### DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [4910-13-P]

[Docket No. FAA-2011-1037; Directorate Identifier 2011-NE-30-AD; Amendment 39-17373; AD 2013-05-01] RIN 2120-AA64 Airworthiness Directives; Turbomeca S.A. Turboshaft Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. SUMMARY: We are superseding an existing airworthiness directive (AD) for all Turbomeca S.A. Makila 1A2 turboshaft engines. That AD currently requires replacement ofcertain serial number (SIN) N2 sensor harnesses. This AD requires replacement ofthe

same 

### SIN harnesses, and requires replacement ofadditional 

### SIN N2 sensor harnesses

. This AD was prompted by corrosion detected in affected N2 sensor harnesses. We are issuing this AD to prevent inadvertent activation ofthe 65% N1 back up mode, resulting in N2 speed fluctuation, significant power loss, and emergency landing ofthe helicopter. DATES: This AD is effective [INSERT DATE 15 DAYS AFTER DATE OF PUBLICATION IN THE FEDERAL REGISTER]. We must receive any comments on this AD by [INSERT DATE 45 DAYS AFTER DATE OF PUBLICATION IN THE FEDERAL REGISTER]. ADDRESSES: You may send comments by any ofthe following methods:

• Federal eRulemaking Portal : Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: 202-493-2251.• Mail: U.S. Department ofTransportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

• Hand Delivery: U.S. Department ofTransportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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; website: 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 ofthis material at the FAA, call 781-238-7125

. 

### Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations .gov;

or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. 

### FOR FURTHER INFORMATION CONTACT: Rose Len, Aerospace Engineer, Engine Certification Office, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781-238-7772; fax: 781-238-7199; email: rose.len @faa.gov. 

### SUPPLEMENTARY INFORMATION: 

### Discussion On November 9, 2011, we issued AD 2011-24-08, Amendment 39-16872 (76 FR 72091, November 22, 2011), for all Turbomeca S.A. Makila 1A2 turboshaft engines with

2certain part number (PIN) N2 sensor harnesses installed. That AD requires replacement ofcertain SINs ofthe affected N2 sensor harnesses, on the two engines ofthe helicopter. That AD resulted from mandatory continuing airworthiness information issued by an aviation authority ofanother country to identify and correct an unsafe condition on an aviation product. We issued that AD to prevent inadvertent activation ofthe 65% N1 backup control mode, as a result ofdefective N2 sensor harness crimps, which could result in engine power loss and emergency landing ofthe helicopter. 

### Actions Since AD was Issued Since we issued AD 2011-24-08 (76 FR 72091, November 22, 2011), Turbomeca S.A. has determined through investigation that additional SINs ofthe N2 sensor harness, 

### PIN 0 301 52 001 0, are affected and require replacement. The investigation detected corrosion in the harness inside the cable sheath, at the splices with the sensor coils. This corrosion is attributed to a manufacturing error. We are issuing this AD to include additional SINs ofthe N2 sensor harness. 

### Relevant Service Information We reviewed 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. This service information describes procedures for checking and replacing affected N2 sensor harnesses. 

### FAA's Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition exists and is likely to exist or develop on other products ofthe same type design. 

### AD Requirements This AD requires replacement ofcertain SINs ofN2 sensor harnesses, 

### PIN 0 301 52 001 0.

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### FAA's Justification and Determination ofthe Effective Date There are no U.S. operators for this product. Therefore, we find that notice and opportunity for prior public comment are unnecessary and that good cause exists for making this amendment effective in less than 30 days. 

### Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments before it becomes effective. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include "Docket Number FAA-2011-1037 ; Directorate Identifier 2011-NE-30-AD" at the beginning ofyour comments

. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects ofthis AD. We 

### will consider all comments received by the closing date and may amend this AD because ofthose comments. We will post all comments we receive, without change, to http ://www.regulations.gov, including any personal information you provide

. We will also post a report summarizing each substantive verbal contact we receive about this AD. 

### Costs of Compliance There are no engines installed on helicopters ofU.S

. registry that will be affected by this AD. Therefore, we estimate the cost ofthis AD on U.S

. operators to be $0. 

### Authority for this Rulemaking Title 49 ofthe United States Code specifies the FAA' s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority ofthe FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope ofthe Agency' s authority

. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701 , "General requirements. " Under that section, Congress

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### charges the FAA with promoting safe flight ofcivil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope ofthat authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution ofpower and responsibilities among the various levels ofgovernment. For the reasons discussed above, I certify that this AD: (1) Is not a "significant regulatory action" under Executive Order 12866, (2) Is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), and (3) Will not affect intrastate aviation in Alaska to the extent that itjustifies making a regulatory distinction, and (4) Will not have a significant economic impact, positive or negative, on a substantial number ofsmall entities under the criteria ofthe Regulatory Flexibility Act. List ofSubjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption ofthe Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends part 39 ofthe Federal Aviation Regulations (14 CFR part 39) as follows: PART 39

- 

### AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows : Authority: 49 U.S.C

. 106(g), 40113 , 44701. 

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### § 39.13 [Amended] 2. The FAA amends§ 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 [INSERT DATE 15 DAYS AFTER DATE OF PUBLICATION IN THE FEDERAL REGISTER]. 

### (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 (PIN) 0 301 52 001 0, installed, with: (1) A serial number (SIN) 242 through 339, inclusive, or (2) A 

### SIN 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 ofthe 65% N1 back up mode, resulting in N2 speed fluctuation, significant power loss, and emergency landing ofthe helicopter. (e) 

### Compliance Comply with this AD within the compliance times specified, unless already done.

6(1) For engines listed in paragraph (c)(1) ofthis AD with an affected N2 sensor harness installed on both engines ofthe helicopter, do the following: (i) Replace one N2 sensor harness with an N2 sensor harness that is eligible for installation within 1 0 flight hours (FHs) after December 7, 2011 , or before the next flight after the effective date ofthis 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 ofthis AD, whichever occurs later

. (2) For engines listed in paragraph (c)(1) ofthis AD with an affected N2 sensor harness installed on only one engine ofthe 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 ofthis AD, whichever

occurs later. (3) For engines listed in paragraph (c)(2) ofthis AD with an affected N2 sensor harness installed on both engines ofthe 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 ofthis 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 ofthis AD. (4) For engines listed in paragraph (c)(2) ofthis AD with an affected N2 sensor harness installed on only one engine ofthe helicopter, replace the affected N2 sensor harness with an N2 sensor harness that is eligible for installation within 50 FHs after the effective date ofthis AD. (5) Ifan affected N2 sensor harness is installed on both engines ofthe helicopter, one from paragraph (c)(1) ofthis AD and one from paragraph (c)(2) ofthis AD, then within 10 FHs after December 7, 2011 , or before the next flight after the effective date of

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### 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 ofthis 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, 

### PIN 0 301 52 001 0, with a 

### SIN listed in paragraphs (c)(1) and (c)(2) ofthis AD, unless the N2 sensor harness has "SB 0815 " marked on its identification plate. (2) After the effective date ofthis AD, do not install in a helicopter, any engine with an N2 sensor harness, 

### PIN 0 301 52 001 0, installed, with a 

### SIN listed in paragraphs (c)(1) and (c)(2) ofthis 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.lencmfaa

.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 ofthis 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, 8MA 01803. For information on the availability ofthis material at the FAA, call 781-238- 7125. 

### (i) Material Incorporated 

### by Reference None.

Issued in Burlington, Massachusetts, on February 25 , 2013.

Colleen M. D'Alessandro, Assistant Manager, Engine & Propeller Diorectorate, Aircraft Certification Service.

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