Airworthiness Limitation Items (DT ALI) are currently listed in 
Airbus ALI Documents, which are referenced in the A300, A310, and 
A300-600 Airworthiness Limitations Section (ALS) Part 2. Airbus has 
recently revised the ALI Documents, which have been approved by the 
European Aviation Safety Agency (EASA).

--Airbus A300 ALI Document issue 04.
--Airbus A310 ALI Document issue 07 and
--Airbus A300-600 ALI Document issue 12

    The actions contained in these revised documents, which 
introduce more restrictive maintenance requirements and/or 
airworthiness limitations, have been identified as mandatory actions 
for continued airworthiness. EASA issued ADs 2006-0071, 2006-0260, 
and 2006-0374 [which correspond to FAA ADs 2007-04-11, 2007-25-02, 
and 2007-20-03] to require compliance with the maintenance 
requirements and associated airworthiness limitations defined in 
previous issues of these Airbus ALI documents.
    For the reason described above, [the] EASA AD supersedes 
existing ADs 2006-0071, 2006-0260, and 2006-0374 and requires an 
update to the approved aircraft maintenance programme and compliance 
with the maintenance requirements and associated airworthiness 
limitations defined in the Airbus ALI Documents listed above.

    The unsafe condition is fatigue cracking, damage, or corrosion in 
principal structural elements, which could result in reduced structural 
integrity of the airplane. The required actions include revising the 
Airworthiness Limitations section of the Instructions for Continued 
Airworthiness to incorporate new and revised structural inspections and 
inspection intervals. You may obtain further information by examining 
the MCAI in the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a NOTE within the AD.

Costs of Compliance

    We estimate that this AD will affect about 206 products of U.S. 
registry.
    The actions that are required by AD 2007-04-11, AD 2007-20-03, and 
AD 2007-25-02, and retained in this proposed AD, take about 1 work hour 
per product. The average labor rate is $85 per work-hour. Based on 
these figures, we estimate the cost of those actions on U.S. operators 
to be $85 per product.
    We estimate that it will take about 1 work-hour per product to 
comply with the new basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD to the U.S. operators to be $17,510, or $85 per product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

[[Page 27877]]

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains the NPRM, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Amendment 39-14943 (72 FR 
8604, February 27, 2007); Amendment 39-15213 (72 FR 54536, September 
26, 2007); and Amendment 39-15283 (72 FR 69612, December 10, 2007); and 
adding the following new AD:

2011-10-17 Airbus: Amendment 39-16698. Docket No. FAA-2011-0030; 
Directorate Identifier 2009-NM-183-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective June 17, 
2011.

Affected ADs

    (b) This AD supersedes AD 2007-04-11, Amendment 39-14943; AD 
2007-20-03, Amendment 39-15213; and AD 2007-25-02, Amendment 39-
15283.

Applicability

    (c) 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.

Subject

    (d) Air Transport Association (ATA) of America Codes 52: Doors; 
53: Fuselage; 54: Nacelles/pylons; 55: Stabilizers; 57: Wings; and 
71: Powerplant (for Model A300-600 only).

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    The airworthiness limitations applicable to the Damage Tolerant 
Airworthiness Limitation Items (DT ALI) are currently listed in 
Airbus ALI Documents, which are referenced in the A300, A310, and 
A300-600 Airworthiness Limitations Section (ALS) Part 2. Airbus has 
recently revised the ALI Documents, which have been approved by the 
European Aviation Safety Agency (EASA).
* * * * *
    The actions contained in these revised documents, which 
introduce more restrictive maintenance requirements and/or 
airworthiness limitations, have been identified as mandatory actions 
for continued airworthiness. * * *

The unsafe condition is fatigue cracking, damage, or corrosion in 
principal structural elements, which could result in reduced 
structural integrity of the airplane.

Compliance

    (f) 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,

[[Page 27878]]

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

Actions and Compliance

    (n) 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.

[[Page 27879]]



                                Table 1--Airworthiness Limitations Items Document
----------------------------------------------------------------------------------------------------------------
                 Model                              Document                Issue                Date
----------------------------------------------------------------------------------------------------------------
A300...................................  Airbus A300 Airworthiness                 4  June 2008.
                                          Limitation Items Document AI/
                                          SE-M2/95A.1308/07.
A310...................................  Airbus A310 Airworthiness                 7  June 2008.
                                          Limitation Items Document AI/
                                          SE-M2/95A.1309/07.
A300-600...............................  Airbus A300-600 Airworthiness            12  June 2008.
                                          Limitation Items Document AI/
                                          SE-M2/95A.1310/07.
----------------------------------------------------------------------------------------------------------------

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    4....................................  June 2008.
 Items Document AI/SE-M2/95A.1308/07.
Airbus A300 Airworthiness Limitation    3....................................  September 2005.
 Items Document SEM2/95A.1090/05, as
 revised by Airbus A300 TR 3.1, dated
 April 2006.
Airbus A300 Airworthiness Limitation    Original.............................  April 2006.
 Items, Document SEM2/95A.1090/05,
 Temporary Revision 3.1, including
 attachment, dated April 2006, and
 including attachments dated September
 2005.
Airbus Temporary Revision 6.1,          Original.............................  November 2006.
 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.
Airbus A310 Airworthiness Limitation    7....................................  June 2008.
 Items Document AI/SE[dash]M2/95A.1309/
 07.
Airbus A310 Airworthiness Limitations   6....................................  April 2006.
 Items Document AI/SE[dash]M2/95A.0263/
 06.
Airbus A300-600 Airworthiness           12...................................  June 2008.
 Limitation Items Document AI/
 SE[dash]M2/95A.1310/07.
Airbus A300-600 Airworthiness           11...................................  April 2006.
 Limitation Items Document AI/
 SE[dash]M2/95A.0502/06.
Airbus Industrie A300 Structural        2....................................  June 1994.
 Inspection Document.
----------------------------------------------------------------------------------------------------------------

     (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.

[[Page 27880]]



             Table 3--New Material Incorporated by Reference
------------------------------------------------------------------------
               Document                  Issue             Date
------------------------------------------------------------------------
Airbus A300 Airworthiness Limitation           4  June 2008.
 Items Document AI/SE-M2/95A.1308/07.
Airbus A310 Airworthiness Limitation           7  June 2008.
 Items Document AI/SE-M2/95A.1309/07.
Airbus A300-600 Airworthiness                 12  June 2008.
 Limitation Items Document AI/SE-M2/
 95A.1310/07.
------------------------------------------------------------------------

     (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 https://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: https://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