2017-04-09: Powerplant

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 removing Airworthiness Directive (AD) 2012-22-12, Amendment 39-17248 (77 FR 67263, November 9, 2012), and adding the following new AD: 2017-04-09 Airbus: Amendment 39-18804; Docket No. FAA-2016-9305; Directorate Identifier 2016-NM-073-AD. (a) Effective Date This AD is effective March 29, 2017. (b) Affected ADs This AD replaces AD 2012-22-12, Amendment 39-17248 (77 FR 67263, November 9, 2012) (``AD 2012-22-12''). (c) Applicability This AD applies to Airbus Model A330-243, -243F, -341, -342, and -343 airplanes, certificated in any category, all serial numbers. (d) SubjectAir Transport Association (ATA) of America Code 71, Powerplant. (e) Reason This AD was prompted by reports of cracking of air intake cowls on Rolls-Royce Trent engines, worn and detached attachment links, and fractured thermal anti-ice (TAI) piccolo tubes, and loose, or missing attachment rivets of the inner boundary angles (IBAs) and the outer boundary angles (OBAs) of the forward bulkhead. We are issuing this AD to detect and correct degraded structural integrity of the engine nose cowl, which in the case of forward bulkhead damage in conjunction with a broken piccolo tube, could lead to damage to the engine and operation in icing conditions with reduced TAI performance. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Affected Engine Air Intake Nose Cowl Assemblies The engine air intake nose cowl assemblies affected by this AD have part numbers (P/N) SJ30020, P/N SJ30361, P/N SJ30687, P/N SJ30810, and P/N SJ30811, as specified in Rolls-Royce Service Bulletin RB.211-71-H205, dated July 7, 2014. (1) The engine air intake nose cowl assemblies having P/N SJ30020, P/N SJ30361, and P/N SJ30687 can be modified (reworked and re-identified as P/N SJ30810 (for P/N SJ30020 and P/N SJ30361) and P/N SJ30811 (for P/N SJ30687)), as specified in Rolls-Royce Service Bulletin RB.211-71-H205, dated July 7, 2014. (2) The engine air intake nose cowl assemblies having P/N SJ30810 and P/N SJ30811 can be modified (reworked and re-identified as P/N SJ30820 and P/N SJ30821, respectively), as specified in Rolls-Royce Service Bulletin RB.211-71-H847, dated December 2, 2014. (h) Inspections, Related Investigative Actions, and Corrective Actions For airplanes in pre-Airbus Modification 204615 and pre-Airbus Service Bulletin A330-71-3032 configuration: At the applicable times specified in paragraph (h)(1) or (h)(2) of this AD, do a special detailed inspection of the piccolo tube and affected mount links, the aft side of the forward bulkhead, and the IBAs and OBAs of the affected engine air intake cowl assemblies specified in paragraph (g) of this AD; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-71-3025, Revision 02, dated December 9, 2015, except as required by paragraph (i) of this AD. Do all applicable related investigative and corrective actions at the applicable time specified in paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A330-71-3025, Revision 02, dated December 9, 2015. Repeat the inspections of the piccolo tube and affected mount links, the aft side of the forward bulkhead, and the IBAs and OBAs of the engine air intake cowl assemblies thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A330-71-3025, Revision 02, dated December 9, 2015. Accomplishment of corrective actions does not constitute terminating action for the repetitive inspections required by this paragraph. (1) For any engine air intake cowl assembly that has accumulated fewer than 5,000 flight cycles since its first installation on an airplane as of the effective date of this AD: Inspect within 24 months after the engine air intake cowl assembly has accumulated 5,000 total flight cycles. (2) For any engine air intake cowl assembly that has accumulated 5,000 or more flight cycles since its first installation on an airplane as of the effective date of this AD: Inspect within 24 months after the effective date of this AD. (i) Service Information Exception Where Airbus Service Bulletin A330-71-3025, Revision 02, dated December 9, 2015, specifies to contact Bombardier Aerospace--Shorts for instructions, 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). (j) Optional Terminating Action Modification of an airplane in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-71-3032, dated December 10, 2014, constitutes terminating action for the repetitive inspections required by paragraph (h) of this AD for the modified airplane only. (k) Parts Installation Limitation As of the effective date of this AD, any pre-Airbus Modification 204615 part may be installed on any airplane provided that, at the earlier of the applicable times specified in paragraphs (h)(1) and (h)(2) of this AD following installation, the actions required by [[Page 11307]] paragraph (h) of this AD have been accomplished on the pre-Airbus Modification 204615 part. (l) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A330-71-3025, dated January 10, 2011, which was incorporated by reference in AD 2012-22- 12; or Airbus Service Bulletin A330-71-3025, Revision 01, dated October 24, 2012, which is not incorporated by reference in this AD; provided that, within 1,050 flight cycles after the effective date of this AD, a special detailed inspection for pulled, loose, and missing attachment rivets of the IBAs and OBAs of the forward bulkhead is accomplished; and all applicable corrective actions are done; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-71-3033, dated December 14, 2015. Do all applicable corrective actions before further flight. Accomplishment of corrective actions does not constitute terminating action for the repetitive inspections required by paragraph (h) of this AD. (m) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information may be emailed to: [email protected]. (i) 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. (ii) AMOCs approved previously for AD 2012-22-12 are not approved as AMOCs with this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016-0086R1, dated May 13, 2016, 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-2016-9305. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(3) and (o)(5) of this AD. (o) 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 Service Bulletin A330-71-3025, Revision 02, dated December 9, 2015. (ii) Airbus Service Bulletin A330-71-3032, dated December 10, 2014. (iii) Airbus Service Bulletin A330-71-3033, dated December 14, 2015. (iv) Rolls-Royce Service Bulletin RB.211-71-H205, dated July 7, 2014. (v) Rolls-Royce Service Bulletin RB.211-71-H847, dated December 2, 2014. (3) For Airbus 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 [email protected]; Internet http://www.airbus.com. (4) For Rolls-Royce service information identified in this AD, contact Rolls-Royce Plc, Technical Publications, P.O. Box 31, Derby, DE24 8BJ, United Kingdom; telephone 44 (0) 1332 245882; fax 44 (0) 1332 249936; Internet http://www.Rolls-Royce.com. (5) 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. (6) 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.