Airworthiness Directives; Turbomeca S.A. Turboshaft Engines

[Federal Register Volume 78, Number 44 (Wednesday, March 6, 2013)]
[Rules and Regulations]
[Pages 14442-14444]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-04996]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[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.

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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 (S/N) N2 sensor 
harnesses. This AD requires replacement of the same S/N harnesses, and 
requires replacement of additional S/N 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 March 21, 2013.
    We must receive any comments on this AD by April 22, 2013.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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.

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: 
[email protected].

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 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.

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 S/
Ns of the N2 sensor harness, P/N 0 301 52 001 0, are affected and 
require replacement.

[[Page 14443]]

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.

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 S/Ns of N2 sensor 
harnesses, P/N 0 301 52 001 0.

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 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.

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

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 of this 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: [email protected].
    (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.

    Issued in Burlington, Massachusetts, on February 25, 2013.
Colleen M. D'Alessandro,
Assistant Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2013-04996 Filed 3-5-13; 8:45 am]
BILLING CODE 4910-13-P

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