2018-07-05: Turbine Section

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): 2018-07-05 General Electric Company: Amendment 39-19236; Docket No. FAA-2017-0668; Product Identifier 2017-NE-17-AD. (a) Effective Date This AD is effective May 11, 2018. (b) Affected ADs None. [[Page 14743]] (c) Applicability This AD applies to General Electric (GE) CF6-80A, -80A1, -80A2, and -80A3 turbofan engines with low-pressure turbine (LPT) stage 3 nozzles, part numbers (P/Ns) 9290M52P05 and 9290M52P06, installed. (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine Section. (e) Unsafe Condition This AD was prompted by high cycle fatigue (HCF) cracking of the LPT stage 3 nozzles resulting in LPT uncontainment. We are issuing this AD to prevent cracking of the LPT stage 3 nozzles. The unsafe condition, if not addressed, could result in LPT uncontainment, damage to the engine, and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions Within 36 months or during the next engine shop visit after the effective date of this AD, whichever occurs later, replace LPT stage 3 nozzles, P/Ns 9290M52P05 and 9290M52P06, with a part eligible for installation. (h) Definition (1) 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. The separation of engine flanges is not considered an engine shop visit for the following purposes:(i) Transportation of an engine not attached to an aircraft without subsequent engine maintenance. (ii) Removing the turbine rear frame (TRF) for repair of TRF cracking. (iii) Removing the top or bottom high-pressure compressor (HPC) case for HPC airfoil maintenance. (iv) Removing only the accessory gearbox and/or transfer gearbox. (2) Reserved. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO Branch, 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 manager of the ECO Branch, send it to the attention of the person identified in paragraph (j) of this AD. You may email your request to: ANE-AD-AMOC@faa.gov. (2) 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. (j) Related Information For more information about this AD, contact Herman Mak, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7147; fax: 781-238-7199; email: herman.mak@faa.gov. (k) Material Incorporated by Reference None.