2016-17-01: Stage 1 HPT disks

Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends part 39 of the Federal Aviation Regulations (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) 2006-18-14, Amendment 39-14753 (71 FR 52988, September 8, 2006), (``AD 2006-18-14''), and adding the following new AD: 2016-17-01 Rolls-Royce Deutschland Ltd & Co KG (formerly Rolls-Royce plc): Amendment 39-18614; Docket No. FAA-2006-25513; Directorate Identifier 99-NE-61-AD. (a) Effective Date This AD is effective September 27, 2016. (b) Affected ADs This AD supersedes AD 2006-18-14. (c) Applicability This AD applies to Rolls-Royce Deutschland Ltd & Co (RRD) KG Tay 650-15 and Tay 651-54 turbofan engines with stage 1 high-pressure turbine (HPT) disks, part number (P/N) JR32013 or P/N JR33838, or stage 1 low-pressure turbine (LPT) disks, P/N JR32318A, installed. (d) Unsafe Condition This AD was prompted by RRD review of the cyclic life limit of parts affected by AD 2006-18-14 and the RRD conclusion that the stage 1 HPT disk, P/N JR32013, requires further cyclic life limit reduction. We are issuing this AD to prevent failure of stage 1 HPT disks, P/N JR32013 and P/N JR33838, and stage 1 LPT disk, P/N JR32318A, which could result in an uncontained engine failure and damage to the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) Re-calculate the cyclic life of stage 1 HPT disks, P/N JR32013, as follows: (i) If a stage 1 HPT disk, P/N JR32013, was ever operated under a different engine flight plan profile than the engine flight plan profile operated on the last flight, or was ever installed andoperated in a different engine model, do the following: (A) Within 30 days after the effective date of this AD, re- calculate the cyclic life for each stage 1 HPT disk, P/N JR32013. Use the RRD Time Limits Manual (TLM) T-TAY-3RR, Chapter 05, Time Limits, Subject 05-10-01, Task 05-10-01-800-000, Subtask 05-10-01- 860-036, paragraph 1(E) or (1)(F), dated September 15, 2014 to re- calculate the cyclic life. (B) Reserved. (ii) If you change your flight plan profile or install a stage 1 HPT disk, P/N JR32013 or P/N JR33838, or stage 1 LPT disk, P/N JR32318A, into a different engine model after the effective date of this AD, re-calculate the cyclic life within 30 days of making the change. Use the RRD TLM T-TAY-3RR, Chapter 05, Time Limits, Subject 05-10-01, Task 05-10-01-800-000, Subtask 05-10-01-860-036, paragraph 1(E) or (1)(F), dated September 15, 2014 to re-calculate the cyclic life. (2) For engines with a stage 1 HPT disk, P/N JR32013, installed, do the following: (i) Remove from service any stage 1 HPT disk, P/N JR32013, within 100 flight cycles after the effective date of this AD or before exceeding the new, reduced cyclic life limits specified in paragraphs (e)(2)(i)(A) through (e)(2)(i)(E) of this AD, whichever occurs later, as follows: (A) For RRD Tay 650-15 engines operated under engine flight plan profile A, the new, reduced cyclic life limit is 18,900 flight cycles-since-new (FCSN). (B) For RRD Tay 650-15 engines operated under engine flight plan profile B, the new, reduced cyclic life limit is 15,500 FCSN. (C) For RRD Tay 650-15 engines operated under engine flight plan profile C, the new, reduced cyclic life limit is 11,500 FCSN. (D) For RRD Tay 650-15 engines operated under engine flight plan profile D, the new, reduced cyclic life limit is 9,300 FCSN. (E) For RRD Tay 651-54 engines operated under any engine flight plan profile, the new, reduced cyclic life limit is 10,873 FCSN. (ii) Reserved. (3) For engines with a stage 1 HPT disk, P/N JR33838, or stage 1 LPT disk, P/N JR32318A, installed, do the following: (i) Remove from service any stage 1 HPT disk, P/N JR33838, or stage 1 LPT disk, P/N JR32318A, before exceeding the cyclic life limits specified in paragraphs (e)(3)(i)(A) through (e)(3)(i)(E) of this AD, as follows: (A) For RRD Tay 650-15 engines operated under engine flight plan profile A, the cyclic life limit for stage 1 HPT disk, P/N JR33838, and stage 1 LPT disk, P/N JR32318A, is 23,000 FCSN. (B) For RRD Tay 650-15 engines operated under engine flight plan profile B, the cyclic life limit for stage 1 HPT disk, P/N JR33838, and stage 1 LPT disk, P/N JR32318A, is 21,000 FCSN. (C) For RRD Tay 650-15 engines operated under engine flight plan profile C, the cyclic [[Page 57449]] life limit for stage 1 HPT disk, P/N JR33838, and stage 1 LPT disk, P/N JR32318A, is 18,000 FCSN. (D) For RRD Tay 650-15 engines operated under engine flight plan profile D, the cyclic life limitfor stage 1 HPT disk, P/N JR33838, and stage 1 LPT disk, P/N JR32318A, is 14,250 FCSN. (E) For RRD Tay 651-54 engines operated under any engine flight plan profile, the cyclic life limit for stage 1 HPT disk, P/N JR33838, is 14,250 FCSN and the cyclic life limit for stage 1 LPT disk, P/N JR32318A, is 20,000 FCSN. (ii) Reserved. (f) Installation Prohibition After the effective date of this AD, do not install any part identified in paragraph (e) of this AD into any engine, or return any engine to service with any part identified in paragraph (e) of this AD, installed, if the part exceeds the cyclic life limit specified in paragraphs (e)(2) and (e)(3) of this AD. (g) 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. You may email your request to: ANE-AD-AMOC@faa.gov. (h) Related Information (1) For more information about this AD, contact Philip Haberlen, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7770; fax: 781-238-7199; email: philip.haberlen@faa.gov. (2) Refer to MCAI European Aviation Safety Agency, AD 2015-0056, dated March 31, 2015, for more information. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA-2006-25513. (3) Rolls-Royce Deutschland Ltd & Co KG Alert Non-Modification Service Bulletin No. TAY-72-A1821, Revision 1, dated March 26, 2015, which is not incorporated by reference in this AD, can be obtained from Rolls-Royce Deutschland Ltd & Co KG, using the contact information in paragraph (i)(3) of this AD. (4) RRD TLM T-TAY-5RR, Chapter 05-10-01, dated September 15, 2014. (5) You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. (i) 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 Deutschland Ltd & Co KG, Time Limits Manual T- TAY-3RR, Chapter 05, Time Limits, Subject 05-10-01, dated September 15, 2014. (ii) Reserved. (3) For Rolls-Royce Deutschland Ltd & Co KG service information identified in this AD, contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlewitz, 15827 Blankenfelde-Mahlow, Germany; phone: 49-0-33-7086-1064; fax: 49-0-33-7086-3276. (4) You may view this service information at FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on theavailability 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). 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.