Airworthiness Directives; Airbus Airplanes, 66518-66523 [2016-21150]

Download as PDF 66518 Federal Register / Vol. 81, No. 188 / Wednesday, September 28, 2016 / Rules and Regulations Instructions of Bombardier Service Bulletin 84–30–10, Revision E, dated October 10, 2014, within the compliance times specified in paragraph (g) of this AD. (2) Bombardier Service Bulletin 84–30–10, Revision A, dated April 7, 2008. (3) Bombardier Service Bulletin 84–30–10, Revision B, dated January 20, 2010. (4) Bombardier Service Bulletin 84–30–10, Revision C, dated July 14, 2011. (5) Bombardier Service Bulletin 84–30–10, Revision D, dated December 20, 2011. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York ACO, ANE–170, 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 ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. 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. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO, ANE–170, Engine and Propeller Directorate, FAA; or TCCA; or Bombardier, Inc.’s TCCA DAO. If approved by the DAO, the approval must include the DAO-authorized signature. sradovich on DSK3GMQ082PROD with RULES (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2015–24, dated August 24, 2015, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2016–6148. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (l)(3) and (l)(4) of this AD. (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 this AD specifies otherwise. (i) Bombardier Service Bulletin 84–30–10, Revision E, dated October 10, 2014. (ii) Reserved. (3) For service information identified in this AD, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone: 416–375–4000; fax: 416–375– 4539; email: thd.qseries@ VerDate Sep<11>2014 17:53 Sep 27, 2016 Jkt 238001 aero.bombardier.com; Internet: http:// www.bombardier.com. (4) You may view this 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. (5) 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 September 12, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–22705 Filed 9–27–16; 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; Amendment 39–18637; AD 2016–18–07] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2009–15– 17 for certain Airbus Model A330–200 and –300 series airplanes; 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. This new AD continues to require inspections for damage to the protective treatments or any corrosion of all MLG bogie beams, application of protective treatments, and corrective action if necessary. This new AD also requires modification of the MLG bogie beams, which terminates the repetitive inspections for any modified bogie beam. This new AD allows optional methods of compliance for certain actions, and adds Airbus Model A330– 200 Freighter series airplanes to the applicability. This new AD revises the SUMMARY: PO 00000 Frm 00032 Fmt 4700 Sfmt 4700 compliance times and adds a one-time inspection for airplanes that were inspected too early. This AD was prompted by reports of thin paint coats and paint degradation on enhanced main landing gear (MLG) bogie beams, as well as reports that some airplanes have been inspected too early and not re-inspected as needed. 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 MLG collapse, and could result in damage to the airplane and injury to the occupants. DATES: This AD is effective November 2, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 2, 2016. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of September 2, 2009 (74 FR 37523, July 29, 2009). ADDRESSES: For Airbus service information identified in this final rule, 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 final rule, 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 view this 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. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2013– 0828. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2013– 0828; 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone: 800–647– E:\FR\FM\28SER1.SGM 28SER1 Federal Register / Vol. 81, No. 188 / Wednesday, September 28, 2016 / Rules and Regulations 5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. 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: sradovich on DSK3GMQ082PROD with RULES Discussion We issued a second supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 to supersede AD 2009–15–17, Amendment 39–15980 (74 FR 37523, July 29, 2009) (‘‘AD 2009– 15–17’’). AD 2009–15–17 applied to certain Airbus Model A330–200 and –300 series airplanes, and Model A340– 200 and –300 series airplanes. The second SNPRM published in the Federal Register on February 5, 2016 (81 FR 6185) (‘‘the second SNPRM’’). We preceded the second SNPRM with the first SNPRM, which was published in the Federal Register on March 5, 2014 (79 FR 12414) (‘‘the first SNPRM’’). We preceded the first SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on September 25, 2013 (78 FR 58978) (‘‘the NPRM’’). The NPRM was prompted by reports of thin paint coats and paint degradation on enhanced MLG bogie beams. The NPRM proposed to continue to require inspections for damage to the protective treatments or any corrosion of all MLG bogie beams, application of protective treatments, and corrective action if necessary. The NPRM also proposed to require modification of the MLG bogie beams, which would terminate the repetitive inspections for any modified bogie beam. In addition, the NPRM proposed to allow optional methods of compliance for certain actions, and to add Airbus Model A330–200 Freighter series airplanes to the applicability. The first SNPRM proposed to revise the compliance times and add a one-time inspection for airplanes that were inspected too early. The second SNPRM proposed to clarify the required actions and the specific configurations to which the actions must be applied. 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 MLG collapse, and could result in damage to the airplane and injury to the occupants. VerDate Sep<11>2014 17:53 Sep 27, 2016 Jkt 238001 The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2013– 0267R1, dated March 4, 2014; corrected May 8, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A330–200 Freighter, –200, and –300 series airplanes; and Model A340– 200 and –300 series airplanes. 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 investigations revealed that this event was due to corrosion pitting occurring on the bore of the bogie beam. 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 period. 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 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, EASA issued EASA AD 2012–0015 retaining the requirements of EASA AD 2011–0141, which was superseded, and introducing repetitive inspections of the MLG bogie beams, which allows extension of the compliance time for the MLG bogie beam modification from 15 years to 21 years. Modification of a MLG bogie beam constitutes terminating action for the repetitive inspections for that MLG bogie beam. Reports on inspection results provided to Airbus show that some aeroplanes were PO 00000 Frm 00033 Fmt 4700 Sfmt 4700 66519 initially inspected too early (before 4 years and 6 months since aeroplane first flight with bogie beam installed/installed after overhaul) and have not been re-inspected as required. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2012–0015, which is superseded, and redefines the inspection periodicity. This [EASA] AD also introduces a specific onetime inspection for aeroplanes that have been inspected too early. Prompted by operator comments, this [EASA] AD is revised to clarify the required actions and the specific configurations to which the actions must be applied. Appendix 1 of this [EASA] AD has been amended accordingly. This [EASA] AD is republished to editorially correct paragraph (4). You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2013– 0828. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the second SNPRM and the FAA’s response. Request To Revise the Applicability of the Second SNPRM American Airlines (AAL) requested that we revise the applicability of the proposed AD (in the second SNPRM) to exclude airplanes with MLG bogie beams that have had Airbus modification 58896 embodied inservice, as specified in Airbus Service Bulletin A330–32–3237. AAL pointed out that paragraph (c) of the proposed AD (in the second SNPRM) does not reflect MLG bogie beams that were modified in-service. We disagree with the request to revise the applicability of the proposed AD (in the second SNPRM). Paragraph (k) of this AD specifically requires inspection, repair, modification, and reidentification of the MLG bogie beams. However, paragraph (f) of this AD states that actions already done need not be repeated. If an operator has already accomplished the actions required by paragraph (k) of this AD before the effective date of this AD, then the modified airplane is already in compliance with the corresponding requirements of this AD. We have not made any changes to this AD in this regard. Additional Changes Made in This AD We have revised paragraph (m)(1) of this AD to remove reference to paragraph (g) of this AD; the reporting requirement specified in paragraph (m)(1) of this AD is required only for the E:\FR\FM\28SER1.SGM 28SER1 66520 Federal Register / Vol. 81, No. 188 / Wednesday, September 28, 2016 / Rules and Regulations inspection required by paragraph (k) of this AD. We have also revised paragraph (m)(2) of this AD to reference the correct service information for reporting inspection findings for the inspection required by paragraph (h) of this AD. Conclusion We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the second SNPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the second SNPRM. sradovich on DSK3GMQ082PROD with RULES Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. • Airbus Service Bulletin A330–32– 3225, Revision 02, including Appendix 1, dated October 26, 2012. This service information describes procedures for cleaning the internal bore and accomplishing a detailed inspection of internal surfaces of the left-hand (LH) and right-hand (RH) MLG bogie beams to detect any damage to the protective treatments and any corrosion, and measuring the paint thickness on the internal bore. • Airbus Service Bulletin A330–32– 3237, Revision 01, including Reporting Sheet, dated October 14, 2011. This service information describes procedures for a detailed inspection for damage and corrosion of the internal bores of the LH and RH MLG bogie beam and repair, as well as modification and re-identification. • Airbus Service Bulletin A340–32– 4268, Revision 03, including Appendix 1, dated January 14, 2013. This service information describes procedures for cleaning the internal bore and accomplishing a detailed inspection of internal surfaces of the LH and RH MLG bogie beams to detect any damage to the protective treatments and any corrosion, and measuring the paint thickness on the internal bore. • Airbus Service Bulletin A340–32– 4279, Revision 01, including Reporting Sheet, dated October 14, 2011. This service information describes procedures for a detailed inspection for damage and corrosion of the internal bores of the LH and RH MLG bogie beam, repair, modification, and reidentification. VerDate Sep<11>2014 17:53 Sep 27, 2016 Jkt 238001 Messier-Bugatti-Dowty has issued the following service information. • Messier-Dowty Service Bulletin A33/34–32–278, Revision 1, including Appendixes A and B, dated August 24, 2011. This service information describes procedures for inspections for damage and corrosion to the protective treatment of the internal bores of the LH and RH MLG bogie beam, and repairs. • Messier-Dowty Service Bulletin A33/34–32–283, Revision 1, including Appendix A, dated July 10, 2012. This service information describes procedures for modification of the LH and RH MLG bogie beams. • Messier-Dowty Service Bulletin A33/34–32–284, Revision 1, including Appendix A, dated July 10, 2012. This service information describes procedures for modification of the LH and RH MLG bogie beams. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 51 airplanes of U.S. registry. We also estimate that it takes about 34 work-hours per product to comply with this AD, and 1 work-hour per product for reporting. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $151,725, or $2,975 per product. In addition, we estimate that any necessary follow-on actions would take about 10 work-hours at a labor rate of $85 per work-hour, for a cost of $850 per product. We have no way of determining the number of aircraft that might need these actions. 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 AD is 2120–0056. The paperwork cost associated with this 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 AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden PO 00000 Frm 00034 Fmt 4700 Sfmt 4700 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 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. 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: E:\FR\FM\28SER1.SGM 28SER1 Federal Register / Vol. 81, No. 188 / Wednesday, September 28, 2016 / Rules and Regulations 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: ■ 2016–18–07 Airbus: Amendment 39–18637; Docket No. FAA–2013–0828; Directorate Identifier 2012–NM–036–AD. (a) Effective Date This AD is effective November 2, 2016. (b) Affected ADs This AD replaces AD 2009–15–17, Amendment 39–15980 (74 FR 37523, July 29, 2009) (‘‘AD 2009–15–17’’). (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category, all manufacturer serial numbers (MSN), except those on which Airbus modification 58896 has been embodied in production. (1) Airbus Model A330–223F, –243F, –201, –202, –203, –223, –243, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes. (2) Airbus Model A340–211, –212, –213, –311, –312, and –313 airplanes. (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, as well as reports that some airplanes have been inspected too early and not reinspected as needed. 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 MLG collapse, and could result in damage to the airplane and injury to the occupants. sradovich on DSK3GMQ082PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections for Certain Airplane Configurations For airplanes equipped with basic MLG (201252 series), or growth MLG (201490 series): After 54 months at the earliest, but no later than 72 months since the left-hand (LH) or right-hand (RH) MLG bogie beam’s first flight on an airplane, or since its first flight on an airplane after overhaul, as applicable, clean the internal bore and accomplish a detailed inspection of internal surfaces of the LH and RH MLG bogie beams to detect any damage to the protective treatments and any VerDate Sep<11>2014 17:53 Sep 27, 2016 Jkt 238001 corrosion, and measure the paint thickness on the internal bore, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–32–3225, Revision 02, including Appendix 1, dated October 26, 2012; or Airbus Service Bulletin A340–32– 4268, Revision 03, including Appendix 1, dated January 14, 2013; as applicable. Repeat the inspections thereafter at intervals not less than 54 months, but not exceeding 72 months, after the most recent inspection. During overhaul of a MLG bogie beam, any corrosion will be removed, which means that the first inspection after overhaul of that MLG bogie beam, as required by this paragraph, is between 54 months and 72 months since its first flight on an airplane after overhaul. (h) One-Time Detailed Inspection for Certain Airplane Configurations For airplanes equipped with basic MLG (201252 series), or growth MLG (201490 series) having a LH or RH MLG bogie beam that has already exceeded 72 months since its first flight on an airplane, or since its first flight on an airplane after overhaul, as applicable, as of the effective date of this AD; and that has been inspected as specified in Airbus Service Bulletin A330–32–3225 or Airbus Service Bulletin A340–32–4268, as applicable, earlier than 54 months since first flight of the affected MLG bogie beam on an airplane, or since its first flight on an airplane after its most recent overhaul, as applicable: Within the applicable compliance time indicated in paragraphs (h)(1) through (h)(4) of this AD, clean the internal bore and accomplish a detailed inspection of the internal surfaces of the LH and RH MLG bogie beams to detect any damage to the protective treatments and any corrosion, and measure the paint thickness on the internal bore, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–32–3225, Revision 02, including Appendix 1, dated October 26, 2012; or Airbus Service Bulletin A340–32– 4268, Revision 03, including Appendix 1, dated January 14, 2013; as applicable. (1) For MLG bogie beams having the configurations specified in both paragraphs (h)(1)(i) and (h)(1)(ii) of this AD: Do the detailed inspection specified in the introductory text of paragraph (h) of this AD within 9 months after the effective date of this AD. (i) MLG bogie beams having between 72 and 120 months since first flight on an airplane, or since the MLG bogie beam’s first flight on an airplane after the MLG bogie beam’s most recent overhaul, as applicable. (ii) MLG bogie beams on which the first inspection was done after 51 months and before 54 months since first flight of the MLG bogie beam on an airplane, or since the MLG bogie beam’s first flight on an airplane after the MLG bogie beam’s most recent overhaul, as applicable. (2) For MLG bogie beams having the configurations specified in both paragraphs (h)(2)(i) and (h)(2)(ii) of this AD: Do the detailed inspection specified in the introductory text of paragraph (h) of this AD within 3 months after the effective date of this AD. PO 00000 Frm 00035 Fmt 4700 Sfmt 4700 66521 (i) MLG bogie beams having between 72 and 120 months since first flight on an airplane, or since the MLG bogie beam’s first flight on an airplane after the MLG bogie beam’s most recent overhaul, as applicable. (ii) MLG bogie beams on which the first inspection was done after 45 months and before 51 months since first flight of the MLG bogie beam on an airplane, or since the MLG bogie beam’s first flight on an airplane after the MLG bogie beam’s most recent overhaul, as applicable. (3) For MLG bogie beams having the configurations specified in both paragraphs (h)(3)(i) and (h)(3)(ii) of this AD: Do the detailed inspection specified in the introductory text of paragraph (h) of this AD within 3 months after the effective date of this AD. (i) MLG bogie beams having between 72 and 96 months since first flight on an airplane, or since the MLG bogie beam’s first flight on an airplane after the MLG bogie beam’s most recent overhaul, as applicable. (ii) MLG bogie beams which have accumulated, at the effective date of this AD, less than 96 months and on which the first inspection was done before 51 months since first flight of the MLG bogie beam on an airplane, or since the MLG bogie beam’s first flight on an airplane after the after the MLG bogie beam’s most recent overhaul, as applicable. (4) For MLG bogie beams having the configurations specified in both paragraphs (h)(4)(i) and (h)(4)(ii) of this AD: Do the detailed inspection specified in the introductory text of paragraph (h) of this AD within 1 month after the effective date of this AD. (i) MLG bogie beams having between 96 and 120 months since first flight on an airplane, or since the MLG bogie beam’s first flight on an airplane after the MLG bogie beam’s most recent overhaul, as applicable. (ii) MLG bogie beams which has accumulated, at the effective date of this AD, 96 months or more and on which the first inspection was done before 45 months since first flight of the MLG bogie beam on an airplane, or since the MLG bogie beam’s first flight on an airplane after the MLG bogie beam’s most recent overhaul, as applicable. (i) Application of Protective Treatment If, during any inspection required by paragraph (g) or (h) of this AD, no damage or corrosion is found: Before further flight, apply the protective treatments to the MLG bogie beam, in accordance with the Accomplishment Instructions of MessierDowty Service Bulletin A33/34–32–272, Revision 1, including Appendixes A, B, C, and D, dated September 22, 2008. (j) Repair and Application of Protective Treatment If, during any inspection required by paragraph (g) or (h) of this AD, any damage or corrosion is found: Before further flight, repair and apply the protective treatments to the MLG bogie beam, in accordance with the Accomplishment Instructions of MessierDowty Service Bulletin A33/34–32–272, Revision 1, including Appendixes A, B, C, and D, dated September 22, 2008. E:\FR\FM\28SER1.SGM 28SER1 66522 Federal Register / Vol. 81, No. 188 / Wednesday, September 28, 2016 / Rules and Regulations (k) Inspection and Corrective Actions For airplanes equipped with basic MLG (201252 series), growth MLG (201490 series), or enhanced MLG (10–210 series): Before the accumulation of 252 total months on an MLG bogie beam, or within 90 days after the effective date of this AD, whichever occurs later, do the actions specified in paragraphs (k)(1) and (k)(2) of this AD concurrently and in sequence. (1) Except as provided by paragraph (k)(3) of this AD: Do a detailed inspection for damage and corrosion of the internal bores of the LH and RH MLG bogie beam, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 32–3237 or A340–32–4279, both Revision 01, both including Reporting Sheet, both dated October 14, 2011, as applicable. If any damage or corrosion is found, before further flight, repair in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–32–3237 or A340–32– 4279, both Revision 01, both including Reporting Sheet, both dated October 14, 2011, as applicable. (2) Except as provided by paragraph (k)(3) of this AD: Modify and re-identify, as applicable, the LH and RH MLG bogie beams, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 32–3237 or A340–32–4279, both Revision 01, both including Reporting Sheet, both dated October 14, 2011, as applicable. (3) The inspection requirements of paragraph (k)(1) of this AD, and the modification requirements only of paragraph (k)(2) of this AD, do not apply to any MLG bogie beam with a serial number listed in Appendix A of Messier-Dowty Service Bulletin A33/34–32–283 or A33/34–32–284, both Revision 1, both dated July 10, 2012, as applicable. sradovich on DSK3GMQ082PROD with RULES (l) Optional Methods of Compliance for Certain Airplane Configurations Inspections and corrective actions on both MLG bogie beams done in accordance with the instructions of Messier-Dowty Service Bulletin A33/34–32–271, Revision 1, including Appendixes A and B, dated November 16, 2007; or Messier-Dowty Service Bulletin A33/34–32–272, Revision 1, including Appendixes A, B, C, and D, dated September 22, 2008; as applicable; are acceptable methods of compliance for the requirements of paragraph (g) of this AD, provided each inspection is accomplished between 54 months and 72 months since the first flight of the affected MLG bogie beam on an airplane, or since the MLG bogie beam’s first flight after the MLG bogie beam’s most recent overhaul, as applicable. (m) Reporting Requirement (1) Submit a report of the findings (both positive and negative) of each inspection required by paragraph (k) of this AD, as applicable, 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, Revision 01, including Reporting Sheet, dated October 14, 2011; or Airbus Service Bulletin A340–32– 4279, Revision 01, including Reporting VerDate Sep<11>2014 17:53 Sep 27, 2016 Jkt 238001 Sheet, dated October 14, 2011; at the applicable time specified in paragraph (m)(1)(i) or (m)(1)(ii) of this AD. (i) If the inspection was done on or after the effective date of this AD: Submit the report within 90 days after the inspection. (ii) 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. (2) Submit a report of the findings (both positive and negative) of the inspection required by paragraph (h) 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 A330–32–3225, Revision 02, including Appendix 1, dated October 26, 2012; or Airbus Service Bulletin A340–32–4268, Revision 03, including Appendix 1, dated January 14, 2013; at the applicable time specified in paragraph (m)(2)(i) or (m)(2)(ii) of this AD. (i) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (ii) 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. (n) Optional Method of Compliance for Certain Requirements (1) Inspections for damage and corrosion to the protective treatment of the internal bores of the LH and RH MLG bogie beam, and repairs, done in accordance with MessierDowty Service Bulletin A33/34–32–278, Revision 1, including Appendixes A and B, dated August 24, 2011, are acceptable methods of compliance with the corresponding requirements of paragraph (k)(1) of this AD. (2) Modification of the LH and RH MLG bogie beams, done in accordance with Messier-Dowty Service Bulletins A33/34–32– 283 or A33/34–32–284, both Revision 1, both including Appendix A, both dated July 10, 2012, as applicable, is an acceptable method of compliance with the corresponding requirements of paragraph (k)(2) of this AD. (o) Optional Terminating Action for Certain Requirements Modification of both LH and RH MLG bogie beams on an airplane, done in accordance with paragraph (k) of this AD, or as specified in paragraphs (n)(1) and (n)(2) of this AD, terminates the repetitive inspections required by paragraph (g) of this AD for this airplane. (p) Credit for Previous Actions (1) This paragraph provides credit for the corresponding inspections and corrective actions done on an LH or RH MLG bogie beam required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A330–32–3225, dated November 21, 2007; or Revision 1, dated October 30, 2008; provided the inspections and corrective actions were accomplished between 54 months and 72 months since first flight of the affected MLG bogie beam on an airplane, or since its first flight after the MLG bogie PO 00000 Frm 00036 Fmt 4700 Sfmt 4700 beam’s most recent overhaul, as applicable. Airbus Service Bulletin A330–32–3225, dated November 21, 2007, is not incorporated by reference in this AD. Airbus Mandatory Service Bulletin A330–32–3225, Revision 01, including Appendix 1, dated October 30, 2008, was incorporated by reference in AD 2009–15–07. (2) This paragraph provides credit for the corresponding inspections and corrective actions done on an LH or RH MLG bogie beam required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus Mandatory Service Bulletin A340–32–4268, dated November 21, 2007; Revision 01, including Appendix 1, dated October 30, 2008; or Revision 02, dated October 26, 2012; provided these inspections and corrective actions were accomplished between 54 months and 72 months since first flight of the affected MLG bogie beam on an airplane, or since its first flight after the MLG bogie beam’s most recent overhaul, as applicable. Airbus Service Bulletin A340–32–4268, dated November 21, 2007; and Revision 02, dated October 26, 2012; are not incorporated by reference in this AD. Airbus Mandatory Service Bulletin A340–32–4268, Revision 01, including Appendix 1, dated October 30, 2008, was incorporated by reference in AD 2009–15–17. (3) This paragraph provides credit for the corresponding actions required by paragraph (n)(1) of this AD, if those actions were performed before the effective date of this AD using Messier-Dowty Service Bulletin A33/ 34–32–271, dated September 13, 2007, which is not incorporated by reference in this AD. (4) This paragraph provides credit for the corresponding actions required by paragraphs (j) and (n)(1) of this AD, if those actions were performed before the effective date of this AD using Messier-Dowty Service Bulletin A33/34–32–272, including Appendixes A, B, C, and D, dated November 16, 2007, which is not incorporated by reference in this AD. (5) This paragraph provides credit for the corresponding actions required by paragraphs (k), (m), and (r)(1)(i) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A330–32–3237, including Reporting Sheet, dated January 18, 2011. (6) This paragraph provides credit for the corresponding actions required by paragraphs (k), (m), and (r)(1)(i) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A340–32–4279, including Reporting Sheet, dated January 18, 2011. (7) This paragraph provides credit for the corresponding actions required by paragraphs (k)(3), (n)(2), (r)(1)(ii), and (r)(1)(iii) of this AD, if those actions were performed before the effective date of this AD using Messier-Dowty Service Bulletin A33/ 34–32–283, including Appendix A, dated May 11, 2010, which is not incorporated by reference in this AD. (8) This paragraph provides credit for the corresponding actions required by paragraphs (k)(3), (n)(2), (r)(1)(ii), and (r)(1)(iii) of this AD, if those actions were performed before the effective date of this AD E:\FR\FM\28SER1.SGM 28SER1 Federal Register / Vol. 81, No. 188 / Wednesday, September 28, 2016 / Rules and Regulations using Messier-Dowty Service Bulletin A33/ 34–32–284, including Appendix A, dated May 11, 2010, which is not incorporated by reference in this AD. (9) This paragraph provides credit for the corresponding actions required by paragraphs (n)(1) and (r)(1)(ii) of this AD, if those actions were performed before the effective date of this AD using Messier-Dowty Service Bulletin A33/34–32–278, including Appendixes A and B, dated February 17, 2010, which is not incorporated by reference in this AD. (q) Clarification of Inspection Compliance Times After accomplishment of the one-time detailed inspection required by paragraph (h) of this AD, the repetitive actions required by paragraph (g) of this AD remain applicable, and must be done within the compliance times specified in paragraph (g) of this AD. sradovich on DSK3GMQ082PROD with RULES (r) Parts Installation Limitations (1) After modification of an airplane, as required by paragraph (k) of this AD, or as specified in paragraphs (n)(1) and (n)(2) of this AD, do not install an MLG bogie beam on any airplane unless it is done in compliance with the requirements of paragraph (r)(1)(i), (r)(1)(ii), or (r)(1)(iii) of this AD. (i) The MLG bogie beam has been modified and re-identified in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–32–3237 or A340–32– 4279, both Revision 01, both including Reporting Sheet, both dated October 14, 2011, as applicable. (ii) The MLG bogie beam has been inspected and all applicable corrective actions have been done in accordance with the Accomplishment Instructions of MessierDowty Service Bulletin A33/34–32–278, Revision 1, dated August 24, 2011; and modified in accordance with the Accomplishment Instructions of MessierDowty Service Bulletin A33/34–32–283 or A33/34–32–284, both Revision 1, both including Appendix A, both dated July 10, 2012. (iii) The MLG bogie beam has a serial number listed in Appendix A of MessierDowty Service Bulletin A33/34–32–283 or A33/34–32–284, both Revision 1, both dated July 10, 2012, as applicable. (2) As of the effective date of this AD, except as specified in paragraph (r)(1) of this AD, installation of an MLG bogie beam on an airplane is allowed, provided that following the installation it is inspected and all applicable repairs and corrective actions have been done in accordance with the requirements of this AD. (s) 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 VerDate Sep<11>2014 17:53 Sep 27, 2016 Jkt 238001 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: 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) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (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. (t) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) AD 2013– 0267R1, dated March 4, 2014; corrected March 8, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA– 2013–0828. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (u)(5), (u)(6), and (u)(7) of this AD. (u) 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 this AD specifies otherwise. PO 00000 Frm 00037 Fmt 4700 Sfmt 4700 66523 (3) The following service information was approved for IBR on November 2, 2016. (i) Airbus Service Bulletin A330–32–3225, Revision 02, including Appendix 1, dated October 26, 2012. (ii) Airbus Service Bulletin A330–32–3237, Revision 01, including Reporting Sheet, dated October 14, 2011. (iii) Airbus Service Bulletin A340–32– 4268, Revision 03, including Appendix 1, dated January 14, 2013. (iv) Airbus Service Bulletin A340–32– 4279, Revision 01, including Reporting Sheet, dated October 14, 2011. (v) Messier-Dowty Service Bulletin A33/ 34–32–278, Revision 1, including Appendixes A and B, dated August 24, 2011. (vi) Messier-Dowty Service Bulletin A33/ 34–32–283, Revision 1, including Appendix A, dated July 10, 2012. (vii) Messier-Dowty Service Bulletin A33/ 34–32–284, Revision 1, including Appendix A, dated July 10, 2012. (4) The following service information was approved for IBR on September 2, 2009 (74 FR 37523, July 29, 2009). (i) Messier-Dowty Service Bulletin A33/ 34–32–271, Revision 1, including Appendixes A and B, dated November 16, 2007. (ii) Messier-Dowty Service Bulletin A33/ 34–32–272, Revision 1, including Appendixes A, B, C, and D, dated September 22, 2008. (5) For Airbus service information identified in this 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. (6) 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. (7) You may view this 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. (8) 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 August 24, 2016. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–21150 Filed 9–27–16; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\28SER1.SGM 28SER1

Agencies

[Federal Register Volume 81, Number 188 (Wednesday, September 28, 2016)]
[Rules and Regulations]
[Pages 66518-66523]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-21150]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0828; Directorate Identifier 2012-NM-036-AD; 
Amendment 39-18637; AD 2016-18-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2009-15-17 for 
certain Airbus Model A330-200 and -300 series airplanes; 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. This new AD continues to require 
inspections for damage to the protective treatments or any corrosion of 
all MLG bogie beams, application of protective treatments, and 
corrective action if necessary. This new AD also requires modification 
of the MLG bogie beams, which terminates the repetitive inspections for 
any modified bogie beam. This new AD allows optional methods of 
compliance for certain actions, and adds Airbus Model A330-200 
Freighter series airplanes to the applicability. This new AD revises 
the compliance times and adds a one-time inspection for airplanes that 
were inspected too early. This AD was prompted by reports of thin paint 
coats and paint degradation on enhanced main landing gear (MLG) bogie 
beams, as well as reports that some airplanes have been inspected too 
early and not re-inspected as needed. 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 MLG collapse, and could result in damage to the airplane 
and injury to the occupants.

DATES: This AD is effective November 2, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 2, 
2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of 
September 2, 2009 (74 FR 37523, July 29, 2009).

ADDRESSES: For Airbus service information identified in this final 
rule, 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 final rule, 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 
view this 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. It is also 
available on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2013-0828.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2013-
0828; 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 AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (telephone: 800-
647-

[[Page 66519]]

5527) is Docket Management Facility, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC 20590.

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: 

Discussion

    We issued a second supplemental notice of proposed rulemaking 
(SNPRM) to amend 14 CFR part 39 to supersede AD 2009-15-17, Amendment 
39-15980 (74 FR 37523, July 29, 2009) (``AD 2009-15-17''). AD 2009-15-
17 applied to certain Airbus Model A330-200 and -300 series airplanes, 
and Model A340-200 and -300 series airplanes. The second SNPRM 
published in the Federal Register on February 5, 2016 (81 FR 6185) 
(``the second SNPRM''). We preceded the second SNPRM with the first 
SNPRM, which was published in the Federal Register on March 5, 2014 (79 
FR 12414) (``the first SNPRM''). We preceded the first SNPRM with a 
notice of proposed rulemaking (NPRM) that published in the Federal 
Register on September 25, 2013 (78 FR 58978) (``the NPRM''). The NPRM 
was prompted by reports of thin paint coats and paint degradation on 
enhanced MLG bogie beams. The NPRM proposed to continue to require 
inspections for damage to the protective treatments or any corrosion of 
all MLG bogie beams, application of protective treatments, and 
corrective action if necessary. The NPRM also proposed to require 
modification of the MLG bogie beams, which would terminate the 
repetitive inspections for any modified bogie beam. In addition, the 
NPRM proposed to allow optional methods of compliance for certain 
actions, and to add Airbus Model A330-200 Freighter series airplanes to 
the applicability. The first SNPRM proposed to revise the compliance 
times and add a one-time inspection for airplanes that were inspected 
too early. The second SNPRM proposed to clarify the required actions 
and the specific configurations to which the actions must be applied. 
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 MLG collapse, and could result in 
damage to the airplane and injury to the occupants.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2013-0267R1, dated March 4, 2014; corrected May 8, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A330-200 Freighter, -200, and -300 series airplanes; and Model A340-200 
and -300 series airplanes. 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 investigations revealed that this event was due to corrosion 
pitting occurring on the bore of the bogie beam.
    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 period.
    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 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, EASA issued EASA AD 2012-0015 
retaining the requirements of EASA AD 2011-0141, which was 
superseded, and introducing repetitive inspections of the MLG bogie 
beams, which allows extension of the compliance time for the MLG 
bogie beam modification from 15 years to 21 years. Modification of a 
MLG bogie beam constitutes terminating action for the repetitive 
inspections for that MLG bogie beam.
    Reports on inspection results provided to Airbus show that some 
aeroplanes were initially inspected too early (before 4 years and 6 
months since aeroplane first flight with bogie beam installed/
installed after overhaul) and have not been re-inspected as 
required.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2012-0015, which is superseded, and 
redefines the inspection periodicity. This [EASA] AD also introduces 
a specific one-time inspection for aeroplanes that have been 
inspected too early.
    Prompted by operator comments, this [EASA] AD is revised to 
clarify the required actions and the specific configurations to 
which the actions must be applied. Appendix 1 of this [EASA] AD has 
been amended accordingly.
    This [EASA] AD is republished to editorially correct paragraph 
(4).

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2013-
0828.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the second 
SNPRM and the FAA's response.

Request To Revise the Applicability of the Second SNPRM

    American Airlines (AAL) requested that we revise the applicability 
of the proposed AD (in the second SNPRM) to exclude airplanes with MLG 
bogie beams that have had Airbus modification 58896 embodied in-
service, as specified in Airbus Service Bulletin A330-32-3237. AAL 
pointed out that paragraph (c) of the proposed AD (in the second SNPRM) 
does not reflect MLG bogie beams that were modified in-service.
    We disagree with the request to revise the applicability of the 
proposed AD (in the second SNPRM). Paragraph (k) of this AD 
specifically requires inspection, repair, modification, and re-
identification of the MLG bogie beams. However, paragraph (f) of this 
AD states that actions already done need not be repeated. If an 
operator has already accomplished the actions required by paragraph (k) 
of this AD before the effective date of this AD, then the modified 
airplane is already in compliance with the corresponding requirements 
of this AD. We have not made any changes to this AD in this regard.

Additional Changes Made in This AD

    We have revised paragraph (m)(1) of this AD to remove reference to 
paragraph (g) of this AD; the reporting requirement specified in 
paragraph (m)(1) of this AD is required only for the

[[Page 66520]]

inspection required by paragraph (k) of this AD.
    We have also revised paragraph (m)(2) of this AD to reference the 
correct service information for reporting inspection findings for the 
inspection required by paragraph (h) of this AD.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
second SNPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the second SNPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.
     Airbus Service Bulletin A330-32-3225, Revision 02, 
including Appendix 1, dated October 26, 2012. This service information 
describes procedures for cleaning the internal bore and accomplishing a 
detailed inspection of internal surfaces of the left-hand (LH) and 
right-hand (RH) MLG bogie beams to detect any damage to the protective 
treatments and any corrosion, and measuring the paint thickness on the 
internal bore.
     Airbus Service Bulletin A330-32-3237, Revision 01, 
including Reporting Sheet, dated October 14, 2011. This service 
information describes procedures for a detailed inspection for damage 
and corrosion of the internal bores of the LH and RH MLG bogie beam and 
repair, as well as modification and re-identification.
     Airbus Service Bulletin A340-32-4268, Revision 03, 
including Appendix 1, dated January 14, 2013. This service information 
describes procedures for cleaning the internal bore and accomplishing a 
detailed inspection of internal surfaces of the LH and RH MLG bogie 
beams to detect any damage to the protective treatments and any 
corrosion, and measuring the paint thickness on the internal bore.
     Airbus Service Bulletin A340-32-4279, Revision 01, 
including Reporting Sheet, dated October 14, 2011. This service 
information describes procedures for a detailed inspection for damage 
and corrosion of the internal bores of the LH and RH MLG bogie beam, 
repair, modification, and reidentification.
    Messier-Bugatti-Dowty has issued the following service information.
     Messier-Dowty Service Bulletin A33/34-32-278, Revision 1, 
including Appendixes A and B, dated August 24, 2011. This service 
information describes procedures for inspections for damage and 
corrosion to the protective treatment of the internal bores of the LH 
and RH MLG bogie beam, and repairs.
     Messier-Dowty Service Bulletin A33/34-32-283, Revision 1, 
including Appendix A, dated July 10, 2012. This service information 
describes procedures for modification of the LH and RH MLG bogie beams.
     Messier-Dowty Service Bulletin A33/34-32-284, Revision 1, 
including Appendix A, dated July 10, 2012. This service information 
describes procedures for modification of the LH and RH MLG bogie beams.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 51 airplanes of U.S. registry.
    We also estimate that it takes about 34 work-hours per product to 
comply with this AD, and 1 work-hour per product for reporting. The 
average labor rate is $85 per work-hour. Based on these figures, we 
estimate the cost of this AD on U.S. operators to be $151,725, or 
$2,975 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 10 work-hours at a labor rate of $85 per work-hour, for a 
cost of $850 per product. We have no way of determining the number of 
aircraft that might need these actions.

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 AD is 2120-
0056. The paperwork cost associated with this 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 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 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.

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:

[[Page 66521]]

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:

2016-18-07 Airbus: Amendment 39-18637; Docket No. FAA-2013-0828; 
Directorate Identifier 2012-NM-036-AD.

(a) Effective Date

    This AD is effective November 2, 2016.

(b) Affected ADs

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

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category, all 
manufacturer serial numbers (MSN), except those on which Airbus 
modification 58896 has been embodied in production.
    (1) Airbus Model A330-223F, -243F, -201, -202, -203, -223, -243, 
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
    (2) Airbus Model A340-211, -212, -213, -311, -312, and -313 
airplanes.

(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, as well 
as reports that some airplanes have been inspected too early and not 
re-inspected as needed. 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 
MLG collapse, and could result in damage to the airplane and injury 
to the occupants.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Repetitive Inspections for Certain Airplane Configurations

    For airplanes equipped with basic MLG (201252 series), or growth 
MLG (201490 series): After 54 months at the earliest, but no later 
than 72 months since the left-hand (LH) or right-hand (RH) MLG bogie 
beam's first flight on an airplane, or since its first flight on an 
airplane after overhaul, as applicable, clean the internal bore and 
accomplish a detailed inspection of internal surfaces of the LH and 
RH MLG bogie beams to detect any damage to the protective treatments 
and any corrosion, and measure the paint thickness on the internal 
bore, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A330-32-3225, Revision 02, including Appendix 1, 
dated October 26, 2012; or Airbus Service Bulletin A340-32-4268, 
Revision 03, including Appendix 1, dated January 14, 2013; as 
applicable. Repeat the inspections thereafter at intervals not less 
than 54 months, but not exceeding 72 months, after the most recent 
inspection. During overhaul of a MLG bogie beam, any corrosion will 
be removed, which means that the first inspection after overhaul of 
that MLG bogie beam, as required by this paragraph, is between 54 
months and 72 months since its first flight on an airplane after 
overhaul.

(h) One-Time Detailed Inspection for Certain Airplane Configurations

    For airplanes equipped with basic MLG (201252 series), or growth 
MLG (201490 series) having a LH or RH MLG bogie beam that has 
already exceeded 72 months since its first flight on an airplane, or 
since its first flight on an airplane after overhaul, as applicable, 
as of the effective date of this AD; and that has been inspected as 
specified in Airbus Service Bulletin A330-32-3225 or Airbus Service 
Bulletin A340-32-4268, as applicable, earlier than 54 months since 
first flight of the affected MLG bogie beam on an airplane, or since 
its first flight on an airplane after its most recent overhaul, as 
applicable: Within the applicable compliance time indicated in 
paragraphs (h)(1) through (h)(4) of this AD, clean the internal bore 
and accomplish a detailed inspection of the internal surfaces of the 
LH and RH MLG bogie beams to detect any damage to the protective 
treatments and any corrosion, and measure the paint thickness on the 
internal bore, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A330-32-3225, Revision 02, including 
Appendix 1, dated October 26, 2012; or Airbus Service Bulletin A340-
32-4268, Revision 03, including Appendix 1, dated January 14, 2013; 
as applicable.
    (1) For MLG bogie beams having the configurations specified in 
both paragraphs (h)(1)(i) and (h)(1)(ii) of this AD: Do the detailed 
inspection specified in the introductory text of paragraph (h) of 
this AD within 9 months after the effective date of this AD.
    (i) MLG bogie beams having between 72 and 120 months since first 
flight on an airplane, or since the MLG bogie beam's first flight on 
an airplane after the MLG bogie beam's most recent overhaul, as 
applicable.
    (ii) MLG bogie beams on which the first inspection was done 
after 51 months and before 54 months since first flight of the MLG 
bogie beam on an airplane, or since the MLG bogie beam's first 
flight on an airplane after the MLG bogie beam's most recent 
overhaul, as applicable.
    (2) For MLG bogie beams having the configurations specified in 
both paragraphs (h)(2)(i) and (h)(2)(ii) of this AD: Do the detailed 
inspection specified in the introductory text of paragraph (h) of 
this AD within 3 months after the effective date of this AD.
    (i) MLG bogie beams having between 72 and 120 months since first 
flight on an airplane, or since the MLG bogie beam's first flight on 
an airplane after the MLG bogie beam's most recent overhaul, as 
applicable.
    (ii) MLG bogie beams on which the first inspection was done 
after 45 months and before 51 months since first flight of the MLG 
bogie beam on an airplane, or since the MLG bogie beam's first 
flight on an airplane after the MLG bogie beam's most recent 
overhaul, as applicable.
    (3) For MLG bogie beams having the configurations specified in 
both paragraphs (h)(3)(i) and (h)(3)(ii) of this AD: Do the detailed 
inspection specified in the introductory text of paragraph (h) of 
this AD within 3 months after the effective date of this AD.
    (i) MLG bogie beams having between 72 and 96 months since first 
flight on an airplane, or since the MLG bogie beam's first flight on 
an airplane after the MLG bogie beam's most recent overhaul, as 
applicable.
    (ii) MLG bogie beams which have accumulated, at the effective 
date of this AD, less than 96 months and on which the first 
inspection was done before 51 months since first flight of the MLG 
bogie beam on an airplane, or since the MLG bogie beam's first 
flight on an airplane after the after the MLG bogie beam's most 
recent overhaul, as applicable.
    (4) For MLG bogie beams having the configurations specified in 
both paragraphs (h)(4)(i) and (h)(4)(ii) of this AD: Do the detailed 
inspection specified in the introductory text of paragraph (h) of 
this AD within 1 month after the effective date of this AD.
    (i) MLG bogie beams having between 96 and 120 months since first 
flight on an airplane, or since the MLG bogie beam's first flight on 
an airplane after the MLG bogie beam's most recent overhaul, as 
applicable.
    (ii) MLG bogie beams which has accumulated, at the effective 
date of this AD, 96 months or more and on which the first inspection 
was done before 45 months since first flight of the MLG bogie beam 
on an airplane, or since the MLG bogie beam's first flight on an 
airplane after the MLG bogie beam's most recent overhaul, as 
applicable.

(i) Application of Protective Treatment

    If, during any inspection required by paragraph (g) or (h) of 
this AD, no damage or corrosion is found: Before further flight, 
apply the protective treatments to the MLG bogie beam, in accordance 
with the Accomplishment Instructions of Messier-Dowty Service 
Bulletin A33/34-32-272, Revision 1, including Appendixes A, B, C, 
and D, dated September 22, 2008.

(j) Repair and Application of Protective Treatment

    If, during any inspection required by paragraph (g) or (h) of 
this AD, any damage or corrosion is found: Before further flight, 
repair and apply the protective treatments to the MLG bogie beam, in 
accordance with the Accomplishment Instructions of Messier-Dowty 
Service Bulletin A33/34-32-272, Revision 1, including Appendixes A, 
B, C, and D, dated September 22, 2008.

[[Page 66522]]

(k) Inspection and Corrective Actions

    For airplanes equipped with basic MLG (201252 series), growth 
MLG (201490 series), or enhanced MLG (10-210 series): Before the 
accumulation of 252 total months on an MLG bogie beam, or within 90 
days after the effective date of this AD, whichever occurs later, do 
the actions specified in paragraphs (k)(1) and (k)(2) of this AD 
concurrently and in sequence.
    (1) Except as provided by paragraph (k)(3) of this AD: Do a 
detailed inspection for damage and corrosion of the internal bores 
of the LH and RH MLG bogie beam, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-32-3237 
or A340-32-4279, both Revision 01, both including Reporting Sheet, 
both dated October 14, 2011, as applicable. If any damage or 
corrosion is found, before further flight, repair in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A330-32-
3237 or A340-32-4279, both Revision 01, both including Reporting 
Sheet, both dated October 14, 2011, as applicable.
    (2) Except as provided by paragraph (k)(3) of this AD: Modify 
and re-identify, as applicable, the LH and RH MLG bogie beams, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-32-3237 or A340-32-4279, both Revision 01, both 
including Reporting Sheet, both dated October 14, 2011, as 
applicable.
    (3) The inspection requirements of paragraph (k)(1) of this AD, 
and the modification requirements only of paragraph (k)(2) of this 
AD, do not apply to any MLG bogie beam with a serial number listed 
in Appendix A of Messier-Dowty Service Bulletin A33/34-32-283 or 
A33/34-32-284, both Revision 1, both dated July 10, 2012, as 
applicable.

(l) Optional Methods of Compliance for Certain Airplane Configurations

    Inspections and corrective actions on both MLG bogie beams done 
in accordance with the instructions of Messier-Dowty Service 
Bulletin A33/34-32-271, Revision 1, including Appendixes A and B, 
dated November 16, 2007; or Messier-Dowty Service Bulletin A33/34-
32-272, Revision 1, including Appendixes A, B, C, and D, dated 
September 22, 2008; as applicable; are acceptable methods of 
compliance for the requirements of paragraph (g) of this AD, 
provided each inspection is accomplished between 54 months and 72 
months since the first flight of the affected MLG bogie beam on an 
airplane, or since the MLG bogie beam's first flight after the MLG 
bogie beam's most recent overhaul, as applicable.

(m) Reporting Requirement

    (1) Submit a report of the findings (both positive and negative) 
of each inspection required by paragraph (k) of this AD, as 
applicable, 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, Revision 
01, including Reporting Sheet, dated October 14, 2011; or Airbus 
Service Bulletin A340-32-4279, Revision 01, including Reporting 
Sheet, dated October 14, 2011; at the applicable time specified in 
paragraph (m)(1)(i) or (m)(1)(ii) of this AD.
    (i) If the inspection was done on or after the effective date of 
this AD: Submit the report within 90 days after the inspection.
    (ii) 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.
    (2) Submit a report of the findings (both positive and negative) 
of the inspection required by paragraph (h) 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 A330-32-3225, Revision 02, including 
Appendix 1, dated October 26, 2012; or Airbus Service Bulletin A340-
32-4268, Revision 03, including Appendix 1, dated January 14, 2013; 
at the applicable time specified in paragraph (m)(2)(i) or 
(m)(2)(ii) of this AD.
    (i) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (ii) 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.

(n) Optional Method of Compliance for Certain Requirements

    (1) Inspections for damage and corrosion to the protective 
treatment of the internal bores of the LH and RH MLG bogie beam, and 
repairs, done in accordance with Messier-Dowty Service Bulletin A33/
34-32-278, Revision 1, including Appendixes A and B, dated August 
24, 2011, are acceptable methods of compliance with the 
corresponding requirements of paragraph (k)(1) of this AD.
    (2) Modification of the LH and RH MLG bogie beams, done in 
accordance with Messier-Dowty Service Bulletins A33/34-32-283 or 
A33/34-32-284, both Revision 1, both including Appendix A, both 
dated July 10, 2012, as applicable, is an acceptable method of 
compliance with the corresponding requirements of paragraph (k)(2) 
of this AD.

(o) Optional Terminating Action for Certain Requirements

    Modification of both LH and RH MLG bogie beams on an airplane, 
done in accordance with paragraph (k) of this AD, or as specified in 
paragraphs (n)(1) and (n)(2) of this AD, terminates the repetitive 
inspections required by paragraph (g) of this AD for this airplane.

(p) Credit for Previous Actions

    (1) This paragraph provides credit for the corresponding 
inspections and corrective actions done on an LH or RH MLG bogie 
beam required by paragraph (g) of this AD, if those actions were 
performed before the effective date of this AD using Airbus Service 
Bulletin A330-32-3225, dated November 21, 2007; or Revision 1, dated 
October 30, 2008; provided the inspections and corrective actions 
were accomplished between 54 months and 72 months since first flight 
of the affected MLG bogie beam on an airplane, or since its first 
flight after the MLG bogie beam's most recent overhaul, as 
applicable. Airbus Service Bulletin A330-32-3225, dated November 21, 
2007, is not incorporated by reference in this AD. Airbus Mandatory 
Service Bulletin A330-32-3225, Revision 01, including Appendix 1, 
dated October 30, 2008, was incorporated by reference in AD 2009-15-
07.
    (2) This paragraph provides credit for the corresponding 
inspections and corrective actions done on an LH or RH MLG bogie 
beam required by paragraph (g) of this AD, if those actions were 
performed before the effective date of this AD using Airbus 
Mandatory Service Bulletin A340-32-4268, dated November 21, 2007; 
Revision 01, including Appendix 1, dated October 30, 2008; or 
Revision 02, dated October 26, 2012; provided these inspections and 
corrective actions were accomplished between 54 months and 72 months 
since first flight of the affected MLG bogie beam on an airplane, or 
since its first flight after the MLG bogie beam's most recent 
overhaul, as applicable. Airbus Service Bulletin A340-32-4268, dated 
November 21, 2007; and Revision 02, dated October 26, 2012; are not 
incorporated by reference in this AD. Airbus Mandatory Service 
Bulletin A340-32-4268, Revision 01, including Appendix 1, dated 
October 30, 2008, was incorporated by reference in AD 2009-15-17.
    (3) This paragraph provides credit for the corresponding actions 
required by paragraph (n)(1) of this AD, if those actions were 
performed before the effective date of this AD using Messier-Dowty 
Service Bulletin A33/34-32-271, dated September 13, 2007, which is 
not incorporated by reference in this AD.
    (4) This paragraph provides credit for the corresponding actions 
required by paragraphs (j) and (n)(1) of this AD, if those actions 
were performed before the effective date of this AD using Messier-
Dowty Service Bulletin A33/34-32-272, including Appendixes A, B, C, 
and D, dated November 16, 2007, which is not incorporated by 
reference in this AD.
    (5) This paragraph provides credit for the corresponding actions 
required by paragraphs (k), (m), and (r)(1)(i) of this AD, if those 
actions were performed before the effective date of this AD using 
Airbus Service Bulletin A330-32-3237, including Reporting Sheet, 
dated January 18, 2011.
    (6) This paragraph provides credit for the corresponding actions 
required by paragraphs (k), (m), and (r)(1)(i) of this AD, if those 
actions were performed before the effective date of this AD using 
Airbus Service Bulletin A340-32-4279, including Reporting Sheet, 
dated January 18, 2011.
    (7) This paragraph provides credit for the corresponding actions 
required by paragraphs (k)(3), (n)(2), (r)(1)(ii), and (r)(1)(iii) 
of this AD, if those actions were performed before the effective 
date of this AD using Messier-Dowty Service Bulletin A33/34-32-283, 
including Appendix A, dated May 11, 2010, which is not incorporated 
by reference in this AD.
    (8) This paragraph provides credit for the corresponding actions 
required by paragraphs (k)(3), (n)(2), (r)(1)(ii), and (r)(1)(iii) 
of this AD, if those actions were performed before the effective 
date of this AD

[[Page 66523]]

using Messier-Dowty Service Bulletin A33/34-32-284, including 
Appendix A, dated May 11, 2010, which is not incorporated by 
reference in this AD.
    (9) This paragraph provides credit for the corresponding actions 
required by paragraphs (n)(1) and (r)(1)(ii) of this AD, if those 
actions were performed before the effective date of this AD using 
Messier-Dowty Service Bulletin A33/34-32-278, including Appendixes A 
and B, dated February 17, 2010, which is not incorporated by 
reference in this AD.

(q) Clarification of Inspection Compliance Times

    After accomplishment of the one-time detailed inspection 
required by paragraph (h) of this AD, the repetitive actions 
required by paragraph (g) of this AD remain applicable, and must be 
done within the compliance times specified in paragraph (g) of this 
AD.

(r) Parts Installation Limitations

    (1) After modification of an airplane, as required by paragraph 
(k) of this AD, or as specified in paragraphs (n)(1) and (n)(2) of 
this AD, do not install an MLG bogie beam on any airplane unless it 
is done in compliance with the requirements of paragraph (r)(1)(i), 
(r)(1)(ii), or (r)(1)(iii) of this AD.
    (i) The MLG bogie beam has been modified and re-identified in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-32-3237 or A340-32-4279, both Revision 01, both 
including Reporting Sheet, both dated October 14, 2011, as 
applicable.
    (ii) The MLG bogie beam has been inspected and all applicable 
corrective actions have been done in accordance with the 
Accomplishment Instructions of Messier-Dowty Service Bulletin A33/
34-32-278, Revision 1, dated August 24, 2011; and modified in 
accordance with the Accomplishment Instructions of Messier-Dowty 
Service Bulletin A33/34-32-283 or A33/34-32-284, both Revision 1, 
both including Appendix A, both dated July 10, 2012.
    (iii) The MLG bogie beam has a serial number listed in Appendix 
A of Messier-Dowty Service Bulletin A33/34-32-283 or A33/34-32-284, 
both Revision 1, both dated July 10, 2012, as applicable.
    (2) As of the effective date of this AD, except as specified in 
paragraph (r)(1) of this AD, installation of an MLG bogie beam on an 
airplane is allowed, provided that following the installation it is 
inspected and all applicable repairs and corrective actions have 
been done in accordance with the requirements of this AD.

(s) 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: 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) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the European Aviation Safety Agency 
(EASA); or Airbus's EASA Design Organization Approval (DOA). If 
approved by the DOA, the approval must include the DOA-authorized 
signature.
    (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.

(t) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) AD 2013-0267R1, dated March 4, 2014; corrected March 8, 2014, 
for related information. This MCAI may be found in the AD docket on 
the Internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2013-0828.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (u)(5), (u)(6), and (u)(7) of this AD.

(u) 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 this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
November 2, 2016.
    (i) Airbus Service Bulletin A330-32-3225, Revision 02, including 
Appendix 1, dated October 26, 2012.
    (ii) Airbus Service Bulletin A330-32-3237, Revision 01, 
including Reporting Sheet, dated October 14, 2011.
    (iii) Airbus Service Bulletin A340-32-4268, Revision 03, 
including Appendix 1, dated January 14, 2013.
    (iv) Airbus Service Bulletin A340-32-4279, Revision 01, 
including Reporting Sheet, dated October 14, 2011.
    (v) Messier-Dowty Service Bulletin A33/34-32-278, Revision 1, 
including Appendixes A and B, dated August 24, 2011.
    (vi) Messier-Dowty Service Bulletin A33/34-32-283, Revision 1, 
including Appendix A, dated July 10, 2012.
    (vii) Messier-Dowty Service Bulletin A33/34-32-284, Revision 1, 
including Appendix A, dated July 10, 2012.
    (4) The following service information was approved for IBR on 
September 2, 2009 (74 FR 37523, July 29, 2009).
    (i) Messier-Dowty Service Bulletin A33/34-32-271, Revision 1, 
including Appendixes A and B, dated November 16, 2007.
    (ii) Messier-Dowty Service Bulletin A33/34-32-272, Revision 1, 
including Appendixes A, B, C, and D, dated September 22, 2008.
    (5) For Airbus service information identified in this 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.
    (6) 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.
    (7) You may view this 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.
    (8) 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 August 24, 2016.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-21150 Filed 9-27-16; 8:45 am]
 BILLING CODE 4910-13-P