AD 2013-05-01

This AD is effective March 21, 2013.

We must receive any comments on this AD by April 22, 2013.

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; 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.

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.

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 certain part number (P/N) N2 sensor harnesses installed. That AD requires replacement of certain S/Ns of the affected N2 sensor harnesses, on the two engines of the 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.

Since we issued AD 2011-24-08 (76 FR 72091, November 22, 2011), Turbomeca S.A. has determined through investigation that additional S/Ns of the N2 sensor harness, P/N 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 S/Ns of the N2 sensor harness.

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.

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.

This AD requires replacement of certain S/Ns of N2 sensor harnesses, P/N 0 301 52 001 0.

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.

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.

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.

Title 49 of the 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 44701, “General requirements.” Under that section, Congress 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.

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.

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:

1. The authority citation for part 39 continues to read as follows:

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: