Airworthiness Directives; Airbus Airplanes, 81216-81220 [2015-32547]

Download as PDF 81216 Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Proposed Rules catalogs, and in other product advertising literature. Original equipment manufacturer or OEM means any person who produces or assembles a unit of a covered product or covered equipment. Only one OEM is responsible for the manufacture (production or assembly) of a particular unit. ■ 3. Section 429.5 is amended by adding paragraph (c) to read as follows: number (depending on the certification method) for each brand must be submitted. For commercial HVAC, WH, and refrigeration equipment, an individual model number may be identified as a ‘‘private model number’’ if it meets the requirements of § 429.7(b). * * * * * ■ 6. Section 429.500 is added to read as follows: § 429.5 § 429.500. Imported products. * * * * * (c) Any person importing a unit of a covered product or covered equipment subject to an applicable energy conservation standard set forth in parts 430 or 431 of this chapter for entry into the United States on or after [2 YEARS AFTER DATE OF PUBLICATION OF FINAL RULE IN THE FEDERAL REGISTER], whether the unit is a component part of another product or a final product, must provide a certification of admissibility to the Secretary in accordance with § 429.500. ■ 4. Section 429.7 is amended by revising paragraph (b) to read as follows: § 429.7 Confidentiality. * * * * * (b) An individual model number is public information unless: (1) The individual model number is a unique model number of a commercial packaged boiler, commercial water heating equipment, commercial HVAC equipment or commercial refrigeration equipment that was developed for an individual customer, (2) The individual model number is not displayed on product literature, and (3) Disclosure of the individual model number would reveal confidential business information as described at § 1004.11 of this title—in which case, under these limited circumstances, a manufacturer may identify the individual model number as a private model number on a certification report submitted pursuant to § 429.12(b)(6). * * * * * ■ 5. Section 429.12 is amended by revising paragraph (b)(6) to read as follows: § 429.12. General requirements applicable to certification reports. jstallworth on DSK7TPTVN1PROD with PROPOSALS * * * * * (b) * * * (6) For each brand, the basic model number and the individual model number(s) in that basic model with the following exceptions: For walk-in coolers, the basic model number for each brand must be submitted. For distribution transformers, the basic model number or kVA grouping model VerDate Sep<11>2014 15:26 Dec 28, 2015 Jkt 238001 Certification of admissibility. (a) A certification of admissibility submitted pursuant to § 429.5(c) must meet the provisions of this section. (b) The certification must be submitted through the Automated Commercial Environment (ACE) of the U.S. Customs and Border Protection (CBP) before the entry of the unit(s) at the port of arrival. (c) The certification must include whether the basic model of the product or equipment being imported has been certified to DOE as compliant with all applicable energy conservation standards; (d) If the importer has not submitted a certification report for the basic model of the product or equipment being imported pursuant to § 429.12, the certification of admissibility must include: (1) The type of product or equipment (using a three-digit code corresponding to the applicable section in 10 CFR part 429, subpart B); (2) The brand name of the covered product or equipment; (3) The individual model number of the covered product or equipment; (4) Whether the covered product or equipment being imported is a final product or a component of a final product and, if the covered product or equipment is a component, the brand name and individual model number of the final product; (5) The original equipment manufacturer (OEM) of the covered product or equipment being imported as defined in § 429.2 and, in the case of electric motors, the Compliance Certification number; and (6) A contact name and email address of the importer of record. (e) If the importer has submitted a certification report for the basic model of the product or equipment being imported pursuant to § 429.12, the certification of admissibility must include: (1)The CCMS ticket number of the most recent certification submission; (2)The CCMS attachment identification number assigned to the certification submission; PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 (3) The line number in the submission corresponding to the basic model certified; and (4) If the covered product or equipment is a component of a final product, the brand name and individual model number of the final product. [FR Doc. 2015–32796 Filed 12–28–15; 8:45 am] BILLING CODE 6450–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–7533; Directorate Identifier 2015–NM–080–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A330–200 and –300 series airplanes, Model A330–200 Freighter series airplanes, and Airbus Model A340–541 and A340–642 airplanes. This proposed AD was prompted by a report of an under-torqued forward engine mount bolt. This proposed AD would require a one-time torque check of the forward and aft engine mount bolts, and corrective actions if necessary. We are proposing this AD to detect and correct improperly torqued engine mount bolts, which could lead to detachment of the engine from the airplane during flight; and consequent damage to the airplane and injury to persons on the ground. DATES: We must receive comments on this proposed AD by February 12, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 SUMMARY: E:\FR\FM\29DEP1.SGM 29DEP1 Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Proposed Rules p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. 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. jstallworth on DSK7TPTVN1PROD with PROPOSALS 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– 7533; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2015–7533; Directorate Identifier 2015–NM–080–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency, which is the Technical Agent VerDate Sep<11>2014 15:26 Dec 28, 2015 Jkt 238001 for the Member States of the European Union, has issued EASA Airworthiness Directive 2015–0082, dated May 11, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition on certain Airbus Model A330–200 and –300 series airplanes, Model A330–200 Freighter series airplanes, and Airbus Model A340–541 and A340–642 airplanes. The MCAI states: In 2013, during a pre-delivery test on an A330 aeroplane fitted with Pratt & Whitney (PW) PW4170 engines, an issue with N1 vibrations level on [engine] ENG1 was identified. While performing an engine removal, one forward engine mount bolt was found improperly torqued. The investigation concluded this was due to a production line engine installation quality issue. Further analysis showed that some aeroplanes, delivered between June 2006 and January 2014, may have had the rear (AFT) and forward (FWD) engine mount bolts improperly torqued. This condition, if not detected and corrected, could ultimately lead to an inflight detachment of the engine from the aeroplane, possibly resulting in damage to the aeroplane and/or injury to persons on the ground. Prompted by these findings, Airbus issued four Alert Operators Transmissions (AOT) A71L004–14 (for A330 aeroplanes fitted Pratt & Whitney (PW) engines), AOT A71L006–14 (for A330 aeroplanes fitted with General Electric (GE) engines), AOT A71L005–14 (for A330 aeroplanes fitted with Rolls Royce (RR) Trent 700 engines) and AOT A71L008–14 (for A340 aeroplanes fitted with RR Trent 500 engines) to provide torque check instructions. For the reasons described above, this [EASA] AD requires a one-time torque check of the FWD and AFT engine mount bolts and, depending on findings, [corrective actions] re-torque of the affected bolt(s) and/or replacement of all four bolts and associated nuts. Findings (or discrepancies) include one bolt that is loose or able to rotate, two or more bolts that are loose or able to rotate, or one or more pylon bolts that are fully broken. Corrective actions include re-torqueing the affected bolt(s), and replacing all bolts and associated nuts with new bolts and nuts on the engine where the loose or fully broken bolt(s) were detected. This proposed AD specifies reporting of all findings (including no discrepancies). The corrective actions include re-torqueing loose bolts before further flight. The compliance times for replacing loose or fully broken bolts ranges, depend on airplane configuration, and range from before further flight if more than one bolt rotates or is fully broken to no later than 2,350 flight cycles or 24,320 flight hours since first flight of the airplane, if only one bolt rotates. You may examine PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 81217 the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–7533. Related Service Information Under 1 CFR Part 51 We have reviewed the following service information. • Airbus AOT A71L004–14, Revision 01, dated April 7, 2014. The service information describes procedures for doing a one-time torque check to determine if there are any loose or fully broken engine mount pylon bolts at four positions at the forward engine pylon 1 and pylon 2 of Airbus Model A330 series airplanes having Pratt and Whitney engines, doing corrective actions, and reporting all findings. • Airbus AOT A71L005–14, Revision 01, dated December 11, 2014. The service information describes procedures for doing a one-time torque check to determine if there are any loose or fully broken engine mount pylon bolts at four positions at the forward engine pylon 1 and pylon 2 of Airbus Model A330 series airplanes having Trent 700 engines, doing corrective actions, and reporting all findings. • Airbus AOT A71L006–14, dated July 22, 2014. The service information describes procedures for doing a onetime torque check to determine if there are any loose or fully broken engine mount pylon bolts at five FWD and four AFT positions at the forward engine pylon 1 and pylon 2 of Airbus Model A330 series airplanes having GE engines, doing corrective actions, and reporting all findings. • Airbus AOT A71L008–14, Revision 01, dated December 18, 2014. The service information describes procedures for doing a one-time torque check to determine if there are any loose or fully broken engine mount pylon bolts at four positions at the forward engine pylon 1 and pylon 2 of Airbus Model A340 series airplanes having Trent 500 engines, doing corrective actions, and reporting all findings. 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 of this NPRM. Other Related Rulemaking On June 21, 2013, we issued AD 2013–14–04, Amendment 39–17509 (78 FR 68352, November 14, 2013). AD 2013–14–04 requires a torque check of forward engine mount bolts, and replacement if necessary on all Airbus Model A330–223F, –223, –321, –322, and –323 airplanes. AD 2013–14–04 was E:\FR\FM\29DEP1.SGM 29DEP1 81218 Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Proposed Rules prompted by a fatigue load analysis that determined that the inspection interval for certain pylon bolts must be reduced. We issued AD 2013–04–04 to detect and correct loose or broken bolts, which could lead to engine detachment inflight, and damage to the airplane. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. jstallworth on DSK7TPTVN1PROD with PROPOSALS Costs of Compliance We estimate that this proposed AD affects 55 airplanes of U.S. registry. We also estimate that it would take about 12 work-hours per product to comply with the basic requirements of this proposed AD, and 1 work-hour per product to report torque check findings. The average labor rate is $85 per workhour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $60,755, or $1,105 per product. In addition, we estimate that any necessary follow-on actions would take about 20 work-hours and require parts costing $90,200 for a cost of $91,900 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 proposed AD is 2120– 0056. The paperwork cost associated with this proposed AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this proposed AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden VerDate Sep<11>2014 15:26 Dec 28, 2015 Jkt 238001 should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES–200. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 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 adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2015–7533; Directorate Identifier 2015–NM–080–AD. (a) Comments Due Date We must receive comments by February 12, 2016. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes specified in paragraphs (c)(1) through (c)(5) of this AD, certificated in any category, from manufacturer serial number (MSN) 0715 through MSN 1507 inclusive, and MSN 1509, except airplanes on which all engines have been removed and/or replaced since the date of the first flight of the airplane. (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. (4) Airbus Model A340–541 airplanes. (5) Airbus Model A340–642 airplanes. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. (e) Reason This AD was prompted by a report of an under-torqued forward engine mount bolt. We are issuing this AD to detect and correct improperly torqued engine mount bolts, which could lead to detachment of the engine from the airplane during flight; and consequent damage to the airplane and injury to persons on the ground. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definition of Affected Engine For the purpose of this AD, an affected engine is an engine that has never been removed and/or replaced since first flight of the airplane. (h) Action for Airbus Model A330 Airplanes Equipped With Pratt and Whitney (PW) Engines (1) For Model A330–200, –200 Freighter, and –300 series airplanes equipped with PW engines: At the earlier of the times specified in paragraph (h)(1)(i) and (h)(1)(ii) of this AD, accomplish a one-time torque check of the forward (FWD) and rear (AFT) engine mount bolts on each affected engine, at the locations E:\FR\FM\29DEP1.SGM 29DEP1 jstallworth on DSK7TPTVN1PROD with PROPOSALS Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Proposed Rules specified in, and in accordance with the instructions of Section 4.2.2, ‘‘Inspection Requirements,’’ of Airbus Alert Operators Transmission (AOT) A71L004–14, Revision 01, dated April 7, 2014. (i) Within 2,000 flight hours after the effective date of this AD. (ii) During the accomplishment of Airbus Service Bulletin A330–71–3028, Revision 01, dated February 20, 2012, if done after the effective date of this AD. (2) If, during the torque check required by paragraph (h)(1) of this AD, only one FWD bolt is found that rotates: Do the actions specified in paragraph (h)(2)(i), (h)(2)(ii), (h)(2)(iii), or (h)(2)(iv) of this AD, as applicable. (i) For Model A330–200 and –300 series airplanes with an average flight time of greater than 132 minutes and having accumulated less than 2,350 flight cycles and less than 24,320 flight hours since first flight of the airplane: Before further flight, retorque the affected bolt, and, within 2,350 flight cycles or 24,320 flight hours since first flight of the airplane, whichever occurs first, replace the 4 bolts and associated nuts, in accordance with the instructions of Section 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004– 14, Revision 01, dated April 7, 2014. (ii) For Model A330–200 and –300 series airplanes with an average flight time of 132 minutes or lower and having accumulated less than 1,950 flight cycles and less than 20,210 flight hours since first flight of the airplane: Before further flight, re-torque the affected bolt, and within 2,350 flight cycles or 24,320 flight hours since first flight of the airplane, whichever occurs first, replace the 4 bolts and associated nuts, in accordance with the instructions of Section 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004–14, Revision 01, dated April 7, 2014. (iii) For Model A330–200 Freighter series airplanes having accumulated less than 2,140 flight cycles and less than 6,600 flight hours since first flight of the airplane: Before further flight, re-torque the affected bolt and within 2,140 flight cycles or 6,600 flight hours since first flight of the airplane, whichever occurs first, replace the 4 bolts and associated nuts, in accordance with the instructions of Section 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004–14, Revision 01, dated April 7, 2014. (iv) For airplanes identified in paragraphs (h)(2)(iv)(A), (h)(2)(iv)(B), and (h)(2)(iv)(C) of this AD: Before further flight, replace the 4 bolts and associated nuts in accordance with the instructions of Section 4.2.3, ‘‘Findings,’’ of AOT A71L004–14, Revision 01, dated April 7, 2014. (A) Model A330–200 and –300 series airplanes with an average flight time of greater than 132 minutes and having accumulated 2,350 flight cycles or more or 24,320 flight hours or more since first flight of the airplane. (B) Model A330–200 and –300 series airplanes with an average flight time of 132 minutes or lower and having accumulated 1,950 flight cycles or more or 20,210 flight hours or more since first flight of the airplane. (C) Model A330–200 Freighter series airplanes having accumulated 2,140 flight VerDate Sep<11>2014 15:26 Dec 28, 2015 Jkt 238001 cycles or more or 6,600 flight hours or more since first flight of the airplane: (3) If, during the torque check required by paragraph (h)(1) of this AD, two or more FWD bolts are found that rotate: Before further flight, replace the 4 bolts and associated nuts in accordance with the instructions of Section 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004–14, Revision 01, dated April 7, 2014. (4) If, during the torque check required by paragraph (h)(1) of this AD, one or more FWD pylon bolts are found fully broken: Before further flight, replace the 4 bolts and associated nuts in accordance with the instructions of Section 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004–14, Revision 01, dated April 7, 2014, except as required by paragraph (m)(2) of this AD. (5) If, during the torque check required by paragraph (h)(1) of this AD, only one AFT bolt is found that rotates: Before further flight, re-torque the affected bolt, and replace the 4 bolts and associated nuts at the next engine removal, in accordance with the instructions of Section 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004–14, Revision 01, dated April 7, 2014. (6) If, during the torque check required by paragraph (h)(1) of this AD, two or more AFT bolts are found that rotate: Before further flight, replace the 4 bolts and associated nuts in accordance with the instructions of Section 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004–14, Revision 01, dated April 7, 2014. (7) If, during the torque check required by paragraph (h)(1) of this AD, one or more AFT pylon bolts are found fully broken: Before further flight, replace the 4 bolts and associated nuts in accordance with the instructions of Section 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004–14, Revision 01, dated April 7, 2014, except as required by paragraph (m)(2) of this AD. (i) Concurrent Actions AD 2013–14–04, Amendment 39–17509 (78 FR 68352, November 14, 2013), requires a torque check of forward engine mount bolts using Airbus Service Bulletin A330–71–3028, Revision 01, dated February 20, 2012. If accomplishing the torque check of FWD engine mount bolts within the compliance times specified in paragraph (g) of the FAA AD 2013–14–04 using Airbus Service Bulletin A330–71–3028, Revision 01, dated February 20, 2012, perform the torque check of the AFT engine mount bolts at the same time. (j) Action for Airbus Model A330 Airplanes Equipped With General Electric (GE) Engines (1) For Airbus Model A330–200, –200 Freighter, and –300 series airplanes equipped with GE engines: Within 2,000 flight hours after the effective date of this AD, accomplish a one-time torque check of the FWD and AFT engine mount bolts on each affected engine, at the locations specified in, and in accordance with the instructions of Section 4.2.2, ‘‘Inspection Requirements,’’ of Airbus AOT A71L006–14, dated July 22, 2014. (2) If, during the torque check required by paragraph (j)(1) of this AD, only one FWD PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 81219 bolt is found that rotates: Do the actions specified in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD, as applicable. (i) For airplanes that have accumulated less than 4,000 flight cycles and less than 30,800 flight hours since first flight of the airplane: Before further flight, re-torque affected FWD engine mount bolt(s), in accordance with the instructions of Section 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L006–14, dated July 22, 2014, and, within 4,000 flight cycles or 30,800 flight hours since first flight of the airplane, whichever is first, replace the 5 bolts, as applicable, and their associated nuts with new bolts and nuts in accordance with the instructions of Section 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L006–14, dated July 22, 2014. (ii) For airplanes that have accumulated 4,000 flight cycles or more or 30,800 flight hours or more since first flight of the airplane: Before further flight, replace the 5 FWD engine mount bolts, as applicable, and their associated nuts with new bolts and nuts in accordance with the instructions of Section 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L006–14, dated July 22, 2014. (3) If, during the torque check required by paragraph (j)(1) of this AD, two or more FWD bolts are found that rotate: Repair before further flight using a method approved in accordance with the procedures specified in paragraph (p)(1) of this AD. (4) If, during the torque check required by paragraph (j)(1) of this AD, one or more FWD pylon bolts are found fully broken: Repair before further flight using a method approved in accordance with the procedures specified in paragraph (p)(1) of this AD. (5) If, during the torque check required by paragraph (j)(1) of this AD, only one AFT bolt is found that rotates: Before further flight, retorque the affected AFT engine mount bolt(s) in accordance with the instructions of Section 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L006–14, dated July 22, 2014, and, at the next engine removal, replace the 4 bolts and associated nuts with new bolts and nuts in accordance with the instructions of Section 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L006– 14, dated July 22, 2014. (6) If, during the torque check required by paragraph (j)(1) of this AD, two or more AFT bolts are found that rotate: Repair before further flight using a method approved in accordance with the procedures specified in paragraph (p)(1) of this AD. (7) If, during the torque check required by paragraph (j)(1) of this AD, one or more AFT pylon bolts are found fully broken: before further flight, do all applicable corrective actions in accordance with the instructions of Section 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L006–14, dated July 22, 2014, except as required by paragraph (m)(2) of this AD. (k) Action for Airbus Model A330 Airplanes Equipped With Rolls-Royce (RR) Trent 700 Engines (1) For Airbus Model A330–200, –200 Freighter, and –300 series airplanes equipped with RR Trent 700 Engines: Within 2,000 flight hours after the effective date of this AD, accomplish a one-time torque check of the FWD and AFT engine mount bolts on each affected engine, at the locations specified in, E:\FR\FM\29DEP1.SGM 29DEP1 81220 Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Proposed Rules and in accordance with the instructions of Section 4.2.2, ‘‘Inspection Requirements,’’ of Airbus AOT A71L005–14, Revision 01, dated December 11, 2014. (2) If, during the torque check required by paragraph (k)(1) of this AD, any discrepancy is detected (one bolt rotates, two or more bolts rotate, or one or more bolts are fully broken): Within the compliance time specified in Airbus AOT A71L005–14, Revision 01, dated December 11, 2014, accomplish all applicable corrective actions in accordance with the instructions of Section 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L005–14, Revision 01, dated December 11, 2014, except as required by paragraphs (m)(1) and (m)(2) of this AD. jstallworth on DSK7TPTVN1PROD with PROPOSALS (l) Action for Airbus Model A340–541 and –642 Airplanes Equipped With Rolls-Royce Trent 500 Engines (1) For Airbus Model A340–541 and –642 airplanes equipped with Rolls-Royce Trent 500 Engines: Within 2,000 flight hours after the effective date of this AD, accomplish a one-time torque check of FWD and AFT engine mount bolts on each affected engine, at the locations specified in, and in accordance with the instructions of Section 4.2.2, ‘‘Inspection requirements,’’ of Airbus AOT A71L008–14, Revision 01, dated December 18, 2014. (2) If, during the torque check required by paragraph (l)(1) of this AD, any discrepancy is detected (one bolt rotates, two or more bolts rotate, or one or more bolts are fully broken): Within the compliance time specified in Airbus AOT A71L008–14, Revision 01, dated December 18, 2014, accomplish all applicable corrective actions, in accordance with the instructions of Section 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L008–14, Revision 01, dated December 18, 2014, except as required by paragraphs (m)(1) and (m)(2) of this AD. (m) Service Information Exceptions (1) Where Airbus AOTs A71L005–14, Revision 01, dated December 11, 2014; A71L006–14, dated July 22, 2014; and A71L008–14, dated September 29, 2014, specify to contact Airbus for further actions, before further flight, repair 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). (2) Where Airbus AOT A71L004–14, Revision 01, dated April 7, 2014; AOT A71L005–14, Revision 01, dated December 11, 2014; AOT A71L006–14, dated July 22, 2014; and AOT A71L008–14, Revision 01, dated December 18, 2014, specify actions ‘‘if one pylon bolt fully broken,’’ this AD requires that those actions be done if one or more pylon bolt is found fully broken during any torque check required by paragraph (h)(1), (j)(1), (k)(1) or (l)(1) of this AD. (n) Reporting At the applicable time specified in paragraphs (n)(1) and (n)(2) of this AD: After accomplishment of any torque check required by paragraphs (h), (j), (k), and (l) of this AD, report all inspection results to Airbus, including no findings, in accordance VerDate Sep<11>2014 15:26 Dec 28, 2015 Jkt 238001 with the ‘‘Reporting’’ section of the applicable service information specified in paragraphs (h), (j), (k), and (l) of this AD. (1) If the torque check was done on or after the effective date of this AD: Submit the report within 30 days after the torque check. (2) If the torque check was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (o) Credit for Previous Actions (1) This paragraph provides credit for the actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Airbus AOT A71L004–14, dated April 1, 2014 (for Airbus Model A330 Airplanes Equipped with Pratt and Whitney Engines), which is not incorporated by reference in this AD. (2) This paragraph provides credit for the actions required by paragraph (k) of this AD, if those actions were performed before the effective date of this AD using Airbus AOT A71L005–14, dated September 29, 2014 (for Airbus Model A330 Airplanes Equipped with Rolls-Royce Trent 700 Engines), which is not incorporated by reference in this AD. (3) This paragraph provides credit for the actions required by paragraph (l) of this AD, if those actions were performed before the effective date of this AD using Airbus AOT A71L008–14, dated September 29, 2014 (for Airbus Model A340 Airplanes Equipped with Rolls-Royce Trent 500 Engines), which is not incorporated by reference in this AD. (p) 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-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) 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, 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 PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 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. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0082, dated May 11, 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– 2015–7533. (2) For 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. 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. Issued in Renton, Washington, on December 18, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–32547 Filed 12–28–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–7531; Directorate Identifier 2015–NM–052–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 787–8 airplanes. This proposed AD was SUMMARY: E:\FR\FM\29DEP1.SGM 29DEP1

Agencies

[Federal Register Volume 80, Number 249 (Tuesday, December 29, 2015)]
[Proposed Rules]
[Pages 81216-81220]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-32547]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-7533; Directorate Identifier 2015-NM-080-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Airbus Model A330-200 and -300 series airplanes, Model A330-200 
Freighter series airplanes, and Airbus Model A340-541 and A340-642 
airplanes. This proposed AD was prompted by a report of an under-
torqued forward engine mount bolt. This proposed AD would require a 
one-time torque check of the forward and aft engine mount bolts, and 
corrective actions if necessary. We are proposing this AD to detect and 
correct improperly torqued engine mount bolts, which could lead to 
detachment of the engine from the airplane during flight; and 
consequent damage to the airplane and injury to persons on the ground.

DATES: We must receive comments on this proposed AD by February 12, 
2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5

[[Page 81217]]

p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. 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.

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-
7533; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-7533; 
Directorate Identifier 2015-NM-080-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency, which is the Technical Agent 
for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0082, dated May 11, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition on certain Airbus Model 
A330-200 and -300 series airplanes, Model A330-200 Freighter series 
airplanes, and Airbus Model A340-541 and A340-642 airplanes. The MCAI 
states:

    In 2013, during a pre-delivery test on an A330 aeroplane fitted 
with Pratt & Whitney (PW) PW4170 engines, an issue with N1 
vibrations level on [engine] ENG1 was identified. While performing 
an engine removal, one forward engine mount bolt was found 
improperly torqued. The investigation concluded this was due to a 
production line engine installation quality issue. Further analysis 
showed that some aeroplanes, delivered between June 2006 and January 
2014, may have had the rear (AFT) and forward (FWD) engine mount 
bolts improperly torqued.
    This condition, if not detected and corrected, could ultimately 
lead to an in-flight detachment of the engine from the aeroplane, 
possibly resulting in damage to the aeroplane and/or injury to 
persons on the ground.
    Prompted by these findings, Airbus issued four Alert Operators 
Transmissions (AOT) A71L004-14 (for A330 aeroplanes fitted Pratt & 
Whitney (PW) engines), AOT A71L006-14 (for A330 aeroplanes fitted 
with General Electric (GE) engines), AOT A71L005-14 (for A330 
aeroplanes fitted with Rolls Royce (RR) Trent 700 engines) and AOT 
A71L008-14 (for A340 aeroplanes fitted with RR Trent 500 engines) to 
provide torque check instructions.
    For the reasons described above, this [EASA] AD requires a one-
time torque check of the FWD and AFT engine mount bolts and, 
depending on findings, [corrective actions] re-torque of the 
affected bolt(s) and/or replacement of all four bolts and associated 
nuts.

    Findings (or discrepancies) include one bolt that is loose or able 
to rotate, two or more bolts that are loose or able to rotate, or one 
or more pylon bolts that are fully broken. Corrective actions include 
re-torqueing the affected bolt(s), and replacing all bolts and 
associated nuts with new bolts and nuts on the engine where the loose 
or fully broken bolt(s) were detected. This proposed AD specifies 
reporting of all findings (including no discrepancies). The corrective 
actions include re-torqueing loose bolts before further flight. The 
compliance times for replacing loose or fully broken bolts ranges, 
depend on airplane configuration, and range from before further flight 
if more than one bolt rotates or is fully broken to no later than 2,350 
flight cycles or 24,320 flight hours since first flight of the 
airplane, if only one bolt rotates. 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-2015-7533.

Related Service Information Under 1 CFR Part 51

    We have reviewed the following service information.
     Airbus AOT A71L004-14, Revision 01, dated April 7, 2014. 
The service information describes procedures for doing a one-time 
torque check to determine if there are any loose or fully broken engine 
mount pylon bolts at four positions at the forward engine pylon 1 and 
pylon 2 of Airbus Model A330 series airplanes having Pratt and Whitney 
engines, doing corrective actions, and reporting all findings.
     Airbus AOT A71L005-14, Revision 01, dated December 11, 
2014. The service information describes procedures for doing a one-time 
torque check to determine if there are any loose or fully broken engine 
mount pylon bolts at four positions at the forward engine pylon 1 and 
pylon 2 of Airbus Model A330 series airplanes having Trent 700 engines, 
doing corrective actions, and reporting all findings.
     Airbus AOT A71L006-14, dated July 22, 2014. The service 
information describes procedures for doing a one-time torque check to 
determine if there are any loose or fully broken engine mount pylon 
bolts at five FWD and four AFT positions at the forward engine pylon 1 
and pylon 2 of Airbus Model A330 series airplanes having GE engines, 
doing corrective actions, and reporting all findings.
     Airbus AOT A71L008-14, Revision 01, dated December 18, 
2014. The service information describes procedures for doing a one-time 
torque check to determine if there are any loose or fully broken engine 
mount pylon bolts at four positions at the forward engine pylon 1 and 
pylon 2 of Airbus Model A340 series airplanes having Trent 500 engines, 
doing corrective actions, and reporting all findings.
    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 of this 
NPRM.

Other Related Rulemaking

    On June 21, 2013, we issued AD 2013-14-04, Amendment 39-17509 (78 
FR 68352, November 14, 2013). AD 2013-14-04 requires a torque check of 
forward engine mount bolts, and replacement if necessary on all Airbus 
Model A330-223F, -223, -321, -322, and -323 airplanes. AD 2013-14-04 
was

[[Page 81218]]

prompted by a fatigue load analysis that determined that the inspection 
interval for certain pylon bolts must be reduced. We issued AD 2013-04-
04 to detect and correct loose or broken bolts, which could lead to 
engine detachment in-flight, and damage to the airplane.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 55 airplanes of U.S. 
registry.
    We also estimate that it would take about 12 work-hours per product 
to comply with the basic requirements of this proposed AD, and 1 work-
hour per product to report torque check findings. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this proposed AD on U.S. operators to be $60,755, or $1,105 per 
product.
    In addition, we estimate that any necessary follow-on actions would 
take about 20 work-hours and require parts costing $90,200 for a cost 
of $91,900 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 proposed AD 
is 2120-0056. The paperwork cost associated with this proposed AD has 
been detailed in the Costs of Compliance section of this document and 
includes time for reviewing instructions, as well as completing and 
reviewing the collection of information. Therefore, all reporting 
associated with this proposed AD is mandatory. Comments concerning the 
accuracy of this burden and suggestions for reducing the burden should 
be directed to the FAA at 800 Independence Ave. SW., Washington, DC 
20591, ATTN: Information Collection Clearance Officer, AES-200.

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2015-7533; Directorate Identifier 2015-NM-
080-AD.

(a) Comments Due Date

    We must receive comments by February 12, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes specified in paragraphs 
(c)(1) through (c)(5) of this AD, certificated in any category, from 
manufacturer serial number (MSN) 0715 through MSN 1507 inclusive, 
and MSN 1509, except airplanes on which all engines have been 
removed and/or replaced since the date of the first flight of the 
airplane.
    (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.
    (4) Airbus Model A340-541 airplanes.
    (5) Airbus Model A340-642 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Powerplant.

(e) Reason

    This AD was prompted by a report of an under-torqued forward 
engine mount bolt. We are issuing this AD to detect and correct 
improperly torqued engine mount bolts, which could lead to 
detachment of the engine from the airplane during flight; and 
consequent damage to the airplane and injury to persons on the 
ground.

(f) Compliance

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

(g) Definition of Affected Engine

    For the purpose of this AD, an affected engine is an engine that 
has never been removed and/or replaced since first flight of the 
airplane.

(h) Action for Airbus Model A330 Airplanes Equipped With Pratt and 
Whitney (PW) Engines

    (1) For Model A330-200, -200 Freighter, and -300 series 
airplanes equipped with PW engines: At the earlier of the times 
specified in paragraph (h)(1)(i) and (h)(1)(ii) of this AD, 
accomplish a one-time torque check of the forward (FWD) and rear 
(AFT) engine mount bolts on each affected engine, at the locations

[[Page 81219]]

specified in, and in accordance with the instructions of Section 
4.2.2, ``Inspection Requirements,'' of Airbus Alert Operators 
Transmission (AOT) A71L004-14, Revision 01, dated April 7, 2014.
    (i) Within 2,000 flight hours after the effective date of this 
AD.
    (ii) During the accomplishment of Airbus Service Bulletin A330-
71-3028, Revision 01, dated February 20, 2012, if done after the 
effective date of this AD.
    (2) If, during the torque check required by paragraph (h)(1) of 
this AD, only one FWD bolt is found that rotates: Do the actions 
specified in paragraph (h)(2)(i), (h)(2)(ii), (h)(2)(iii), or 
(h)(2)(iv) of this AD, as applicable.
    (i) For Model A330-200 and -300 series airplanes with an average 
flight time of greater than 132 minutes and having accumulated less 
than 2,350 flight cycles and less than 24,320 flight hours since 
first flight of the airplane: Before further flight, re-torque the 
affected bolt, and, within 2,350 flight cycles or 24,320 flight 
hours since first flight of the airplane, whichever occurs first, 
replace the 4 bolts and associated nuts, in accordance with the 
instructions of Section 4.2.3, ``Findings,'' of Airbus AOT A71L004-
14, Revision 01, dated April 7, 2014.
    (ii) For Model A330-200 and -300 series airplanes with an 
average flight time of 132 minutes or lower and having accumulated 
less than 1,950 flight cycles and less than 20,210 flight hours 
since first flight of the airplane: Before further flight, re-torque 
the affected bolt, and within 2,350 flight cycles or 24,320 flight 
hours since first flight of the airplane, whichever occurs first, 
replace the 4 bolts and associated nuts, in accordance with the 
instructions of Section 4.2.3, ``Findings,'' of Airbus AOT A71L004-
14, Revision 01, dated April 7, 2014.
    (iii) For Model A330-200 Freighter series airplanes having 
accumulated less than 2,140 flight cycles and less than 6,600 flight 
hours since first flight of the airplane: Before further flight, re-
torque the affected bolt and within 2,140 flight cycles or 6,600 
flight hours since first flight of the airplane, whichever occurs 
first, replace the 4 bolts and associated nuts, in accordance with 
the instructions of Section 4.2.3, ``Findings,'' of Airbus AOT 
A71L004-14, Revision 01, dated April 7, 2014.
    (iv) For airplanes identified in paragraphs (h)(2)(iv)(A), 
(h)(2)(iv)(B), and (h)(2)(iv)(C) of this AD: Before further flight, 
replace the 4 bolts and associated nuts in accordance with the 
instructions of Section 4.2.3, ``Findings,'' of AOT A71L004-14, 
Revision 01, dated April 7, 2014.
    (A) Model A330-200 and -300 series airplanes with an average 
flight time of greater than 132 minutes and having accumulated 2,350 
flight cycles or more or 24,320 flight hours or more since first 
flight of the airplane.
    (B) Model A330-200 and -300 series airplanes with an average 
flight time of 132 minutes or lower and having accumulated 1,950 
flight cycles or more or 20,210 flight hours or more since first 
flight of the airplane.
    (C) Model A330-200 Freighter series airplanes having accumulated 
2,140 flight cycles or more or 6,600 flight hours or more since 
first flight of the airplane:
    (3) If, during the torque check required by paragraph (h)(1) of 
this AD, two or more FWD bolts are found that rotate: Before further 
flight, replace the 4 bolts and associated nuts in accordance with 
the instructions of Section 4.2.3, ``Findings,'' of Airbus AOT 
A71L004-14, Revision 01, dated April 7, 2014.
    (4) If, during the torque check required by paragraph (h)(1) of 
this AD, one or more FWD pylon bolts are found fully broken: Before 
further flight, replace the 4 bolts and associated nuts in 
accordance with the instructions of Section 4.2.3, ``Findings,'' of 
Airbus AOT A71L004-14, Revision 01, dated April 7, 2014, except as 
required by paragraph (m)(2) of this AD.
    (5) If, during the torque check required by paragraph (h)(1) of 
this AD, only one AFT bolt is found that rotates: Before further 
flight, re-torque the affected bolt, and replace the 4 bolts and 
associated nuts at the next engine removal, in accordance with the 
instructions of Section 4.2.3, ``Findings,'' of Airbus AOT A71L004-
14, Revision 01, dated April 7, 2014.
    (6) If, during the torque check required by paragraph (h)(1) of 
this AD, two or more AFT bolts are found that rotate: Before further 
flight, replace the 4 bolts and associated nuts in accordance with 
the instructions of Section 4.2.3, ``Findings,'' of Airbus AOT 
A71L004-14, Revision 01, dated April 7, 2014.
    (7) If, during the torque check required by paragraph (h)(1) of 
this AD, one or more AFT pylon bolts are found fully broken: Before 
further flight, replace the 4 bolts and associated nuts in 
accordance with the instructions of Section 4.2.3, ``Findings,'' of 
Airbus AOT A71L004-14, Revision 01, dated April 7, 2014, except as 
required by paragraph (m)(2) of this AD.

(i) Concurrent Actions

    AD 2013-14-04, Amendment 39-17509 (78 FR 68352, November 14, 
2013), requires a torque check of forward engine mount bolts using 
Airbus Service Bulletin A330-71-3028, Revision 01, dated February 
20, 2012. If accomplishing the torque check of FWD engine mount 
bolts within the compliance times specified in paragraph (g) of the 
FAA AD 2013-14-04 using Airbus Service Bulletin A330-71-3028, 
Revision 01, dated February 20, 2012, perform the torque check of 
the AFT engine mount bolts at the same time.

(j) Action for Airbus Model A330 Airplanes Equipped With General 
Electric (GE) Engines

    (1) For Airbus Model A330-200, -200 Freighter, and -300 series 
airplanes equipped with GE engines: Within 2,000 flight hours after 
the effective date of this AD, accomplish a one-time torque check of 
the FWD and AFT engine mount bolts on each affected engine, at the 
locations specified in, and in accordance with the instructions of 
Section 4.2.2, ``Inspection Requirements,'' of Airbus AOT A71L006-
14, dated July 22, 2014.
    (2) If, during the torque check required by paragraph (j)(1) of 
this AD, only one FWD bolt is found that rotates: Do the actions 
specified in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD, as 
applicable.
    (i) For airplanes that have accumulated less than 4,000 flight 
cycles and less than 30,800 flight hours since first flight of the 
airplane: Before further flight, re-torque affected FWD engine mount 
bolt(s), in accordance with the instructions of Section 4.2.3, 
``Findings,'' of Airbus AOT A71L006-14, dated July 22, 2014, and, 
within 4,000 flight cycles or 30,800 flight hours since first flight 
of the airplane, whichever is first, replace the 5 bolts, as 
applicable, and their associated nuts with new bolts and nuts in 
accordance with the instructions of Section 4.2.3, ``Findings,'' of 
Airbus AOT A71L006-14, dated July 22, 2014.
    (ii) For airplanes that have accumulated 4,000 flight cycles or 
more or 30,800 flight hours or more since first flight of the 
airplane: Before further flight, replace the 5 FWD engine mount 
bolts, as applicable, and their associated nuts with new bolts and 
nuts in accordance with the instructions of Section 4.2.3, 
``Findings,'' of Airbus AOT A71L006-14, dated July 22, 2014.
    (3) If, during the torque check required by paragraph (j)(1) of 
this AD, two or more FWD bolts are found that rotate: Repair before 
further flight using a method approved in accordance with the 
procedures specified in paragraph (p)(1) of this AD.
    (4) If, during the torque check required by paragraph (j)(1) of 
this AD, one or more FWD pylon bolts are found fully broken: Repair 
before further flight using a method approved in accordance with the 
procedures specified in paragraph (p)(1) of this AD.
    (5) If, during the torque check required by paragraph (j)(1) of 
this AD, only one AFT bolt is found that rotates: Before further 
flight, re-torque the affected AFT engine mount bolt(s) in 
accordance with the instructions of Section 4.2.3, ``Findings,'' of 
Airbus AOT A71L006-14, dated July 22, 2014, and, at the next engine 
removal, replace the 4 bolts and associated nuts with new bolts and 
nuts in accordance with the instructions of Section 4.2.3, 
``Findings,'' of Airbus AOT A71L006-14, dated July 22, 2014.
    (6) If, during the torque check required by paragraph (j)(1) of 
this AD, two or more AFT bolts are found that rotate: Repair before 
further flight using a method approved in accordance with the 
procedures specified in paragraph (p)(1) of this AD.
    (7) If, during the torque check required by paragraph (j)(1) of 
this AD, one or more AFT pylon bolts are found fully broken: before 
further flight, do all applicable corrective actions in accordance 
with the instructions of Section 4.2.3, ``Findings,'' of Airbus AOT 
A71L006-14, dated July 22, 2014, except as required by paragraph 
(m)(2) of this AD.

(k) Action for Airbus Model A330 Airplanes Equipped With Rolls-Royce 
(RR) Trent 700 Engines

    (1) For Airbus Model A330-200, -200 Freighter, and -300 series 
airplanes equipped with RR Trent 700 Engines: Within 2,000 flight 
hours after the effective date of this AD, accomplish a one-time 
torque check of the FWD and AFT engine mount bolts on each affected 
engine, at the locations specified in,

[[Page 81220]]

and in accordance with the instructions of Section 4.2.2, 
``Inspection Requirements,'' of Airbus AOT A71L005-14, Revision 01, 
dated December 11, 2014.
    (2) If, during the torque check required by paragraph (k)(1) of 
this AD, any discrepancy is detected (one bolt rotates, two or more 
bolts rotate, or one or more bolts are fully broken): Within the 
compliance time specified in Airbus AOT A71L005-14, Revision 01, 
dated December 11, 2014, accomplish all applicable corrective 
actions in accordance with the instructions of Section 4.2.3, 
``Findings,'' of Airbus AOT A71L005-14, Revision 01, dated December 
11, 2014, except as required by paragraphs (m)(1) and (m)(2) of this 
AD.

(l) Action for Airbus Model A340-541 and -642 Airplanes Equipped With 
Rolls-Royce Trent 500 Engines

    (1) For Airbus Model A340-541 and -642 airplanes equipped with 
Rolls-Royce Trent 500 Engines: Within 2,000 flight hours after the 
effective date of this AD, accomplish a one-time torque check of FWD 
and AFT engine mount bolts on each affected engine, at the locations 
specified in, and in accordance with the instructions of Section 
4.2.2, ``Inspection requirements,'' of Airbus AOT A71L008-14, 
Revision 01, dated December 18, 2014.
    (2) If, during the torque check required by paragraph (l)(1) of 
this AD, any discrepancy is detected (one bolt rotates, two or more 
bolts rotate, or one or more bolts are fully broken): Within the 
compliance time specified in Airbus AOT A71L008-14, Revision 01, 
dated December 18, 2014, accomplish all applicable corrective 
actions, in accordance with the instructions of Section 4.2.3, 
``Findings,'' of Airbus AOT A71L008-14, Revision 01, dated December 
18, 2014, except as required by paragraphs (m)(1) and (m)(2) of this 
AD.

(m) Service Information Exceptions

    (1) Where Airbus AOTs A71L005-14, Revision 01, dated December 
11, 2014; A71L006-14, dated July 22, 2014; and A71L008-14, dated 
September 29, 2014, specify to contact Airbus for further actions, 
before further flight, repair 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).
    (2) Where Airbus AOT A71L004-14, Revision 01, dated April 7, 
2014; AOT A71L005-14, Revision 01, dated December 11, 2014; AOT 
A71L006-14, dated July 22, 2014; and AOT A71L008-14, Revision 01, 
dated December 18, 2014, specify actions ``if one pylon bolt fully 
broken,'' this AD requires that those actions be done if one or more 
pylon bolt is found fully broken during any torque check required by 
paragraph (h)(1), (j)(1), (k)(1) or (l)(1) of this AD.

(n) Reporting

    At the applicable time specified in paragraphs (n)(1) and (n)(2) 
of this AD: After accomplishment of any torque check required by 
paragraphs (h), (j), (k), and (l) of this AD, report all inspection 
results to Airbus, including no findings, in accordance with the 
``Reporting'' section of the applicable service information 
specified in paragraphs (h), (j), (k), and (l) of this AD.
    (1) If the torque check was done on or after the effective date 
of this AD: Submit the report within 30 days after the torque check.
    (2) If the torque check was done before the effective date of 
this AD: Submit the report within 30 days after the effective date 
of this AD.

(o) Credit for Previous Actions

    (1) This paragraph provides credit for the actions required by 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using Airbus AOT A71L004-14, dated April 
1, 2014 (for Airbus Model A330 Airplanes Equipped with Pratt and 
Whitney Engines), which is not incorporated by reference in this AD.
    (2) This paragraph provides credit for the actions required by 
paragraph (k) of this AD, if those actions were performed before the 
effective date of this AD using Airbus AOT A71L005-14, dated 
September 29, 2014 (for Airbus Model A330 Airplanes Equipped with 
Rolls-Royce Trent 700 Engines), which is not incorporated by 
reference in this AD.
    (3) This paragraph provides credit for the actions required by 
paragraph (l) of this AD, if those actions were performed before the 
effective date of this AD using Airbus AOT A71L008-14, dated 
September 29, 2014 (for Airbus Model A340 Airplanes Equipped with 
Rolls-Royce Trent 500 Engines), which is not incorporated by 
reference in this AD.

(p) 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: 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.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0082, dated May 11, 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-2015-7533.
    (2) For 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. 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.

    Issued in Renton, Washington, on December 18, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-32547 Filed 12-28-15; 8:45 am]
 BILLING CODE 4910-13-P