2013-19-17: Failure of rotating life limited parts

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): 2013-19-17 Rolls-Royce plc: Amendment 39-17599; Docket No. FAA-2013- 0029; Directorate Identifier 2013-NE-01-AD. (a) Effective Date This AD becomes effective November 7, 2013. (b) Affected ADs None. (c) Applicability This AD applies to all Rolls-Royce plc (RR) RB211-535E4-B-37 series turbofan engines. (d) Unsafe Condition This AD was prompted by recalculating the lives of certain rotating life limited parts (LLPs) operated to certain flight profiles. We are issuing this AD to prevent the failure of rotating LLPs, which could result in uncontained failure of the engine and damage to the airplane. (e) Actions and Compliance Comply with this AD within the compliance times specified, unless already done. (1) Within 30 days after the effective date of this AD, for engines that have operated to Flight Profile D or E, recalculate the life of the low-pressure (LP) turbine disc stage 2, intermediate- pressure (IP) compressor rotor shaft (stage 1 to 6), high-pressure (HP) compressor rear rotor shaft assembly, and HP turbine disc installed on that engine. Use the part lives, prorated life formulas, and flight profiles in Appendices 2, 4, and 5 of RR Alert Non-Modification Service Bulletin (NMSB) No. RB.211-72-AG875, dated December 13, 2012, to make that calculation. (2) Within 30 days after the effective date of this AD, for engines that will operate to Flight Profile D or E, assign the maximum approved lives defined in Appendix 2 of RR Alert NMSB No. RB.211-72-AG875, dated December 13, 2012, to the LP turbine disc stage 2, IP compressor rotor shaft (stage 1 to 6), HP compressor rear rotor shaft assembly, and HP turbine disc based on the flight profile that will be flown. (3) For engines that have only operated to, and will continue to operate to, Flight Profile C, as defined in Appendix 5 of RR Alert NMSB No. RB.211-72-AG875, dated December 13, 2012, no further action is required by this AD. (4) After the effective date of this AD, for engines that incorporate an LP turbine disc stage 2, IP compressor rotor shaft (stage 1 to 6), HP compressor rear rotor shaft assembly, or HP turbine disc whose part life is defined by paragraph (e)(1) of this AD, that have an engine shop visit (ESV) before reaching the part life assigned in paragraph (e)(2) of this AD, remove each part from service before the part exceeds the part life assigned in paragraph (e)(2). (5) For those engines that incorporate an LP turbine disc stage 2, IP compressor rotor shaft (stage 1 to 6),HP compressor rear rotor shaft assembly, or HP turbine disc whose part life is defined by paragraph (e)(1) of this AD, that do not have an ESV after the effective date of this AD before the part exceeds the part life assigned in paragraph (e)(2) of this AD, remove the part from service at the next ESV. (f) Installation Prohibition Any LP turbine disc stage 2, IP compressor rotor shaft (stage 1 to 6), HP compressor rear rotor shaft assembly, or HP turbine disc whose part life is defined by paragraph (e)(1) of this AD that is re-installed in any engine after the effective date of this AD must be removed from service before the part exceeds the part life assigned in paragraph (e)(2) of this AD. (g) Definition For the purpose of this AD, ESV is whenever engine maintenance performed prior to reinstallation requires the separation of a pair of major mating engine module flanges. Separation of flanges solely for the purpose of shipment without subsequent internal maintenance is not an ESV. Separation of the external gearbox engine mating flanges or removal of the external gearbox is also not classified as a shop visit. (h) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. (i) Related Information (1) For more information about this AD, contact Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781-238-7754; fax: 781-238-7199; email: robert.green@faa.gov. (2) Refer to European Aviation Safety Agency AD 2012-0265, dated December 18, 2012, for related information. You may examine the AD on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0029-0007. (j) 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 the AD specifies otherwise. (i) Rolls-Royce plc Alert Non-Modification Service Bulletin No. RB.211-72-AG875, dated December 13, 2012. (ii) Reserved. (3) For Rolls-Royce plc service information identified in this AD, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE248BJ; phone: 011-44-1332-242424; fax: 011-44- 1332-249936; email: http://www.rolls-royce.com/contact/civil_team.jsp; or download from https://www.aeromanager.com. (4) You may view this service information at FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. (5) You may view this service information at the National Archives and Records Administration (NARA). Forinformation 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.