Airworthiness Directives; Airbus Airplanes, 58978-58982 [2013-23324]

Download as PDF 58978 Federal Register / Vol. 78, No. 186 / Wednesday, September 25, 2013 / Proposed Rules 27–1206, Revision 01, dated October 10, 2011. For the purpose of this AD, a serviceable interconnecting strut is a unit which has been determined to be in compliance with the requirements of this AD. (A) A target part number (P/N) ABS0121– 13 or P/N 8–536–01, and (B) A target serial number lower than 1600, or a target serial number that is unreadable, and (C) A proximity sensor having P/N ABS0121–31 or P/N 8–372–04, and (D) A proximity sensor having a serial number between C59198 and C59435, or a serial number (S/N) C500000 or higher. (ii) For a target having S/N 1600 or higher and target P/N ABS0121–13 or P/N 8–536– 01: Within 8,000 flight hours after the effective date of this AD, re-identify the interconnecting strut, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–27–1206, Revision 01, dated October 10, 2011. of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (h) Parts Installation Prohibition As of the effective date of this AD, no person may install an interconnecting strut with a part number specified in figure 1 to paragraph (g) of this AD, on any airplane, except for parts identified in paragraph (g)(2)(ii) of this AD, provided that the actions in paragraph (g)(2)(ii) are done. Issued in Renton, Washington, on September 13, 2013. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. TKELLEY on DSK3SPTVN1PROD with PROPOSALS (i) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–27–1206, dated January 28, 2011, and if additional work has been accomplished using Airbus Service Bulletin A320–27–1206, Revision 01, dated October 10, 2011. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone (425) 227–1405; 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. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAAapproved if they are approved by the State VerDate Mar<15>2010 16:14 Sep 24, 2013 Jkt 229001 (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2012–0012, dated January 23, 2012, for related information, which can be found in the AD docket on the Internet at http://www.regulations.gov. (2) For service information identified in this AD, contact Airbus, Airworthiness Office—EAS, 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, WA. For information on the availability of this material at the FAA, call 425–227–1221. [FR Doc. 2013–23269 Filed 9–24–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0828; Directorate Identifier 2012–NM–036–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede airworthiness directive (AD) 2009–15– 17, which applied to certain Airbus Model A330–200 and –300; and Model A340–200 and –300 series airplanes. AD 2009–15–17 required an inspection for damage to the protective treatments or any corrosion of all main landing gear (MLG) bogie beams, and application of protective treatments if no damage or corrosion was found. If any damage or corrosion was found, corrective action followed by the application of protective treatments was required. Since we issued AD 2009–15–17, we received reports of thin paint coats and paint degradation on enhanced MLG bogie beams. This proposed AD would add repetitive detailed inspections of the MLG bogie beams. This proposed AD would also require modification of the MLG bogie beams, which would SUMMARY: PO 00000 Frm 00023 Fmt 4702 Sfmt 4702 terminate the repetitive inspections for any modified bogie beam. This proposed AD would also provide optional methods of compliance for inspections for corrosion, damage of the protective treatment, repair, and modification, of the MLG bogie beam. This proposed AD would also revise the applicability. We are proposing this AD to detect and correct damage or corrosion of the MLG bogie beams, which could cause a runway excursion event, bogie beam detachment from the airplane, or MLG collapse, which could result in damage to the airplane and injury to the occupants. DATES: We must receive comments on this proposed AD by November 12, 2013. 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– 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 Airbus service information identified in this proposed AD, contact Airbus SAS—Airworthiness Office— EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@ airbus.com; Internet http:// www.airbus.com. For Messier-Dowty service information identified in this AD, contact Messier-Dowty: Messier Services Americas, Customer Support Center, 45360 Severn Way, Sterling, VA 20166–8910; telephone 703–450–8233; fax 703–404–1621; Internet https:// techpubs.services/messier-dowty.com. You may review copies of the referenced 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. ADDRESSES: 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 E:\FR\FM\25SEP1.SGM 25SEP1 Federal Register / Vol. 78, No. 186 / Wednesday, September 25, 2013 / Proposed Rules 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; 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–2013–0828; Directorate Identifier 2012–NM–036–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. TKELLEY on DSK3SPTVN1PROD with PROPOSALS Discussion On July 2, 2009, we issued AD 2009– 15–17, Amendment 39–15980 (74 FR 37523, July 29, 2009). That AD required actions intended to address an unsafe condition on the products listed above. Since we issued AD 2009–15–17, Amendment 39–15980 (74 FR 37523, July 29, 2009), we received reports of thin paint coats and paint degradation on enhanced MLG bogie beams. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2012–0015, dated January 23, 2012 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: The operator of an A330 aeroplane (which has a common bogie beam with the A340) reported a fracture of the right-hand (RH) main landing gear (MLG) bogie beam, which occurred while turning during low speed taxi maneuvers. The bogie fractured aft of the pivot point and remained attached to the VerDate Mar<15>2010 16:14 Sep 24, 2013 Jkt 229001 sliding tube by the brake torque reaction rods. After this RH bogie failure, the aeroplane continued for approximately 40 meters on the forks of the sliding member before coming to rest on the taxiway. The preliminary investigations revealed that his event was due to corrosion pitting occurring on the bore of the bogie beam. Investigations are ongoing to determine why bogie beam internal paint has been degraded, leading to a loss of cadmium plating, thereby allowing development of corrosion pitting. This condition if not detected and corrected, could lead to a runway excursion event or to detachment of the bogie from the aeroplane, or to MLG collapse, possibly resulting in damage to the aeroplane and injury to the occupants. To enable early detection and repair of corrosion of the internal surfaces, EASA issued EASA AD 2007–0314 to require a onetime inspection of all MLG bogie beams, except Enhanced MLG bogie beams, and the reporting of the results to Airbus. EASA AD 2007–0314 was revised and later superseded by EASA AD 2008–0093, reducing the inspection threshold. The results of subsequent investigations showed thin paint coats and paint degradation, confirmed as well on Enhanced MLG bogie beams. To address this additional concern, EASA issued EASA AD 2011–0141 [which was not mandated by the FAA], retaining the requirements of EASA AD 2008–0093, which was superseded, to require a one-time visual inspection of all MLG bogie beams, including a visual examination of the internal diameter for corrosion or damage to protective treatments of the bogie beam and measurement of the paint thickness on the internal bore, accomplishment of the applicable corrective actions and a modification of the MLG bogie beam to improve the coat paint application method, and application of corrosion protection. Prompted by in-service requests, this [EASA] AD retains the requirements of EASA AD 2011–0141, which is superseded, and introduces repetitive inspections [for damage to protective treatments or corrosion] of the MLG bogie beams, which allows extension of the compliance time for the MLG bogie beam modification [for improved protection from corrosion] from 15 years to 21 years. Modification of a MLG bogie beam constitutes terminating action for the repetitive inspections for that MLG bogie beam. 58979 unsafe condition identified in the MCAI. • Airbus Mandatory Service Bulletins A330–32–3237 (for Model A330 series airplanes), dated January 18, 2011. • Airbus Mandatory Service Bulletin A340–32–4279 (for Model A340 series airplanes), dated January 18, 2011. • Messier-Dowty Service Bulletin A33/34–32–272, including Appendices A, B, C, and D, Revision 1, dated September 22, 2008. • Messier-Dowty Service Bulletin A33/34–32–278, including Appendices A and B, dated February 17, 2010. • Messier-Dowty Service Bulletin A33/34–32–283, including Appendix A, dated May 11, 2010. • Messier-Dowty Service Bulletin A33/34–32–284, including Appendix A, dated May 11, 2010. FAA’s Determination and Requirements of This Proposed AD This product has 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 the same type design. Differences Between This AD and the MCAI or Service Information This proposed AD also provides optional methods of compliance for inspections for corrosion, damage of the protective treatment, repair, and modification, of the MLG bogie beam. You may obtain further information by examining the MCAI in the AD docket. This AD differs from the MCAI and/ or service information as follows: The MCAI specifies repair and corrective actions in accordance with Airbus Mandatory Service Bulletin A330–32– 3225, Revision 1, dated October 30, 2008; or A340–32–4268, Revision 1, dated October 30, 2008. However, Airbus Mandatory Service Bulletins A330–32–3225, Revision 1, dated October 30, 2008; and A340–32–4268, Revision 1, dated October 30, 2008; do not describe those actions. Paragraphs (g)(1)(i) and (g)(1)(ii) of this proposed AD specify repair and corrective actions in accordance with Messier-Dowty Service Bulletin A33/34–32–272, Revision 1, including Appendices A, B, C, and D, dated September 22, 2008. Relevant Service Information Costs of Compliance Airbus and Messier-Dowty have issued the following service bulletins. The actions described in this service information are intended to correct the We estimate that this proposed AD affects 51 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: PO 00000 Frm 00024 Fmt 4702 Sfmt 4702 E:\FR\FM\25SEP1.SGM 25SEP1 58980 Federal Register / Vol. 78, No. 186 / Wednesday, September 25, 2013 / Proposed Rules ESTIMATED COSTS Action Inspection and actions retained from AD 2009–15– 17 (74 FR 37523, July 29, 2009). Inspection and modification [new proposed actions]. Labor cost Parts cost Cost per product Cost on U.S. operators 22 work-hours × $85 per hour = $1,870 per inspection cycle. $0 $1,870 per inspection cycle ... $95,370 per inspection cycle. 44 work-hours × $85 per hour = $3,740 per inspection cycle. 0 3,740 per inspection cycle ..... 190,740 per inspection cycle. TKELLEY on DSK3SPTVN1PROD with PROPOSALS Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to 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 control number for the collection of information required by this proposed AD is 2120– 0056. The paperwork cost associated with this proposed AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this proposed AD is 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. 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. 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. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Regulatory Findings We determined that this proposed AD would not have federalism implications VerDate Mar<15>2010 16:14 Sep 24, 2013 Jkt 229001 List of Subjects in 14 CFR Part 39 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) 2009–15–17, Amendment 39–15980 (74 FR 37523, July 29, 2009), and adding the following new AD: ■ Airbus: Docket No. FAA–2012–0828; Directorate Identifier 2012–NM–036–AD. (a) Comments Due Date We must receive comments by November 12, 2013. PO 00000 Frm 00025 Fmt 4702 Sfmt 4702 (b) Affected ADs This AD supersedes AD 2009–15–17, Amendment 39–15980 (74 FR 37523, July 29, 2009). (c) Applicability This AD applies to Airbus Model A330– 201, –202, –203, –223, –223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; and Model A340– 211, –212, –213, –311, –312, and –313 airplanes; certificated in any category; all manufacturer serial numbers, except those airplanes on which Airbus modification 58896 has been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 32, Landing gear. (e) Reason This AD was prompted by reports of thin paint coats and paint degradation on enhanced main landing gear (MLG) bogie beams. We are issuing this AD to detect and correct damage or corrosion of the MLG bogie beams, which could cause a runway excursion event, bogie beam detachment from the airplane, or main landing gear collapse, which could in result damage to the airplane and injury to the occupants. (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 Actions and Compliance This paragraph restates the requirements of paragraph (f) of AD 2009–15–17, Amendment 39–15980 (74 FR 37523, July 29, 2009). For Airbus Model A330–200, A330–300, A340– 200, and A340–300 series airplanes, all serial numbers, except those on which Airbus modification 54500 has been embodied in production or Airbus Service Bulletin A330– 32–3212 has been embodied in service: Unless already done, do the following actions. (1) At the applicable compliance time specified in paragraph (g)(2) or (g)(3) of this AD: Clean the internal bore and perform a detailed visual inspection of internal surfaces of the MLG bogie beam (right-hand and lefthand) for any damage to the protective treatments or any corrosion, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330–32– 3225 or A340–32–4268, both Revision 01, both dated October 30, 2008; as applicable. (i) If no damage and corrosion is found, before further flight, apply the protective E:\FR\FM\25SEP1.SGM 25SEP1 TKELLEY on DSK3SPTVN1PROD with PROPOSALS Federal Register / Vol. 78, No. 186 / Wednesday, September 25, 2013 / Proposed Rules treatments of the bogie beam, in accordance with the Accomplishment Instructions of Messier-Dowty Service Bulletin A33/34–32– 272, Revision 1, including Appendices A, B, C, and D, dated September 22, 2008. (ii) If any damage or corrosion is found, before further flight, do all applicable corrective actions and apply the protective treatments of the bogie beam, in accordance with the Accomplishment Instructions of Messier-Dowty Service Bulletin A33/34–32– 272, Revision 1, including Appendices A, B, C, and D, dated September 22, 2008. (2) For airplanes with 54 months or less time-in-service since the date of issuance of the original French airworthiness certificate or the date of issuance of the original French or EASA export certificate of airworthiness as of September 2, 2009 (the effective date of AD 2009–15–17, Amendment 39–15980 (74 FR 37523, July 29, 2009): At the latest of the applicable times specified in paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD, do the actions required by paragraph (g)(1) of this AD. (i) Not before 54 months since the date of issuance of the original French airworthiness certificate or the date of issuance of the original French or EASA export certificate of airworthiness, but no later than 72 months since the date of issuance of the original French airworthiness certificate or the date of issuance of the original French or EASA export certificate of airworthiness. (ii) Not before 54 months since the installation of a new bogie beam in-service before September 2, 2009 (the effective date of AD 2009–15–17, Amendment 39–15980 (74 FR 37523, July 29, 2009)), but no later than 72 months since the installation of a new bogie beam in-service before September 2, 2009 (the effective date of AD 2009–15– 17). (iii) Not before 54 months since the last overhaul of a bogie beam before September 2, 2009 (the effective date of AD 2009–15–17, Amendment 39–15980 (74 FR 37523, July 29, 2009), but no later than 72 months since the last overhaul of a bogie beam before September 2, 2009 (the effective date of AD 2009–15–17). (3) For airplanes with more than 54 months time-in-service since the date of issuance of the original French airworthiness certificate or the date of issuance of the original French or EASA export certificate of airworthiness as of September 2, 2009 (the effective date of AD 2009–15–17, Amendment 39–15980 (74 FR 37523, July 29, 2009): At the applicable time specified in paragraph (g)(3)(i), (g)(3)(ii), (g)(3)(iii), (g)(3)(iv), or (g)(3)(v) of this AD, do the actions required by paragraph (g)(1) of this AD. (i) For airplanes on which the bogie beam has not been replaced or overhauled since the date of issuance of the original French airworthiness certificate or the date of issuance of the original French or EASA export certificate of airworthiness as of September 2, 2009 (the effective date of AD 2009–15–17, Amendment 39–15980 (74 FR 37523, July 29, 2009): Within 18 months after September 2, 2009 (the effective date of AD 2009–15–17). (ii) For airplanes on which the bogie beam has been replaced in-service with a new VerDate Mar<15>2010 16:14 Sep 24, 2013 Jkt 229001 bogie beam and the new bogie beam has more than 54 months time-in-service as of September 2, 2009 (the effective date of AD 2009–15–17, Amendment 39–15980 (74 FR 37523, July 29, 2009): Within 18 months after September 2, 2009 (the effective date of AD 2009–15–17). (iii) For airplanes on which the bogie beam has been replaced in-service with a new bogie beam and the new bogie beam has 54 months or less time-in-service as of September 2, 2009 (the effective date of AD 2009–15–17, Amendment 39–15980 (74 FR 37523, July 29, 2009): Not before 54 months since the installation of a new bogie beam inservice before September 2, 2009 (the effective date of AD 2009–15–17), but no later than 72 months since the installation of a new bogie beam in-service before September 2, 2009 (the effective date of AD 2009–15–17). (iv) For airplanes on which the bogie beam has been overhauled and the overhauled bogie beam has more than 54 months timein-service as of September 2, 2009 (the effective date of AD 2009–15–17, Amendment 39–15980 (74 FR 37523, July 29, 2009): Within 18 months after September 2, 2009 (the effective date of AD 2009–15–17), or at the next scheduled bogie beam overhaul, whichever occurs first. (v) For airplanes on which the bogie beam has been overhauled and the overhauled bogie beam has 54 months or less time-inservice as of September 2, 2009 (the effective date of AD 2009–15–17, Amendment 39– 15980 (74 FR 37523, July 29, 2009): Not before 54 months since the last overhaul of a bogie beam before September 2, 2009 (the effective date of AD 2009–15–17), but no later than 72 months since the last overhaul of a bogie beam before September 2, 2009 (the effective date of AD 2009–15–17). (4) Within 30 days after accomplishment of the inspection required by paragraph (g)(1) of this AD, or within 30 days after September 2, 2009 (the effective date of AD 2009–15–17, Amendment 39–15980 (74 FR 37523, July 29, 2009), whichever occurs later: Report the results, including no findings, to Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; email airworthiness.A330A340@airbus.com. (5) Actions accomplished in accordance with Messier-Dowty Service Bulletin A33/ 34–32–271, Revision 1, including Appendices A and B, dated November 16, 2007, are considered acceptable for compliance with the corresponding requirements of this AD. (6) Actions accomplished before September 2, 2009 (the effective date of AD 2009–15–17, Amendment 39–15980 (74 FR 37523, July 29, 2009), in accordance with the service bulletins specified in paragraphs (g)(6)(i) through (g)(6)(iv) of this AD are considered acceptable for compliance with the corresponding requirements of this AD. (i) Airbus Mandatory Service Bulletin A330–32–3225, dated November 21, 2007. (ii) Airbus Mandatory Service Bulletin A340–32–4268, dated November 21, 2007. (iii) Messier-Dowty Service Bulletin A33/ 34–32–271, including Appendix A, dated September 13, 2007. PO 00000 Frm 00026 Fmt 4702 Sfmt 4702 58981 (iv) Messier-Dowty Service Bulletin A33/ 34–32–272, including Appendices A, B, C, and D, dated November 16, 2007. (h) New Requirement of This AD: Repetitive Inspections For Airbus Model A330–201, –202, –203, –223, –223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; and Model A340–211, –212, –213, –311, –312, and –313 airplanes; all manufacturer serial numbers, except those airplanes on which Airbus modification 58896 has been embodied in production: Repeat the inspection required by paragraph (g)(1) of this AD at intervals not to exceed 72 months, but not before 48 months since first flight after the most recent MLG bogie beam overhaul done after the most recent inspection, until the modification specified in paragraph (i) of this AD is done. (i) New Inspection and Modification For Airbus Model A330–201, –202, –203, –223, –223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; and Model A340–211, –212, –213, –311, –312, and –313 airplanes; all manufacturer serial numbers, except those airplanes on which Airbus modification 58896 has been embodied in production: Before the accumulation of 252 months on a MLG bogie beam, or within 90 days after the effective date of this AD, whichever occurs later, do the actions specified in paragraphs (i)(1) and (i)(2) of this AD. (1) Do a detailed inspection for damage and corrosion of the internal bores of the MLG bogie beam, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330–32–3237 or A340–32–4279, both dated January 18, 2011, as applicable. If any damage or corrosion is found, repair, as applicable, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330–32–3237 or A340–32–4279, both dated January 18, 2011, as applicable. (2) Modify and re-identify, as applicable, the MLG bogie beam, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–32–3237 or A340–32– 4279, both dated January 18, 2011, as applicable. (j) New Optional Terminating Action For Airbus Model A330–201, –202, –203, –223, –223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; and Model A340–211, –212, –213, –311, –312, and –313 airplanes; all manufacturer serial numbers, except those airplanes on which Airbus modification 58896 has been embodied in production: Modification of a MLG bogie beam done in accordance with paragraph (i) of this AD, terminates the repetitive inspections required by paragraphs (g) and (h) of this AD for that modified MLG bogie beam. (k) New Exception to Service Information Specifications The inspection requirement of paragraph (i)(1) of this AD and the modification requirement of paragraph (i)(2) of this AD do not apply to any MLG bogie beam having any serial number listed in Appendix A of E:\FR\FM\25SEP1.SGM 25SEP1 58982 Federal Register / Vol. 78, No. 186 / Wednesday, September 25, 2013 / Proposed Rules Messier-Dowty Service Bulletin A33/34–32– 283 or A33/34–32–284, both including Appendix A, both dated May 11, 2010, as applicable. (l) New Optional Methods of Compliance (1) Inspections for corrosion and damage to the protective treatment of the bogie beam, and repairs, done in accordance with Messier-Dowty Service Bulletin A33/34–32– 278, including appendices A and B, dated February 17, 2010, are acceptable methods of compliance with the requirements of paragraph (i)(1) of this AD. (2) Modification of a MLG bogie beam, done in accordance with Messier-Dowty Service Bulletins A33/34–32–283 and A33/ 34–32–284, both including Appendix A, both dated May 11, 2010, as applicable, is an acceptable method of compliance with the requirements of paragraph (i)(2) of this AD. (m) New Parts Installation Limitation As of the effective date of this AD, no person may install a MLG bogie beam on any airplane unless it is in compliance with the requirements and compliance times of paragraphs (g), (h), and (i) of this AD. TKELLEY on DSK3SPTVN1PROD with PROPOSALS (n) New Reporting Requirement Submit a report of the findings (both positive and negative) of the inspection required by paragraph (g) or (i) of this AD to Airbus, Customer Service Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, using the applicable reporting sheet in Airbus Service Bulletin A330–32– 3237 or A340–32–4279, both dated January 18, 2011, at the applicable time specified in paragraph (n)(1) or (n)(2) of this AD. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 90 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 90 days after the effective date of this AD. (o) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-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 VerDate Mar<15>2010 16:14 Sep 24, 2013 Jkt 229001 actions if they are FAA-approved. Corrective actions are considered FAA-approved if they were approved by the State of Design Authority (or its delegated agent). For a repair method to be approved, the repair approval must specifically refer to this AD. You are required to ensure 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. (p) Related Information Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2012–0015, dated January 23, 2012, for related information, which can be found in the AD docket on the internet at http:// www.regulations.gov. Issued in Renton, Washington, on September 17, 2013. Ross Landes, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–23324 Filed 9–24–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0796; Directorate Identifier 2013–NM–111–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede airworthiness directive (AD) 2013–07– 07, which applies to all The Boeing Company Model 737–600, –700, –700C, –800, –900, and –900ER series airplanes. AD 2013–07–07 requires inspecting to determine the part number SUMMARY: PO 00000 Frm 00027 Fmt 4702 Sfmt 4702 of the attach pins of the horizontal stabilizer rear spar, and replacing certain attach pins. Since we issued AD 2013–07–07, we received inquiries from affected operators regarding the parts installation limitation and prohibition, and re-installation of certain attach pins that were removed for inspection. This proposed AD would clarify the parts installation limitation and prohibition, and would add a new requirement for certain airplanes on which certain attach pins were installed. We are proposing this AD to prevent premature failure of the attach pins, which could cause reduced structural integrity of the horizontal stabilizer to fuselage attachment, resulting in loss of control of the airplane. DATES: We must receive comments on this proposed AD by November 12, 2013. You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206– 766–5680; Internet https:// www.myboeingfleet.com. You may review copies of the referenced 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. ADDRESSES: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Management Facility 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 Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be E:\FR\FM\25SEP1.SGM 25SEP1

Agencies

[Federal Register Volume 78, Number 186 (Wednesday, September 25, 2013)]
[Proposed Rules]
[Pages 58978-58982]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-23324]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0828; Directorate Identifier 2012-NM-036-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 airworthiness directive (AD) 2009-15-
17, which applied to certain Airbus Model A330-200 and -300; and Model 
A340-200 and -300 series airplanes. AD 2009-15-17 required an 
inspection for damage to the protective treatments or any corrosion of 
all main landing gear (MLG) bogie beams, and application of protective 
treatments if no damage or corrosion was found. If any damage or 
corrosion was found, corrective action followed by the application of 
protective treatments was required. Since we issued AD 2009-15-17, we 
received reports of thin paint coats and paint degradation on enhanced 
MLG bogie beams. This proposed AD would add repetitive detailed 
inspections of the MLG bogie beams. This proposed AD would also require 
modification of the MLG bogie beams, which would terminate the 
repetitive inspections for any modified bogie beam. This proposed AD 
would also provide optional methods of compliance for inspections for 
corrosion, damage of the protective treatment, repair, and 
modification, of the MLG bogie beam. This proposed AD would also revise 
the applicability. We are proposing this AD to detect and correct 
damage or corrosion of the MLG bogie beams, which could cause a runway 
excursion event, bogie beam detachment from the airplane, or MLG 
collapse, which could result in damage to the airplane and injury to 
the occupants.

DATES: We must receive comments on this proposed AD by November 12, 
2013.

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-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 Airbus service information identified in this proposed AD, 
contact Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet 
http://www.airbus.com. For Messier-Dowty service information identified 
in this AD, contact Messier-Dowty: Messier Services Americas, Customer 
Support Center, 45360 Severn Way, Sterling, VA 20166-8910; telephone 
703-450-8233; fax 703-404-1621; Internet https://techpubs.services/messier-dowty.com. You may review copies of the referenced 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.

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

[[Page 58979]]

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: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 
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-2013-0828; 
Directorate Identifier 2012-NM-036-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 July 2, 2009, we issued AD 2009-15-17, Amendment 39-15980 (74 FR 
37523, July 29, 2009). That AD required actions intended to address an 
unsafe condition on the products listed above.
    Since we issued AD 2009-15-17, Amendment 39-15980 (74 FR 37523, 
July 29, 2009), we received reports of thin paint coats and paint 
degradation on enhanced MLG bogie beams. The European Aviation Safety 
Agency (EASA), which is the Technical Agent for the Member States of 
the European Community, has issued EASA Airworthiness Directive 2012-
0015, dated January 23, 2012 (referred to after this as ``the MCAI''), 
to correct an unsafe condition for the specified products. The MCAI 
states:

    The operator of an A330 aeroplane (which has a common bogie beam 
with the A340) reported a fracture of the right-hand (RH) main 
landing gear (MLG) bogie beam, which occurred while turning during 
low speed taxi maneuvers. The bogie fractured aft of the pivot point 
and remained attached to the sliding tube by the brake torque 
reaction rods. After this RH bogie failure, the aeroplane continued 
for approximately 40 meters on the forks of the sliding member 
before coming to rest on the taxiway.
    The preliminary investigations revealed that his event was due 
to corrosion pitting occurring on the bore of the bogie beam. 
Investigations are ongoing to determine why bogie beam internal 
paint has been degraded, leading to a loss of cadmium plating, 
thereby allowing development of corrosion pitting.
    This condition if not detected and corrected, could lead to a 
runway excursion event or to detachment of the bogie from the 
aeroplane, or to MLG collapse, possibly resulting in damage to the 
aeroplane and injury to the occupants.
    To enable early detection and repair of corrosion of the 
internal surfaces, EASA issued EASA AD 2007-0314 to require a one-
time inspection of all MLG bogie beams, except Enhanced MLG bogie 
beams, and the reporting of the results to Airbus. EASA AD 2007-0314 
was revised and later superseded by EASA AD 2008-0093, reducing the 
inspection threshold.
    The results of subsequent investigations showed thin paint coats 
and paint degradation, confirmed as well on Enhanced MLG bogie 
beams. To address this additional concern, EASA issued EASA AD 2011-
0141 [which was not mandated by the FAA], retaining the requirements 
of EASA AD 2008-0093, which was superseded, to require a one-time 
visual inspection of all MLG bogie beams, including a visual 
examination of the internal diameter for corrosion or damage to 
protective treatments of the bogie beam and measurement of the paint 
thickness on the internal bore, accomplishment of the applicable 
corrective actions and a modification of the MLG bogie beam to 
improve the coat paint application method, and application of 
corrosion protection.
    Prompted by in-service requests, this [EASA] AD retains the 
requirements of EASA AD 2011-0141, which is superseded, and 
introduces repetitive inspections [for damage to protective 
treatments or corrosion] of the MLG bogie beams, which allows 
extension of the compliance time for the MLG bogie beam modification 
[for improved protection from corrosion] from 15 years to 21 years. 
Modification of a MLG bogie beam constitutes terminating action for 
the repetitive inspections for that MLG bogie beam.

This proposed AD also provides optional methods of compliance for 
inspections for corrosion, damage of the protective treatment, repair, 
and modification, of the MLG bogie beam. You may obtain further 
information by examining the MCAI in the AD docket.

Relevant Service Information

    Airbus and Messier-Dowty have issued the following service 
bulletins. The actions described in this service information are 
intended to correct the unsafe condition identified in the MCAI.
     Airbus Mandatory Service Bulletins A330-32-3237 (for Model 
A330 series airplanes), dated January 18, 2011.
     Airbus Mandatory Service Bulletin A340-32-4279 (for Model 
A340 series airplanes), dated January 18, 2011.
     Messier-Dowty Service Bulletin A33/34-32-272, including 
Appendices A, B, C, and D, Revision 1, dated September 22, 2008.
     Messier-Dowty Service Bulletin A33/34-32-278, including 
Appendices A and B, dated February 17, 2010.
     Messier-Dowty Service Bulletin A33/34-32-283, including 
Appendix A, dated May 11, 2010.
     Messier-Dowty Service Bulletin A33/34-32-284, including 
Appendix A, dated May 11, 2010.

FAA's Determination and Requirements of This Proposed AD

    This product has 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 the same 
type design.

Differences Between This AD and the MCAI or Service Information

    This AD differs from the MCAI and/or service information as 
follows: The MCAI specifies repair and corrective actions in accordance 
with Airbus Mandatory Service Bulletin A330-32-3225, Revision 1, dated 
October 30, 2008; or A340-32-4268, Revision 1, dated October 30, 2008. 
However, Airbus Mandatory Service Bulletins A330-32-3225, Revision 1, 
dated October 30, 2008; and A340-32-4268, Revision 1, dated October 30, 
2008; do not describe those actions. Paragraphs (g)(1)(i) and 
(g)(1)(ii) of this proposed AD specify repair and corrective actions in 
accordance with Messier-Dowty Service Bulletin A33/34-32-272, Revision 
1, including Appendices A, B, C, and D, dated September 22, 2008.

Costs of Compliance

    We estimate that this proposed AD affects 51 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

[[Page 58980]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection and actions retained    22 work-hours x $85              $0  $1,870 per           $95,370 per
 from AD 2009-15-17 (74 FR 37523,   per hour = $1,870                    inspection cycle.    inspection cycle.
 July 29, 2009).                    per inspection
                                    cycle.
Inspection and modification [new   44 work-hours x $85               0  3,740 per            190,740 per
 proposed actions].                 per hour = $3,740                    inspection cycle.    inspection cycle.
                                    per inspection
                                    cycle.
----------------------------------------------------------------------------------------------------------------

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to 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 control 
number for the collection of information required by this proposed AD 
is 2120-0056. The paperwork cost associated with this proposed AD has 
been detailed in the Costs of Compliance section of this document and 
includes time for reviewing instructions, as well as completing and 
reviewing the collection of information. Therefore, all reporting 
associated with this proposed AD is 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.

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

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) 
2009-15-17, Amendment 39-15980 (74 FR 37523, July 29, 2009), and adding 
the following new AD:

Airbus: Docket No. FAA-2012-0828; Directorate Identifier 2012-NM-
036-AD.

(a) Comments Due Date

    We must receive comments by November 12, 2013.

(b) Affected ADs

    This AD supersedes AD 2009-15-17, Amendment 39-15980 (74 FR 
37523, July 29, 2009).

(c) Applicability

    This AD applies to Airbus Model A330-201, -202, -203, -223, -
223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes; and Model A340-211, -212, -213, -311, -312, and 
-313 airplanes; certificated in any category; all manufacturer 
serial numbers, except those airplanes on which Airbus modification 
58896 has been embodied in production.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
gear.

(e) Reason

    This AD was prompted by reports of thin paint coats and paint 
degradation on enhanced main landing gear (MLG) bogie beams. We are 
issuing this AD to detect and correct damage or corrosion of the MLG 
bogie beams, which could cause a runway excursion event, bogie beam 
detachment from the airplane, or main landing gear collapse, which 
could in result damage to the airplane and injury to the occupants.

(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 Actions and Compliance

    This paragraph restates the requirements of paragraph (f) of AD 
2009-15-17, Amendment 39-15980 (74 FR 37523, July 29, 2009). For 
Airbus Model A330-200, A330-300, A340-200, and A340-300 series 
airplanes, all serial numbers, except those on which Airbus 
modification 54500 has been embodied in production or Airbus Service 
Bulletin A330-32-3212 has been embodied in service: Unless already 
done, do the following actions.
    (1) At the applicable compliance time specified in paragraph 
(g)(2) or (g)(3) of this AD: Clean the internal bore and perform a 
detailed visual inspection of internal surfaces of the MLG bogie 
beam (right-hand and left-hand) for any damage to the protective 
treatments or any corrosion, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-32-3225 or 
A340-32-4268, both Revision 01, both dated October 30, 2008; as 
applicable.
    (i) If no damage and corrosion is found, before further flight, 
apply the protective

[[Page 58981]]

treatments of the bogie beam, in accordance with the Accomplishment 
Instructions of Messier-Dowty Service Bulletin A33/34-32-272, 
Revision 1, including Appendices A, B, C, and D, dated September 22, 
2008.
    (ii) If any damage or corrosion is found, before further flight, 
do all applicable corrective actions and apply the protective 
treatments of the bogie beam, in accordance with the Accomplishment 
Instructions of Messier-Dowty Service Bulletin A33/34-32-272, 
Revision 1, including Appendices A, B, C, and D, dated September 22, 
2008.
    (2) For airplanes with 54 months or less time-in-service since 
the date of issuance of the original French airworthiness 
certificate or the date of issuance of the original French or EASA 
export certificate of airworthiness as of September 2, 2009 (the 
effective date of AD 2009-15-17, Amendment 39-15980 (74 FR 37523, 
July 29, 2009): At the latest of the applicable times specified in 
paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD, do the 
actions required by paragraph (g)(1) of this AD.
    (i) Not before 54 months since the date of issuance of the 
original French airworthiness certificate or the date of issuance of 
the original French or EASA export certificate of airworthiness, but 
no later than 72 months since the date of issuance of the original 
French airworthiness certificate or the date of issuance of the 
original French or EASA export certificate of airworthiness.
    (ii) Not before 54 months since the installation of a new bogie 
beam in-service before September 2, 2009 (the effective date of AD 
2009-15-17, Amendment 39-15980 (74 FR 37523, July 29, 2009)), but no 
later than 72 months since the installation of a new bogie beam in-
service before September 2, 2009 (the effective date of AD 2009-15-
17).
    (iii) Not before 54 months since the last overhaul of a bogie 
beam before September 2, 2009 (the effective date of AD 2009-15-17, 
Amendment 39-15980 (74 FR 37523, July 29, 2009), but no later than 
72 months since the last overhaul of a bogie beam before September 
2, 2009 (the effective date of AD 2009-15-17).
    (3) For airplanes with more than 54 months time-in-service since 
the date of issuance of the original French airworthiness 
certificate or the date of issuance of the original French or EASA 
export certificate of airworthiness as of September 2, 2009 (the 
effective date of AD 2009-15-17, Amendment 39-15980 (74 FR 37523, 
July 29, 2009): At the applicable time specified in paragraph 
(g)(3)(i), (g)(3)(ii), (g)(3)(iii), (g)(3)(iv), or (g)(3)(v) of this 
AD, do the actions required by paragraph (g)(1) of this AD.
    (i) For airplanes on which the bogie beam has not been replaced 
or overhauled since the date of issuance of the original French 
airworthiness certificate or the date of issuance of the original 
French or EASA export certificate of airworthiness as of September 
2, 2009 (the effective date of AD 2009-15-17, Amendment 39-15980 (74 
FR 37523, July 29, 2009): Within 18 months after September 2, 2009 
(the effective date of AD 2009-15-17).
    (ii) For airplanes on which the bogie beam has been replaced in-
service with a new bogie beam and the new bogie beam has more than 
54 months time-in-service as of September 2, 2009 (the effective 
date of AD 2009-15-17, Amendment 39-15980 (74 FR 37523, July 29, 
2009): Within 18 months after September 2, 2009 (the effective date 
of AD 2009-15-17).
    (iii) For airplanes on which the bogie beam has been replaced 
in-service with a new bogie beam and the new bogie beam has 54 
months or less time-in-service as of September 2, 2009 (the 
effective date of AD 2009-15-17, Amendment 39-15980 (74 FR 37523, 
July 29, 2009): Not before 54 months since the installation of a new 
bogie beam in-service before September 2, 2009 (the effective date 
of AD 2009-15-17), but no later than 72 months since the 
installation of a new bogie beam in-service before September 2, 2009 
(the effective date of AD 2009-15-17).
    (iv) For airplanes on which the bogie beam has been overhauled 
and the overhauled bogie beam has more than 54 months time-in-
service as of September 2, 2009 (the effective date of AD 2009-15-
17, Amendment 39-15980 (74 FR 37523, July 29, 2009): Within 18 
months after September 2, 2009 (the effective date of AD 2009-15-
17), or at the next scheduled bogie beam overhaul, whichever occurs 
first.
    (v) For airplanes on which the bogie beam has been overhauled 
and the overhauled bogie beam has 54 months or less time-in-service 
as of September 2, 2009 (the effective date of AD 2009-15-17, 
Amendment 39-15980 (74 FR 37523, July 29, 2009): Not before 54 
months since the last overhaul of a bogie beam before September 2, 
2009 (the effective date of AD 2009-15-17), but no later than 72 
months since the last overhaul of a bogie beam before September 2, 
2009 (the effective date of AD 2009-15-17).
    (4) Within 30 days after accomplishment of the inspection 
required by paragraph (g)(1) of this AD, or within 30 days after 
September 2, 2009 (the effective date of AD 2009-15-17, Amendment 
39-15980 (74 FR 37523, July 29, 2009), whichever occurs later: 
Report the results, including no findings, to Airbus, 1 Rond Point 
Maurice Bellonte, 31707 Blagnac Cedex, France; email 
airworthiness.A330-A340@airbus.com.
    (5) Actions accomplished in accordance with Messier-Dowty 
Service Bulletin A33/34-32-271, Revision 1, including Appendices A 
and B, dated November 16, 2007, are considered acceptable for 
compliance with the corresponding requirements of this AD.
    (6) Actions accomplished before September 2, 2009 (the effective 
date of AD 2009-15-17, Amendment 39-15980 (74 FR 37523, July 29, 
2009), in accordance with the service bulletins specified in 
paragraphs (g)(6)(i) through (g)(6)(iv) of this AD are considered 
acceptable for compliance with the corresponding requirements of 
this AD.
    (i) Airbus Mandatory Service Bulletin A330-32-3225, dated 
November 21, 2007.
    (ii) Airbus Mandatory Service Bulletin A340-32-4268, dated 
November 21, 2007.
    (iii) Messier-Dowty Service Bulletin A33/34-32-271, including 
Appendix A, dated September 13, 2007.
    (iv) Messier-Dowty Service Bulletin A33/34-32-272, including 
Appendices A, B, C, and D, dated November 16, 2007.

(h) New Requirement of This AD: Repetitive Inspections

    For Airbus Model A330-201, -202, -203, -223, -223F, -243, -243F, 
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; 
and Model A340-211, -212, -213, -311, -312, and -313 airplanes; all 
manufacturer serial numbers, except those airplanes on which Airbus 
modification 58896 has been embodied in production: Repeat the 
inspection required by paragraph (g)(1) of this AD at intervals not 
to exceed 72 months, but not before 48 months since first flight 
after the most recent MLG bogie beam overhaul done after the most 
recent inspection, until the modification specified in paragraph (i) 
of this AD is done.

(i) New Inspection and Modification

    For Airbus Model A330-201, -202, -203, -223, -223F, -243, -243F, 
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; 
and Model A340-211, -212, -213, -311, -312, and -313 airplanes; all 
manufacturer serial numbers, except those airplanes on which Airbus 
modification 58896 has been embodied in production: Before the 
accumulation of 252 months on a MLG bogie beam, or within 90 days 
after the effective date of this AD, whichever occurs later, do the 
actions specified in paragraphs (i)(1) and (i)(2) of this AD.
    (1) Do a detailed inspection for damage and corrosion of the 
internal bores of the MLG bogie beam, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A330-32-3237 or A340-32-4279, both dated January 18, 2011, as 
applicable. If any damage or corrosion is found, repair, as 
applicable, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A330-32-3237 or A340-32-4279, both 
dated January 18, 2011, as applicable.
    (2) Modify and re-identify, as applicable, the MLG bogie beam, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-32-3237 or A340-32-4279, both dated January 18, 2011, 
as applicable.

(j) New Optional Terminating Action

    For Airbus Model A330-201, -202, -203, -223, -223F, -243, -243F, 
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; 
and Model A340-211, -212, -213, -311, -312, and -313 airplanes; all 
manufacturer serial numbers, except those airplanes on which Airbus 
modification 58896 has been embodied in production: Modification of 
a MLG bogie beam done in accordance with paragraph (i) of this AD, 
terminates the repetitive inspections required by paragraphs (g) and 
(h) of this AD for that modified MLG bogie beam.

(k) New Exception to Service Information Specifications

    The inspection requirement of paragraph (i)(1) of this AD and 
the modification requirement of paragraph (i)(2) of this AD do not 
apply to any MLG bogie beam having any serial number listed in 
Appendix A of

[[Page 58982]]

Messier-Dowty Service Bulletin A33/34-32-283 or A33/34-32-284, both 
including Appendix A, both dated May 11, 2010, as applicable.

(l) New Optional Methods of Compliance

    (1) Inspections for corrosion and damage to the protective 
treatment of the bogie beam, and repairs, done in accordance with 
Messier-Dowty Service Bulletin A33/34-32-278, including appendices A 
and B, dated February 17, 2010, are acceptable methods of compliance 
with the requirements of paragraph (i)(1) of this AD.
    (2) Modification of a MLG bogie beam, done in accordance with 
Messier-Dowty Service Bulletins A33/34-32-283 and A33/34-32-284, 
both including Appendix A, both dated May 11, 2010, as applicable, 
is an acceptable method of compliance with the requirements of 
paragraph (i)(2) of this AD.

(m) New Parts Installation Limitation

    As of the effective date of this AD, no person may install a MLG 
bogie beam on any airplane unless it is in compliance with the 
requirements and compliance times of paragraphs (g), (h), and (i) of 
this AD.

(n) New Reporting Requirement

    Submit a report of the findings (both positive and negative) of 
the inspection required by paragraph (g) or (i) of this AD to 
Airbus, Customer Service Directorate, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France, using the applicable reporting sheet in 
Airbus Service Bulletin A330-32-3237 or A340-32-4279, both dated 
January 18, 2011, at the applicable time specified in paragraph 
(n)(1) or (n)(2) of this AD.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 90 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 90 days after the effective date of 
this AD.

(o) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 
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 were approved by the State of Design Authority 
(or its delegated agent). For a repair method to be approved, the 
repair approval must specifically refer to this AD. You are required 
to ensure 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.

(p) Related Information

    Refer to MCAI European Aviation Safety Agency (EASA) 
Airworthiness Directive 2012-0015, dated January 23, 2012, for 
related information, which can be found in the AD docket on the 
internet at http://www.regulations.gov.

    Issued in Renton, Washington, on September 17, 2013.
Ross Landes,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-23324 Filed 9-24-13; 8:45 am]
BILLING CODE 4910-13-P