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):
2017-20-09 General Electric Company: Amendment 39-19066; Docket No. FAA-2017-0254; Product Identifier 2017-NE-10-AD.
(a) Effective Date
This AD is effective November 13, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all General Electric Company (GE) CF34-8E2; CF34-8E2A1; CF34-8E5; CF34-8E5A1; CF34-8E5A2; CF34-8E6; and CF34- 8E6A1 model turbofan engines.
(d) Subject
Joint Aircraft System Component (JASC), 7270, Turbine Engine Bypass Section.
(e) Unsafe Condition
This AD was promptedby a report that using a certain repair procedure for the fan outlet guide vane (OGV) frame could alter the strength capability of the fan OGV frame. We are issuing this AD to prevent failure of the fan OGV frame, engine separation, and loss of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified, unless already done.
(g) Required Actions
(1) For engines with a fan OGV frame installed that was repaired using GE CF34-8E Engine Manual, GEK 112031, 72-00-23, REPAIR 006:
(i) If the fan OGV frame has 24,900 cycles since new (CSN) or more on the effective date of this AD, remove the OGV frame from service within 100 cycles after the effective date of this AD.
(ii) If the OGV frame has less than 24,900 CSN on the effective date of this AD, remove the fan OGV frame from service at the next shop visit after the effective date of this AD, or before exceeding 25,000 CSN, whichever occurs earlier.
(2) After the effective date of this AD, do not install a fan OGV frame that was repaired using GE CF34-8E Engine Manual, GEK 112031, 72-00-23, REPAIR 006.
(h) 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.
(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 certification office, send it to the attention of the person identified in paragraph (j)(1) of this AD. You may email your request to:
[email protected].
(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the managerof the local flight standards district office/certificate holding district office.
(j) Related Information
(1) For more information about this AD, contact David Bethka, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7129; fax: 781-238-7199; email:
[email protected].
(2) For General Electric service information identified in this AD, contact General Electric Company, GE-Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215, phone: 513-552-3272; fax: 513- 552-3329; email:
[email protected]. You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125.
(k) Material Incorporated by Reference
None.
