[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