2017-19-20: Turbine Engine Compressor 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): 2017-19-20 General Electric Company: Amendment 39-19050; Docket No. FAA-2017-0452; Product Identifier 2017-NE-14-AD. (a) Effective Date This AD is effective October 27, 2017. (b) Affected ADs None. (c) Applicability This AD applies to General Electric Company (GE) CT7-8A and CT7- 9B model turboshaft engines with a high-pressure compressor (HPC) impeller, part number 5123T51P02, and serial number, GLHTPH9G, GLHTPP7P, or GLHTPJHN, installed. (d) Subject Joint Aircraft System Component (JASC) Code 7230, Turbine Engine Compressor Section. (e) Unsafe Condition This AD was prompted by reports from the manufacturer that the HPC impeller installed on these engines may have suffered from material degradation during the manufacturing process. We are issuing this AD to prevent failure of the HPC impeller. [[Page 44301]] This unsafe condition, if not corrected, could result in failure of the HPC impeller, uncontained HPC impeller release, damage to the engine, and damage to the airplane/helicopter. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (1) For CT7-9B engines, remove the affected HPC impeller from service at the next engine shop visit after the effective date of this AD, or prior to accumulating 12,000 cycles since new, whichever is earlier. (2) For CT7-8A engines, remove the affected HPC impeller from service at the next engine shop visit after the effective date of this AD, or prior to accumulating 1,500 engine hours after the effective date of this AD, whichever is earlier. (g) Definition For the purpose of this AD, an ``engine shop visit'' is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine flanges. (h) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, 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. (i) Related Information (1) For more information about this AD, contact Kasra Sharifi, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7773; fax: 781-238-7199; email: kasra.sharifi@faa.gov. (2) GE Service Bulletin CT7-TP S/B 72-0524, dated June 16, 2016, can be obtained from GE using the contact information in paragraph (i)(3) of this AD. (3) For service information identified in this AD, contact General ElectricCompany, GE-Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215; phone: 513-552-3272; fax: 513-552-3329; email: geae.aoc@ge.com. (4) You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781-238-7125. (j) Material Incorporated by Reference None.