[Federal Register: April 17, 2009 (Volume 74, Number 73)]
[Proposed Rules]
[Page 17797-17799]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr17ap09-12]
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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:
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-2009-0348;
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:
james.lawrence@faa.gov; 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