2018-12-01: Engine Fuel and Control

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 removing Airworthiness Directive (AD) 2012-03-11, Amendment 39-16953 (77 FR 8092, February 14, 2012), and adding the following new AD: 2018-12-01 Safran Helicopter Engines (Type Certificate previously held by Turbomeca, S.A.): Amendment 39-19305; Docket No. FAA-2009- 0889; Product Identifier 2009-NE-35-AD. (a) Effective Date This AD is effective September 12, 2018. (b) Affected ADs This AD replaces AD 2012-03-11, Amendment 39-16953 (77 FR 8092, February 14, 2012). (c) Applicability This AD applies to Safran Helicopter Engines, S.A., Arriel 2B and 2B1 turboshaft engines, except those incorporating Modification TU 178. (d) Subject Joint Aircraft System Component (JASC) Code 7300, Engine Fuel and Control. (e) Unsafe Condition This AD was prompted by analysis that indicated the modification of an engine to incorporate Modification TU 178 provides a more effective method than Modification TU [[Page 38953]] 147 to reduce the risk of uncoupling between the low-pressure (LP) fuel pump impeller and the high-pressure (HP) fuel pump shaft of the HP/LP pump and hydro-mechanical metering unit (HMU). We are issuing this AD to prevent failure of the HMU. The unsafe condition, if not corrected, could result in failure of the engine, in-flight shutdown, and loss of the helicopter. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Check the transmissible torque between the LP fuel pump impeller and the HP fuel pump shaft as follows: (i) For pre-Modification TU 147 HMUs, check the torque before accumulating 500 engine flight hours (FHs) since March 11, 2010 or before the next flight after the effective date of this AD, whichever occurs later. Use Paragraph 2.A. of Turbomeca Alert Mandatory Service Bulletin (MSB) A292 73 2830, Version B, dated July 10, 2009 to do the check. (ii) For HMUs that incorporated Modification TU 147 on or before March 31, 2010, and those HMUs not listed in Figure 2 or 3 of Turbomeca Alert MSB A292 73 2836, Version A, dated August 17, 2010, check the torque before the next flight after the effective date of this AD. Use Paragraph 2.A. of Turbomeca Alert MSB A292 73 2836, Version A, dated August 17, 2010, to do the check. (2) If the HMU does not pass the torque check, replace the HMU with a post-Modification TU 178 HMU before the next flight after the effective date of this AD. (h) Mandatory Terminating Action Within 2,200 engine FHs or 72 months after the effective date of this AD, whichever occurs first, replace any pre-Modification TU 178 HMU with a post-Modification TU 178 configuration HMU. (i) Installation Prohibition After the effective date of this AD, do not install a pre- Modification TU 178 HMU on engines incorporating a post-Modification TU 178 HMU. (j) 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 (k)(1) 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. (k) Related Information (1) For more information about this AD, contact John Frost, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7756; fax: 781-238-7199; email: john.frost@faa.gov. (2) Refer to European Aviation Safety Agency (EASA) AD 2017- 0102, dated June 13, 2017, for more information. You may examine the EASA AD on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2009-0889. (l) 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. (3) The following service information was approved for IBR on March 11, 2010 (75 FR 5689, February 4, 2010).(i) Turbomeca Alert Mandatory Service Bulletin (MSB) No. A292 73 2830, Version B, dated July 10, 2009. (ii) Reserved. (4) The following service information was approved for IBR on March 20, 2012 (77 FR 8092, February 14, 2012). (i) Turbomeca Alert MSB No. A292 73 2836, Version A, dated August 17, 2010. (ii) Reserved. (5) For Safran Helicopter Engines, S.A, service information identified in this AD, contact Safran Helicopter Engines, S.A., 40220 Tarnos, France; phone: (33) 05 59 74 40 00; fax: (33) 05 59 74 45 15. (6) You may view this service information at FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781-238-7759. (7) You may view this service information that is incorporated by reference 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.