AD 2016-11-01

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.

(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.

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.

(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.

(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.

(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.

(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.

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.