Airworthiness Directives; Airbus Airplanes, 75833-75836 [2012-29992]

Download as PDF Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations (2) If the HP/IP turbine bearing support oil feed tube outer heat shield is not present, accept the module as compliant. No further action is required. DEPARTMENT OF TRANSPORTATION (h) Mandatory Terminating Action As mandatory terminating action to the repetitive inspections required by this AD, install a revised HP/IP turbine bearing support structure, at the next 05 Module overhaul after the effective date of this AD, in accordance with either: (1) Sections 3.B (1)(a) through 3.B (1)(f) of RR Service Bulletin (SB) No. RB.211–72– F117, Revision 2, dated September 25, 2006; or (2) Sections 3.B (1)(a) through 3.B (1)(e) and 3.B (2)(a) of RR SB No. RB.211–72–F227, Revision 1, dated October 8, 2007. (i) Definition For the purpose of this AD, ‘‘next 05 Module overhaul’’ is any time that the HP/ IP turbine internal oil tubes have been exposed and the HP/IP turbine bearing support oil feed tube heat shields are subjected to visual inspection. tkelley on DSK3SPTVN1PROD with (k) Related Information (1) For more information about this AD, contact Robert Morlath, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238 7154; fax: 781–238 7199; email: robert.c.morlath@faa.gov. (2) Refer to European Aviation Safety Agency AD 2012–0201, dated September 26, 2012, for related information. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Rolls-Royce plc Alert Service Bulletin No. RB.211–72–AG873, dated February 27, 2012, approved for IBR January 10, 2013. (ii) Reserved. (3) The following service information was approved for IBR on December 14, 2007 (72 FR 67568, November 29, 2007). (i) Rolls-Royce plc Service Bulletin No. RB.211–72–F117, Revision 2, dated September 25, 2006. (ii) Rolls-Royce plc Service Bulletin No. RB.211–72–F227, Revision 1, dated October 8, 2007. Jkt 229001 Discussion Issued in Burlington, Massachusetts, on December 4, 2012. Colleen M. D’Alessandro, Assistant Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2012–30650 Filed 12–21–12; 8:45 am] BILLING CODE 4910–13–P 14 CFR Part 39 (j) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. 04:58 Dec 22, 2012 This AD becomes effective January 30, 2013. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 30, 2013. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of April 15, 2010 (75 FR 11435, March 11, 2010). ADDRESSES: You may examine the AD docket on the Internet at http:// 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, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Federal Aviation Administration (g) Repetitive Inspections If the HP/IP turbine bearing support oil feed tube outer heat shield is present, perform repetitive inspections of the HP/IP turbine bearing support oil feed tube, in accordance with paragraphs 3.A (2)(b) through 3.A (2)(f) of RR ASB No. RB.211–72– AG873, dated February 27, 2012. VerDate Mar<15>2010 (4) For service information identified in this AD, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE248BJ, phone: 011–44–1332– 242424; fax: 011–44–1332–245418; or email: http://www.rolls-royce.com/contact/ civil_team.jsp. (5) You may view this 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. (6) You may view this service information at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. 75833 [Docket No. FAA–2012–0858; Directorate Identifier 2011–NM–183–AD; Amendment 39–17287; AD 2012–25–06] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding an existing airworthiness directive (AD) for certain Airbus Model A300 B4–2C, B4– 103, and B4–203 airplanes; and Model A300 B4–601, B4–603, B4–620, B4–622, B4–605R, and B4–622R airplanes. That AD currently requires performing a onetime detailed visual inspection of the forward fitting at frame (FR) 40 on both sides of the airplane for cracks, and repair if necessary. This new AD requires repetitive detailed inspections of the forward fitting at FR 40 without nut removal, and a one-time eddy current or liquid penetrant inspection of the forward fitting at FR 40 with nut removal, and repair if necessary. This AD was prompted by reports that new cracks were found in the FR 40 forward fitting. We are issuing this AD to detect and correct cracking of the FR 40 forward fitting, which could result in a deterioration of the structural integrity of the frame. SUMMARY: PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 DATES: 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 August 27, 2012 (77 FR 51717), and proposed to supersede AD 2010–06–05, Amendment 39–16229 (75 FR 11435, March 11, 2010). That NPRM proposed to correct an unsafe condition for the specified products. The Mandatory Continuing Airworthiness Information (MCAI) states: One A300–600 aeroplane operator reported that, during a routine inspection, a crack was found in the right hand frame (FR) 40 forward fitting between stringer 32 and stringer 33. The subject aeroplane had previously been modified in accordance with Airbus SB A300–57–6053 (Mod. 10453). Therefore and pending completion of the full analysis using a refined Finite Element Model, EASA [European Aviation Safety Agency] issued AD 2009–0094 [which corresponds with FAA AD 2010–06–05, Amendment 39–16229 (75 FR 11435, March 11, 2010)] to require a one-time Detailed Visual Inspection (DVI) of the post-SB A300– 57–6053 A300–600 aeroplanes and post-SB A300–53–0297 A300 aeroplanes in order to ensure the structural integrity of frame 40. During a recent maintenance check, on two aeroplanes (one A300B4 and one A300–600), cracks were found in the FR 40 forward fitting. These new crack findings are considered as unexpected, since they were found after: —Application of modification SB A300–57– 6053 or SB A300–53–0297 which cancels the inspection programme, and —Accomplishment of EASA AD 2009–0094. E:\FR\FM\26DER1.SGM 26DER1 75834 Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations For the reasons described above, this new [EASA] AD, which supersedes EASA AD 2009–0094, requires repetitive DVI of the FR 40 forward fitting (without nut removal), accomplishment of a one time Eddy Current (EC) inspection or liquid penetrant inspection of this area (with nut removal) and, depending on findings, the accomplishment of associated corrective action [repair if any cracking found]. Passing the EC or liquid penetrant inspection constitutes terminating action for the repetitive DVI. 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 (77 FR 51717, August 27, 2012), 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. tkelley on DSK3SPTVN1PROD with Costs of Compliance We estimate that this AD will affect about 134 products of U.S. registry. The actions that are required by AD 2010–06–05, Amendment 39–16229 (75 FR 11435, March 11, 2010), and retained in this AD take about 3 work-hours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the currently required actions is $255 per product. We estimate that it will take about 3 work-hours 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 $34,170, or $255 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 VerDate Mar<15>2010 04:58 Dec 22, 2012 Jkt 229001 that is likely to exist or develop on products identified in this rulemaking action. 2010–06–05, Amendment 39–16229 (75 FR 11435, March 11, 2010), and adding the following new AD: Regulatory Findings 2012–25–06 Airbus: Amendment 39–17287. Docket No. FAA–2012–0858; Directorate Identifier 2011–NM–183–AD. 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 that 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); 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 AD and placed it in the AD docket. 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 the NPRM (77 FR 51717, August 27, 2012), 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 airworthiness directive (AD) ■ PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 (a) Effective Date This airworthiness directive (AD) becomes effective January 30, 2013. (b) Affected ADs This AD supersedes AD 2010–06–05, Amendment 39–16229 (75 FR 11435, March 11, 2010). (c) Applicability This AD applies to Airbus airplanes, certificated in any category, as identified in paragraphs (c)(1) and (c)(2) of this AD. For airplanes on which Airbus Service Bulletin A300–53–0297 or A300–57–6053 (Airbus Modification 10453), as applicable, has been incorporated as a corrective action (repair following crack finding), no action is required by this AD. (1) Model A300 B4–2C, B4–103, and B4– 203 airplanes, all serial numbers, modified preventively in service (without any preliminary crack findings), as specified in Airbus Service Bulletin A300–53–0297 (Airbus Modification 10453). (2) Model A300 B4–601, B4–603, B4–605R, B4–620, B4–622, and B4–622R airplanes, all serial numbers, modified preventively in service (without any preliminary crack findings), as specified in Airbus Service Bulletin A300–57–6053 (Airbus Modification 10453). (d) Subject Air Transport Association (ATA) of America Code 53, 57: Fuselage, Wings. (e) Reason This AD was prompted by reports that cracks were found in the frame (FR) 40 forward fitting. We are issuing this AD to detect and correct cracking of the FR 40 forward fitting, which could result in a deterioration of the structural integrity of the frame. (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 Detailed Inspection This paragraph restates the actions required by paragraphs (f)(1), (f)(2), and (f)(3) of AD 2010–06–05, Amendment 39–16229 (75 FR 11435, March 11, 2010). (1) At the applicable time specified in table 1 to paragraph (g)(1) of this AD: Do a onetime detailed visual inspection of the forward fitting at FR 40 on both sides of the airplane, in accordance with Airbus Mandatory Service Bulletin A300–57A6108 (for Model A300 B4–601, B4–603, B4–605R, B4–620, B4–622, and B4–622R airplanes) or A300– 53A0387 (for Model A300 B4–2C, B4–103, and B4–203 airplanes), both including Appendices 01 and 02, both dated September 12, 2008. E:\FR\FM\26DER1.SGM 26DER1 Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations 75835 TABLE 1 TO PARAGRAPH (g)(1) OF THIS AD—COMPLIANCE TIMES Airplane models/configuration Compliance time A300 B4–2C and B4–103 airplanes on which Airbus Service Bulletin A300–53–0297 was done prior to the accumulation of 9,000 total flight cycles. Prior to the accumulation of 18,000 total flight cycles, or within 3 months after April 15, 2010 (the effective date of AD 2010–06–05, Amendment 39–16229 (75 FR 11435, March 11, 2010)), whichever occurs later. Within 5,500 flight cycles after accomplishment of Airbus Service Bulletin A300–53–0297, or within 6 months after April 15, 2010 (the effective date of AD 2010–06–05, Amendment 39–16229 (75 FR 11435, March 11, 2010)), whichever occurs later; except, for airplanes that, as of April 15, 2010 (the effective date of AD 2010–06– 05), have accumulated 11,000 flight cycles or more since accomplishment of Airbus Service Bulletin A300–53–0297, within 3 months after April 15, 2010 (the effective date of AD 2010–06–05). Prior to the accumulation of 15,000 total flight cycles, or within 3 months after April 15, 2010 (the effective date of AD 2010–06–05, Amendment 39–16229 (75 FR 11435, March 11, 2010)), whichever occurs later. Within 4,100 flight cycles after accomplishment of Airbus Service Bulletin A300–53–0297, or within 6 months after April 15, 2010 (the effective date of AD 2010–06–05, Amendment 39–16229 (75 FR 11435, March 11, 2010)), whichever occurs later; except, for airplanes that, as of April 15, 2010 (the effective date of AD 2010–06– 05), have accumulated 8,200 flight cycles or more since accomplishment of Airbus Service Bulletin A300–53–0297, within 3 months after April 15, 2010 (the effective date of AD 2010–06–05). Prior to the accumulation of 11,500 total flight cycles, or within 3 months after April 15, 2010 (the effective date of AD 2010–06–05, Amendment 39–16229 (75 FR 11435, March 11, 2010)), whichever occurs later. Within 3,300 flight cycles after accomplishment of Airbus Service Bulletin A300–57–6053, or within 6 months after April 15, 2010 (the effective date of AD 2010–06–05, Amendment 39–16229 (75 FR 11435, March 11, 2010)), whichever occurs later; except, for airplanes that, as of April 15, 2010 (the effective date of AD 2010–06– 05), have accumulated 6,600 flight cycles or more since accomplishment of Airbus Service Bulletin A300–57–6053, within 3 months after April 15, 2010 (the effective date of AD 2010–06–05). A300 B4–2C and B4–103 airplanes on which Airbus Service Bulletin A300–53–0297 was done on or after the accumulation of 9,000 total flight cycles. A300 B4–203 airplanes on which Airbus Service Bulletin A300–53– 0297 was done prior to the accumulation of 8,300 total flight cycles. A300 B4–203 airplanes on which Airbus Service Bulletin A300–53– 0297 was done on or after the accumulation of 8,300 total flight cycles. A300 B4–601, B4–603, B4–605R, B4–620, B4–622, and B4–622R airplanes on which Airbus Service Bulletin A300–57–6053 was done prior to the accumulation of 6,100 total flight cycles. tkelley on DSK3SPTVN1PROD with A300 B4–601, B4–603, B4–605R, B4–620, B4–622, and B4–622R airplanes on which Airbus Service Bulletin A300–57–6053 was done on or after the accumulation of 6,100 total flight cycles. (2) Except as required by paragraph (g)(3) of this AD: If any crack is found during the inspection required by paragraph (g)(1) of this AD, before further flight, do a temporary or definitive repair, as applicable, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 53–0268, Revision 06, dated January 7, 2002 (for Model A300 B4–2C, B4–103, and B4–203 airplanes); or A300–57–6052, Revision 03, dated May 27, 2002, including Airbus Drawings 15R53810394, Issue A, dated December 21, 1998, and 21R57110247, Issue A, dated June 20, 1997 (for Model A300 B4– 601, B4–603, B4–605R, B4–620, B4–622, and B4–622R airplanes). (3) If any crack found during the inspection required by paragraph (g)(1) of this AD cannot be repaired in accordance with Airbus Service Bulletin A300–53–0268, Revision 06, dated January 7, 2002 (for Model A300 B4– 2C, B4–103, and B4–203 airplanes); or A300– 57–6052, Revision 03, dated May 27, 2002, including Airbus Drawings 15R53810394, Issue A, dated December 21, 1998, and 21R57110247, Issue A, dated June 20, 1997 (for Model A300 B4–601, B4–603, B4–605R, B4–620, B4–622, and B4–622R airplanes): Contact Airbus for repair instructions and, before further flight, repair the crack using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, or the European VerDate Mar<15>2010 04:58 Dec 22, 2012 Jkt 229001 Aviation Safety Agency (EASA) (or its delegated agent). (i) New Requirement: Repetitive Detailed Inspections (h) Retained Reporting Requirement Within 300 flight cycles after the effective date of this AD: Perform a detailed inspection for cracks of the forward fitting at FR 40 without nut removal on both sides of the airplane, in accordance with Airbus All Operator Telex A300–53A0391, dated August 9, 2011 (for Model A300 B4–2C, B4–103, and B4–203 airplanes); or Airbus All Operator Telex A300–57A6111, dated August 9, 2011 (for Model A300 B4–601, B4–603, B4–605R, B4–620, B4–622, and B4–622R airplanes). Thereafter, repeat the inspection at intervals not to exceed 300 flight cycles. This paragraph restates the requirements of paragraph (f)(4) of AD 2010–06–05, Amendment 39–16229 (75 FR 11435, March 11, 2010). Submit an inspection report in accordance with Appendix 01 of Airbus Mandatory Service Bulletin A300–53A0387, including Appendices 01 and 02, dated September 12, 2008 (for Model A300 B4–2C, B4–103, and B4–203 airplanes); or Airbus Mandatory Service Bulletin A300–57A6108, including Appendices 01 and 02, dated September 12, 2008 (for Model A300 B4–601, B4–603, B4–605R, B4–620, B4–622, and B4– 622R airplanes); to the address identified on the reporting sheet, at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD. (1) If the inspection was done on or after April 15, 2010 (the effective date of AD 2010–06–05, Amendment 39–16229 (75 FR 11435, March 11, 2010)): Submit the report within 30 days after the inspection. (2) If the inspection was done before April 15, 2010 (the effective date of AD 2010–06– 05, Amendment 39–16229 (75 FR 11435, March 11, 2010)): Submit the report within 30 days after April 15, 2010 (the effective date of AD 2010–06–05). PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 (j) New Requirement: Eddy Current Inspection or Liquid Penetrant Inspection Within 36 months after the effective date of this AD: Perform an eddy current inspection or a liquid penetrant inspection for cracks of the forward fitting at FR 40 with nut removal on both sides of the airplane, in accordance with Airbus All Operator Telex A300–53A0391, dated August 9, 2011 (for Model A300 B4–2C, B4–103, and B4–203 airplanes); or Airbus All Operator Telex A300–57A6111, dated August 9, 2011 (for Model A300 B4–601, B4–603, B4–605R, B4– 620, B4–622, and B4–622R airplanes). E:\FR\FM\26DER1.SGM 26DER1 75836 Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations (k) New Requirement: Corrective Action If, during any inspection required by paragraph (i) or (j) of this AD, any crack is detected: Before further flight, repair the crack in accordance with a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA, or EASA (or its delegated agent). (l) New Requirement: Reporting Requirement Submit a one-time report of the findings (both positive and negative) of the inspections required by paragraphs (i) and (j) of this AD to Airbus, Sebastien Faure, SEES1, SAS—EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 31 68; fax +33 5 61 93 36 14; email sebastien.s.faure@airbus.com, at the applicable time specified in paragraph (l)(1) or (l)(2) of this AD. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. tkelley on DSK3SPTVN1PROD with (m) New Requirement: Terminating Action Accomplishment of the one-time eddy current inspection or a liquid penetrant inspection required by paragraph (j) of this AD, including doing all applicable repairs, constitutes terminating action for the inspections required by paragraph (i) of this AD. (n) Other FAA AD Provisions 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, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–2125; fax (425) 227– 1149. Information may be emailed to: 9ANM-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 2010–06–05, Amendment 39–16229 (75 FR 11435, March 11, 2010), 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 VerDate Mar<15>2010 04:58 Dec 22, 2012 Jkt 229001 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. (o) Related Information Refer to MCAI EASA Airworthiness Directive 2011–0163, dated August 30, 2011, and the service information specified in paragraphs (o)(1) through (o)(6) of this AD, for related information. (1) Airbus All Operator Telex A300– 53A0391, dated August 9, 2011. (2) Airbus All Operator Telex A300– 57A6111, dated August 9, 2011. (3) Airbus Mandatory Service Bulletin A300–57A6108, including Appendices 01 and 02, dated September 12, 2008. (4) Airbus Mandatory Service Bulletin A300–53A0387, including Appendices 01 and 02, dated September 12, 2008. (5) Airbus Service Bulletin A300–53–0268, Revision 06, dated January 7, 2002. (6) Airbus Service Bulletin A300–57–6052, Revision 03, dated May 27, 2002, including Airbus Drawings 15R53810394, Issue A, dated December 21, 1998, and 21R57110247, Issue A, dated June 20, 1997. (p) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on January 30, 2013. (i) Airbus All Operator Telex A300– 53A0391, dated August 9, 2011. (The issue date and document number of this document are specified on only the first page of the document.) (ii) Airbus All Operator Telex A300– 57A6111, dated August 9, 2011. (The issue date and document number of this document are specified on only the first page of the document.) (4) The following service information was approved for IBR on April 15, 2010 (75 FR 11435, March 11, 2010). PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 (i) Airbus Mandatory Service Bulletin A300–57A6108, including Appendices 01 and 02, dated September 12, 2008. (ii) Airbus Mandatory Service Bulletin A300–53A0387, including Appendices 01 and 02, dated September 12, 2008. (iii) Airbus Service Bulletin A300–53– 0268, Revision 06, dated January 7, 2002. (Pages 1–6, 9, 10, and 25–27 of this document are identified as Revision 06, dated January 7, 2002. Pages 7, 8, 11–24, and 28–84 of this AD document are identified as Revision 05, dated June 9, 2000). (iv) Airbus Service Bulletin A300–57– 6052, Revision 03, dated May 27, 2002, which includes Airbus Drawing 15R53810394, Issue A, dated December 21, 1998 and Airbus Drawing 21R57110247, Issue A, dated June 20, 1997. Airbus Drawing 21R57110247, Issue A, dated June 20, 1997 has effective pages 1 and 2, dated May 28, 1997 and pages 3 and 4, dated June 20, 1997. (5) 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; email account.airwortheas@airbus.com; Internet http:// www.airbus.com. (6) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on December 4, 2012. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–29992 Filed 12–21–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2012–0660; Airspace Docket No. 12–ANM–20] Establishment of Class E Airspace; Walsenburg, CO Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: This action establishes Class E airspace at Spanish Peaks Airfield, Walsenburg, CO, to accommodate aircraft using new Area Navigation (RNAV) Global Positioning System (GPS) standard instrument approach SUMMARY: E:\FR\FM\26DER1.SGM 26DER1

Agencies

[Federal Register Volume 77, Number 247 (Wednesday, December 26, 2012)]
[Rules and Regulations]
[Pages 75833-75836]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-29992]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0858; Directorate Identifier 2011-NM-183-AD; 
Amendment 39-17287; AD 2012-25-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are superseding an existing airworthiness directive (AD) 
for certain Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; and 
Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, and B4-622R 
airplanes. That AD currently requires performing a one-time detailed 
visual inspection of the forward fitting at frame (FR) 40 on both sides 
of the airplane for cracks, and repair if necessary. This new AD 
requires repetitive detailed inspections of the forward fitting at FR 
40 without nut removal, and a one-time eddy current or liquid penetrant 
inspection of the forward fitting at FR 40 with nut removal, and repair 
if necessary. This AD was prompted by reports that new cracks were 
found in the FR 40 forward fitting. We are issuing this AD to detect 
and correct cracking of the FR 40 forward fitting, which could result 
in a deterioration of the structural integrity of the frame.

DATES: This AD becomes effective January 30, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 30, 
2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of April 
15, 2010 (75 FR 11435, March 11, 2010).

ADDRESSES: You may examine the AD docket on the Internet at http://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, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 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 August 27, 2012 (77 
FR 51717), and proposed to supersede AD 2010-06-05, Amendment 39-16229 
(75 FR 11435, March 11, 2010). That NPRM proposed to correct an unsafe 
condition for the specified products. The Mandatory Continuing 
Airworthiness Information (MCAI) states:

    One A300-600 aeroplane operator reported that, during a routine 
inspection, a crack was found in the right hand frame (FR) 40 
forward fitting between stringer 32 and stringer 33. The subject 
aeroplane had previously been modified in accordance with Airbus SB 
A300-57-6053 (Mod. 10453).
    Therefore and pending completion of the full analysis using a 
refined Finite Element Model, EASA [European Aviation Safety Agency] 
issued AD 2009-0094 [which corresponds with FAA AD 2010-06-05, 
Amendment 39-16229 (75 FR 11435, March 11, 2010)] to require a one-
time Detailed Visual Inspection (DVI) of the post-SB A300-57-6053 
A300-600 aeroplanes and post-SB A300-53-0297 A300 aeroplanes in 
order to ensure the structural integrity of frame 40.
    During a recent maintenance check, on two aeroplanes (one A300B4 
and one A300-600), cracks were found in the FR 40 forward fitting.
    These new crack findings are considered as unexpected, since 
they were found after:

--Application of modification SB A300-57-6053 or SB A300-53-0297 
which cancels the inspection programme, and
--Accomplishment of EASA AD 2009-0094.

[[Page 75834]]

    For the reasons described above, this new [EASA] AD, which 
supersedes EASA AD 2009-0094, requires repetitive DVI of the FR 40 
forward fitting (without nut removal), accomplishment of a one time 
Eddy Current (EC) inspection or liquid penetrant inspection of this 
area (with nut removal) and, depending on findings, the 
accomplishment of associated corrective action [repair if any 
cracking found]. Passing the EC or liquid penetrant inspection 
constitutes terminating action for the repetitive DVI.

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 (77 FR 51717, August 27, 
2012), 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.

Costs of Compliance

    We estimate that this AD will affect about 134 products of U.S. 
registry.
    The actions that are required by AD 2010-06-05, Amendment 39-16229 
(75 FR 11435, March 11, 2010), and retained in this AD take about 3 
work-hours per product, at an average labor rate of $85 per work-hour. 
Based on these figures, the estimated cost of the currently required 
actions is $255 per product.
    We estimate that it will take about 3 work-hours 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 $34,170, or $255 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 that 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);
    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 AD and placed it in the AD docket.

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 the NPRM (77 FR 51717, August 27, 
2012), 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 airworthiness directive (AD) 
2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010), and 
adding the following new AD:

2012-25-06 Airbus: Amendment 39-17287. Docket No. FAA-2012-0858; 
Directorate Identifier 2011-NM-183-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective January 30, 
2013.

(b) Affected ADs

    This AD supersedes AD 2010-06-05, Amendment 39-16229 (75 FR 
11435, March 11, 2010).

(c) Applicability

    This AD applies to Airbus airplanes, certificated in any 
category, as identified in paragraphs (c)(1) and (c)(2) of this AD. 
For airplanes on which Airbus Service Bulletin A300-53-0297 or A300-
57-6053 (Airbus Modification 10453), as applicable, has been 
incorporated as a corrective action (repair following crack 
finding), no action is required by this AD.
    (1) Model A300 B4-2C, B4-103, and B4-203 airplanes, all serial 
numbers, modified preventively in service (without any preliminary 
crack findings), as specified in Airbus Service Bulletin A300-53-
0297 (Airbus Modification 10453).
    (2) Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-
622R airplanes, all serial numbers, modified preventively in service 
(without any preliminary crack findings), as specified in Airbus 
Service Bulletin A300-57-6053 (Airbus Modification 10453).

(d) Subject

    Air Transport Association (ATA) of America Code 53, 57: 
Fuselage, Wings.

(e) Reason

    This AD was prompted by reports that cracks were found in the 
frame (FR) 40 forward fitting. We are issuing this AD to detect and 
correct cracking of the FR 40 forward fitting, which could result in 
a deterioration of the structural integrity of the frame.

(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 Detailed Inspection

    This paragraph restates the actions required by paragraphs 
(f)(1), (f)(2), and (f)(3) of AD 2010-06-05, Amendment 39-16229 (75 
FR 11435, March 11, 2010).
    (1) At the applicable time specified in table 1 to paragraph 
(g)(1) of this AD: Do a one-time detailed visual inspection of the 
forward fitting at FR 40 on both sides of the airplane, in 
accordance with Airbus Mandatory Service Bulletin A300-57A6108 (for 
Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R 
airplanes) or A300-53A0387 (for Model A300 B4-2C, B4-103, and B4-203 
airplanes), both including Appendices 01 and 02, both dated 
September 12, 2008.

[[Page 75835]]



        Table 1 to Paragraph (g)(1) of this AD--Compliance Times
------------------------------------------------------------------------
     Airplane models/configuration               Compliance time
------------------------------------------------------------------------
A300 B4-2C and B4-103 airplanes on       Prior to the accumulation of
 which Airbus Service Bulletin A300-53-   18,000 total flight cycles, or
 0297 was done prior to the               within 3 months after April
 accumulation of 9,000 total flight       15, 2010 (the effective date
 cycles.                                  of AD 2010-06-05, Amendment 39-
                                          16229 (75 FR 11435, March 11,
                                          2010)), whichever occurs
                                          later.
A300 B4-2C and B4-103 airplanes on       Within 5,500 flight cycles
 which Airbus Service Bulletin A300-53-   after accomplishment of Airbus
 0297 was done on or after the            Service Bulletin A300-53-0297,
 accumulation of 9,000 total flight       or within 6 months after April
 cycles.                                  15, 2010 (the effective date
                                          of AD 2010-06-05, Amendment 39-
                                          16229 (75 FR 11435, March 11,
                                          2010)), whichever occurs
                                          later; except, for airplanes
                                          that, as of April 15, 2010
                                          (the effective date of AD 2010-
                                          06-05), have accumulated
                                          11,000 flight cycles or more
                                          since accomplishment of Airbus
                                          Service Bulletin A300-53-0297,
                                          within 3 months after April
                                          15, 2010 (the effective date
                                          of AD 2010-06-05).
A300 B4-203 airplanes on which Airbus    Prior to the accumulation of
 Service Bulletin A300-53-0297 was done   15,000 total flight cycles, or
 prior to the accumulation of 8,300       within 3 months after April
 total flight cycles.                     15, 2010 (the effective date
                                          of AD 2010-06-05, Amendment 39-
                                          16229 (75 FR 11435, March 11,
                                          2010)), whichever occurs
                                          later.
A300 B4-203 airplanes on which Airbus    Within 4,100 flight cycles
 Service Bulletin A300-53-0297 was done   after accomplishment of Airbus
 on or after the accumulation of 8,300    Service Bulletin A300-53-0297,
 total flight cycles.                     or within 6 months after April
                                          15, 2010 (the effective date
                                          of AD 2010-06-05, Amendment 39-
                                          16229 (75 FR 11435, March 11,
                                          2010)), whichever occurs
                                          later; except, for airplanes
                                          that, as of April 15, 2010
                                          (the effective date of AD 2010-
                                          06-05), have accumulated 8,200
                                          flight cycles or more since
                                          accomplishment of Airbus
                                          Service Bulletin A300-53-0297,
                                          within 3 months after April
                                          15, 2010 (the effective date
                                          of AD 2010-06-05).
A300 B4-601, B4-603, B4-605R, B4-620,    Prior to the accumulation of
 B4-622, and B4-622R airplanes on which   11,500 total flight cycles, or
 Airbus Service Bulletin A300-57-6053     within 3 months after April
 was done prior to the accumulation of    15, 2010 (the effective date
 6,100 total flight cycles.               of AD 2010-06-05, Amendment 39-
                                          16229 (75 FR 11435, March 11,
                                          2010)), whichever occurs
                                          later.
A300 B4-601, B4-603, B4-605R, B4-620,    Within 3,300 flight cycles
 B4-622, and B4-622R airplanes on which   after accomplishment of Airbus
 Airbus Service Bulletin A300-57-6053     Service Bulletin A300-57-6053,
 was done on or after the accumulation    or within 6 months after April
 of 6,100 total flight cycles.            15, 2010 (the effective date
                                          of AD 2010-06-05, Amendment 39-
                                          16229 (75 FR 11435, March 11,
                                          2010)), whichever occurs
                                          later; except, for airplanes
                                          that, as of April 15, 2010
                                          (the effective date of AD 2010-
                                          06-05), have accumulated 6,600
                                          flight cycles or more since
                                          accomplishment of Airbus
                                          Service Bulletin A300-57-6053,
                                          within 3 months after April
                                          15, 2010 (the effective date
                                          of AD 2010-06-05).
------------------------------------------------------------------------

    (2) Except as required by paragraph (g)(3) of this AD: If any 
crack is found during the inspection required by paragraph (g)(1) of 
this AD, before further flight, do a temporary or definitive repair, 
as applicable, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-53-0268, Revision 06, dated January 7, 
2002 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); or A300-
57-6052, Revision 03, dated May 27, 2002, including Airbus Drawings 
15R53810394, Issue A, dated December 21, 1998, and 21R57110247, 
Issue A, dated June 20, 1997 (for Model A300 B4-601, B4-603, B4-
605R, B4-620, B4-622, and B4-622R airplanes).
    (3) If any crack found during the inspection required by 
paragraph (g)(1) of this AD cannot be repaired in accordance with 
Airbus Service Bulletin A300-53-0268, Revision 06, dated January 7, 
2002 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); or A300-
57-6052, Revision 03, dated May 27, 2002, including Airbus Drawings 
15R53810394, Issue A, dated December 21, 1998, and 21R57110247, 
Issue A, dated June 20, 1997 (for Model A300 B4-601, B4-603, B4-
605R, B4-620, B4-622, and B4-622R airplanes): Contact Airbus for 
repair instructions and, before further flight, repair the crack 
using a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA, or the European Aviation 
Safety Agency (EASA) (or its delegated agent).

(h) Retained Reporting Requirement

    This paragraph restates the requirements of paragraph (f)(4) of 
AD 2010-06-05, Amendment 39-16229 (75 FR 11435, March 11, 2010). 
Submit an inspection report in accordance with Appendix 01 of Airbus 
Mandatory Service Bulletin A300-53A0387, including Appendices 01 and 
02, dated September 12, 2008 (for Model A300 B4-2C, B4-103, and B4-
203 airplanes); or Airbus Mandatory Service Bulletin A300-57A6108, 
including Appendices 01 and 02, dated September 12, 2008 (for Model 
A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R 
airplanes); to the address identified on the reporting sheet, at the 
applicable time specified in paragraph (h)(1) or (h)(2) of this AD.
    (1) If the inspection was done on or after April 15, 2010 (the 
effective date of AD 2010-06-05, Amendment 39-16229 (75 FR 11435, 
March 11, 2010)): Submit the report within 30 days after the 
inspection.
    (2) If the inspection was done before April 15, 2010 (the 
effective date of AD 2010-06-05, Amendment 39-16229 (75 FR 11435, 
March 11, 2010)): Submit the report within 30 days after April 15, 
2010 (the effective date of AD 2010-06-05).

(i) New Requirement: Repetitive Detailed Inspections

    Within 300 flight cycles after the effective date of this AD: 
Perform a detailed inspection for cracks of the forward fitting at 
FR 40 without nut removal on both sides of the airplane, in 
accordance with Airbus All Operator Telex A300-53A0391, dated August 
9, 2011 (for Model A300 B4-2C, B4-103, and B4-203 airplanes); or 
Airbus All Operator Telex A300-57A6111, dated August 9, 2011 (for 
Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R 
airplanes). Thereafter, repeat the inspection at intervals not to 
exceed 300 flight cycles.

(j) New Requirement: Eddy Current Inspection or Liquid Penetrant 
Inspection

    Within 36 months after the effective date of this AD: Perform an 
eddy current inspection or a liquid penetrant inspection for cracks 
of the forward fitting at FR 40 with nut removal on both sides of 
the airplane, in accordance with Airbus All Operator Telex A300-
53A0391, dated August 9, 2011 (for Model A300 B4-2C, B4-103, and B4-
203 airplanes); or Airbus All Operator Telex A300-57A6111, dated 
August 9, 2011 (for Model A300 B4-601, B4-603, B4-605R, B4-620, B4-
622, and B4-622R airplanes).

[[Page 75836]]

(k) New Requirement: Corrective Action

    If, during any inspection required by paragraph (i) or (j) of 
this AD, any crack is detected: Before further flight, repair the 
crack in accordance with a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
or EASA (or its delegated agent).

(l) New Requirement: Reporting Requirement

    Submit a one-time report of the findings (both positive and 
negative) of the inspections required by paragraphs (i) and (j) of 
this AD to Airbus, Sebastien Faure, SEES1, SAS--EAW (Airworthiness 
Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; 
telephone +33 5 61 93 31 68; fax +33 5 61 93 36 14; email 
sebastien.s.faure@airbus.com, at the applicable time specified in 
paragraph (l)(1) or (l)(2) of this AD.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

(m) New Requirement: Terminating Action

    Accomplishment of the one-time eddy current inspection or a 
liquid penetrant inspection required by paragraph (j) of this AD, 
including doing all applicable repairs, constitutes terminating 
action for the inspections required by paragraph (i) of this AD.

(n) Other FAA AD Provisions

    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, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 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. AMOCs 
approved previously in accordance with AD 2010-06-05, Amendment 39-
16229 (75 FR 11435, March 11, 2010), 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.

(o) Related Information

    Refer to MCAI EASA Airworthiness Directive 2011-0163, dated 
August 30, 2011, and the service information specified in paragraphs 
(o)(1) through (o)(6) of this AD, for related information.
    (1) Airbus All Operator Telex A300-53A0391, dated August 9, 
2011.
    (2) Airbus All Operator Telex A300-57A6111, dated August 9, 
2011.
    (3) Airbus Mandatory Service Bulletin A300-57A6108, including 
Appendices 01 and 02, dated September 12, 2008.
    (4) Airbus Mandatory Service Bulletin A300-53A0387, including 
Appendices 01 and 02, dated September 12, 2008.
    (5) Airbus Service Bulletin A300-53-0268, Revision 06, dated 
January 7, 2002.
    (6) Airbus Service Bulletin A300-57-6052, Revision 03, dated May 
27, 2002, including Airbus Drawings 15R53810394, Issue A, dated 
December 21, 1998, and 21R57110247, Issue A, dated June 20, 1997.

(p) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
January 30, 2013.
    (i) Airbus All Operator Telex A300-53A0391, dated August 9, 
2011. (The issue date and document number of this document are 
specified on only the first page of the document.)
    (ii) Airbus All Operator Telex A300-57A6111, dated August 9, 
2011. (The issue date and document number of this document are 
specified on only the first page of the document.)
    (4) The following service information was approved for IBR on 
April 15, 2010 (75 FR 11435, March 11, 2010).
    (i) Airbus Mandatory Service Bulletin A300-57A6108, including 
Appendices 01 and 02, dated September 12, 2008.
    (ii) Airbus Mandatory Service Bulletin A300-53A0387, including 
Appendices 01 and 02, dated September 12, 2008.
    (iii) Airbus Service Bulletin A300-53-0268, Revision 06, dated 
January 7, 2002. (Pages 1-6, 9, 10, and 25-27 of this document are 
identified as Revision 06, dated January 7, 2002. Pages 7, 8, 11-24, 
and 28-84 of this AD document are identified as Revision 05, dated 
June 9, 2000).
    (iv) Airbus Service Bulletin A300-57-6052, Revision 03, dated 
May 27, 2002, which includes Airbus Drawing 15R53810394, Issue A, 
dated December 21, 1998 and Airbus Drawing 21R57110247, Issue A, 
dated June 20, 1997. Airbus Drawing 21R57110247, Issue A, dated June 
20, 1997 has effective pages 1 and 2, dated May 28, 1997 and pages 3 
and 4, dated June 20, 1997.
    (5) 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; email account.airworth-eas@airbus.com; 
Internet http://www.airbus.com.
    (6) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on December 4, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2012-29992 Filed 12-21-12; 8:45 am]
BILLING CODE 4910-13-P