2016-06-14: Rotating compressor discharge pressure (CDP) seal

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): 2016-06-14 General Electric Company: Amendment 39-18445; Docket No. FAA-2015-4023; Directorate Identifier 2015-NE-29-AD. (a) Effective Date This AD is effective May 9, 2016. (b) Affected ADs None. (c) Applicability This AD applies to all General Electric Company (GE) CF6-80E1 turbofan engines with rotating compressor discharge pressure (CDP) seals, part number (P/N) 1669M73P02, installed. (d) Unsafe Condition This AD was prompted by reports from the manufacturer of cracks in the teeth of two rotating CDP seals found during engine shop visits. We are issuing this AD to prevent cracking of the CDP seal teeth, which can lead to uncontained part release, damage to the engine, and damage to the airplane. (e) Compliance (1) Comply with this AD within the compliance times specified, unless already done. [[Page 19024]] (2) Strip coating, inspect, and recoat the teeth of the rotating CDP seal, P/N 1669M73P02. Use paragraph 3.C.(2) of GE Service Bulletin (SB) CF6-80E1 S/B 72-0529, Revision 01, dated August 21, 2015 to do the strip coating, inspecting, and recoating, as follows: (i) For engines that have had stationary CDP seal, P/N 1347M28G02, replaced or stationary CDP seal honeycomb repaired; strip coating, inspect, and recoat the teeth of the rotating CDP seal at the next engine shop visit. (ii) For engines that have not had stationary CDP seal, P/N 1347M28G02, replaced or stationary CDP seal honeycomb repaired; strip coating, inspect, and recoat the teeth of the rotating CDP seal at the next part exposure of the rotating CDP seal. (f) Installation Prohibition After the effective date of this AD, do not install any rotating CDP seal, P/N 1669M73P02, that has not had its seal teeth recoated using procedures specified in ESM 72-31-10, REPAIR 002 of GE CF6- 80E1 (GEK99376) Engine Manual, Revision 42, dated March 15, 2014, into any engine. (g) Definitions (1) For the purpose of this AD, exposure of the rotating CDP seal is defined as removal of the compressor rear frame from the high-pressure compressor (HPC) module. (2) For the purpose of this AD, an engine shop visit is defined as the induction of an engine into the shop for maintenance involving the separation of any major mating engine flanges, except that the separation of engine flanges solely for the following purposes is not considered a shop visit: (i) Transportation without subsequent engine maintenance. (ii) Removing the turbine rear frame (TRF) for repair of TRF cracking. (iii) Removing the top or bottom HPC case, or both, for HPC airfoil maintenance. (iv) Removing only the accessory gearbox and/or transfer gearbox. (v) Replacing the high-pressure turbine (HPT) stage 1 blades per CF6-80E1 SB 72-0504 ``Quick-Turn Workscope Procedure to Replace CF6- 80E1 Stage 1 HPT Blades''. (3) For the purpose of this AD, a stationary CDP seal is replaced if at any previous shop visit, the seal has been removed and a different seal is installed. (h) Credit for Previous Action You may take credit for the actions that are required by paragraph (e) of this AD if the actions were performed before the effective date of this AD using the procedures in ESM 72-31-10, REPAIR 002 of the GE CF6-80E1 (GEK99376) Engine Manual, Revision 42, dated March 15, 2014, or earlier versions. (i) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs to this AD. Use the procedures found in 14 CFR 39.19to make your request. You may email your request to: ANE-AD-AMOC@faa.gov. (j) Related Information (1) For more information about this AD, contact Herman Mak, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7147; fax: 781-238-7199; email: herman.mak@faa.gov. (k) 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) General Electric Company Service Bulletin CF6-80E1 S/B 72- 0529, Revision 01, dated August 21, 2015. (ii) Reserved. (3) For GE service information identified in this AD, contact General Electric Company, GE Aviation, Room 285, 1 Neumann Way, Cincinnati, OH45215; phone: 513-552-3272; email: aviation.fleetsupport@ge.com. (4) You may view this service information at FAA, Engine & Propeller Directorate, 1200 District Avenue, 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). 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.