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[Federal Register Volume 77, Number 13 (Friday, January 20, 2012)]
[Proposed Rules]
[Pages 2930-2932]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-1129]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0010; Directorate Identifier 2012-NE-03-AD]
RIN 2120-AA64

Airworthiness Directives; Turbomeca S.A. 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 all 
Turbomeca S.A. Arriel 2B and 2B1 turboshaft engines. This proposed AD 
was prompted by the discovery of non-conformities of certain power 
turbine (PT) blade fir-tree roots. This proposed AD would require 
removing the affected PT blades from service on or before reaching a 
new reduced life limit for those certain PT blades. We are proposing 
this AD to prevent PT blade rupture, which could result in an 
uncommanded in-flight engine shutdown, forced autorotation landing, or 
accident.

DATES: We must receive comments on this proposed AD by March 20, 2012.

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.
    For service information identified in this proposed AD, contact 
Turbomeca,

[[Page 2931]]

40220 Tarnos, France; phone: 33 05 59 74 40 00; fax: 33 05 59 74 45 15. 
You may review copies of the referenced service information at the FAA, 
Engine & Propeller Directorate, 12 New England Executive Park, 
Burlington, MA. For information on the availability of this material at 
the FAA, call (781) 238-7125.

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 (phone: (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: Rose Len, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; phone: (781) 238-7772; 
fax: (781) 238-7199; email: rose.len@faa.gov.

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-2012-0010; 
Directorate Identifier 2012-NE-03-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 2011-0218, dated November 10, 2011 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    During production of Arriel 2 Power Turbine (PT) wheels, 
Turbomeca has detected geometric non-conformities on blade fir-tree 
roots. The technical investigations carried out by Turbomeca have 
shown that this non-conformity is due to PT blade manufacturing and 
that only a limited number of PT blades are potentially affected.
    This situation, if not detected and corrected, may potentially 
lead to a reduction in the fatigue resistance of the PT blades, 
which can reduce their in service use limit. This reduction of 
fatigue resistance can potentially result in blade rupture, which 
could cause an uncommanded in-flight shutdown, ultimately leading to 
an emergency autorotation landing for a single-engine helicopter.
    To address this unsafe condition, Turbomeca has issued Turbomeca 
Mandatory Service Bulletin (MSB) A292 72 2842, Version A, in which 
the life limit of those PT blades is reduced to 5,000 Flight Cycles 
(FC).

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

Relevant Service Information

    Turbomeca S.A. has issued Mandatory Service Bulletin No. A292 72 
2842, Version A, dated September 23, 2011. The actions described in 
this service information are intended to correct the unsafe condition 
identified in the MCAI.

FAA's Determination 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 the European Community, EASA has 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.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 150 engines installed on helicopters of U.S. 
registry. We also estimate that it would take about 4 work-hours per 
product to comply with this proposed AD. The average labor rate is $85 
per work-hour. A prorated replacement M04 module would cost about 
$20,000 per engine. Based on these figures, we estimate the cost of the 
proposed AD on U.S. operators to be $3,051,000.

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,

[[Page 2932]]

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 
airworthiness directive (AD):

Turbomeca S.A.: Docket No. FAA-2012-0010; Directorate Identifier 
2012-NE-03-AD.

(a) Comments Due Date

    We must receive comments by March 20, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Turbomeca S.A. Arriel 2B and 2B1 turboshaft 
engines with at least one installed power turbine (PT) blade part 
number (P/N) 2 292 81 A01 0, serial numbers (S/Ns) 102782 through 
120230 inclusive, or, S/Ns 120293 through 120390 inclusive.

(d) Reason

    This AD was prompted by the detection of geometric non-
conformities on PT blade fir-tree roots. We are issuing this AD to 
prevent PT blade rupture, which could result in an uncommanded in-
flight engine shutdown, forced autorotation landing, or accident.

(e) Actions and Compliance

    Unless already done, do the following actions within 5,000 
flight cycles on the PT blades, or within one month after the 
effective date of this AD, whichever occurs later.
    (1) Replace the PT blades with PT blades eligible for 
installation; or
    (2) Replace the M04 module with an M04 module having PT blades 
eligible for installation; or
    (3) Replace the PT wheel assembly with a PT wheel assembly 
having PT blades eligible for installation.
    (4) Guidance on the replacements specified in paragraphs (e)(1) 
through (e)(3) can be found in Turbomeca S.A. Mandatory Service 
Bulletin No. A292 72 2842, Version A, dated September 23, 2011.

(f) Definition

    For the purposes of this AD, a PT blade eligible for 
installation is one not listed in paragraph (c) of this AD or, one 
listed in paragraph (c) of this AD with fewer than 5,000 flight 
cycles.

(g) Installation Prohibition

    From the effective date of this AD:
    (1) Do not install a PT blade as listed in paragraph (c) of this 
AD, that has 5,000 or more flight cycles, into any engine.
    (2) Do not install any engine with a PT blade as listed in 
paragraph (c) of this AD, that has 5,000 or more flight cycles, onto 
a helicopter.

(h) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, may approve AMOCs for 
this AD. Use the procedures found in 14 CFR 39.19 to make your 
request.

(i) Related Information

    (1) For more information about this AD, contact Rose Len, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: (781) 238-7772; fax: (781) 238-7199; email: 
rose.len@faa.gov.
    (2) Refer to MCAI EASA Airworthiness Directive 2011-0218, dated 
November 10, 2011, and Turbomeca S.A. Alert Service Bulletin No. 
A292 72 2842, Version A, dated September 23, 2011, for related 
information.
    (3) For service information identified in this AD, contact 
Turbomeca, 40220 Tarnos, France; phone: 33 05 59 74 40 00; fax: 33 
05 59 74 45 15. You may review copies of the referenced service 
information at the FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA. For information on the 
availability of this material at the FAA, call (781) 238-7125.

    Issued in Burlington, Massachusetts, on January 13, 2012.
Peter A. White,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-1129 Filed 1-19-12; 8:45 am]
BILLING CODE 4910-13-P
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