2014-16-15: Splines of the high-pressure (HP) fuel pump/metering valve and the module M01 drive gear

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): 2014-16-15 Turbomeca S.A.: Amendment 39-17939; Docket No. FAA-2014- 0219; Directorate Identifier 2014-NE-04-AD. (a) Effective Date This AD becomes effective September 19, 2014. (b) Affected ADs None. (c) Applicability This AD applies to Turbomeca S.A. Makila 2A and Makila 2A1 turboshaft engines with a high-pressure (HP) fuel pump, part number (P/N) 0 298 91 806 0 or P/N 0 298 91 805 0, installed, that have not incorporated Turbomeca modification TU 59. (d) Reason This AD was prompted by the failure of two HP fuelpumps that resulted in engine in-flight shutdowns. We are issuing this AD to prevent failure of the HP fuel pump, which could lead to an in- flight shutdown, damage to the engine, and forced landing or accident. (e) Actions and Compliance Comply with this AD within the compliance times specified, unless already done. (1) Within 25 flight hours (FHs) or 6 months after the effective date of this AD, whichever occurs earlier, clean and visually inspect the splines of the HP fuel pump/metering valve and the module M01 drive gear for wear, corrosion, scaling, pitting, and chafing. (2) Thereafter, reinspect every 100 FHs since-last-inspection. (3) If the HP fuel pump/metering valve or the module M01 drive gear fails the inspection required by this AD, replace it with a part eligible for installation before further flight. (4) After the effective date of this AD, do not install any HP fuel pump, HP fuel pump drive shaft, module M01 drive gear, or module M01 77-tooth gear onto any engine, or install any engine onto any helicopter, unless the HP fuel pump/metering valve and the module M01 drive gear passed the inspection required by paragraph (e) of this AD. (f) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs to this AD. Use the procedures found in 14 CFR 39.19 to make your request. (g) Related Information (1) For more information about this AD, contact Katheryn Malatek, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781-238-7747; fax: 781-238-7199; email: [email protected]. (2) Refer to MCAI European Aviation Safety Agency (EASA) AD 2014-0059, dated March 10, 2014, and EASA AD 2014-0059R1, dated April 15, 2014, for more information. You may examine the MCAIs in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0219-0003. (3) Turbomeca S.A. Mandatory Service Bulletin No. 298 73 2818, Version F, dated March 5, 2014, which is not incorporated by reference in this AD, can be obtained from Turbomeca S.A., using the contact information in paragraph (g)(4) of this AD. (4) For service information identified in this AD, contact Turbomeca, S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 40 00; telex: 570 042; fax: 33 (0)5 59 74 45 15. [[Page 48030]] (5) You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. (h) Material Incorporated by Reference None.