81 FR 36443 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 109 (June 7, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 109 (June 7, 2016)
| Page Range | 36443-36447 | |
| FR Document | 2016-12056 |
[Federal Register Volume 81, Number 109 (Tuesday, June 7, 2016)] [Rules and Regulations] [Pages 36443-36447] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-12056] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-7533; Directorate Identifier 2015-NM-080-AD; Amendment 39-18528; AD 2016-11-01] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200 and -300 series airplanes, Model A330-200 Freighter series airplanes, and Model A340-541 and A340-642 airplanes. This AD was prompted by a report of an under-torqued forward engine mount bolt. This AD requires a one-time torque check of the forward and aft engine mount bolts and corrective actions if necessary. 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. DATES: This AD is effective July 12, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of July 12, 2016. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 7533. 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 AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800-647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus Model A330- 200 and -300 series airplanes, Model A330-200 Freighter series airplanes, and Model A340-541 and A340-642 airplanes. The NPRM published in the Federal Register on December 29, 2015 (80 FR 81216) (``the NPRM''). The NPRM was prompted by a report of an under-torqued forward engine mount bolt. The NPRM proposed to require a one-time torque check of the forward and aft engine mount bolts, and corrective actions if necessary. 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. 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 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 [low pressure spool] 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 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, re-torque of the affected [engine mount] bolt(s) and/or replacement of all four [engine mount] bolts and associated nuts. Findings (or discrepancies) include one engine mount bolt that is loose or able to rotate, two or more engine mount bolts that are loose or able to rotate, or one or more engine mount bolts that are fully broken. Corrective actions include re-torqueing the affected engine mount bolt(s), and replacing all engine mount bolts and associated nuts with new engine mount bolts and nuts on the engine where the loose or fully broken engine mount bolt(s) were detected. This AD specifies reporting of all findings (including no discrepancies). The corrective actions include re-torqueing loose engine mount bolts before further flight. 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. [[Page 36444]] Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Changes to the NPRM Paragraphs (h)(1)(ii) and (i) of the proposed AD refer to the accomplishment of Airbus Service Bulletin A330-71-3028, Revision 01, dated February 20, 2012. However, operators might also accomplish Airbus Service Bulletin A330-71-3028, Revision 02, dated August 31, 2015. Therefore, we have revised paragraphs (h)(1)(ii) and (i) of this AD to refer to the actions specified in ``Airbus Service Bulletin A330- 71-3028.'' Paragraph (m)(1) of the proposed AD refers to Airbus AOT A71L008- 14, dated September 29, 2014, and is an exception to the service information specified in paragraph (l) of the proposed AD. However, paragraph (l) of the proposed AD refers to Airbus AOT A71L008-14, Revision 01, dated December 18, 2014. We have revised paragraph (m)(1) of this AD to refer to Airbus AOT A71L008-14, Revision 01, dated December 18, 2014. For consistency, we have also replaced the words ``bolt(s)'' and ``pylon bolt(s)'' in this AD with ``engine mount bolt(s)'' in order to match the language in the MCAI. In the service information referenced in this AD, the term ``pylon'' is also used in some sentences to describe the engine mount bolts. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this AD with the changes described previously and except for minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. 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 bolts at four positions at the forward engine pylon 1 and pylon 2 of Airbus Model A330 series airplanes having PW 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 bolts at four positions at the forward engine pylon 1 and pylon 2 of Airbus Model A330 series airplanes having RR 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 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 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. Costs of Compliance We estimate that this AD affects 55 airplanes of U.S. registry. We also estimate that it will take about 12 work-hours per product to comply with the basic requirements of this 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 AD on U.S. operators to be $60,755, or $1,105 per product. In addition, we estimate that any necessary follow-on actions will 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 Office of Management and Budget (OMB) control number. The control number for the collection of information required by this AD is 2120-0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES-200. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and [[Page 36445]] 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2016-11-01 Airbus: Amendment 39-18528. Docket No. FAA-2015-7533; Directorate Identifier 2015-NM-080-AD. (a) Effective Date This AD is effective July 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 Airbus 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 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 actions specified in Airbus Service Bulletin A330-71-3028, 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 engine mount 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 Airbus 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 engine mount bolt, and, within 2,350 flight cycles or 24,320 flight hours since first flight of the airplane, whichever occurs first, replace the 4 engine mount 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 Airbus 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 engine mount bolt, and within 2,350 flight cycles or 24,320 flight hours since first flight of the airplane, whichever occurs first, replace the 4 engine mount 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 Airbus 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 engine mount bolt and within 2,140 flight cycles or 6,600 flight hours since first flight of the airplane, whichever occurs first, replace the 4 engine mount 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 engine mount 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. (A) Airbus 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) Airbus 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) Airbus 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 engine mount bolts are found that rotate: Before further flight, replace the 4 engine mount 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 engine mount bolts are found fully broken: Before further flight, replace the 4 engine mount 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 engine mount bolt is found that rotates: Before further flight, re-torque the affected engine mount bolt, and replace the 4 engine mount 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 engine mount bolts are found that rotate: Before further flight, replace the 4 engine mount 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 engine mount bolts are found fully broken: Before further flight, replace the 4 engine mount 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. [[Page 36446]] (i) Clarification of Concurrent Actions for Airbus Model A330-223F, A330-223, A330-321, A330-322, and A330-323 Airplanes Equipped With Pratt and Whitney (PW) Engines AD 2013-14-04, Amendment 39-17509 (78 FR 68352, November 14, 2013), requires a torque check of FWD 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, as specified in Airbus Service Bulletin A330-71-3028, within the compliance times specified in paragraph (g) of AD 2013-14-04, perform the torque check of the AFT engine mount bolts at the same time as required by paragraph (h)(1) of this AD. (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 engine mount 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 engine mount bolts, as applicable, and their associated nuts with new engine mount 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 engine mount 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 engine mount 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 engine mount 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 engine mount 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 engine mount bolts and associated nuts with new engine mount 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 engine mount 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 engine mount 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, 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 engine mount bolt rotates, two or more engine mount bolts rotate, or one or more engine mount 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 RR Trent 500 Engines (1) For Airbus Model A340-541 and -642 airplanes equipped with RR 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 engine mount bolt rotates, two or more engine mount bolts rotate, or one or more engine mount 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, Revision 01, dated December 18, 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 engine mount 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 PW 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 RR 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 RR Trent 500 Engines), which is not incorporated by reference in this AD. [[Page 36447]] (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 with14 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 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 Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 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. (r) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus AOT A71L004-14, Revision 01, dated April 7, 2014. (ii) Airbus AOT A71L005-14, Revision 01, dated December 11, 2014. (iii) Airbus AOT A71L006-14, dated July 22, 2014. (iv) Airbus AOT A71L008-14, Revision 01, dated December 18, 2014. (3) 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. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on May 12, 2016. Suzanne Masterson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-12056 Filed 6-6-16; 8:45 am] BILLING CODE 4910-13-P
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(4) You may view this service information +33 5 61 93 36 96; fax +33 5 61 93 45 Union, has issued EASA Airworthiness
at the FAA, Transport Airplane Directorate, 80; email airworthiness.A330–A340@ Directive 2015–0082, dated May 11,
1601 Lind Avenue SW., Renton, WA. For airbus.com; Internet http:// 2015 (referred to after this as the
information on the availability of this www.airbus.com. You may view this Mandatory Continuing Airworthiness
material at the FAA, call 425–227–1221.
(5) You may view this service information
referenced service information at the Information, or ‘‘the MCAI’’), to correct
that is incorporated by reference at the FAA, Transport Airplane Directorate, an unsafe condition on certain Airbus
National Archives and Records 1601 Lind Avenue SW., Renton, WA. Model A330–200 and –300 series
Administration (NARA). For information on For information on the availability of airplanes, Model A330–200 Freighter
the availability of this material at NARA, call this material at the FAA, call 425–227– series airplanes, and Model A340–541
202–741–6030, or go to: http:// 1221. It is also available on the Internet and A340–642 airplanes. The MCAI
www.archives.gov/federal-register/cfr/ibr- at http://www.regulations.gov by states:
locations.html. searching for and locating Docket No. In 2013, during a pre-delivery test on an
Issued in Renton, Washington, on May 12, FAA–2015–7533. A330 aeroplane fitted with Pratt & Whitney
2016. (PW) PW4170 engines, an issue with N1 [low
Examining the AD Docket
Suzanne Masterson, pressure spool] vibrations level on [engine]
Acting Manager, Transport Airplane You may examine the AD docket on ENG1 was identified. While performing an
Directorate, Aircraft Certification Service. the Internet at http:// engine removal, one forward engine mount
[FR Doc. 2016–11928 Filed 6–6–16; 8:45 am] www.regulations.gov by searching for bolt was found improperly torqued. The
BILLING CODE 4910–13–P
and locating Docket No. FAA–2015– investigation concluded this was due to a
7533; or in person at the Docket production line engine installation quality
Management Facility between 9 a.m. issue. Further analysis showed that some
DEPARTMENT OF TRANSPORTATION and 5 p.m., Monday through Friday, aeroplanes, delivered between June 2006 and
except Federal holidays. The AD docket January 2014, may have had the rear (AFT)
Federal Aviation Administration contains this AD, the regulatory and forward (FWD) engine mount bolts
evaluation, any comments received, and improperly torqued.
14 CFR Part 39 other information. The street address for This condition, if not detected and
the Docket Office (telephone 800–647– corrected, could ultimately lead to an in-
[Docket No. FAA–2015–7533; Directorate flight detachment of the engine from the
Identifier 2015–NM–080–AD; Amendment 5527) is Docket Management Facility,
aeroplane, possibly resulting in damage to
39–18528; AD 2016–11–01] U.S. Department of Transportation,
the aeroplane and/or injury to persons on the
Docket Operations, M–30, West
RIN 2120–AA64 ground.
Building Ground Floor, Room W12–140, Prompted by these findings, Airbus issued
Airworthiness Directives; Airbus 1200 New Jersey Avenue SE., four Alert Operators Transmissions (AOT)
Airplanes Washington, DC 20590. A71L004–14 (for A330 aeroplanes fitted PW
FOR FURTHER INFORMATION CONTACT: engines), AOT A71L006–14 (for A330
AGENCY: Federal Aviation Vladimir Ulyanov, Aerospace Engineer, aeroplanes fitted with General Electric (GE)
Administration (FAA), Department of International Branch, ANM–116, engines), AOT A71L005–14 (for A330
Transportation (DOT). Transport Airplane Directorate, FAA, aeroplanes fitted with Rolls Royce (RR) Trent
ACTION: Final rule. 1601 Lind Avenue SW., Renton, WA 700 engines) and AOT A71L008–14 (for A340
98057–3356; telephone 425–227–1138; aeroplanes fitted with RR Trent 500 engines)
SUMMARY: We are adopting a new fax 425–227–1149. to provide torque check instructions.
airworthiness directive (AD) for certain For the reasons described above, this
SUPPLEMENTARY INFORMATION:
Airbus Model A330–200 and –300 series [EASA] AD requires a one-time torque check
airplanes, Model A330–200 Freighter Discussion of the FWD and AFT engine mount bolts and,
series airplanes, and Model A340–541 depending on findings, re-torque of the
We issued a notice of proposed affected [engine mount] bolt(s) and/or
and A340–642 airplanes. This AD was rulemaking (NPRM) to amend 14 CFR
prompted by a report of an under- replacement of all four [engine mount] bolts
part 39 by adding an AD that would and associated nuts.
torqued forward engine mount bolt. apply to certain Airbus Model A330–
This AD requires a one-time torque 200 and –300 series airplanes, Model Findings (or discrepancies) include
check of the forward and aft engine A330–200 Freighter series airplanes, one engine mount bolt that is loose or
mount bolts and corrective actions if and Model A340–541 and A340–642 able to rotate, two or more engine mount
necessary. We are issuing this AD to airplanes. The NPRM published in the bolts that are loose or able to rotate, or
detect and correct improperly torqued Federal Register on December 29, 2015 one or more engine mount bolts that are
engine mount bolts, which could lead to (80 FR 81216) (‘‘the NPRM’’). The fully broken. Corrective actions include
detachment of the engine from the NPRM was prompted by a report of an re-torqueing the affected engine mount
airplane during flight and consequent under-torqued forward engine mount bolt(s), and replacing all engine mount
damage to the airplane and injury to bolt. The NPRM proposed to require a bolts and associated nuts with new
persons on the ground. one-time torque check of the forward engine mount bolts and nuts on the
DATES: This AD is effective July 12, and aft engine mount bolts, and engine where the loose or fully broken
2016. corrective actions if necessary. We are engine mount bolt(s) were detected.
The Director of the Federal Register issuing this AD to detect and correct This AD specifies reporting of all
approved the incorporation by reference improperly torqued engine mount bolts, findings (including no discrepancies).
jstallworth on DSK7TPTVN1PROD with RULES
of certain publications listed in this AD which could lead to detachment of the The corrective actions include re-
as of July 12, 2016. engine from the airplane during flight torqueing loose engine mount bolts
ADDRESSES: For service information and consequent damage to the airplane before further flight. You may examine
identified in this final rule, contact and injury to persons on the ground. the MCAI in the AD docket on the
Airbus SAS, Airworthiness Office— The European Aviation Safety Internet at http://www.regulations.gov
EAL, 1 Rond Point Maurice Bellonte, Agency, which is the Technical Agent by searching for and locating Docket No.
31707 Blagnac Cedex, France; telephone for the Member States of the European FAA–2015–7533.
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4. Will not have a significant (f) Compliance accordance with the instructions of Section
economic impact, positive or negative, Comply with this AD within the 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004–
on a substantial number of small entities compliance times specified, unless already 14, Revision 01, dated April 7, 2014.
under the criteria of the Regulatory done. (iv) For airplanes identified in paragraphs
Flexibility Act. (h)(2)(iv)(A), (h)(2)(iv)(B), and (h)(2)(iv)(C) of
(g) Definition of Affected Engine
this AD: Before further flight, replace the 4
List of Subjects in 14 CFR Part 39 For the purpose of this AD, an affected engine mount bolts and associated nuts in
engine is an engine that has never been
accordance with the instructions of Section
Air transportation, Aircraft, Aviation removed and/or replaced since first flight of
the airplane. 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004–
safety, Incorporation by reference,
14, Revision 01, dated April 7, 2014.
Safety. (h) Action for Airbus Model A330 Airplanes (A) Airbus Model A330–200 and –300
Adoption of the Amendment Equipped With Pratt and Whitney (PW) series airplanes with an average flight time of
Engines greater than 132 minutes and having
Accordingly, under the authority (1) For Airbus Model A330–200, –200 accumulated 2,350 flight cycles or more or
delegated to me by the Administrator, Freighter, and –300 series airplanes equipped 24,320 flight hours or more since first flight
the FAA amends 14 CFR part 39 as with PW engines: At the earlier of the times of the airplane.
follows: specified in paragraph (h)(1)(i) and (h)(1)(ii)
(B) Airbus Model A330–200 and –300
of this AD, accomplish a one-time torque
check of the forward (FWD) and rear (AFT) series airplanes with an average flight time of
PART 39—AIRWORTHINESS 132 minutes or lower and having
engine mount bolts on each affected engine,
DIRECTIVES at the locations specified in, and in accumulated 1,950 flight cycles or more or
accordance with the instructions of Section 20,210 flight hours or more since first flight
■ 1. The authority citation for part 39 4.2.2, ‘‘Inspection Requirements,’’ of Airbus of the airplane.
continues to read as follows: Alert Operators Transmission (AOT) (C) Airbus Model A330–200 Freighter
A71L004–14, Revision 01, dated April 7, series airplanes having accumulated 2,140
Authority: 49 U.S.C. 106(g), 40113, 44701. 2014. flight cycles or more or 6,600 flight hours or
§ 39.13 [Amended] (i) Within 2,000 flight hours after the more since first flight of the airplane.
effective date of this AD.
(3) If, during the torque check required by
■ 2. The FAA amends § 39.13 by adding (ii) During the accomplishment of actions
specified in Airbus Service Bulletin A330– paragraph (h)(1) of this AD, two or more
the following new airworthiness 71–3028, if done after the effective date of FWD engine mount bolts are found that
directive (AD): this AD. rotate: Before further flight, replace the 4
2016–11–01 Airbus: Amendment 39–18528. (2) If, during the torque check required by engine mount bolts and associated nuts in
Docket No. FAA–2015–7533; Directorate paragraph (h)(1) of this AD, only one FWD accordance with the instructions of Section
Identifier 2015–NM–080–AD. engine mount bolt is found that rotates: Do 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004–
the actions specified in paragraph (h)(2)(i), 14, Revision 01, dated April 7, 2014.
(a) Effective Date (h)(2)(ii), (h)(2)(iii), or (h)(2)(iv) of this AD, as (4) If, during the torque check required by
This AD is effective July 12, 2016. applicable. paragraph (h)(1) of this AD, one or more FWD
(i) For Airbus Model A330–200 and -300 engine mount bolts are found fully broken:
(b) Affected ADs series airplanes with an average flight time of
Before further flight, replace the 4 engine
None. greater than 132 minutes and having
accumulated less than 2,350 flight cycles and mount bolts and associated nuts in
(c) Applicability less than 24,320 flight hours since first flight accordance with the instructions of Section
This AD applies to the Airbus airplanes of the airplane: Before further flight, re- 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004–
specified in paragraphs (c)(1) through (c)(5) torque the affected engine mount bolt, and, 14, Revision 01, dated April 7, 2014, except
of this AD, certificated in any category, from within 2,350 flight cycles or 24,320 flight as required by paragraph (m)(2) of this AD.
manufacturer serial number (MSN) 0715 hours since first flight of the airplane, (5) If, during the torque check required by
through MSN 1507 inclusive, and MSN 1509, whichever occurs first, replace the 4 engine paragraph (h)(1) of this AD, only one AFT
except airplanes on which all engines have mount bolts and associated nuts, in engine mount bolt is found that rotates:
been removed and/or replaced since the date accordance with the instructions of Section Before further flight, re-torque the affected
4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004– engine mount bolt, and replace the 4 engine
of the first flight of the airplane.
14, Revision 01, dated April 7, 2014. mount bolts and associated nuts at the next
(1) Airbus Model A330–201, –202, –203,
(ii) For Airbus Model A330–200 and –300 engine removal, in accordance with the
–223, and –243 airplanes. series airplanes with an average flight time of
(2) Airbus Model A330–223F and –243F instructions of Section 4.2.3, ‘‘Findings,’’ of
132 minutes or lower and having
airplanes. accumulated less than 1,950 flight cycles and Airbus AOT A71L004–14, Revision 01, dated
(3) Airbus Model A330–301, –302, –303, less than 20,210 flight hours since first flight April 7, 2014.
–321, –322, –323, –341, –342, and –343 of the airplane: Before further flight, re- (6) If, during the torque check required by
airplanes. torque the affected engine mount bolt, and paragraph (h)(1) of this AD, two or more AFT
(4) Airbus Model A340–541 airplanes. within 2,350 flight cycles or 24,320 flight engine mount bolts are found that rotate:
(5) Airbus Model A340–642 airplanes. hours since first flight of the airplane, Before further flight, replace the 4 engine
(d) Subject whichever occurs first, replace the 4 engine mount bolts and associated nuts in
mount bolts and associated nuts, in accordance with the instructions of Section
Air Transport Association (ATA) of accordance with the instructions of Section 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004–
America Code 71, Powerplant. 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004– 14, Revision 01, dated April 7, 2014.
(e) Reason 14, Revision 01, dated April 7, 2014. (7) If, during the torque check required by
(iii) For Airbus Model A330–200 Freighter
This AD was prompted by a report of an paragraph (h)(1) of this AD, one or more AFT
jstallworth on DSK7TPTVN1PROD with RULES
series airplanes having accumulated less than
under-torqued forward engine mount bolt. engine mount bolts are found fully broken:
2,140 flight cycles and less than 6,600 flight
We are issuing this AD to detect and correct hours since first flight of the airplane: Before Before further flight, replace the 4 engine
improperly torqued engine mount bolts, further flight, re-torque the affected engine mount bolts and associated nuts in
which could lead to detachment of the mount bolt and within 2,140 flight cycles or accordance with the instructions of Section
engine from the airplane during flight, and 6,600 flight hours since first flight of the 4.2.3, ‘‘Findings,’’ of Airbus AOT A71L004–
consequent damage to the airplane and injury airplane, whichever occurs first, replace the 14, Revision 01, dated April 7, 2014, except
to persons on the ground. 4 engine mount bolts and associated nuts, in as required by paragraph (m)(2) of this AD.
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![Federal Register / Vol. 81, No. 109 / Tuesday, June 7, 2016 / Rules and Regulations 36447
(p) Other FAA AD Provisions (2) You must use this service information with flammable fuel vapors, could result
The following provisions also apply to this as applicable to do the actions required by in fuel tank explosions and consequent
AD: this AD, unless this AD specifies otherwise. loss of the airplane.
(1) Alternative Methods of Compliance (i) Airbus AOT A71L004–14, Revision 01,
dated April 7, 2014. DATES: This AD is effective July 12,
(AMOCs): The Manager, International 2016.
Branch, ANM–116, Transport Airplane (ii) Airbus AOT A71L005–14, Revision 01,
dated December 11, 2014. The Director of the Federal Register
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested (iii) Airbus AOT A71L006–14, dated July approved the incorporation by reference
using the procedures found in 14 CFR 39.19. 22, 2014. of a certain publication listed in this AD
In accordance with14 CFR 39.19, send your (iv) Airbus AOT A71L008–14, Revision 01, as of July 12, 2016.
request to your principal inspector or local dated December 18, 2014. ADDRESSES: For service information
Flight Standards District Office, as (3) For service information identified in
identified in this final rule, contact
appropriate. If sending information directly this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte, Fokker Services B.V., Technical
to the International Branch, send it to ATTN:
Vladimir Ulyanov, Aerospace Engineer, 31707 Blagnac Cedex, France; telephone +33 Services Dept., P.O. Box 1357, 2130 EL
International Branch, ANM–116, Transport 5 61 93 36 96; fax +33 5 61 93 45 80; email Hoofddorp, the Netherlands; telephone
Airplane Directorate, FAA 1601 Lind Avenue airworthiness. A330-A340@airbus.com; +31 (0)88–6280–350; fax +31 (0)88–
SW., Renton, WA 98057–3356; telephone Internet http://www.airbus.com. 6280–111; email technicalservices@
425–227–1138; fax 425–227–1149. (4) You may view this service information fokker.com; Internet http://
Information may be emailed to: 9-ANM-116- at the FAA, Transport Airplane Directorate, www.myfokkerfleet.com. You may view
AMOC-REQUESTS@faa.gov. Before using 1601 Lind Avenue SW., Renton, WA. For this referenced service information at
any approved AMOC, notify your appropriate information on the availability of this
the FAA, Transport Airplane
principal inspector, or lacking a principal material at the FAA, call 425–227–1221.
inspector, the manager of the local flight (5) You may view this service information Directorate, 1601 Lind Avenue SW.,
standards district office/certificate holding that is incorporated by reference at the Renton, WA. For information on the
district office. The AMOC approval letter National Archives and Records availability of this material at the FAA,
must specifically reference this AD. Administration (NARA). For information on call 425–227–1221. It is also available
(2) Contacting the Manufacturer: For any the availability of this material at NARA, call on the Internet at http://
requirement in this AD to obtain corrective 202–741–6030, or go to: http:// www.regulations.gov by searching for
actions from a manufacturer, the action must www.archives.gov/federal-register/cfr/ibr- and locating Docket No. FAA–2015–
be accomplished using a method approved locations.html. 8466.
by the Manager, International Branch, ANM–
Issued in Renton, Washington, on May 12,
116, Transport Airplane Directorate, FAA; or
2016. Examining the AD Docket
EASA; or Airbus’s EASA Design
Organization Approval (DOA). If approved by Suzanne Masterson, You may examine the AD docket on
the DOA, the approval must include the Acting Manager, Transport Airplane the Internet at http://
DOA-authorized signature. Directorate, Aircraft Certification Service. www.regulations.gov by searching for
(3) Reporting Requirements: A federal [FR Doc. 2016–12056 Filed 6–6–16; 8:45 am] and locating Docket No. FAA–2015–
agency may not conduct or sponsor, and a BILLING CODE 4910–13–P
8466; or in person at the Docket
person is not required to respond to, nor Management Facility between 9 a.m.
shall a person be subject to a penalty for and 5 p.m., Monday through Friday,
failure to comply with a collection of except Federal holidays. The AD docket
DEPARTMENT OF TRANSPORTATION
information subject to the requirements of contains this AD, the regulatory
the Paperwork Reduction Act unless that
Federal Aviation Administration evaluation, any comments received, and
collection of information displays a current
valid OMB Control Number. The OMB other information. The street address for
Control Number for this information 14 CFR Part 39 the Docket Office (telephone 800–647–
collection is 2120–0056. Public reporting for 5527) is Docket Management Facility,
[Docket No. FAA–2015–8466; Directorate
this collection of information is estimated to Identifier 2015–NM–045–AD; Amendment U.S. Department of Transportation,
be approximately 5 minutes per response, 39–18542; AD 2016–11–15] Docket Operations, M–30, West
including the time for reviewing instructions, Building Ground Floor, Room W12–140,
completing and reviewing the collection of RIN 2120–AA64 1200 New Jersey Avenue SE.,
information. All responses to this collection Washington, DC 20590.
of information are mandatory. Comments Airworthiness Directives; Fokker
concerning the accuracy of this burden and FOR FURTHER INFORMATION CONTACT: Tom
Services B.V. Airplanes
suggestions for reducing the burden should Rodriguez, Aerospace Engineer,
be directed to the FAA at: 800 Independence AGENCY: Federal Aviation International Branch, ANM–116,
Ave. SW., Washington, DC 20591, Attn: Administration (FAA), Department of Transport Airplane Directorate, FAA,
Information Collection Clearance Officer, Transportation (DOT). 1601 Lind Avenue SW., Renton, WA
AES–200. 98057–3356; telephone 425–227–1137;
ACTION: Final rule.
(q) Related Information fax 425–227–1149.
Refer to Mandatory Continuing SUMMARY: We are adopting a new SUPPLEMENTARY INFORMATION:
Airworthiness Information (MCAI) EASA AD airworthiness directive (AD) for all
Fokker Services B.V. Model F28 Mark Discussion
2015–0082, dated May 11, 2015, for related
information. This MCAI may be found in the 0070 and 0100 airplanes. This AD was We issued a notice of proposed
AD docket on the Internet at http:// prompted by the need for more rulemaking (NPRM) to amend 14 CFR
www.regulations.gov by searching for and restrictive fuel system airworthiness part 39 by adding an AD that would
jstallworth on DSK7TPTVN1PROD with RULES
locating Docket No. FAA–2015–7533. limitations. This AD requires revising apply to all Fokker Services B.V. Model
(r) Material Incorporated by Reference the maintenance program or inspection F28 Mark 0070 and 0100 airplanes. The
(1) The Director of the Federal Register program, as applicable, to incorporate NPRM published in the Federal
approved the incorporation by reference certain fuel system airworthiness Register on January 20, 2016 (81 FR
(IBR) of the service information listed in this limitations. We are issuing this AD to 3059) (‘‘the NPRM’’). The NPRM was
paragraph under 5 U.S.C. 552(a) and 1 CFR reduce the potential of ignition sources prompted by the need for more
part 51. inside fuel tanks, which, in combination restrictive fuel system airworthiness
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Document Created: 2018-02-08 07:32:11
Document Modified: 2018-02-08 07:32:11
| 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 | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective July 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 | 81 FR 36443 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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