Airworthiness Directives; Airbus Airplanes, 66772-66777 [2012-27126]

Download as PDF 66772 Federal Register / Vol. 77, No. 216 / Wednesday, November 7, 2012 / Proposed Rules products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed regulation: 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 proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The FAA amends § 39.13 by adding the following new AD: pmangrum on DSK3VPTVN1PROD with PROPOSALS-1 Rolls-Royce Deutschland Ltd & Co KG (Formerly Rolls-Royce Deutschland GmbH, and BMW Rolls-Royce plc): Docket No. FAA–2012–1100; Directorate Identifier 2012–NE–29–AD. (a) Comments Due Date We must receive comments by January 7, 2013. (b) Affected Airworthiness Directives (ADs) None. (c) Applicability This AD applies to Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700– 710A1–10 and BR700–710A2–20 turbofan engines, all serial numbers, and BR700– 710C4–11 turbofan engines that have either VerDate Mar<15>2010 15:18 Nov 06, 2012 Jkt 229001 Issued in Burlington, Massachusetts, on October 26, 2012. Colleen M. D’Alessandro, Assistant Manager, Engine & Propeller Directorate, Aircraft Certification Service. (d) Reason DEPARTMENT OF TRANSPORTATION This AD was prompted by service experience that demonstrated premature wear of the splined coupling on the fuel pump. We are issuing this AD to prevent failure of the engine and loss of the airplane. (e) Actions and Compliance Unless already done, do the following. (1) After the effective date of this AD, replace the fuel pump splined coupling as follows and every 4,000 hours time in service (TIS) thereafter: (i) If the engine has 3,750 hours TIS or more, within 250 hours TIS. (ii) If the engine has less than 3,750 hours TIS, before reaching 4,000 hours TIS. (2) If you replaced the engine fuel pump splined coupling before the effective date of this AD, replace the fuel pump splined coupling before reaching 4,000 hours TIS since last replacement, or before further flight, whichever comes later. (f) Installation Prohibition After the effective date of this AD, do not approve for return to service any engine with a fuel pump with an affected splined coupling that has accumulated 4,000 hours TIS, or any airplane with an engine with an affected fuel pump splined coupling installed that has accumulated 4,000 hours TIS. (g) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs to this AD. Use the procedures found in 14 CFR 39.19 to make your request. 1. The authority citation for part 39 continues to read as follows: § 39.13 of the following hardware configuration standards engraved on the engine data plate: (1) standard 710C4–11, RRD Alert NonModification Service Bulletin (NMSB) SB– BR700–72–101466 standard not incorporated, or (2) standard 710C4–11/10, RRD Alert NMSB SB–BR700–72–101466 standard incorporated. (h) Related Information (1) For more information about this AD, contact Frederick Zink, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; email: frederick.zink@faa.gov; phone: 781– 238–7779; fax: 781–238–7199. (2) Refer to MCAI Airworthiness Directive No. 2012–0161, dated August 24, 2012, and RRD Alert NMSB SB–BR700–72–A900509, Revision 3, dated August 2, 2012, for related information. (3) For service information identified in this AD, contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlewitz, 15827 Blankenfelde-Mahlow, Germany; telephone: 49 0 33–7086–1883; fax: 49 0 33–7086–3276. You may review copies of the referenced service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. PO 00000 Frm 00025 Fmt 4702 Sfmt 4702 [FR Doc. 2012–27108 Filed 11–6–12; 8:45 am] BILLING CODE 4910–13–P Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–1158; Directorate Identifier 2011–NM–232–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede an existing airworthiness directive (AD) that applies to all Airbus Model A300 and A310 series airplanes; and Model A300 B4–600, B4–600R, and F4–600R series airplanes, and Model A300 C4– 605R Variant F airplanes (collectively called A300–600 series airplanes). The existing AD currently requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness to incorporate new and revised structural inspections and inspection intervals. Since we issued that AD, Airbus has revised certain ALI documents, which require more restrictive maintenance requirements and airworthiness limitations. This proposed AD would revise the maintenance program to incorporate the limitations section. We are proposing this AD to prevent fatigue cracking, damage, or corrosion in principal structural elements, which could result in reduced structural integrity of the airplane. SUMMARY: We must receive comments on this proposed AD by December 24, 2012. DATES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– ADDRESSES: E:\FR\FM\07NOP1.SGM 07NOP1 Federal Register / Vol. 77, No. 216 / Wednesday, November 7, 2012 / Proposed Rules 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed 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; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may review copies of the referenced 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. Examining the AD Docket You may examine the AD docket on the Internet at http:// 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 this proposed AD, 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. Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: pmangrum on DSK3VPTVN1PROD with PROPOSALS-1 Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2012–1158; Directorate Identifier 2011–NM–232–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. VerDate Mar<15>2010 15:18 Nov 06, 2012 Jkt 229001 Discussion On May 2, 2011, we issued AD 2011– 10–17, Amendment 39–16698 (76 FR 27875, May 13, 2011). That AD required actions intended to address an unsafe condition on the products listed above. Since we issued AD 2011–10–17, Amendment 39–16698 (76 FR 27875, May 13, 2011), Airbus has revised certain ALI documents, which require more restrictive maintenance requirements and airworthiness limitations. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2011– 0198, dated October 19, 2011 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: The airworthiness limitations applicable to the Damage Tolerant Airworthiness Limitation Items (DT ALIs) are currently listed in Airbus ALI Documents, which are referenced in the A300, A310 and A300–600 Airworthiness Limitations Section (ALS) Part 2. Airbus have recently revised the A300–600 and A310 ALI Documents, and these issues have been approved by EASA. The Airbus A300–600 ALI Document issue 13 and temporary revision (TR) 13.1 and the A310 ALI document issue 08 introduce more restrictive maintenance requirements and airworthiness limitations, which have been identified as mandatory actions for continued airworthiness. EASA AD 2009–0155 [which corresponds to FAA AD 2011–10–17, Amendment 39– 16698 (76 FR 27875, May 13, 2011)] required compliance with the maintenance requirements and associated airworthiness limitations defined in the following documents: —AIRBUS A300 ALI Document issue 04, —AIRBUS A310 ALI Document issue 07, and —AIRBUS A300–600 ALI Document issue 12. For the reasons described, this EASA AD retains the requirements of EASA AD 2009– 0155, which is superseded, and requires compliance with the airworthiness limitations defined in the Airbus A300–600 ALI Document issue 13 and TR13.1, and the A310 ALI document issue 08. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued the following service information. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. • Airbus A310 Airworthiness Limitation Items Document, AI/SE–M2/ 95A.1309/07, Issue 8, dated October 2010 (for Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes). PO 00000 Frm 00026 Fmt 4702 Sfmt 4702 66773 • Airbus A300–600 Airworthiness Limitation Items Document, AI/SE–M2/ 95A.1310/07, Issue 13, dated October 2010 (Model A300 B4–601, B4–603, B4– 620, B4–622, B4–605R, B4–622R, F4– 605R, F4–622R, and C4–605R Variant F airplanes). • Airbus Temporary Revision 13.1, dated February 2011, to the Airbus A300–600 Airworthiness Limitation Items Document, AI/SE–M2/95A.1310/ 07, Issue 13, dated October 2010 (for Model A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, F4–605R, F4–622R, and C4–605R Variant F airplanes). FAA’s Determination and Requirements of This Proposed AD These products have been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. This proposed AD requires revisions to certain operator maintenance documents to include new actions (e.g., inspections). Compliance with these actions is required by section 91.403(c) of the Federal Aviation Regulations (14 CFR 91.403(c)). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, an operator might not be able to accomplish the actions described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval of an alternative method of compliance (AMOC) in accordance with the provisions of paragraph (u)(1) of this proposed AD. The request should include a description of changes to the required actions that will ensure the continued damage tolerance of the affected structure. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 170 products of U.S. registry. The actions that are required by AD 2011–10–17, Amendment 39–16698 (76 FR 27875, May 13, 2011), and retained in this proposed AD take about 1 workhour per product, at an average labor rate of $85 per work hour. Based on these figures, the estimated cost of the E:\FR\FM\07NOP1.SGM 07NOP1 66774 Federal Register / Vol. 77, No. 216 / Wednesday, November 7, 2012 / Proposed Rules currently required actions is $85 per product. We estimate that it would take about 1 work-hour per product to comply with the new basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $14,450, 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. pmangrum on DSK3VPTVN1PROD with PROPOSALS-1 Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed regulation: 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); 3. Will not affect intrastate aviation in Alaska; and 4. 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 proposed AD and placed it in the AD docket. VerDate Mar<15>2010 15:18 Nov 06, 2012 Jkt 229001 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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 airworthiness directive (AD) 2011–10–17, Amendment 39–16698 (76 FR 27875, May 13, 2011), and adding the following new AD: Airbus: Docket No. FAA–2012–1158; Directorate Identifier 2011–NM–232–AD. (a) Comments Due Date We must receive comments by December 24, 2012. (b) Affected ADs This AD supersedes AD 2011–10–17, Amendment 39–16698 (76 FR 27875, May 13, 2011), which superseded 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). AD 2007– 04–11 superseded AD 96–13–11, Amendment 39–9679 (61 FR 35122, July 5, 1996). (c) Applicability 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) Model A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, F4–605R, F4– 622R, and C4–605R Variant F airplanes. (d) Subject Air Transport Association (ATA) of America Code 57: Wings. (e) Reason This AD was prompted by revisions of certain Airbus Airworthiness Limitation Items (ALI) documents, which require more restrictive maintenance requirements and airworthiness limitations. We are issuing this AD to prevent fatigue cracking, damage, or corrosion in principal structural elements, which could result in reduced structural integrity of the airplane. PO 00000 Frm 00027 Fmt 4702 Sfmt 4702 (f) Compliance You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. (g) Retained Maintenance Program Revision This paragraph restates the requirements of paragraph (g) of AD 2011–10–17, Amendment 39–16698 (76 FR 27875, May 13, 2011). Within one year after August 9, 1996 (the effective date of AD 96–13–11, Amendment 39–9679 (61 FR 35122, July 5, 1996)), 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 (r) 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 (the effective date of AD 96–13–11, Amendment 39–9679 (61 FR 35122, July 5, 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 (the effective date of AD 96–13–11, Amendment 39–9679 (61 FR 35122, July 5, 1996)). (h) Retained Revision of the Maintenance Inspection Program This paragraph restates the requirements of paragraphs (h) and (i) of AD 2011–10–17, Amendment 39–16698 (76 FR 27875, May 13, 2011). (1) 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, Amendment 39–14943 (72 FR 8604, February 27, 2007), 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 E:\FR\FM\07NOP1.SGM 07NOP1 Federal Register / Vol. 77, No. 216 / Wednesday, November 7, 2012 / Proposed Rules 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 (h)(2) 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 (r) of this AD terminates the actions required by this paragraph. (2) 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 (the effective date of AD 2007–04–11, Amendment 39– 14943 (72 FR 8604, February 27, 2007)). pmangrum on DSK3VPTVN1PROD with PROPOSALS-1 (i) Retained Corrective Actions This paragraph restates the requirements of paragraph (j) of AD 2011–10–17, Amendment 39–16698 (76 FR 27875, May 13, 2011). 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 (j) 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). (j) Retained Exception This paragraph restates the requirements of paragraph (k) of AD 2011–10–17, Amendment 39–16698 (76 FR 27875, May 13, 2011). 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). (k) Retained No Fleet Sampling This paragraph restates the requirements of paragraph (l) of AD 2011–10–17, Amendment 39–16698 (76 FR 27875, May 13, 2011). 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 VerDate Mar<15>2010 15:18 Nov 06, 2012 Jkt 229001 program and requires all affected airplanes of the fleet to be inspected. (l) Retained No Reporting This paragraph restates the exception specified in paragraph (m) of AD 2011–10– 17, Amendment 39–16698 (76 FR 27875, May 13, 2011). 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. (m) Retained Actions and Compliance This paragraph restates the requirements of paragraph (n) of AD 2011–10–17, Amendment 39–16698 (76 FR 27875, May 13, 2011). For airplanes identified in paragraph (c)(3) of this AD: Within 3 months after October 31, 2007 (the effective date AD 2007–20–03, Amendment 39–15213 (72 FR 54536, September 26, 2007)), revise the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness (ICA) 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 (the effective date AD 2007–20–03), provided that none of the following is exceeded. Accomplishing the initial ALI tasks required by paragraph (r) 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 (the effective date AD 2007–20–03, Amendment 39–15213 (72 FR 54536, September 26, 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. (n) Retained Revision of the ALS of the ICA This paragraph restates the requirements of paragraph (o) of AD 2011–10–17, Amendment 39–16698 (76 FR 27875, May 13, 2011). 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, Amendment 39–15283 (72 FR 69612, December 10, 2007)), do the actions specified in paragraphs (n)(1) and (n)(2) of this AD. Accomplishing the initial ALI tasks required by paragraph (r) of this AD terminates the actions required by this paragraph. (1) Revise the ALS of the ICA to incorporate the structural inspections and PO 00000 Frm 00028 Fmt 4702 Sfmt 4702 66775 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 (o) of this AD. Thereafter, except as provided by paragraphs (n)(2) and (s) 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 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 (s) of this AD, no alternative structural inspection intervals may be approved. (o) Retained Exception to Issue 6 of the A310 ALI Document This paragraph restates the requirements of paragraph (p) of AD 2011–10–17, Amendment 39–16698 (76 FR 27875, May 13, 2011). 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 (the effective date of AD 2007–25–02, Amendment 39–15283 (72 FR 69612, December 10, 2007)), 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 (the effective date of AD 2007–25–02, Amendment 39–15283 (72 FR 69612, December 10, 2007)). (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. (p) Retained Corrective Actions This paragraph restates certain requirements of paragraph (q) of AD 2011– 10–17, Amendment 39–16698 (76 FR 27875, May 13, 2011). Damaged, cracked, or corroded structure detected during any inspection done in accordance with Airbus A310 Airworthiness Limitations Items E:\FR\FM\07NOP1.SGM 07NOP1 66776 Federal Register / Vol. 77, No. 216 / Wednesday, November 7, 2012 / Proposed Rules 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). (q) Retained Reporting Requirement This paragraph restates the requirements of paragraph (r) of AD 2011–10–17, Amendment 39–16698 (76 FR 27875, May 13, 2011). 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 (q)(1) or (q)(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; email: 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 (the effective date of AD 2007–25– 02, Amendment 39–15283 (72 FR 69612, December 10, 2007)): Submit the report within 30 days after the inspection. (2) If the inspection was accomplished prior to January 14, 2008 (the effective date of AD 2007–25–02, Amendment 39–15283 (72 FR 69612, December 10, 2007)): Submit the report within 30 days after January 14, 2008 (the effective date of AD 2007–25–02). (r) Retained Revision of the ALS of the ICA This paragraph restates the requirements of paragraph (s) of AD 2011–10–17, Amendment 39–16698 (76 FR 27875, May 13, 2011). Within 3 months after June 17, 2011 (the effective date of AD 2011–10–17): Revise the maintenance program to incorporate the structural inspections and inspection intervals defined in the applicable ALI document listed in table 1 to paragraph (r) of this AD. Thereafter, except as provided by paragraphs (u) and (s) 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 to paragraph (r) of this AD. Accomplishing the applicable initial ALI tasks constitutes terminating action for the requirements of paragraphs (g) through (q) of this AD for that airplane only. Doing the actions required by paragraph (s) of this AD terminates the requirements of this paragraph. TABLE 1 TO PARAGRAPH (R) OF THIS AD—AIRWORTHINESS LIMITATIONS ITEMS DOCUMENT Document A300 ................................... A310 ................................... A300–600 ........................... pmangrum on DSK3VPTVN1PROD with PROPOSALS-1 Model 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. (s) New Maintenance Program Revision Within 3 months after the effective date of this AD, do the applicable revision specified in paragraph (s)(1) or (s)(2) of this AD. The initial compliance times for the actions specified in the documents specified in paragraphs (s)(3), (s)(4), and (s)(5) of this AD are at the applicable compliance time specified in the document specified in paragraphs (s)(3), (s)(4), and (s)(5) of this AD, or within 3 months after the effective date of this AD, whichever occurs later; except for actions identified in both documents for the Model A300–600 series airplanes, use the applicable compliance time specified in Airbus TR 13.1, dated February 2011, to the Airbus A300–600 Airworthiness Limitation Items Document AI/SE–M2/95A.1310/07, Issue 13, dated October 2010. Accomplishing the applicable initial actions constitutes terminating action for the requirements of paragraph (r) of this AD for that airplane only. (1) For Model A310 series airplanes: Within 3 months after the effective date of this AD, revise the maintenance program to incorporate the actions (e.g., modifications and structural inspections) and compliance times defined in Airbus A310 Airworthiness Limitation Items Document AI/SE–M2/ 95A.1309/07, Issue 8, dated October 2010. (2) For Model A300–600 series airplanes: Within 3 months after the effective date of this AD, revise the maintenance program to incorporate the structural inspections and inspection intervals defined in Airbus A300– 600 Airworthiness Limitation Items VerDate Mar<15>2010 15:18 Nov 06, 2012 Jkt 229001 Issue Document AI/SE–M2/95A.1310/07, Issue 13.1, dated February 2011. (3) For Model A310 series airplanes: Airbus A310 Airworthiness Limitation Items Document AI/SE–M2/95A.1309/07, Issue 8, dated October 2010. (4) For Model A300–600 series airplanes: Airbus A300–600 Airworthiness Limitation Items Document AI/SE–M2/95A.1310/07, Issue 13, dated October 2010. (5) TR 13.1, dated February 2011, to the Airbus A300–600 Airworthiness Limitation Items Document AI/SE–M2/95A.1310/07, Issue 13, dated October 2010. (t) New Alternative Inspections and Inspection Intervals Limitation After accomplishing the revision required by paragraph (s) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (u) of this AD. (u) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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 PO 00000 Frm 00029 Fmt 4702 Sfmt 4702 Date 4 7 12 June 2008. June 2008. June 2008. to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone (425) 227–2125; fax (425) 227–1149. Information may be emailed 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. (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. (v) Related Information Refer to MCAI EASA Airworthiness Directive 2011–0198, dated October 19, 2011, and the service information specified in paragraphs (v)(1) through (v)(12) of this AD, for related information. (1) Airbus A300 Airworthiness Limitation Items Document AI/SE–M2/95A.1308/07, Issue 4, dated June 2008. (2) Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Revision 3, dated September 2005. E:\FR\FM\07NOP1.SGM 07NOP1 Federal Register / Vol. 77, No. 216 / Wednesday, November 7, 2012 / Proposed Rules (3) Airbus A300–600 Airworthiness Limitation Items Document AI/SE–M2/ 95A.0502/06, Revision 11, dated April 2006. (4) Airbus A300–600 Airworthiness Limitation Items Document AI/SE–M2/ 95A.1310/07, Issue 13, dated October 2010. (5) Airbus A300–600 Airworthiness Limitation Items Document AI/SE–M2/ 95A.1310/07, Revision 12, dated June 2008. (6) Airbus A310 Airworthiness Limitation Items Document AI/SE–M2/95A.1309/07, Issue 8, dated October 2010. (7) Airbus A310 Airworthiness Limitation Items Document AI/SE–M2/95A.1309/07, Revision 7, dated June 2008. (8) Airbus A310 Airworthiness Limitations Items Document AI/SE–M2/95A.0263/06, Revision 6, dated April 2006. (9) Airbus Industrie A300 Structural Inspection Document, Revision 2, dated June 1994. (10) Airbus Temporary Revision 13.1, dated February 2011, to Airbus A300–600 Airworthiness Limitation Items Document AI/SE–M2/95A.1310/07, Revision 13, dated October 2010. (11) Airbus Temporary Revision 3.1, dated April 2006, including attachment, dated April 2006, and including attachments dated September 2005, to Airbus A300 Airworthiness Limitation Items, Document SEM2/95A.1090/05, Issue 3, dated September 2005. (12) 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. Issued in Renton, Washington, on October 30, 2012. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–27126 Filed 11–6–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF COMMERCE Bureau of Industry and Security Background 15 CFR Parts 764 and 766 [Docket No. 120207107–2565–01] RIN 0694–AF59 pmangrum on DSK3VPTVN1PROD with PROPOSALS-1 Time Limit for Completion of Voluntary Self-Disclosures and Revised Notice of the Institution of Administrative Enforcement Proceedings Bureau of Industry and Security, Commerce. ACTION: Proposed rule. AGENCY: This proposed rule would require that the final, comprehensive narrative account required in voluntary self-disclosures (VSDs) of violations of the Export Administration Regulations (EAR) be submitted to the Office of SUMMARY: VerDate Mar<15>2010 15:18 Nov 06, 2012 Jkt 229001 Export Enforcement within 180 days of the initial VSD notification. This proposed rule also would authorize the use of delivery services other than registered or certified mail for providing notice of the issuance of a charging letter instituting an administrative enforcement proceeding under the EAR. It also would remove the phrase ‘‘if delivery is refused’’ from a provision relating to determining the date of service of notice of a charging letter’s issuance based on an attempted delivery to the respondent’s last known address. The Bureau of Industry and Security is proposing these changes to be better able to resolve administrative enforcement proceedings in a timely manner and provide more efficient notice of administrative charging letters. DATES: Comments must be received no later than January 7, 2013. ADDRESSES: You may submit comments by any of the following methods: • Federal eRulemaking Portal: http:// www.regulations.gov. The identification number for this rulemaking is BIS– 2012–0043. • By email directly to publiccomments@bis.doc.gov. Include RIN 0694–AF59 in the subject line. • By mail or delivery to Regulatory Policy Division, Bureau of Industry and Security, U.S. Department of Commerce, Room 2099B, 14th Street and Pennsylvania Avenue NW., Washington, DC 20230. Refer to RIN 0694–AF59. FOR FURTHER INFORMATION CONTACT: Special Agent Kirk Flashner, Office of Export Enforcement, Bureau of Industry and Security, U.S. Department of Commerce, Room H4514, 14th Street and Pennsylvania Avenue NW., Washington, DC 20230. Tel: (202) 482– 1208. Facsimile: (202) 482–5889. SUPPLEMENTARY INFORMATION: The Bureau of Industry and Security (BIS), Office of Export Enforcement (OEE), investigates possible violations of the Export Administration Regulations (EAR) and orders, licenses, and authorizations issued thereunder. These investigations may result in allegations of violations that may be settled, adjudicated in an administrative enforcement proceeding, or referred to the Department of Justice for possible criminal prosecution. This rule proposes three changes to the EAR. One change addresses voluntary selfdisclosures in connection with OEE’s conduct of investigations. The other two changes address service of notice in administrative enforcement proceedings. PO 00000 Frm 00030 Fmt 4702 Sfmt 4702 66777 Proposed Change Regarding Voluntary Self-Disclosures Section 764.5 of the EAR provides a procedure whereby parties that believe that they may have committed a violation of the EAR can voluntarily disclose the facts of the potential violations to OEE. Such disclosures that meet the requirements of § 764.5 typically are afforded ‘‘great weight’’ by BIS, relative to other mitigating factors, in determining what administrative sanctions, if any, to seek. Section 764.5 requires an initial notification, which is to include a description of the general nature and extent of the suspected violations, and is followed at a later date by a thorough review and narrative account of the suspected violations, including all relevant supporting documentation. If the person making the initial notification subsequently completes the narrative account, the disclosure is deemed to have been submitted to OEE on the date of the initial notification. The date of the initial notification may be significant because information provided to OEE may only be considered a voluntary disclosure if the information ‘‘is received by OEE for review prior to the time that OEE or another United States Government agency has learned of the same or substantially similar information from another source and has commenced an investigation or inquiry in connection with that information.’’ 15 CFR 764.5(b)(3). Currently, § 764.5 of the EAR does not include a specific time limit within which a narrative account must be submitted to OEE. Too often, initial notifications are not promptly followed by comprehensive narrative accounts, and as a result, OEE must maintain open files on voluntary disclosures for extended periods of time without making sufficient progress towards resolving the matter disclosed. To address these situations and promote expeditious resolution of self-disclosed violations, BIS proposes to set a 180-day deadline for persons who have submitted an initial notification to complete and submit the final narrative report to OEE. The Director of OEE could extend this 180-day time deadline, at his or her discretion, if U.S. Government interests would be served by an extension or upon a showing by the party making the disclosure that more time is reasonably necessary to complete the narrative account. Some illustrative examples of circumstances that might warrant additional time include the following. • Records or information from multiple entities and/or jurisdictions are E:\FR\FM\07NOP1.SGM 07NOP1

Agencies

[Federal Register Volume 77, Number 216 (Wednesday, November 7, 2012)]
[Proposed Rules]
[Pages 66772-66777]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-27126]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1158; Directorate Identifier 2011-NM-232-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to all Airbus Model A300 and A310 series airplanes; 
and Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model 
A300 C4-605R Variant F airplanes (collectively called A300-600 series 
airplanes). The existing AD currently requires revising the 
Airworthiness Limitations section of the Instructions for Continued 
Airworthiness to incorporate new and revised structural inspections and 
inspection intervals. Since we issued that AD, Airbus has revised 
certain ALI documents, which require more restrictive maintenance 
requirements and airworthiness limitations. This proposed AD would 
revise the maintenance program to incorporate the limitations section. 
We are proposing this AD to prevent fatigue cracking, damage, or 
corrosion in principal structural elements, which could result in 
reduced structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by December 24, 
2012.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-

[[Page 66773]]

30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue 
SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays.
    For service information identified in this proposed 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; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may review copies of the referenced 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://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 this proposed AD, 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.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2012-1158; 
Directorate Identifier 2011-NM-232-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On May 2, 2011, we issued AD 2011-10-17, Amendment 39-16698 (76 FR 
27875, May 13, 2011). That AD required actions intended to address an 
unsafe condition on the products listed above.
    Since we issued AD 2011-10-17, Amendment 39-16698 (76 FR 27875, May 
13, 2011), Airbus has revised certain ALI documents, which require more 
restrictive maintenance requirements and airworthiness limitations. The 
European Aviation Safety Agency (EASA), which is the Technical Agent 
for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2011-0198, dated October 19, 2011 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    The airworthiness limitations applicable to the Damage Tolerant 
Airworthiness Limitation Items (DT ALIs) are currently listed in 
Airbus ALI Documents, which are referenced in the A300, A310 and 
A300-600 Airworthiness Limitations Section (ALS) Part 2.
    Airbus have recently revised the A300-600 and A310 ALI 
Documents, and these issues have been approved by EASA. The Airbus 
A300-600 ALI Document issue 13 and temporary revision (TR) 13.1 and 
the A310 ALI document issue 08 introduce more restrictive 
maintenance requirements and airworthiness limitations, which have 
been identified as mandatory actions for continued airworthiness.
    EASA AD 2009-0155 [which corresponds to FAA AD 2011-10-17, 
Amendment 39-16698 (76 FR 27875, May 13, 2011)] required compliance 
with the maintenance requirements and associated airworthiness 
limitations defined in the following documents:
    --AIRBUS A300 ALI Document issue 04,
    --AIRBUS A310 ALI Document issue 07, and
    --AIRBUS A300-600 ALI Document issue 12.
    For the reasons described, this EASA AD retains the requirements 
of EASA AD 2009-0155, which is superseded, and requires compliance 
with the airworthiness limitations defined in the Airbus A300-600 
ALI Document issue 13 and TR13.1, and the A310 ALI document issue 
08.

You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Airbus has issued the following service information. The actions 
described in this service information are intended to correct the 
unsafe condition identified in the MCAI.
     Airbus A310 Airworthiness Limitation Items Document, AI/
SE-M2/95A.1309/07, Issue 8, dated October 2010 (for Model A310-203, -
204, -221, -222, -304, -322, -324, and -325 airplanes).
     Airbus A300-600 Airworthiness Limitation Items Document, 
AI/SE-M2/95A.1310/07, Issue 13, dated October 2010 (Model A300 B4-601, 
B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R 
Variant F airplanes).
     Airbus Temporary Revision 13.1, dated February 2011, to 
the Airbus A300-600 Airworthiness Limitation Items Document, AI/SE-M2/
95A.1310/07, Issue 13, dated October 2010 (for Model A300 B4-601, B4-
603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R 
Variant F airplanes).

FAA's Determination and Requirements of This Proposed AD

    These products have been approved by the aviation authority of 
another country, and is approved for operation in the United States. 
Pursuant to our bilateral agreement with the State of Design Authority, 
we have been notified of the unsafe condition described in the MCAI and 
service information referenced above. We are proposing this AD because 
we evaluated all pertinent information and determined an unsafe 
condition exists and is likely to exist or develop on other products of 
these same type designs.
    This proposed AD requires revisions to certain operator maintenance 
documents to include new actions (e.g., inspections). Compliance with 
these actions is required by section 91.403(c) of the Federal Aviation 
Regulations (14 CFR 91.403(c)). For airplanes that have been previously 
modified, altered, or repaired in the areas addressed by these 
inspections, an operator might not be able to accomplish the actions 
described in the revisions. In this situation, to comply with 14 CFR 
91.403(c), the operator must request approval of an alternative method 
of compliance (AMOC) in accordance with the provisions of paragraph 
(u)(1) of this proposed AD. The request should include a description of 
changes to the required actions that will ensure the continued damage 
tolerance of the affected structure.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 170 products of U.S. registry.
    The actions that are required by AD 2011-10-17, Amendment 39-16698 
(76 FR 27875, May 13, 2011), and retained in this proposed AD take 
about 1 work-hour per product, at an average labor rate of $85 per work 
hour. Based on these figures, the estimated cost of the

[[Page 66774]]

currently required actions is $85 per product.
    We estimate that it would take about 1 work-hour per product to 
comply with the new basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of the proposed AD on U.S. operators to be $14,450, 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
regulation:
    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);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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 proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing airworthiness directive 
(AD) 2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011), and 
adding the following new AD:

Airbus: Docket No. FAA-2012-1158; Directorate Identifier 2011-NM-
232-AD.

(a) Comments Due Date

    We must receive comments by December 24, 2012.

(b) Affected ADs

    This AD supersedes AD 2011-10-17, Amendment 39-16698 (76 FR 
27875, May 13, 2011), which superseded 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). AD 2007-04-11 
superseded AD 96-13-11, Amendment 39-9679 (61 FR 35122, July 5, 
1996).

(c) Applicability

    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) Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, 
F4-605R, F4-622R, and C4-605R Variant F airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 57: Wings.

(e) Reason

    This AD was prompted by revisions of certain Airbus 
Airworthiness Limitation Items (ALI) documents, which require more 
restrictive maintenance requirements and airworthiness limitations. 
We are issuing this AD to prevent fatigue cracking, damage, or 
corrosion in principal structural elements, which could result in 
reduced structural integrity of the airplane.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Retained Maintenance Program Revision

    This paragraph restates the requirements of paragraph (g) of AD 
2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011). Within 
one year after August 9, 1996 (the effective date of AD 96-13-11, 
Amendment 39-9679 (61 FR 35122, July 5, 1996)), 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 
(r) 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 (the effective date of AD 96-13-11, 
Amendment 39-9679 (61 FR 35122, July 5, 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 (the effective date of AD 96-13-11, Amendment 39-9679 (61 FR 
35122, July 5, 1996)).

(h) Retained Revision of the Maintenance Inspection Program

    This paragraph restates the requirements of paragraphs (h) and 
(i) of AD 2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 
2011).
    (1) 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, Amendment 39-14943 (72 FR 8604, February 27, 2007), 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

[[Page 66775]]

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 (h)(2) 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 (r) of this AD terminates 
the actions required by this paragraph.
    (2) 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 (the effective date of AD 2007-04-11, Amendment 39-14943 (72 
FR 8604, February 27, 2007)).

(i) Retained Corrective Actions

    This paragraph restates the requirements of paragraph (j) of AD 
2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011). 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 (j) 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).

(j) Retained Exception

    This paragraph restates the requirements of paragraph (k) of AD 
2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011). 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).

(k) Retained No Fleet Sampling

    This paragraph restates the requirements of paragraph (l) of AD 
2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011). 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.

(l) Retained No Reporting

    This paragraph restates the exception specified in paragraph (m) 
of AD 2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011). 
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.

(m) Retained Actions and Compliance

    This paragraph restates the requirements of paragraph (n) of AD 
2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011). For 
airplanes identified in paragraph (c)(3) of this AD: Within 3 months 
after October 31, 2007 (the effective date AD 2007-20-03, Amendment 
39-15213 (72 FR 54536, September 26, 2007)), revise the 
Airworthiness Limitations Section (ALS) of the Instructions for 
Continued Airworthiness (ICA) 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 (the effective date AD 2007-20-03), provided that 
none of the following is exceeded. Accomplishing the initial ALI 
tasks required by paragraph (r) 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 (the effective date AD 2007-
20-03, Amendment 39-15213 (72 FR 54536, September 26, 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.

(n) Retained Revision of the ALS of the ICA

    This paragraph restates the requirements of paragraph (o) of AD 
2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011). 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, 
Amendment 39-15283 (72 FR 69612, December 10, 2007)), do the actions 
specified in paragraphs (n)(1) and (n)(2) of this AD. Accomplishing 
the initial ALI tasks required by paragraph (r) 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 (o) of this AD. 
Thereafter, except as provided by paragraphs (n)(2) and (s) 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 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 (s) of this AD, no alternative structural 
inspection intervals may be approved.

(o) Retained Exception to Issue 6 of the A310 ALI Document

    This paragraph restates the requirements of paragraph (p) of AD 
2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011). 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 (the effective date of AD 2007-25-02, Amendment 39-
15283 (72 FR 69612, December 10, 2007)), 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 (the effective date of AD 
2007-25-02, Amendment 39-15283 (72 FR 69612, December 10, 2007)).
    (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.

(p) Retained Corrective Actions

    This paragraph restates certain requirements of paragraph (q) of 
AD 2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011). 
Damaged, cracked, or corroded structure detected during any 
inspection done in accordance with Airbus A310 Airworthiness 
Limitations Items

[[Page 66776]]

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).

(q) Retained Reporting Requirement

    This paragraph restates the requirements of paragraph (r) of AD 
2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011). 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 
(q)(1) or (q)(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; email: 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 (the 
effective date of AD 2007-25-02, Amendment 39-15283 (72 FR 69612, 
December 10, 2007)): Submit the report within 30 days after the 
inspection.
    (2) If the inspection was accomplished prior to January 14, 2008 
(the effective date of AD 2007-25-02, Amendment 39-15283 (72 FR 
69612, December 10, 2007)): Submit the report within 30 days after 
January 14, 2008 (the effective date of AD 2007-25-02).

(r) Retained Revision of the ALS of the ICA

    This paragraph restates the requirements of paragraph (s) of AD 
2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011). Within 3 
months after June 17, 2011 (the effective date of AD 2011-10-17): 
Revise the maintenance program to incorporate the structural 
inspections and inspection intervals defined in the applicable ALI 
document listed in table 1 to paragraph (r) of this AD. Thereafter, 
except as provided by paragraphs (u) and (s) 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 
to paragraph (r) of this AD. Accomplishing the applicable initial 
ALI tasks constitutes terminating action for the requirements of 
paragraphs (g) through (q) of this AD for that airplane only. Doing 
the actions required by paragraph (s) of this AD terminates the 
requirements of this paragraph.

                  Table 1 to Paragraph (r) of This AD--Airworthiness Limitations Items Document
----------------------------------------------------------------------------------------------------------------
               Model                              Document                     Issue               Date
----------------------------------------------------------------------------------------------------------------
A300..............................  Airbus A300 Airworthiness Limitation               4  June 2008.
                                     Items Document AI/SE-M2/95A.1308/07.
A310..............................  Airbus A310 Airworthiness Limitation               7  June 2008.
                                     Items Document AI/SE[dash]M2/
                                     95A.1309/07.
A300-600..........................  Airbus A300-600 Airworthiness                     12  June 2008.
                                     Limitation Items Document AI/
                                     SE[dash]M2/95A.1310/07.
----------------------------------------------------------------------------------------------------------------

(s) New Maintenance Program Revision

    Within 3 months after the effective date of this AD, do the 
applicable revision specified in paragraph (s)(1) or (s)(2) of this 
AD. The initial compliance times for the actions specified in the 
documents specified in paragraphs (s)(3), (s)(4), and (s)(5) of this 
AD are at the applicable compliance time specified in the document 
specified in paragraphs (s)(3), (s)(4), and (s)(5) of this AD, or 
within 3 months after the effective date of this AD, whichever 
occurs later; except for actions identified in both documents for 
the Model A300-600 series airplanes, use the applicable compliance 
time specified in Airbus TR 13.1, dated February 2011, to the Airbus 
A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.1310/
07, Issue 13, dated October 2010. Accomplishing the applicable 
initial actions constitutes terminating action for the requirements 
of paragraph (r) of this AD for that airplane only.
    (1) For Model A310 series airplanes: Within 3 months after the 
effective date of this AD, revise the maintenance program to 
incorporate the actions (e.g., modifications and structural 
inspections) and compliance times defined in Airbus A310 
Airworthiness Limitation Items Document AI/SE-M2/95A.1309/07, Issue 
8, dated October 2010.
    (2) For Model A300-600 series airplanes: Within 3 months after 
the effective date of this AD, revise the maintenance program to 
incorporate the structural inspections and inspection intervals 
defined in Airbus A300-600 Airworthiness Limitation Items Document 
AI/SE-M2/95A.1310/07, Issue 13.1, dated February 2011.
    (3) For Model A310 series airplanes: Airbus A310 Airworthiness 
Limitation Items Document AI/SE-M2/95A.1309/07, Issue 8, dated 
October 2010.
    (4) For Model A300-600 series airplanes: Airbus A300-600 
Airworthiness Limitation Items Document AI/SE-M2/95A.1310/07, Issue 
13, dated October 2010.
    (5) TR 13.1, dated February 2011, to the Airbus A300-600 
Airworthiness Limitation Items Document AI/SE-M2/95A.1310/07, Issue 
13, dated October 2010.

(t) New Alternative Inspections and Inspection Intervals Limitation

    After accomplishing the revision required by paragraph (s) of 
this AD, no alternative actions (e.g., inspections) or intervals may 
be used unless the actions or intervals are approved as an 
alternative method of compliance (AMOC) in accordance with the 
procedures specified in paragraph (u) of this AD.

(u) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-2125; fax (425) 227-1149. Information may be emailed 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.
    (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.

(v) Related Information

    Refer to MCAI EASA Airworthiness Directive 2011-0198, dated 
October 19, 2011, and the service information specified in 
paragraphs (v)(1) through (v)(12) of this AD, for related 
information.
    (1) Airbus A300 Airworthiness Limitation Items Document AI/SE-
M2/95A.1308/07, Issue 4, dated June 2008.
    (2) Airbus A300 Airworthiness Limitation Items Document SEM2/
95A.1090/05, Revision 3, dated September 2005.

[[Page 66777]]

    (3) Airbus A300-600 Airworthiness Limitation Items Document AI/
SE-M2/95A.0502/06, Revision 11, dated April 2006.
    (4) Airbus A300-600 Airworthiness Limitation Items Document AI/
SE-M2/95A.1310/07, Issue 13, dated October 2010.
    (5) Airbus A300-600 Airworthiness Limitation Items Document AI/
SE-M2/95A.1310/07, Revision 12, dated June 2008.
    (6) Airbus A310 Airworthiness Limitation Items Document AI/SE-
M2/95A.1309/07, Issue 8, dated October 2010.
    (7) Airbus A310 Airworthiness Limitation Items Document AI/SE-
M2/95A.1309/07, Revision 7, dated June 2008.
    (8) Airbus A310 Airworthiness Limitations Items Document AI/SE-
M2/95A.0263/06, Revision 6, dated April 2006.
    (9) Airbus Industrie A300 Structural Inspection Document, 
Revision 2, dated June 1994.
    (10) Airbus Temporary Revision 13.1, dated February 2011, to 
Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/
95A.1310/07, Revision 13, dated October 2010.
    (11) Airbus Temporary Revision 3.1, dated April 2006, including 
attachment, dated April 2006, and including attachments dated 
September 2005, to Airbus A300 Airworthiness Limitation Items, 
Document SEM2/95A.1090/05, Issue 3, dated September 2005.
    (12) 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.


    Issued in Renton, Washington, on October 30, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-27126 Filed 11-6-12; 8:45 am]
BILLING CODE 4910-13-P