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 

of certain serial number (SIN) N2 sensor harnesses. This AD requires replacement of the 

same SIN harnesses, and requires replacement of additional 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 of the 65% N1 back up mode, resulting 

in N2 speed fluctuation, significant power loss, and emergency landing of the 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 of the 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 of Transportation, Docket Operations, M-30, West 

Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 

20590. 

• Hand Delivery: U.S. Department of Transportation, 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 

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certain part number (PIN) N2 sensor harnesses installed. That AD requires replacement 

of certain SINs of the affected N2 sensor harnesses, on the two engines ofthe helicopter. 

That AD resulted from mandatory continuing airworthiness information issued by an 

aviation authority of another country to identify and correct an unsafe condition on an 

aviation product. We issued that AD to prevent inadvertent activation of the 65% N1 

backup control mode, as a result of defective N2 sensor harness crimps, which could 

result in engine power loss and emergency landing of the 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 of the 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 of the 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 

of the same type design. 

AD Requirements 

This AD requires replacement of certain SINs ofN2 sensor harnesses, 

PIN 0 301 52 001 0. 

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FAA's Justification and Determination of the 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 of your comments. We specifically invite comments on the overall regulatory, 

economic, environmental, and energy aspects of this AD. We will consider all comments 

received by the closing date and may amend this AD because of those 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 of U.S. registry that will be affected 

by this AD. Therefore, we estimate the cost of this 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 of the FAA Administrator. 

Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's 

authority. 

We are issuing this rulemaking under the authority described in Subtitle VII, 

Part A, Subpart III, Section 44 701 , "General requirements." Under that section, Congress 

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charges the FAA with promoting safe flight of civil 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 of that 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 of power and responsibilities 

among the various levels of government. 

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 it justifies 

making a regulatory distinction, and 

(4) Will not have a significant economic impact, positive or negative, on a 

substantial number of small entities under the criteria of the Regulatory Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 

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 

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 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. 

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(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 1 0 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) ofthis 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. 

(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 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 of this AD. 

(4) For engines listed in paragraph (c)(2) ofthis 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 ofthis AD. 

( 5) If an affected N2 sensor harness is installed on both engines of the 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 of this 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) 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, PIN 0 301 52 001 0, installed, with a SIN 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.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, 

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MA 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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