Airworthiness Directives; Airbus Airplanes, 24035-24039 [2017-10266]

Download as PDF Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations that is likely to exist or develop on products identified in this rulemaking action. (d) Subject Joint Aircraft System Component (JASC) 7230, Turbine Engine Compressor Section. Regulatory Findings (e) Reason This AD was prompted by CICs that were weld repaired and have a higher probability of cracking due to increased residual stresses as a result of the weld repair process. We are issuing this AD to prevent CIC failure, engine separation and loss of the airplane. We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction, 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: 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2017–10–06 Rolls-Royce plc: Amendment 39–18880; Docket No. FAA–2017–0114; Directorate Identifier 2017–NE–03–AD. (a) Effective Date This AD is effective June 9, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Rolls-Royce plc (RR) RB211 Trent 768–60, RB211 Trent 772–60, and RB211 Trent 772B–60 turbofan engines that have a compressor intermediate case (CIC) that was repaired using RR Repair FRSC005. VerDate Sep<11>2014 15:57 May 24, 2017 Jkt 241001 (g) Required Actions (1) Inspect repaired CICs during the next shop visit, or within 6,000 engine flight cycles, whichever occurs first, after the effective date of this AD, using paragraph 3.B.(1)(c) of the Accomplishment Instructions, of RR Alert Non-Modification Service Bulletin (NMSB) RB.211–72–AH976, Revision 2, dated March 16, 2017. (2) If a CIC fails inspection required by paragraph (g)(1) of this AD, either repair the CIC using paragraph 3.B.(2)(b) of the Accomplishment Instructions, of RR Alert NMSB RB.211–72–AH976, Revision 2, dated March 16, 2017, or, replace the CIC with a part eligible for installation, before next flight. (h) Definitions For the purpose of this AD, a shop visit is the induction of an engine into the shop for maintenance or overhaul that requires the separation of major mating engine module flanges. The separation of engine flanges solely for the purpose of transporting the engine without subsequent engine maintenance does not constitute an engine shop visit. (i) Installation Prohibition After the effective date of this AD, do not install an affected intermediate module on an engine unless the CIC has passed the inspection required by paragraph (g)(1) of this AD. PART 39—AIRWORTHINESS DIRECTIVES § 39.13 (f) Compliance Comply with this AD within the compliance times specified, unless already done. (j) Credit for Previous Actions You may take credit for the inspections and corrective action required by paragraph (g) of this AD, if you performed these actions before the effective date of this AD using RR Alert NMSB RB.211–72–AH976, original issue, dated November 3, 2016 or RR Alert NMSB RB.211–72–AH976, Revision 1, dated November 17, 2016. (k) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email your request to: ANE-AD-AMOC@faa.gov. (l) Related Information (1) For more information about this AD, contact Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781–238– PO 00000 Frm 00037 Fmt 4700 Sfmt 4700 24035 7754; fax: 781–238–7199; email: Robert.Green@faa.gov. (2) Refer to MCAI European Aviation Safety Agency (EASA), AD 2017–0071, dated April 26, 2017, for more information. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA–2017–0114. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Rolls-Royce plc Alert Non-Modification Service Bulletin RB.211–72–AH976, Revision 2, dated March 16, 2017. (ii) Reserved. (3) For Rolls-Royce plc service information identified in this AD, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE24 8BJ; phone: 011–44– 1332–242424; fax: 011–44–1332–249936; email: http://www.rolls-royce.com/contact/ civil_team.jsp; Internet: https:// customers.rolls-royce.com/public/ rollsroycecare. (4) You may view this service information at FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238–7125. (5) You may view this service information at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on May 4, 2017. Robert J. Ganley, Acting Assistant Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2017–10438 Filed 5–24–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–8428; Directorate Identifier 2014–NM–032–AD; Amendment 39–18898; AD 2017–10–24] 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) 2011–17– SUMMARY: E:\FR\FM\25MYR1.SGM 25MYR1 24036 Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations 09 for all Airbus Model A330–200, –200 Freighter, and –300 series airplanes; and AD 2012–25–12 for all Airbus Model A330–200 and –300 series airplanes. AD 2011–17–09 required revisions to certain operator maintenance documents to include new inspections. AD 2012–25–12 required replacing certain main landing gear (MLG) bogie beams before reaching new reduced life limits. This new AD requires revising the maintenance or inspection program, as applicable, to incorporate new, more restrictive, or revised instructions and/ or airworthiness limitation requirements. This AD was prompted by revisions to certain airworthiness limitation item (ALI) documents, which specify more restrictive instructions and/or airworthiness limitations. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective June 29, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 29, 2017. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of January 30, 2013 (77 FR 75825, December 26, 2012). The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of September 30, 2011 (76 FR 53305, August 26, 2011). 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.A330A340@airbus.com; Internet http:// www.airbus.com. For Messier-Bugatti-Dowty service information identified in this final rule, contact Messier-Bugatti USA, One Carbon Way, Walton, KY 41094; telephone 859–525–8583; fax 859–485 8827; email americascsc@ safranmbd.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–2015– 8428. Examining the AD Docket You may examine the AD docket on the Internet at http:// VerDate Sep<11>2014 15:57 May 24, 2017 Jkt 241001 www.regulations.gov by searching for and locating Docket No. FAA–2015– 8428; 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 800–647–5527) 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 supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 to supersede AD 2011–17–09, Amendment 39–16773 (76 FR 53305, August 26, 2011) (‘‘AD 2011– 17–09’’); and AD 2012–25–12, Amendment 39–17293 (77 FR 75825, December 26, 2012) (‘‘AD 2012–25– 12’’). AD 2011–17–09 applied to all Airbus Model A330–200, –200 Freighter, and –300 series airplanes. AD 2012–25–12 applied to all Airbus Model A330–200 and –300 series airplanes. The SNPRM published in the Federal Register on December 16, 2016 (81 FR 91062). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on January 13, 2016 (81 FR 1570). The NPRM was prompted by a determination that more restrictive instructions and/or airworthiness limitations should be incorporated into the maintenance or inspection program, as applicable. The NPRM proposed to require revising the maintenance or inspection program, as applicable, to incorporate new or revised airworthiness limitation requirements. The SNPRM proposed to require revising the maintenance or inspection program, as applicable, to incorporate more restrictive instructions and/or airworthiness limitations that the manufacturer has recently issued. We are issuing this AD to detect and correct fatigue cracking, accidental damage, or corrosion in principal structural elements, and possible failure of certain life limited parts, which could result in reduced structural integrity of the airplane. PO 00000 Frm 00038 Fmt 4700 Sfmt 4700 The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive, 2014–0009, dated January 8, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A330–200, –200 Freighter, and –300 series airplanes; and Model A340– 200, –300, –500, and –600 series airplanes. The MCAI states: The airworthiness limitations for Airbus aeroplanes are currently published in Airworthiness Limitations Section (ALS) documents. The instructions and airworthiness limitations applicable to the Safe Life Airworthiness Limitation Items (SL ALI) are given in Airbus A330 ALS Part 1 and A340 ALS Part 1, which are approved by EASA. The revision 07 of Airbus A330 and A340 ALS Part 1 introduces more restrictive instructions and/or airworthiness limitations. Failure to comply with this revision could result in an unsafe condition. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2012–0179, which is superseded, and requires accomplishment of the actions specified in Airbus A330 or A340 ALS Part 1 revision 07. In addition, this [EASA] AD also supersedes EASA AD 2011–0122–E and EASA AD 2011–0212, whose requirements have been transferred into Airbus A330 and A340 ALS Part 1 revision 07. The unsafe condition is fatigue cracking, accidental damage, or corrosion in certain principal structural elements, and possible failure of certain life limited parts, which could result in reduced structural integrity of the airplane. 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–2015– 8428. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the SNPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the SNPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the SNPRM. E:\FR\FM\25MYR1.SGM 25MYR1 Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations Related Service Information Under 1 CFR Part 51 Airbus has issued Airbus A330 ALS Part 1, SL–ALI, Revision 08, dated April 11, 2016. Messier-Bugatti-Dowty has issued Service Letter A33–34 A20, Revision 7, including Appendixes A through F, dated July 20, 2012. This service information describes SL–ALI for the landing gear. This service information is distinct since it was issued by two different manufacturers for different purposes. 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 82 airplanes of U.S. registry. The actions that are required by AD 2011–17–09, and retained in this AD, take about 1 work-hour per product, at an average labor rate of $85 per workhour. Based on these figures, the estimated cost of the actions that are required by AD 2011–17–09 is $85 per product. The actions that are required by AD 2012–25–12, and retained in this AD, take about 16 work-hours, at an average labor rate of $85 per work-hour, with required parts cost of about $255,000 per MLG bogie beam. Based on these figures, the estimated cost of the actions that are required by AD 2012–25–12 is up to $256,360 per MLG bogie beam. We also estimate that it would take about 1 work-hour per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $6,970, or $85 per product. 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: 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. Authority for This Rulemaking § 39.13 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 ■ VerDate Sep<11>2014 15:57 May 24, 2017 Jkt 241001 [Amended] 2.The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2011–17–09, Amendment 39–16773 (76 FR 53305, August 26, 2011); and AD 2012–25–12, Amendment 39–17293 (77 FR 75825, December 26, 2012); and adding the following new AD: 2017–10–24 Airbus: Amendment 39–18898; Docket No. FAA–2015–8428; Directorate Identifier 2014–NM–032–AD. (a) Effective Date This AD is effective June 29, 2017. (b) Affected ADs This AD replaces AD 2011–17–09, Amendment 39–16773 (76 FR 53305, August 26, 2011) (‘‘AD 2011–17–09’’); and AD 2012– 25–12, Amendment 39–17293 (77 FR 75825, December 26, 2012) (‘‘AD 2012–25–12’’). PO 00000 Frm 00039 Fmt 4700 Sfmt 4700 24037 (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, with an original certificate of airworthiness or original export certificate of airworthiness issued on or before April 11, 2016. (1) Airbus Model A330–201, –202, –203, –223, and –243 airplanes. (2) Airbus Model A330–223F and –243F airplanes. (3) Airbus Model A330–301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes. (d) Subject Air Transport Association (ATA) of America Code 05, Periodic inspections. (e) Reason This AD was prompted by revisions to certain airworthiness limitation item documents, which specify more restrictive instructions and/or airworthiness limitations. We are issuing this AD to detect and correct fatigue cracking, accidental damage, or corrosion in principal structural elements, and possible failure of certain life limited parts, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Maintenance Program Revision, With New Terminating Action This paragraph restates the requirements of paragraph (h) of AD 2011–17–09, with new terminating action. Within 3 months after September 30, 2011 (the effective date of AD 2011–17–09): Revise the maintenance program by incorporating Airbus A330 Airworthiness Limitations Section (ALS) Part 1, Safe Life Airworthiness Limitation Items (SL–ALI), Revision 05, dated July 29, 2010. Comply with all ALIs in Airbus A330 ALS Part 1, SL–ALI, Revision 05, dated July 29, 2010, at the times specified therein. Accomplishing the actions specified in paragraph (k) of this AD terminates the requirements of this paragraph. (h) Retained Limitation of No Alternative Intervals or Limits, With Additional Exception This paragraph restates the requirements of paragraph (i) of AD 2011–17–09, with additional exception. Except as provided by paragraphs (k) and (m)(1) of this AD, after accomplishment of the actions specified in paragraph (g) of this AD, no alternatives to the maintenance tasks, intervals, or limitations specified in paragraph (g) of this AD may be used. (i) Retained Bogie Beam Replacement, With Specific Delegation Approval Language, New Terminating Action, and New Service Information This paragraph restates the requirements of paragraph (g) of AD 2012–25–12, with specific delegation approval language and terminating action and new service information. For airplanes identified in paragraphs (c)(1) and (c)(3) of this AD: At the E:\FR\FM\25MYR1.SGM 25MYR1 24038 Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations later of the times specified in paragraphs (i)(1) and (i)(2) of this AD, replace all main landing gear (MLG) bogie beams having part number (P/N) 201485300, 201485301, 201272302, 201272304, 201272306, or 201272307, except those that have serial number (S/N) S2A, S2B, or S2C, as identified in Messier-Dowty Service Letter A33–34 A20, Revision 5, including Appendixes A through F, dated July 31, 2009; or Messier-BugattiDowty Service Letter A33–34 A20, Revision 7, including Appendixes A through F, dated July 20, 2012; with a new or serviceable part, 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). As of the effective date of this AD, the applicable MLG bogie beams specified in this paragraph must be replaced using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. Accomplishing the actions specified in paragraph (k) of this AD terminates the requirements of this paragraph. (1) At the applicable time specified in paragraphs (i)(1)(i), (i)(1)(ii), and (i)(1)(iii) of this AD. (i) For Model A330–201, –202, –203, –223, –243 series airplanes, weight variant (WV)02x, WV05x (except WV058), and WV06x series: Before the accumulation of a life limit of 50,000 landings or 72,300 total flight hours, whichever occurs first from the first installation of a MLG bogie beam on the airplane. (ii) For Model A330–201, –202, –203, –223, –243 WV058 series airplanes: Before the accumulation of a life limit of 50,000 landings or 57,900 total flight hours, whichever occurs first from the first installation of a MLG bogie beam on the airplane. (iii) For Model A330–301, –302, –303, –321, –322, –323, –341, –342, –343 series airplanes, WV00x, WV01x, WV02x, and WV05x series: Before the accumulation of a life limit of 46,000 landings or 75,000 total flight hours, whichever occurs first from the first installation of a MLG bogie beam on the airplane. (2) Within 6 months after January 30, 2013 (the effective date of AD 2012–25–12). (j) Retained Parts Installation Limitation, With New Terminating Action This paragraph restates the requirements of paragraph (h) of AD 2012–25–12, with new terminating action. For airplanes identified in paragraphs (c)(1) and (c)(3) of this AD, as of January 30, 2013 (the effective date of AD 2012–25–12), a MLG bogie beam having any part number identified in paragraph (i) of this AD may be installed on an airplane, provided its life has not exceeded the life limit specified in paragraphs (i)(1)(i), (i)(1)(ii), and (i)(1)(iii) of this AD, and it is replaced with a new or serviceable part before reaching the life limit specified in paragraphs (i)(1)(i), (i)(1)(ii), and (i)(1)(iii) of this AD. Accomplishing the actions specified in paragraph (k) of this AD terminates the requirements of this paragraph. VerDate Sep<11>2014 15:57 May 24, 2017 Jkt 241001 (k) New Maintenance or Inspection Program Revision Within 3 months after the effective date of this AD: Revise the maintenance or inspection program, as applicable, by incorporating the information in Airbus A330 ALS Part 1, SL–ALI, Revision 08, dated April 11, 2016. The initial compliance times for the actions specified in Airbus A330 ALS Part 1, SL–ALI, Revision 08, dated April 11, 2016, are at the times specified in Airbus A330 ALS Part 1, SL–ALI, Revision 08, dated April 11, 2016, or within 3 months after the effective date of this AD, whichever occurs later. Accomplishing the actions specified in this paragraph terminates the requirements specified in paragraphs (g) through (j) of this AD. (l) New Limitation of No Alternative Actions or Intervals After the maintenance or inspection program, as applicable, has been revised, as required by paragraph (k) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (m)(1) of this AD. (m) 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 manager of the International Branch, send it to the attention of the person identified in paragraph (n)(2) of this AD. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (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 EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0009, dated January 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– 2015–8428. (2) For more information about this AD, contact Vladimir Ulyanov, Aerospace PO 00000 Frm 00040 Fmt 4700 Sfmt 4700 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. (o) 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 June 29, 2017. (i) Airbus A330 Airworthiness Limitations Section Part 1, Safe Life Airworthiness Limitation Items, Revision 08, dated April 11, 2016. (ii) Messier-Bugatti-Dowty Service Letter A33–34 A20, Revision 7, including Appendixes A through F, dated July 20, 2012. (4) The following service information was approved for IBR on January 30, 2013 (77 FR 75825, December 26, 2012). (i) Messier-Dowty Service Letter A33–34 A20, Revision 5, including Appendixes A through F, dated July 31, 2009. (ii) Reserved. (5) The following service information was approved for IBR on September 30, 2011 (76 FR 53305, August 26, 2011). (i) Airbus A330 Airworthiness Limitations Section, Part 1, Safe Life Airworthiness Limitation Items, Revision 05, dated July 29, 2010. The revision level of this document is indicated only on the title page and in the Record of Revisions; the revision date of this document is not indicated on the title page of this document. (ii) Reserved. (6) 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.A330A340@airbus.com; Internet http:// www.airbus.com. (7) For Messier-Bugatti-Dowty service information identified in this AD, contact Messier-Bugatti USA, One Carbon Way, Walton, KY 41094; telephone 859–525–8583; fax 859–485 8827; email americascsc@ safranmbd.com. (8) 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. (9) 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. E:\FR\FM\25MYR1.SGM 25MYR1 Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations Issued in Renton, Washington, on May 10, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–10266 Filed 5–24–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–8849; Directorate Identifier 2015–NM–174–AD; Amendment 39–18892; AD 2017–10–18] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus Model A330–223F, –223, –321, –322, and –323 airplanes. This AD was prompted by fatigue load analysis that determined the need for reduced inspection intervals and updated torque values of the bolts. This AD requires repetitive torque checks of the forward engine mount bolts, an inspection of the forward mount assembly, and replacement of the bolts or repair of the forward mount assembly as necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective June 29, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 29, 2017. ADDRESSES: For 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. 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–2016–8849. SUMMARY: VerDate Sep<11>2014 15:57 May 24, 2017 Jkt 241001 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–2016– 8849; 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 800–647–5527) 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 notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A330–223F, –223, –321, –322, and –323 airplanes. The NPRM published in the Federal Register on August 30, 2016 (81 FR 59535). The NPRM was prompted by fatigue load analysis that determined the need for reduced inspection intervals (for torque checks required by AD 2013–14–04, Amendment 39–17509 (78 FR 68352, November 14, 2013) (‘‘AD 2013–14–04’’)) and updated torque values of the bolts. The NPRM proposed to require repetitive torque checks to determine if there are any loose or broken forward engine mount bolts, and, if necessary, replacement of all four forward engine mount bolts and associated nuts, inspection of the forward mount assembly, and repair. We are issuing this AD to detect and correct loose and broken bolts, which could lead to engine detachment in flight and damage to the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2015–0214, dated October 19, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A330–223F, –223, –321, –322, and –323 airplanes. The MCAI states: The forward mount engine pylon bolts, Part Number (P/N) 51U615, fitted on Airbus PO 00000 Frm 00041 Fmt 4700 Sfmt 4700 24039 A330 aeroplanes with Pratt & Whitney (PW) PW4000 engines, are made from MP159 material. Analysis made by PW identified that MP159 material pylon bolts do not meet the full life cycle torque check interval requirement, in a bolt-out condition. Consequently, PW issued Alert Service Bulletin (ASB) PW4G–100–A71–32, and the U.S. Federal Aviation Administration (FAA), as Engine Certification Authority, issued FAA AD 2006–16–05 [Amendment 39–14705 (71 FR 44185, August 4, 2006) (‘‘AD 2006– 16–05’’)] to require repetitive torque checks of MP159 material forward mount pylon bolts fitted on certain PW4000 series engines. However, the engine mount system is considered to be part of aeroplane certification rather than the engine certification. Following further fatigue load analysis by Airbus of the A330 engine mount system, it was determined that the torque check interval for MP159 material forward mount pylon bolts, as required by FAA AD 2006–16–05 (2,700 flight cycles (FC)), provided an insufficient level of safety for Airbus A330 aeroplanes. This condition, if not detected and corrected, could ultimately lead to detachment of the engine from the aeroplane, possibly resulting in damage to the aeroplane and/or injury to persons on the ground. Consequently, EASA issued AD 2012–0094 [which corresponds to FAA AD 2013–14–04] to require accomplishment of repetitive torque checks of the forward mount pylon bolts installed on affected A330 aeroplanes and, depending on findings, replacement of all four bolts and associated nuts, in accordance with PW ASB PW4G–100–A71– 32 Revision 01 and Airbus Service Bulletin (SB) A330–71–3028. Since that AD was issued, it has been concluded that a new torque value must be applied. Consequently, Airbus issued SB A330–71– 3028 Revision 02 and PW issued ASB PW4G–100–A71–32 Revision 02 to update the torque value. Additional forward mount inspections are also provided in case of one or more forward engine mount bolts is found loose, broken or missing. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2012–0094, which is superseded, introduces a new torque value, and requires additional inspections and, depending on findings, corrective action(s). Corrective actions include repetitive torque checks to determine if there are any loose or broken forward engine mount bolts on both engines, and, if necessary, replacement of all four forward engine mount bolts and associated nuts, inspection of the forward mount assembly, and repair. 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–2016– 8849. Comments We gave the public the opportunity to participate in developing this AD. The E:\FR\FM\25MYR1.SGM 25MYR1

Agencies

[Federal Register Volume 82, Number 100 (Thursday, May 25, 2017)]
[Rules and Regulations]
[Pages 24035-24039]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10266]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-8428; Directorate Identifier 2014-NM-032-AD; 
Amendment 39-18898; AD 2017-10-24]
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) 2011-17-

[[Page 24036]]

09 for all Airbus Model A330-200, -200 Freighter, and -300 series 
airplanes; and AD 2012-25-12 for all Airbus Model A330-200 and -300 
series airplanes. AD 2011-17-09 required revisions to certain operator 
maintenance documents to include new inspections. AD 2012-25-12 
required replacing certain main landing gear (MLG) bogie beams before 
reaching new reduced life limits. This new AD requires revising the 
maintenance or inspection program, as applicable, to incorporate new, 
more restrictive, or revised instructions and/or airworthiness 
limitation requirements. This AD was prompted by revisions to certain 
airworthiness limitation item (ALI) documents, which specify more 
restrictive instructions and/or airworthiness limitations. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective June 29, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 29, 
2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
January 30, 2013 (77 FR 75825, December 26, 2012).
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
September 30, 2011 (76 FR 53305, August 26, 2011).

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-Bugatti-Dowty service information identified in this 
final rule, contact Messier-Bugatti USA, One Carbon Way, Walton, KY 
41094; telephone 859-525-8583; fax 859-485 8827; email 
americascsc@safranmbd.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-2015-
8428.

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-2015-
8428; 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-
647-5527) 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 supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 to supersede AD 2011-17-09, Amendment 39-16773 (76 
FR 53305, August 26, 2011) (``AD 2011-17-09''); and AD 2012-25-12, 
Amendment 39-17293 (77 FR 75825, December 26, 2012) (``AD 2012-25-
12''). AD 2011-17-09 applied to all Airbus Model A330-200, -200 
Freighter, and -300 series airplanes. AD 2012-25-12 applied to all 
Airbus Model A330-200 and -300 series airplanes. The SNPRM published in 
the Federal Register on December 16, 2016 (81 FR 91062). We preceded 
the SNPRM with a notice of proposed rulemaking (NPRM) that published in 
the Federal Register on January 13, 2016 (81 FR 1570). The NPRM was 
prompted by a determination that more restrictive instructions and/or 
airworthiness limitations should be incorporated into the maintenance 
or inspection program, as applicable. The NPRM proposed to require 
revising the maintenance or inspection program, as applicable, to 
incorporate new or revised airworthiness limitation requirements. The 
SNPRM proposed to require revising the maintenance or inspection 
program, as applicable, to incorporate more restrictive instructions 
and/or airworthiness limitations that the manufacturer has recently 
issued. We are issuing this AD to detect and correct fatigue cracking, 
accidental damage, or corrosion in principal structural elements, and 
possible failure of certain life limited parts, which could result in 
reduced structural integrity of the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive, 2014-0009, dated January 8, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A330-200, -200 Freighter, and -300 series airplanes; and Model A340-
200, -300, -500, and -600 series airplanes. The MCAI states:

    The airworthiness limitations for Airbus aeroplanes are 
currently published in Airworthiness Limitations Section (ALS) 
documents.
    The instructions and airworthiness limitations applicable to the 
Safe Life Airworthiness Limitation Items (SL ALI) are given in 
Airbus A330 ALS Part 1 and A340 ALS Part 1, which are approved by 
EASA.
    The revision 07 of Airbus A330 and A340 ALS Part 1 introduces 
more restrictive instructions and/or airworthiness limitations. 
Failure to comply with this revision could result in an unsafe 
condition.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2012-0179, which is superseded, and requires 
accomplishment of the actions specified in Airbus A330 or A340 ALS 
Part 1 revision 07.
    In addition, this [EASA] AD also supersedes EASA AD 2011-0122-E 
and EASA AD 2011-0212, whose requirements have been transferred into 
Airbus A330 and A340 ALS Part 1 revision 07.

    The unsafe condition is fatigue cracking, accidental damage, or 
corrosion in certain principal structural elements, and possible 
failure of certain life limited parts, which could result in reduced 
structural integrity of the airplane. 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-2015-8428.

Comments

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

Conclusion

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

[[Page 24037]]

Related Service Information Under 1 CFR Part 51

    Airbus has issued Airbus A330 ALS Part 1, SL-ALI, Revision 08, 
dated April 11, 2016. Messier-Bugatti-Dowty has issued Service Letter 
A33-34 A20, Revision 7, including Appendixes A through F, dated July 
20, 2012. This service information describes SL-ALI for the landing 
gear. This service information is distinct since it was issued by two 
different manufacturers for different purposes.
    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 82 airplanes of U.S. registry.
    The actions that are required by AD 2011-17-09, and retained in 
this AD, take about 1 work-hour per product, at an average labor rate 
of $85 per work-hour. Based on these figures, the estimated cost of the 
actions that are required by AD 2011-17-09 is $85 per product.
    The actions that are required by AD 2012-25-12, and retained in 
this AD, take about 16 work-hours, at an average labor rate of $85 per 
work-hour, with required parts cost of about $255,000 per MLG bogie 
beam. Based on these figures, the estimated cost of the actions that 
are required by AD 2012-25-12 is up to $256,360 per MLG bogie beam.
    We also estimate that it would take about 1 work-hour per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $6,970, or $85 per product.

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government. For the 
reasons discussed above, I certify 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:

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) 
2011-17-09, Amendment 39-16773 (76 FR 53305, August 26, 2011); and AD 
2012-25-12, Amendment 39-17293 (77 FR 75825, December 26, 2012); and 
adding the following new AD:

2017-10-24 Airbus: Amendment 39-18898; Docket No. FAA-2015-8428; 
Directorate Identifier 2014-NM-032-AD.

(a) Effective Date

    This AD is effective June 29, 2017.

(b) Affected ADs

    This AD replaces AD 2011-17-09, Amendment 39-16773 (76 FR 53305, 
August 26, 2011) (``AD 2011-17-09''); and AD 2012-25-12, Amendment 
39-17293 (77 FR 75825, December 26, 2012) (``AD 2012-25-12'').

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, 
with an original certificate of airworthiness or original export 
certificate of airworthiness issued on or before April 11, 2016.
    (1) Airbus Model A330-201, -202, -203, -223, and -243 airplanes.
    (2) Airbus Model A330-223F and -243F airplanes.
    (3) Airbus Model A330-301, -302, -303, -321, -322, -323, -341, -
342, and -343 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 05, Periodic 
inspections.

(e) Reason

    This AD was prompted by revisions to certain airworthiness 
limitation item documents, which specify more restrictive 
instructions and/or airworthiness limitations. We are issuing this 
AD to detect and correct fatigue cracking, accidental damage, or 
corrosion in principal structural elements, and possible failure of 
certain life limited parts, which could result in reduced structural 
integrity of the airplane.

(f) Compliance

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

(g) Retained Maintenance Program Revision, With New Terminating Action

    This paragraph restates the requirements of paragraph (h) of AD 
2011-17-09, with new terminating action. Within 3 months after 
September 30, 2011 (the effective date of AD 2011-17-09): Revise the 
maintenance program by incorporating Airbus A330 Airworthiness 
Limitations Section (ALS) Part 1, Safe Life Airworthiness Limitation 
Items (SL-ALI), Revision 05, dated July 29, 2010. Comply with all 
ALIs in Airbus A330 ALS Part 1, SL-ALI, Revision 05, dated July 29, 
2010, at the times specified therein. Accomplishing the actions 
specified in paragraph (k) of this AD terminates the requirements of 
this paragraph.

(h) Retained Limitation of No Alternative Intervals or Limits, With 
Additional Exception

    This paragraph restates the requirements of paragraph (i) of AD 
2011-17-09, with additional exception. Except as provided by 
paragraphs (k) and (m)(1) of this AD, after accomplishment of the 
actions specified in paragraph (g) of this AD, no alternatives to 
the maintenance tasks, intervals, or limitations specified in 
paragraph (g) of this AD may be used.

(i) Retained Bogie Beam Replacement, With Specific Delegation Approval 
Language, New Terminating Action, and New Service Information

    This paragraph restates the requirements of paragraph (g) of AD 
2012-25-12, with specific delegation approval language and 
terminating action and new service information. For airplanes 
identified in paragraphs (c)(1) and (c)(3) of this AD: At the

[[Page 24038]]

later of the times specified in paragraphs (i)(1) and (i)(2) of this 
AD, replace all main landing gear (MLG) bogie beams having part 
number (P/N) 201485300, 201485301, 201272302, 201272304, 201272306, 
or 201272307, except those that have serial number (S/N) S2A, S2B, 
or S2C, as identified in Messier-Dowty Service Letter A33-34 A20, 
Revision 5, including Appendixes A through F, dated July 31, 2009; 
or Messier-Bugatti-Dowty Service Letter A33-34 A20, Revision 7, 
including Appendixes A through F, dated July 20, 2012; with a new or 
serviceable part, 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). As of the effective date of this 
AD, the applicable MLG bogie beams specified in this paragraph must 
be replaced using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or 
Airbus's EASA DOA. Accomplishing the actions specified in paragraph 
(k) of this AD terminates the requirements of this paragraph.
    (1) At the applicable time specified in paragraphs (i)(1)(i), 
(i)(1)(ii), and (i)(1)(iii) of this AD.
    (i) For Model A330-201, -202, -203, -223, -243 series airplanes, 
weight variant (WV)02x, WV05x (except WV058), and WV06x series: 
Before the accumulation of a life limit of 50,000 landings or 72,300 
total flight hours, whichever occurs first from the first 
installation of a MLG bogie beam on the airplane.
    (ii) For Model A330-201, -202, -203, -223, -243 WV058 series 
airplanes: Before the accumulation of a life limit of 50,000 
landings or 57,900 total flight hours, whichever occurs first from 
the first installation of a MLG bogie beam on the airplane.
    (iii) For Model A330-301, -302, -303, -321, -322, -323, -341, -
342, -343 series airplanes, WV00x, WV01x, WV02x, and WV05x series: 
Before the accumulation of a life limit of 46,000 landings or 75,000 
total flight hours, whichever occurs first from the first 
installation of a MLG bogie beam on the airplane.
    (2) Within 6 months after January 30, 2013 (the effective date 
of AD 2012-25-12).

(j) Retained Parts Installation Limitation, With New Terminating Action

    This paragraph restates the requirements of paragraph (h) of AD 
2012-25-12, with new terminating action. For airplanes identified in 
paragraphs (c)(1) and (c)(3) of this AD, as of January 30, 2013 (the 
effective date of AD 2012-25-12), a MLG bogie beam having any part 
number identified in paragraph (i) of this AD may be installed on an 
airplane, provided its life has not exceeded the life limit 
specified in paragraphs (i)(1)(i), (i)(1)(ii), and (i)(1)(iii) of 
this AD, and it is replaced with a new or serviceable part before 
reaching the life limit specified in paragraphs (i)(1)(i), 
(i)(1)(ii), and (i)(1)(iii) of this AD. Accomplishing the actions 
specified in paragraph (k) of this AD terminates the requirements of 
this paragraph.

(k) New Maintenance or Inspection Program Revision

    Within 3 months after the effective date of this AD: Revise the 
maintenance or inspection program, as applicable, by incorporating 
the information in Airbus A330 ALS Part 1, SL-ALI, Revision 08, 
dated April 11, 2016. The initial compliance times for the actions 
specified in Airbus A330 ALS Part 1, SL-ALI, Revision 08, dated 
April 11, 2016, are at the times specified in Airbus A330 ALS Part 
1, SL-ALI, Revision 08, dated April 11, 2016, or within 3 months 
after the effective date of this AD, whichever occurs later. 
Accomplishing the actions specified in this paragraph terminates the 
requirements specified in paragraphs (g) through (j) of this AD.

(l) New Limitation of No Alternative Actions or Intervals

    After the maintenance or inspection program, as applicable, has 
been revised, as required by paragraph (k) of this AD, no 
alternative actions (e.g., inspections) or intervals may be used 
unless the actions or intervals are approved as an alternative 
method of compliance (AMOC) in accordance with the procedures 
specified in paragraph (m)(1) of this AD.

(m) 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 manager of the International Branch, send it to the 
attention of the person identified in paragraph (n)(2) of this AD. 
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.
    (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 EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0009, dated January 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-2015-8428.
    (2) For more information about this AD, 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.

(o) 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 
June 29, 2017.
    (i) Airbus A330 Airworthiness Limitations Section Part 1, Safe 
Life Airworthiness Limitation Items, Revision 08, dated April 11, 
2016.
    (ii) Messier-Bugatti-Dowty Service Letter A33-34 A20, Revision 
7, including Appendixes A through F, dated July 20, 2012.
    (4) The following service information was approved for IBR on 
January 30, 2013 (77 FR 75825, December 26, 2012).
    (i) Messier-Dowty Service Letter A33-34 A20, Revision 5, 
including Appendixes A through F, dated July 31, 2009.
    (ii) Reserved.
    (5) The following service information was approved for IBR on 
September 30, 2011 (76 FR 53305, August 26, 2011).
    (i) Airbus A330 Airworthiness Limitations Section, Part 1, Safe 
Life Airworthiness Limitation Items, Revision 05, dated July 29, 
2010. The revision level of this document is indicated only on the 
title page and in the Record of Revisions; the revision date of this 
document is not indicated on the title page of this document.
    (ii) Reserved.
    (6) 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.
    (7) For Messier-Bugatti-Dowty service information identified in 
this AD, contact Messier-Bugatti USA, One Carbon Way, Walton, KY 
41094; telephone 859-525-8583; fax 859-485 8827; email 
americascsc@safranmbd.com.
    (8) 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.
    (9) 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.


[[Page 24039]]


    Issued in Renton, Washington, on May 10, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-10266 Filed 5-24-17; 8:45 am]
 BILLING CODE 4910-13-P