Document ID: FAA-2009-0503-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Turbomeca S.A. Model Arriel 1B, 1D, and 1D1 Turboshaft Engines
Posted Date: 2009-06-12T04:00Z

[Federal Register: June 12, 2009 (Volume 74, Number 112)]
[Proposed Rules]               
[Page 27946-27947]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr12jn09-18]                         

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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]
RIN 2120-AA64

 
Airworthiness Directives; Turbomeca S.A. Model Arriel 1B, 1D, and 
1D1 Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed 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 proposing 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: We must receive comments on this proposed AD by July 13, 2009.

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: Docket Management Facility, 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.
    Contact Turbomeca, 40220 Tarnos, France; telephone 33 05 59 74 40 
00; fax 33 05 59 74 45 15, for the service information identified in 
this proposed AD.

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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (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 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:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-0503; 
Directorate Identifier 2009-NE-12-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on 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 proposed 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).

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2009-0002, dated January 7, 2009, (referred to 
after this as ``the MCAI''), 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.

Relevant Service Information

    Turbomeca has issued Mandatory Service Bulletin No. 292 72 0276, 
Version B, dated November 6, 2008. 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 Proposed 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 France, they have notified us of the unsafe 
condition described in the MCAI and service information referenced 
above. We are proposing 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.

[[Page 27947]]

Costs of Compliance

    Based on the service information, we estimate that this proposed 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 
proposed 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 proposed AD on U.S. operators to be $22,776. 
Our cost estimate is exclusive of possible warranty coverage.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
regulation:
    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 proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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.

Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Turbomeca S.A.: Docket No. FAA-2009-0503; Directorate Identifier 
2009-NE-12-AD.

Comments Due Date

    (a) We must receive comments by July 13, 2009.

Affected Airworthiness Directives (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, and Turbomeca Mandatory Service Bulletin No. 292 72 
0276, Version B, dated November 6, 2008, for related information. 
Contact Turbomeca, 40220 Tarnos, France; telephone 33 05 59 74 40 
00; fax 33 05 59 74 45 15, for a copy of this service 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.

    Issued in Burlington, Massachusetts, on June 8, 2009.
Robert G. Mann,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-13850 Filed 6-11-09; 8:45 am]

BILLING CODE 4910-13-P