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[Federal Register: January 14, 2010 (Volume 75, Number 9)]
[Rules and Regulations]               
[Page 2067-2068]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14ja10-6]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0503; Directorate Identifier 2009-NE-12-AD; 
Amendment 39-16172; AD 2010-02-01]
RIN 2120-AA64

 
Airworthiness Directives; Turbomeca S.A. Model Arriel 1B, 1D, and 
1D1 Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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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:

    The rupture of the Reduction Gear Box Intermediate Pinion may 
result in an overspeed of the Power Turbine and, subsequently, an 
uncommanded engine in-flight shutdown. This could lead to an 
emergency autorotation landing on a single-engine helicopter.

We are issuing this AD to prevent the rupture of the reduction gear box 
intermediate pinion, which could result in an overspeed of the power 
turbine, an uncommanded in-flight shutdown of the engine, and an 
emergency autorotation landing.

DATES: This AD becomes effective February 18, 2010. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in this AD as of February 18, 2010.

ADDRESSES: The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on June 12, 2009 (74 FR 
27946). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    Several events of rupture of the Arriel 1 Reduction Gear Box 
Intermediate Pinion have been reported in service. The ruptures have 
been determined to be originated at the pinion teeth root due to 
increased vibratory stresses. This increase in vibratory stresses is 
mainly caused by increased teeth wear over engine life time.
    The rupture of the Reduction Gear Box Intermediate Pinion may 
result in an overspeed of the Power Turbine and, subsequently, an 
uncommanded engine in-flight shutdown. This could lead to an 
emergency autorotation landing on a single-engine helicopter.
    To reduce the level of vibratory stresses and improve tooth 
resistance, Turbom[eacute]ca modification incorporates the addition 
of a damping ring below the teeth and a shot peening of the teeth 
roots. These modifications reduce the risk of incipient fatigue 
cracks.
    This AD requires the replacement of all Reduction Gear Box 
Intermediate Pinions with Pinions incorporating Turbom[eacute]ca 
modification TU 232.

You may obtain further information by examining the MCAI in the AD 
docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or

[[Page 2068]]

on the determination of the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

Costs of Compliance

    Based on the service information, we estimate that this AD would 
affect about 13 products of U.S. registry. We also estimate that it 
would take about 6 work-hours per product to comply with this AD. The 
average labor rate is $80 per work-hour. Required parts would cost 
about $1,272 per product. Based on these figures, we estimate the cost 
of the AD on U.S. operators to be $22,776.

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.

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 (telephone (800) 647-5527) is provided in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
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:

2010-02-01 Turbomeca S.A.: Amendment 39-16172: Docket No. FAA-2009-
0503; Directorate Identifier 2009-NE-12-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective February 
18, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Turbomeca Arriel 1B, 1D, and 1D1 
turboshaft engines. These engines are installed on, but not limited 
to, Eurocopter France AS350B, AS350BA, AS350B1, and AS350B2 
helicopters.

Reason

    (d) This AD results from several events of rupture of the Arriel 
1 reduction gear box intermediate pinions. We are issuing this AD to 
prevent the rupture of the reduction gear box intermediate pinion, 
which could result in an overspeed of the power turbine, an 
uncommanded in-flight shutdown of the engine, and an emergency 
autorotation landing.

Actions and Compliance

    (e) Unless already done, do the following actions.
    (f) No later than 28 February 2011, replace the Reduction Gear 
Box Intermediate Pinions (P/N 0 292 70 779 0) with Pinions 
incorporating Turbom[eacute]ca modification TU 232 in accordance 
with Turbom[eacute]ca Mandatory Service Bulletin 292 72 0276 Version 
B dated 06 November 2008.

FAA AD Differences

    (g) None.
    (h) Alternative Methods of Compliance (AMOCs): The Manager, 
Engine Certification Office, FAA, has the authority to approve AMOCs 
for this AD, if requested using the procedures found in 14 CFR 
39.19.

Related Information

    (i) Refer to MCAI EASA Airworthiness Directive 2009-0002, dated 
January 7, 2009, for related information.
    (j) Contact James Lawrence, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-
7199, for more information about this AD.

Material Incorporated by Reference

    (k) You must use Turbomeca Mandatory Service Bulletin No. 292 72 
0276, Version B, dated November 6, 2008, to do the actions required 
by this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Turbomeca, 40220 Tarnos, France; telephone: 33 05 59 74 40 00; fax: 
33 05 59 74 45 15, or go to: http://www.turbomeca-support.com.
    (3) You may review copies at the FAA, New England Region, 12 New 
England Executive Park, Burlington, MA; or at the National Archives 
and Records Administration (NARA). For information on the 
availability of this material at NARA, call (202) 741-6030, or go 
to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on December 31, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2010-337 Filed 1-13-10; 8:45 am]
BILLING CODE 4910-13-P
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