[Federal Register Volume 76, Number 225 (Tuesday, November 22, 2011)]
[Rules and Regulations]
[Pages 72091-72093]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-30061]


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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 39-16872; AD 2011-24-08]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. Makila 1A2 Turboshaft 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) issued by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    A helicopter experienced an inadvertent activation of the 65% N1 
(gas generator speed) back up control mode.
    The subsequent technical investigations carried by Turbomeca 
revealed that an N2 (power turbine speed) sensor harness wire 
crimping discrepancy was at the origin of this event. Further 
quality investigations performed with the supplier led to the 
conclusion that N2 sensor Part Number (P/N) 0 301 52 001 0 whose 
Serial Numbers (S/N) are between S/N 242 and S/N 339 inclusive are 
potentially concerned by the same manufacturing discrepancy.
    This condition, if not corrected, could lead to the inadvertent 
activation of the 65% N1 back up mode and consequently to 
significant power loss on one or more or both engines installed on 
the same helicopter, potentially resulting in an emergency landing 
of the helicopter.

We are issuing this AD to prevent inadvertent activation of the backup 
control mode, which could result in engine power loss and emergency 
landing of the helicopter.

DATES: This AD becomes effective December 7, 2011.

[[Page 72092]]

    We must receive comments on this AD by December 22, 2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: U.S. Department of Transportation, 1200 New Jersey 
Avenue SE., West Building Ground Floor, Room W12-140, Washington, DC 
20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: (202) 493-2251.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
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 Operations office (phone: (800) 647-5527) is the same as the 
Mail address provided in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; email: 
[email protected]; phone: (781) 238-7176; fax: (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, issued EASA 
Airworthiness Directive 2011-0147, dated August 5, 2011 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    A helicopter experienced an inadvertent activation of the 65% N1 
(gas generator speed) back up control mode.
    The subsequent technical investigations carried by Turbomeca 
revealed that an N2 (power turbine speed) sensor harness wire 
crimping discrepancy was at the origin of this event. Further 
quality investigations performed with the supplier led to the 
conclusion that N2 sensor Part Number (P/N) 0 301 52 001 0 whose 
Serial Numbers (S/N) are between S/N 242 and S/N 339 inclusive are 
potentially concerned by the same manufacturing discrepancy.
    This condition, if not corrected, could lead to the inadvertent 
activation of the 65% N1 back up mode and consequently to 
significant power loss on one or more or both engines installed on 
the same helicopter, potentially resulting in an emergency landing 
of the helicopter.
    For the reasons described above, this AD requires replacement of 
affected N2 sensor harnesses with serviceable parts. This AD also 
prohibits the installation of non serviceable N2 sensor harnesses on 
an engine.

You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Turbomeca has issued Service Bulletin 298 77 0817, Version B, dated 
August 23, 2011. The actions described in this service information are 
intended to correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This AD

    This product has been approved by the aviation authority of France 
and is approved for operation in the United States. Pursuant to our 
bilateral agreement with the European Community, EASA has notified us 
of the unsafe condition described in the MCAI and service information 
referenced above. We are issuing this AD because we evaluated all 
information provided by EASA 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 the affected N2 sensor 
harnesses with N2 sensor harnesses eligible for installation.

FAA's Determination of the Effective Date

    Since no domestic operators use this product, notice and 
opportunity for public comment before issuing this AD are unnecessary. 
Therefore, we are adopting this regulation immediately.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. 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 
with FAA personnel concerning this AD. Using the search function of the 
Web site, anyone can find and read the comments in any of our dockets, 
including, if provided, the name of the individual who sent the comment 
(or signed the comment on behalf of an association, business, labor 
union, etc.). You may review the DOT's complete Privacy Act Statement 
in the Federal Register published on April 11, 2000 (65 FR 19477-78).

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

    We determined that 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 this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866,
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979), and
    3. 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

[[Page 72093]]

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 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 adding the following new AD:

2011-24-08 Turbomeca S.A.: Amendment 39-16872; Docket No. FAA-2011-
1037; Directorate Identifier 2011-NE-30-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective December 7, 
2011.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Makila 1A2 turboshaft engines, all serial 
numbers.

(d) Reason

    (1) This AD results from mandatory continuing airworthiness 
information (MCAI) issued by an aviation authority of another 
country to identify and correct an unsafe condition on an aviation 
product. The MCAI describes the unsafe condition as:

    A helicopter experienced an inadvertent activation of the 65% N1 
(gas generator speed) back up control mode.
    The subsequent technical investigations carried by Turbomeca 
revealed that an N2 (power turbine speed) sensor harness wire 
crimping discrepancy was at the origin of this event. Further 
quality investigations performed with the supplier led to the 
conclusion that N2 sensor Part Number (P/N) 0 301 52 001 0 whose 
Serial Numbers (S/N) are between S/N 242 and S/N 339 inclusive are 
potentially concerned by the same manufacturing discrepancy.
    This condition, if not corrected, could lead to the inadvertent 
activation of the 65% N1 back up mode and consequently to 
significant power loss on one or more or both engines installed on 
the same helicopter, potentially resulting in an emergency landing 
of the helicopter.
    (2) We are issuing this AD to prevent inadvertent activation of 
the backup control mode, which could result in engine power loss and 
emergency landing of the helicopter.

(e) Actions and Compliance

    (1) Unless already done, do the following actions.
    (2) For engines equipped with N2 sensor harnesses, P/N 0 301 52 
001 0, whose S/Ns are between S/N 242 and S/N 339 inclusive, do the 
following:
    (i) If an affected P/N is installed on each of the 2 (two) 
engines of the helicopter, then within 10 flight hours (FHs) after 
the effective date of this AD, replace one N2 sensor harness with an 
N2 sensor harness that is eligible for installation, and within 50 
FHs after the effective date of this AD, replace the second harness 
with an N2 sensor harness that is eligible for installation.
    (ii) If an affected P/N is installed only on 1 (one) engine of 
the helicopter, then within 50 FHs after the effective date of this 
AD, replace the affected N2 sensor harness with an N2 harness that 
is eligible for installation.
    (3) After the effective date of this AD, do not install in an 
engine any N2 sensor harness, P/N 0 301 52 001 0, whose S/N is 
between S/N 242 and S/N 339 inclusive, unless the part has ``SB 
0815'' marked on the identification plate.
    (4) After the effective date of this AD, do not install in a 
helicopter an engine equipped with an N2 sensor harness, P/N 0 301 
52 001 0, whose S/N is between S/N 242 and S/N 339 inclusive, unless 
the part has ``SB 0815'' marked on the identification plate.

(f) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
for this AD. Use the procedures found in 14 CFR 39.19 to make your 
request.

(g) Related Information

    (1) Refer to MCAI EASA AD 2011-0147, dated August 5, 2011, and 
Turbomeca Service Bulletin No. 298 77 0817, for related information. 
Contact Turbomeca; 40220 Tarnos, France; phone: 33-05-59-74-40-00; 
fax: 33-05-59-74-45-11; for a copy of this service information.
    (2) Contact James Lawrence, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; email: 
[email protected]; phone: (781)-238-7176; fax: (781) 238-7199, 
for more information about this AD.

(h) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on November 9, 2011.
Peter A. White,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-30061 Filed 11-21-11; 8:45 am]
BILLING CODE 4910-13-P