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.

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

4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

• Air transportation
• Aircraft
• Aviation safety
• Incorporation by reference
• Safety

Adoption of the Amendment

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

PART 39—AIRWORTHINESS DIRECTIVES

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

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

2. The FAA amends § 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.

(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.

(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.