[Federal Register Volume 74, Number 73 (Friday, April 17, 2009)]
[Proposed Rules]
[Pages 17797-17799]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-8786]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0348; Directorate Identifier 2008-NE-39-AD]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. ARRIUS 1A 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:

    Cycle life limit value for ARRIUS 1A balancing piston Part 
Number (P/N) 0 319 20 152 0, initially set at 40 000 cycles, has 
been reduced to 16 000 cycles, following the discovery of a 
calculation error during a recent review of the ARRIUS 1 engine 
family files.

We are proposing this AD to prevent failure of the balancing piston, 
which could result in an engine in-flight-shutdown and the release of 
high-energy debris and damage to the helicopter.

DATES: We must receive comments on this proposed AD by May 18, 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.

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 & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
[email protected]; 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-2009-0348; 
Directorate Identifier 2008-NE-39-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 2008-0133, dated July 17, 2008, [(referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products]. The MCAI states:

    Cycle life limit value for ARRIUS 1A balancing piston Part 
Number (P/N) 0 319 20 152 0, initially set at 40 000 cycles, has 
been reduced to 16 000 cycles, following the discovery of a 
calculation error during a recent review of the ARRIUS 1 engine 
family files.
    As of the publication date of this Airworthiness Directive, no 
ARRIUS 1A engines in service are fitted with a balancing piston that 
has logged more than 16 000 cycles, and the outlook for the 
consumption

[[Page 17798]]

of cycles on the ARRIUS 1A fleet indicates that no balancing pistons 
will exceed this new limit for a few years' time.
    Moreover, this new cycle life limit value for the balancing 
piston has been incorporated since the end of 2007 in ARRIUS 1A 
Maintenance documentation.
    Failure to comply with the new life limits provided in the 
Airworthiness Limitations Section of ARRIUS 1A Maintenance 
documentation could potentially result in an engine in-flight-
shutdown and the release of high energy debris.

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

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.

Differences Between This AD and the MCAI or Service Information

    The MCAI requires modifying the cyclic life limit value of the 
balancing piston in the engine log book as specified in Turbomeca 
Mandatory Service Bulletin 319 72 0811, dated April 30, 2008, and 
updating the approved operator's maintenance program.
    We are requiring removing the balancing piston, P/N 0 319 20 152 0, 
before it meets or exceeds the new, reduced cyclic life limit value of 
16,000 cycles-since-new.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 33 products of U.S. registry. We also estimate that 
it would take about 0.5 work-hour per product to comply with this 
proposed AD. The average labor rate is $80 per work-hour. Required 
parts would cost about $5,280 per product. Based on these figures, we 
estimate the cost of the proposed AD on U.S. operators to be $175,560. 
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, 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-2009-0348; Directorate Identifier 
2008-NE-39-AD.

Comments Due Date

    (a) We must receive comments by May 18, 2009.

Affected Airworthiness Directives (ADs)

    (b) None.

Applicability

    (c) This AD applies to Turbomeca S.A. ARRIUS 1A turboshaft 
engines with balancing pistons, part number (P/N) 0 319 20 152 0, 
installed. These engines are installed on, but not limited to, 
Eurocopter AS355N helicopters.

Reason

    (d) Cycle life limit value for ARRIUS 1A balancing piston Part 
Number (P/N) 0 319 20 152 0, initially set at 40 000 cycles, has 
been reduced to 16 000 cycles, following the discovery of a 
calculation error during a recent review of the ARRIUS 1 engine 
family files.
    We are issuing this AD to prevent failure of the balancing 
piston, which could result in an engine in-flight-shutdown and the 
release of high-energy debris and damage to the helicopter.

Actions and Compliance

    (e) Unless already done, for ARRIUS 1A engines with a balancing 
piston, P/N 0 319 20 152 0, installed, remove the engine from 
service before the balancing piston accumulates 16,000 cycles-since-
new (CSN).

Installation Prohibition

    (f) After the effective date of this AD, don't return to service 
any engine that has a balancing piston that has accumulated 16,000 
or more CSN.

FAA AD Differences

    (g) This AD differs from the Mandatory Continuing Airworthiness 
Information (MCAI) or service information as follows:
    (1) This AD requires removing from service, any ARRIUS 1A engine 
that has a balancing piston, P/N 0 319 20 152 0, with 16,000 CSN 
installed.
    (2) We prohibit returning to service ARRIUS 1A engine that has a 
balancing piston, P/N 0 319 20 152 0, with 16,000 or more CSN.

Other FAA AD Provisions

    (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 Airworthiness Directive 2008-0133, dated July 
17, 2008 for related information.
    (j) Contact James Lawrence, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
[email protected]; telephone (781) 238-7176; fax (781) 238-
7199, for more information about this AD.


[[Page 17799]]


    Issued in Burlington, Massachusetts, on April 9, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-8786 Filed 4-16-09; 8:45 am]
BILLING CODE 4910-13-P