2013-05-01: N2 sensor harnesses

Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends part 39 of the Federal Aviation Regulations (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) 2011-24-08, Amendment 39-16872 (76 FR 72091, November 22, 2011) and adding the following new AD: 2013-05-01 Turbomeca S.A.: Amendment 39-17373; Docket No. FAA-2011- 1037; Directorate Identifier 2011-NE-30-AD. (a) Effective Date This AD is effective March 21, 2013. (b) Affected ADs This AD supersedes AD 2011-24-08, Amendment 39-16872 (76 FR 72091, November 22, 2011). (c) Applicability This AD applies to all Turbomeca S.A. Makila 1A2 turboshaft engines with an N2 sensor harness, part number (P/N) 0 301 52 001 0, installed, with: (1) A serial number (S/N) 242 through 339, inclusive, or (2) A S/N 691 through 705, inclusive, 707 through 728, inclusive, or 813 through 844, inclusive. (d) Unsafe Condition This AD was prompted by corrosion detected in affected N2 sensor harnesses. We are issuing this AD to prevent inadvertent activation of the 65% N1 back up mode, resulting in N2 speed fluctuation, significant power loss, and emergency landing of the helicopter. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) For engines listed in paragraph (c)(1) of this AD with an affected N2 sensor harness installed on both engines of the helicopter, do the following: (i) Replace one N2 sensor harness with an N2 sensor harness that is eligible for installation within 10 flight hours (FHs) after December 7, 2011, or before the next flight after the effective date of this AD, whichever occurs later, and (ii)Replace the second N2 sensor harness with an N2 sensor harness that is eligible for installation within 50 FHs after December 7, 2011, or before the next flight after the effective date of this AD, whichever occurs later. (2) For engines listed in paragraph (c)(1) of this AD with an affected N2 sensor harness installed on only one engine of the helicopter, replace the affected N2 sensor harness with an N2 sensor harness that is eligible for installation within 50 FHs after December 7, 2011, or before the next flight after the effective date of this AD, whichever occurs later. [[Page 14444]] (3) For engines listed in paragraph (c)(2) of this AD with an affected N2 sensor harness installed on both engines of the helicopter, do the following: (i) Replace one N2 sensor harness with an N2 sensor harness that is eligible for installation within 10 FHs after the effective date of this AD, and (ii) Replace the second N2 sensor harness with an N2 sensor harness that is eligible for installation within 50 FHs after the effective date of this AD. (4) For engines listed in paragraph (c)(2) of this AD with an affected N2 sensor harness installed on only one engine of the helicopter, replace the affected N2 sensor harness with an N2 sensor harness that is eligible for installation within 50 FHs after the effective date of this AD. (5) If an affected N2 sensor harness is installed on both engines of the helicopter, one from paragraph (c)(1) of this AD and one from paragraph (c)(2) of this AD, then within 10 FHs after December 7, 2011, or before the next flight after the effective date of this AD, whichever occurs later, replace the N2 sensor harness from paragraph (c)(1) with an N2 sensor harness that is eligible for installation and within 50 FHs after the effective date of this AD, replace the harness from paragraph (c)(2) with an N2 sensor harness that is eligible for installation. (f) Installation Prohibition (1) After the effective date ofthis AD, do not install on any engine any N2 sensor harness, P/N 0 301 52 001 0, with a S/N listed in paragraphs (c)(1) and (c)(2) of this AD, unless the N2 sensor harness has ``SB 0815'' marked on its identification plate. (2) After the effective date of this AD, do not install in a helicopter, any engine with an N2 sensor harness, P/N 0 301 52 001 0, installed, with a S/N listed in paragraphs (c)(1) and (c)(2) of this AD, unless the N2 sensor harness has ``SB 0815'' marked on its identification plate. (g) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures in 14 CFR 39.19 to make your request. (h) Related Information (1) For more information about this AD, contact Rose Len, Aerospace Engineer, Engine Certification Office, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781-2328-7772; fax: 781-238-7199; email: rose.len@faa.gov. (2) Turbomeca S.A. Alert Mandatory Service Bulletin (MSB) No. A298 77 0821, Version A, dated October 9, 2012, and MSB No. 298 77 0817, Version B, dated August 23, 2011, pertain to the subject of this AD. (3) For service information identified in this AD, contact Turbomeca, 40220 Tarnos, France, phone: +33 (0)5 59 74 40 00; telex: 570 042; fax: +33 (0)5 59 74 45 15; Web site: http://www.turbomeca-support.com. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781-238-7125. (i) Material Incorporated by Reference None.