80 FR 81216 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 249 (December 29, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 249 (December 29, 2015)
| Page Range | 81216-81220 | |
| FR Document | 2015-32547 |
[Federal Register Volume 80, Number 249 (Tuesday, December 29, 2015)] [Proposed Rules] [Pages 81216-81220] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-32547] ======================================================================= ----------------------------------------------------------------------- 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
![81216 Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Proposed Rules
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OEM means any person who produces and refrigeration equipment, an (4) If the covered product or
or assembles a unit of a covered product individual model number may be equipment is a component of a final
or covered equipment. Only one OEM is identified as a ‘‘private model number’’ product, the brand name and individual
responsible for the manufacture if it meets the requirements of model number of the final product.
(production or assembly) of a particular § 429.7(b). [FR Doc. 2015–32796 Filed 12–28–15; 8:45 am]
unit. * * * * * BILLING CODE 6450–01–P
■ 3. Section 429.5 is amended by adding ■ 6. Section 429.500 is added to read as
paragraph (c) to read as follows: follows:
§ 429.5 Imported products. § 429.500. Certification of admissibility. DEPARTMENT OF TRANSPORTATION
* * * * * (a) A certification of admissibility
(c) Any person importing a unit of a Federal Aviation Administration
submitted pursuant to § 429.5(c) must
covered product or covered equipment meet the provisions of this section.
subject to an applicable energy 14 CFR Part 39
(b) The certification must be
conservation standard set forth in parts submitted through the Automated [Docket No. FAA–2015–7533; Directorate
430 or 431 of this chapter for entry into Commercial Environment (ACE) of the Identifier 2015–NM–080–AD]
the United States on or after [2 YEARS U.S. Customs and Border Protection
AFTER DATE OF PUBLICATION OF RIN 2120–AA64
(CBP) before the entry of the unit(s) at
FINAL RULE IN THE FEDERAL the port of arrival.
REGISTER], whether the unit is a Airworthiness Directives; Airbus
(c) The certification must include Airplanes
component part of another product or a whether the basic model of the product
final product, must provide a or equipment being imported has been AGENCY: Federal Aviation
certification of admissibility to the certified to DOE as compliant with all Administration (FAA), DOT.
Secretary in accordance with § 429.500. applicable energy conservation ACTION: Notice of proposed rulemaking
■ 4. Section 429.7 is amended by
standards; (NPRM).
revising paragraph (b) to read as follows: (d) If the importer has not submitted
a certification report for the basic model SUMMARY: We propose to adopt a new
§ 429.7 Confidentiality.
of the product or equipment being airworthiness directive (AD) for certain
* * * * * Airbus Model A330–200 and –300 series
(b) An individual model number is imported pursuant to § 429.12, the
certification of admissibility must airplanes, Model A330–200 Freighter
public information unless: series airplanes, and Airbus Model
(1) The individual model number is a include:
(1) The type of product or equipment A340–541 and A340–642 airplanes.
unique model number of a commercial This proposed AD was prompted by a
packaged boiler, commercial water (using a three-digit code corresponding
to the applicable section in 10 CFR part report of an under-torqued forward
heating equipment, commercial HVAC engine mount bolt. This proposed AD
equipment or commercial refrigeration 429, subpart B);
(2) The brand name of the covered would require a one-time torque check
equipment that was developed for an of the forward and aft engine mount
individual customer, product or equipment;
(3) The individual model number of bolts, and corrective actions if
(2) The individual model number is necessary. We are proposing this AD to
not displayed on product literature, and the covered product or equipment;
(4) Whether the covered product or detect and correct improperly torqued
(3) Disclosure of the individual model engine mount bolts, which could lead to
number would reveal confidential equipment being imported is a final
product or a component of a final detachment of the engine from the
business information as described at airplane during flight; and consequent
§ 1004.11 of this title—in which case, product and, if the covered product or
equipment is a component, the brand damage to the airplane and injury to
under these limited circumstances, a persons on the ground.
manufacturer may identify the name and individual model number of
individual model number as a private the final product; DATES: We must receive comments on
model number on a certification report (5) The original equipment this proposed AD by February 12, 2016.
submitted pursuant to § 429.12(b)(6). manufacturer (OEM) of the covered ADDRESSES: You may send comments,
* * * * * product or equipment being imported as using the procedures found in 14 CFR
■ 5. Section 429.12 is amended by
defined in § 429.2 and, in the case of 11.43 and 11.45, by any of the following
revising paragraph (b)(6) to read as electric motors, the Compliance methods:
follows: Certification number; and • Federal eRulemaking Portal: Go to
(6) A contact name and email address http://www.regulations.gov. Follow the
§ 429.12. General requirements applicable of the importer of record. instructions for submitting comments.
to certification reports. (e) If the importer has submitted a • Fax: 202–493–2251.
* * * * * certification report for the basic model • Mail: U.S. Department of
(b) * * * of the product or equipment being Transportation, Docket Operations, M–
jstallworth on DSK7TPTVN1PROD with PROPOSALS
(6) For each brand, the basic model imported pursuant to § 429.12, the 30, West Building Ground Floor, Room
number and the individual model certification of admissibility must W12–140, 1200 New Jersey Avenue SE.,
number(s) in that basic model with the include: Washington, DC 20590.
following exceptions: For walk-in (1)The CCMS ticket number of the • Hand Delivery: U.S. Department of
coolers, the basic model number for most recent certification submission; Transportation, Docket Operations, M–
each brand must be submitted. For (2)The CCMS attachment 30, West Building Ground Floor, Room
distribution transformers, the basic identification number assigned to the W12–140, 1200 New Jersey Avenue SE.,
model number or kVA grouping model certification submission; Washington, DC, between 9 a.m. and 5
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![Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Proposed Rules 81217
p.m., Monday through Friday, except for the Member States of the European the MCAI in the AD docket on the
Federal holidays. Union, has issued EASA Airworthiness Internet at http://www.regulations.gov
For service information identified in Directive 2015–0082, dated May 11, by searching for and locating Docket No.
this proposed AD, contact Airbus SAS, 2015 (referred to after this as the FAA–2015–7533.
Airworthiness Office—EAL, 1 Rond Mandatory Continuing Airworthiness
Point Maurice Bellonte, 31707 Blagnac Related Service Information Under 1
Information, or ‘‘the MCAI’’), to correct
Cedex, France; telephone +33 5 61 93 36 CFR Part 51
an unsafe condition on certain Airbus
96; fax +33 5 61 93 45 80; email Model A330–200 and –300 series We have reviewed the following
airworthiness.A330-A340@airbus.com; airplanes, Model A330–200 Freighter service information.
Internet http://www.airbus.com. You series airplanes, and Airbus Model • Airbus AOT A71L004–14, Revision
may view this referenced service A340–541 and A340–642 airplanes. The 01, dated April 7, 2014. The service
information at the FAA, Transport MCAI states: information describes procedures for
Airplane Directorate, 1601 Lind Avenue doing a one-time torque check to
In 2013, during a pre-delivery test on an
SW., Renton, WA. For information on A330 aeroplane fitted with Pratt & Whitney
determine if there are any loose or fully
the availability of this material at the (PW) PW4170 engines, an issue with N1 broken engine mount pylon bolts at four
FAA, call 425–227–1221. vibrations level on [engine] ENG1 was positions at the forward engine pylon 1
identified. While performing an engine and pylon 2 of Airbus Model A330
Examining the AD Docket removal, one forward engine mount bolt was series airplanes having Pratt and
You may examine the AD docket on found improperly torqued. The investigation Whitney engines, doing corrective
the Internet at http:// concluded this was due to a production line actions, and reporting all findings.
www.regulations.gov by searching for engine installation quality issue. Further • Airbus AOT A71L005–14, Revision
and locating Docket No. FAA–2015– analysis showed that some aeroplanes,
delivered between June 2006 and January
01, dated December 11, 2014. The
7533; or in person at the Docket 2014, may have had the rear (AFT) and service information describes
Management Facility between 9 a.m. forward (FWD) engine mount bolts procedures for doing a one-time torque
and 5 p.m., Monday through Friday, improperly torqued. check to determine if there are any loose
except Federal holidays. The AD docket This condition, if not detected and or fully broken engine mount pylon
contains this proposed AD, the corrected, could ultimately lead to an in- bolts at four positions at the forward
regulatory evaluation, any comments flight detachment of the engine from the engine pylon 1 and pylon 2 of Airbus
received, and other information. The aeroplane, possibly resulting in damage to Model A330 series airplanes having
street address for the Docket Operations the aeroplane and/or injury to persons on the
ground. Trent 700 engines, doing corrective
office (telephone 800–647–5527) is in Prompted by these findings, Airbus issued actions, and reporting all findings.
the ADDRESSES section. Comments will four Alert Operators Transmissions (AOT) • Airbus AOT A71L006–14, dated
be available in the AD docket shortly A71L004–14 (for A330 aeroplanes fitted Pratt July 22, 2014. The service information
after receipt. & Whitney (PW) engines), AOT A71L006–14 describes procedures for doing a one-
FOR FURTHER INFORMATION CONTACT: (for A330 aeroplanes fitted with General time torque check to determine if there
Vladimir Ulyanov, Aerospace Engineer, Electric (GE) engines), AOT A71L005–14 (for are any loose or fully broken engine
International Branch, ANM–116, A330 aeroplanes fitted with Rolls Royce (RR) mount pylon bolts at five FWD and four
Trent 700 engines) and AOT A71L008–14
Transport Airplane Directorate, FAA, (for A340 aeroplanes fitted with RR Trent 500 AFT positions at the forward engine
1601 Lind Avenue SW., Renton, WA engines) to provide torque check pylon 1 and pylon 2 of Airbus Model
98057–3356; telephone 425–227–1138; instructions. A330 series airplanes having GE
fax 425–227–1149. For the reasons described above, this engines, doing corrective actions, and
SUPPLEMENTARY INFORMATION: [EASA] AD requires a one-time torque check reporting all findings.
of the FWD and AFT engine mount bolts and, • Airbus AOT A71L008–14, Revision
Comments Invited depending on findings, [corrective actions] 01, dated December 18, 2014. The
We invite you to send any written re-torque of the affected bolt(s) and/or service information describes
replacement of all four bolts and associated
relevant data, views, or arguments about nuts.
procedures for doing a one-time torque
this proposed AD. Send your comments check to determine if there are any loose
to an address listed under the Findings (or discrepancies) include or fully broken engine mount pylon
ADDRESSES section. Include ‘‘Docket No. one bolt that is loose or able to rotate, bolts at four positions at the forward
FAA–2015–7533; Directorate Identifier two or more bolts that are loose or able engine pylon 1 and pylon 2 of Airbus
2015–NM–080–AD’’ at the beginning of to rotate, or one or more pylon bolts that Model A340 series airplanes having
your comments. We specifically invite are fully broken. Corrective actions Trent 500 engines, doing corrective
comments on the overall regulatory, include re-torqueing the affected bolt(s), actions, and reporting all findings.
economic, environmental, and energy and replacing all bolts and associated This service information is reasonably
aspects of this proposed AD. We will nuts with new bolts and nuts on the available because the interested parties
consider all comments received by the engine where the loose or fully broken have access to it through their normal
closing date and may amend this bolt(s) were detected. This proposed AD course of business or by the means
proposed AD based on those comments. specifies reporting of all findings identified in the ADDRESSES section of
We will post all comments we (including no discrepancies). The this NPRM.
receive, without change, to http:// corrective actions include re-torqueing
loose bolts before further flight. The Other Related Rulemaking
jstallworth on DSK7TPTVN1PROD with PROPOSALS
www.regulations.gov, including any
personal information you provide. We compliance times for replacing loose or On June 21, 2013, we issued AD
will also post a report summarizing each fully broken bolts ranges, depend on 2013–14–04, Amendment 39–17509 (78
substantive verbal contact we receive airplane configuration, and range from FR 68352, November 14, 2013). AD
about this proposed AD. before further flight if more than one 2013–14–04 requires a torque check of
bolt rotates or is fully broken to no later forward engine mount bolts, and
Discussion than 2,350 flight cycles or 24,320 flight replacement if necessary on all Airbus
The European Aviation Safety hours since first flight of the airplane, if Model A330–223F, –223, –321, –322,
Agency, which is the Technical Agent only one bolt rotates. You may examine and –323 airplanes. AD 2013–14–04 was
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![81218 Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Proposed Rules
prompted by a fatigue load analysis that should be directed to the FAA at 800 PART 39—AIRWORTHINESS
determined that the inspection interval Independence Ave. SW., Washington, DIRECTIVES
for certain pylon bolts must be reduced. DC 20591, ATTN: Information
We issued AD 2013–04–04 to detect and Collection Clearance Officer, AES–200. ■ 1. The authority citation for part 39
correct loose or broken bolts, which continues to read as follows:
Authority for This Rulemaking
could lead to engine detachment in- Authority: 49 U.S.C. 106(g), 40113, 44701.
flight, and damage to the airplane. Title 49 of the United States Code
specifies the FAA’s authority to issue § 39.13 [Amended]
FAA’s Determination and Requirements
of This Proposed AD rules on aviation safety. Subtitle I, ■ 2. The FAA amends § 39.13 by adding
section 106, describes the authority of the following new airworthiness
This product has been approved by the FAA Administrator. ‘‘Subtitle VII: directive (AD):
the aviation authority of another Aviation Programs,’’ describes in more Airbus: Docket No. FAA–2015–7533;
country, and is approved for operation detail the scope of the Agency’s Directorate Identifier 2015–NM–080–AD.
in the United States. Pursuant to our authority.
bilateral agreement with the State of (a) Comments Due Date
Design Authority, we have been notified We are issuing this rulemaking under We must receive comments by February
of the unsafe condition described in the the authority described in ‘‘Subtitle VII, 12, 2016.
MCAI and service information Part A, Subpart III, Section 44701:
General requirements.’’ Under that (b) Affected ADs
referenced above. We are proposing this
section, Congress charges the FAA with None.
AD because we evaluated all pertinent
information and determined an unsafe promoting safe flight of civil aircraft in (c) Applicability
condition exists and is likely to exist or air commerce by prescribing regulations
This AD applies to the Airbus airplanes
develop on other products of these same for practices, methods, and procedures specified in paragraphs (c)(1) through (c)(5)
type designs. the Administrator finds necessary for of this AD, certificated in any category, from
safety in air commerce. This regulation manufacturer serial number (MSN) 0715
Costs of Compliance is within the scope of that authority through MSN 1507 inclusive, and MSN 1509,
We estimate that this proposed AD because it addresses an unsafe condition except airplanes on which all engines have
affects 55 airplanes of U.S. registry. that is likely to exist or develop on been removed and/or replaced since the date
We also estimate that it would take products identified in this rulemaking of the first flight of the airplane.
about 12 work-hours per product to action. (1) Airbus Model A330–201, –202, –203,
–223, and –243 airplanes.
comply with the basic requirements of Regulatory Findings (2) Airbus Model A330–223F and –243F
this proposed AD, and 1 work-hour per airplanes.
product to report torque check findings. We determined that this proposed AD (3) Airbus Model A330–301, –302, –303,
The average labor rate is $85 per work- would not have federalism implications –321, –322, –323, –341, –342, and –343
hour. Based on these figures, we under Executive Order 13132. This airplanes.
estimate the cost of this proposed AD on proposed AD would not have a (4) Airbus Model A340–541 airplanes.
U.S. operators to be $60,755, or $1,105 substantial direct effect on the States, on (5) Airbus Model A340–642 airplanes.
per product. the relationship between the national (d) Subject
In addition, we estimate that any Government and the States, or on the Air Transport Association (ATA) of
necessary follow-on actions would take distribution of power and America Code 71, Powerplant.
about 20 work-hours and require parts responsibilities among the various
costing $90,200 for a cost of $91,900 per levels of government. (e) Reason
product. We have no way of For the reasons discussed above, I This AD was prompted by a report of an
determining the number of aircraft that under-torqued forward engine mount bolt.
certify this proposed regulation: We are issuing this AD to detect and correct
might need these actions.
1. Is not a ‘‘significant regulatory improperly torqued engine mount bolts,
Paperwork Reduction Act action’’ under Executive Order 12866; which could lead to detachment of the
A federal agency may not conduct or engine from the airplane during flight; and
2. Is not a ‘‘significant rule’’ under the consequent damage to the airplane and injury
sponsor, and a person is not required to DOT Regulatory Policies and Procedures to persons on the ground.
respond to, nor shall a person be subject (44 FR 11034, February 26, 1979);
to penalty for failure to comply with a (f) Compliance
3. Will not affect intrastate aviation in
collection of information subject to the Alaska; and Comply with this AD within the
requirements of the Paperwork compliance times specified, unless already
Reduction Act unless that collection of 4. Will not have a significant done.
information displays a current valid economic impact, positive or negative,
on a substantial number of small entities (g) Definition of Affected Engine
OMB control number. The control
under the criteria of the Regulatory For the purpose of this AD, an affected
number for the collection of information engine is an engine that has never been
required by this proposed AD is 2120– Flexibility Act.
removed and/or replaced since first flight of
0056. The paperwork cost associated List of Subjects in 14 CFR Part 39 the airplane.
with this proposed AD has been
detailed in the Costs of Compliance Air transportation, Aircraft, Aviation (h) Action for Airbus Model A330 Airplanes
jstallworth on DSK7TPTVN1PROD with PROPOSALS
safety, Incorporation by reference, Equipped With Pratt and Whitney (PW)
section of this document and includes Engines
time for reviewing instructions, as well Safety.
as completing and reviewing the (1) For Model A330–200, –200 Freighter,
The Proposed Amendment and –300 series airplanes equipped with PW
collection of information. Therefore, all engines: At the earlier of the times specified
reporting associated with this proposed Accordingly, under the authority in paragraph (h)(1)(i) and (h)(1)(ii) of this AD,
AD is mandatory. Comments concerning delegated to me by the Administrator, accomplish a one-time torque check of the
the accuracy of this burden and the FAA proposes to amend 14 CFR part forward (FWD) and rear (AFT) engine mount
suggestions for reducing the burden 39 as follows: bolts on each affected engine, at the locations
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![81220 Federal Register / Vol. 80, No. 249 / Tuesday, December 29, 2015 / Proposed Rules
and in accordance with the instructions of with the ‘‘Reporting’’ section of the person is not required to respond to, nor
Section 4.2.2, ‘‘Inspection Requirements,’’ of applicable service information specified in shall a person be subject to a penalty for
Airbus AOT A71L005–14, Revision 01, dated paragraphs (h), (j), (k), and (l) of this AD. failure to comply with a collection of
December 11, 2014. (1) If the torque check was done on or after information subject to the requirements of
(2) If, during the torque check required by the effective date of this AD: Submit the the Paperwork Reduction Act unless that
paragraph (k)(1) of this AD, any discrepancy report within 30 days after the torque check. collection of information displays a current
is detected (one bolt rotates, two or more (2) If the torque check was done before the valid OMB Control Number. The OMB
bolts rotate, or one or more bolts are fully effective date of this AD: Submit the report Control Number for this information
broken): Within the compliance time within 30 days after the effective date of this collection is 2120–0056. Public reporting for
specified in Airbus AOT A71L005–14, AD. this collection of information is estimated to
Revision 01, dated December 11, 2014, be approximately 5 minutes per response,
(o) Credit for Previous Actions
accomplish all applicable corrective actions including the time for reviewing instructions,
in accordance with the instructions of (1) This paragraph provides credit for the completing and reviewing the collection of
Section 4.2.3, ‘‘Findings,’’ of Airbus AOT actions required by paragraph (h) of this AD, information. All responses to this collection
A71L005–14, Revision 01, dated December if those actions were performed before the of information are mandatory. Comments
11, 2014, except as required by paragraphs effective date of this AD using Airbus AOT concerning the accuracy of this burden and
(m)(1) and (m)(2) of this AD. A71L004–14, dated April 1, 2014 (for Airbus suggestions for reducing the burden should
Model A330 Airplanes Equipped with Pratt be directed to the FAA at: 800 Independence
(l) Action for Airbus Model A340–541 and and Whitney Engines), which is not Ave. SW., Washington, DC 20591, Attn:
–642 Airplanes Equipped With Rolls-Royce incorporated by reference in this AD. Information Collection Clearance Officer,
Trent 500 Engines (2) This paragraph provides credit for the AES–200.
(1) For Airbus Model A340–541 and –642 actions required by paragraph (k) of this AD,
airplanes equipped with Rolls-Royce Trent if those actions were performed before the (q) Related Information
500 Engines: Within 2,000 flight hours after effective date of this AD using Airbus AOT (1) Refer to Mandatory Continuing
the effective date of this AD, accomplish a A71L005–14, dated September 29, 2014 (for Airworthiness Information (MCAI) EASA
one-time torque check of FWD and AFT Airbus Model A330 Airplanes Equipped with Airworthiness Directive 2015–0082, dated
engine mount bolts on each affected engine, Rolls-Royce Trent 700 Engines), which is not May 11, 2015, for related information. This
at the locations specified in, and in incorporated by reference in this AD. MCAI may be found in the AD docket on the
accordance with the instructions of Section (3) This paragraph provides credit for the Internet at http://www.regulations.gov by
4.2.2, ‘‘Inspection requirements,’’ of Airbus actions required by paragraph (l) of this AD, searching for and locating Docket No. FAA–
AOT A71L008–14, Revision 01, dated if those actions were performed before the 2015–7533.
December 18, 2014. effective date of this AD using Airbus AOT (2) For service information identified in
(2) If, during the torque check required by A71L008–14, dated September 29, 2014 (for this AD, contact Airbus SAS, Airworthiness
paragraph (l)(1) of this AD, any discrepancy Airbus Model A340 Airplanes Equipped with Office—EAL, 1 Rond Point Maurice Bellonte,
is detected (one bolt rotates, two or more Rolls-Royce Trent 500 Engines), which is not 31707 Blagnac Cedex, France; telephone +33
bolts rotate, or one or more bolts are fully incorporated by reference in this AD. 5 61 93 36 96; fax +33 5 61 93 45 80; email
broken): Within the compliance time (p) Other FAA AD Provisions airworthiness.A330-A340@airbus.com;
specified in Airbus AOT A71L008–14, Internet http://www.airbus.com. You may
Revision 01, dated December 18, 2014, The following provisions also apply to this view this service information at the FAA,
accomplish all applicable corrective actions, AD: Transport Airplane Directorate, 1601 Lind
in accordance with the instructions of (1) Alternative Methods of Compliance Avenue SW., Renton, WA. For information
Section 4.2.3, ‘‘Findings,’’ of Airbus AOT (AMOCs): The Manager, International on the availability of this material at the
A71L008–14, Revision 01, dated December Branch, ANM–116, Transport Airplane FAA, call 425–227–1221.
18, 2014, except as required by paragraphs Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested Issued in Renton, Washington, on
(m)(1) and (m)(2) of this AD.
using the procedures found in 14 CFR 39.19. December 18, 2015.
(m) Service Information Exceptions In accordance with 14 CFR 39.19, send your Jeffrey E. Duven,
(1) Where Airbus AOTs A71L005–14, request to your principal inspector or local Manager, Transport Airplane Directorate,
Revision 01, dated December 11, 2014; Flight Standards District Office, as Aircraft Certification Service.
A71L006–14, dated July 22, 2014; and appropriate. If sending information directly
[FR Doc. 2015–32547 Filed 12–28–15; 8:45 am]
A71L008–14, dated September 29, 2014, to the International Branch, send it to ATTN:
Vladimir Ulyanov, Aerospace Engineer, BILLING CODE 4910–13–P
specify to contact Airbus for further actions,
before further flight, repair using a method International Branch, ANM–116, Transport
approved by the Manager, International Airplane Directorate, FAA 1601 Lind Avenue
Branch, ANM–116, Transport Airplane SW., Renton, WA 98057–3356; telephone DEPARTMENT OF TRANSPORTATION
Directorate, FAA; or the European Aviation 425–227–1138; fax 425–227–1149.
Safety Agency (EASA); or Airbus’s EASA Information may be emailed to: 9-ANM-116- Federal Aviation Administration
Design Organization Approval (DOA). AMOC-REQUESTS@faa.gov. Before using
(2) Where Airbus AOT A71L004–14, any approved AMOC, notify your appropriate 14 CFR Part 39
Revision 01, dated April 7, 2014; AOT principal inspector, or lacking a principal
A71L005–14, Revision 01, dated December inspector, the manager of the local flight [Docket No. FAA–2015–7531; Directorate
11, 2014; AOT A71L006–14, dated July 22, standards district office/certificate holding Identifier 2015–NM–052–AD]
2014; and AOT A71L008–14, Revision 01, district office. The AMOC approval letter
RIN 2120–AA64
dated December 18, 2014, specify actions ‘‘if must specifically reference this AD.
one pylon bolt fully broken,’’ this AD (2) Contacting the Manufacturer: For any
Airworthiness Directives; The Boeing
requires that those actions be done if one or requirement in this AD to obtain corrective
actions from a manufacturer, the action must Company Airplanes
more pylon bolt is found fully broken during
any torque check required by paragraph be accomplished using a method approved
jstallworth on DSK7TPTVN1PROD with PROPOSALS
AGENCY: Federal Aviation
(h)(1), (j)(1), (k)(1) or (l)(1) of this AD. by the Manager, International Branch, ANM– Administration (FAA), DOT.
116, Transport Airplane Directorate, FAA; or
(n) Reporting the European Aviation Safety Agency ACTION: Notice of proposed rulemaking
At the applicable time specified in (EASA); or Airbus’s EASA Design (NPRM).
paragraphs (n)(1) and (n)(2) of this AD: After Organization Approval (DOA). If approved by
accomplishment of any torque check the DOA, the approval must include the SUMMARY: We propose to adopt a new
required by paragraphs (h), (j), (k), and (l) of DOA-authorized signature. airworthiness directive (AD) for certain
this AD, report all inspection results to (3) Reporting Requirements: A federal The Boeing Company Model 787–8
Airbus, including no findings, in accordance agency may not conduct or sponsor, and a airplanes. This proposed AD was
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Document Created: 2015-12-29 10:15:30
Document Modified: 2015-12-29 10:15:30
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by February 12, 2016. | |
| 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. | |
| FR Citation | 80 FR 81216 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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