
[Federal Register: September 21, 2010 (Volume 75, Number 182)]
[Rules and Regulations]               
[Page 57371-57373]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr21se10-1]                         


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[[Page 57371]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0710; Directorate Identifier 2010-NE-26-AD; 
Amendment 39-16434; AD 2010-19-06]
RIN 2120-AA64

 
Airworthiness Directives; Turbomeca Arriel 1 Series Turboshaft 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This 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:

    Metallurgical non-conformities have been found when performing 
quality inspections during production of Arriel 1 gas generator (GG) 
second stage turbine discs introduced by Turbomeca Modification 
TU347 (P/N 0 292 25 040 0). Analysis has concluded that the approved 
life limit of the post-TU347 GG second stage turbine disc needs to 
be reduced to 2,500 GG cycles.

We are issuing this AD to prevent failure of the gas generator second 
stage turbine disc which could result in the release of high energy 
debris and damage to the helicopter.

DATES: This AD becomes effective October 6, 2010.
    We must receive comments on this AD by October 21, 2010.
     Federal eRulemaking Portal: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: 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 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: Richard Woldan, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
richard.woldan@faa.gov; telephone (781) 238-7136; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, previously 
issued EASA AD 2010-0101-E, dated June 4, 2010, and has now issued a 
revision to that AD, which is AD 2010-0101R1, dated August 4, 2010 
(referred to after this as ``the MCAI''), to correct an unsafe 
condition for the specified products. The MCAI states:

    Metallurgical non-conformities have been found when performing 
quality inspections during production of Arriel 1 gas generator (GG) 
second stage turbine discs introduced by Turbomeca Modification 
TU347 (P/N 0 292 25 040 0). Analysis has concluded that the approved 
life limit of the post-TU347 GG second stage turbine disc needs to 
be reduced to 2,500 GG cycles.
    Since issuance of AD 2010-0101-E, Turbomeca has introduced a 
reinforced Eddy-current inspection which provides a lower (improved) 
detection threshold of the metallurgical non-conformities. This 
reinforced Eddy-current inspection, named ``CFR'', combined with a 
revised analysis, allows to increase the life limit of the post-
TU347 GG second Stage Turbine Discs identified as ``CFR'' over the 
2,500 GG life cycles of the ``non-CFR'' Discs.

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

FAA's Determination and Requirements of This 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 issuing 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. 
This AD requires:
     For gas generator second stage turbine discs, part number 
(P/N) 0 292 25 040 0 that do not have the ``CFR'' marking, removing 
them from service before exceeding 2,500 cycles-in-service (CIS) since-
new or within 20 CIS from the effective date of the AD, whichever 
occurs later; and
     For gas generator second stage turbine discs, P/N 0 292 25 
040 0 that have the ``CFR'' marking, removing them from service before 
exceeding 3,500 CIS since-new.

Differences Between the AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. This AD differs from the MCAI and/
or service information as follows:
     EASA AD 2010-0101R1, dated August 4, 2010, requires second 
stage turbine discs with fewer than 2,500 CIS to be removed upon 
accumulating 2,500 CIS.
     EASA AD 2010-0101R1, dated August 4, 2010, requires 
revising the approved aircraft maintenance program to reflect the life 
limit of 2,500 CIS.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because of 
the short compliance

[[Page 57372]]

time in removing affected gas generator second stage discs that are 
near or over the reduced life limit. Therefore, we determined that 
notice and opportunity for public comment before issuing this AD are 
impracticable and that good cause exists for making this amendment 
effective in fewer than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2010-0710; Directorate 
Identifier 2010-NE-26-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
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 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).

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

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2010-19-06 Turbomeca: Amendment 39-16434.; Docket No. FAA-2010-0710; 
Directorate Identifier 2010-NE-26-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective October 
6, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Turbomeca Arriel 1A, 1A1, 1B, 1C, 1C1, 
1C2, 1D, 1D1, and 1S1 turboshaft engines that have incorporated 
Modification TU347. These engines are installed on, but not limited 
to, Eurocopter AS350 series, AS365 and SA365 series, Sikorsky S-76A 
series and S-76C series helicopters.

Reason

    (d) Metallurgical non-conformities have been found when 
performing quality inspections during production of Arriel 1 gas 
generator (GG) second stage turbine discs introduced by Turbomeca 
Modification TU347 (P/N 0 292 25 040 0). Analysis has concluded that 
the approved life limit of the post-TU347 GG second stage turbine 
disc needs to be reduced to 2,500 GG cycles.

We are issuing this AD to prevent failure of the gas generator 
second stage turbine disc which could result in the release of high 
energy debris and damage to the helicopter.

Actions and Compliance

    (e) Unless already done, do the following:
    (1) For gas generator second stage turbine discs, part number 
(P/N) 0 292 25 040 0 that do not have the ``CFR'' marking, remove 
from service before exceeding 2,500 cycles-in-service (CIS) since-
new or within 20 CIS from the effective date of this AD, whichever 
occurs later.
    (2) For gas generator second stage turbine discs, P/N 0 292 25 
040 0 that have the ``CFR'' marking, remove from service before 
exceeding 3,500 CIS since-new.

Gas Generator Second Stage Turbine Installation Prohibition

    (3) After the effective date of this AD, for gas generator 
second stage turbine discs, P/N 0 292 25 040 0 that do not have the 
``CFR'' marking, and have 2,500 or more CIS since-new, do not 
install into any engine.
    (4) After the effective date of this AD, for gas generator 
second stage turbine discs, P/N 0 292 25 040 0 that have the ``CFR'' 
marking, and have 3,500 or more CIS since-new, do not install into 
any engine.

FAA AD Differences

    (f) This AD differs from the Mandatory Continuing Airworthiness 
Information (MCAI) and/or service information as follows:
    (1) European Aviation Safety Agency (EASA) AD 2010-0101R1, dated 
August 4, 2010, requires second stage turbine discs with fewer than 
2,500 CIS to be removed upon accumulating 2,500 CIS.
    (2) EASA AD 2010-0101R1, dated August 4, 2010, requires revising 
the approved aircraft maintenance program to reflect the new reduced 
life limit of 2,500 CIS.

Alternative Methods of Compliance (AMOCs)

    (g) 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

    (h) Refer to EASA AD 2010-0101R1, dated August 4, 2010, and 
Turbomeca Alert Mandatory Service Bulletin No. A292 72 0831, Version 
B, dated July 7, 2010, 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.
    (i) Contact Richard Woldan, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New

[[Page 57373]]

England Executive Park, Burlington, MA 01803; e-mail: 
richard.woldan@faa.gov; telephone (781) 238-7136; fax (781) 238-
7199, for more information about this AD.

Material Incorporated by Reference

    (j) None.

    Issued in Burlington, Massachusetts, on September 10, 2010.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-23100 Filed 9-20-10; 8:45 am]
BILLING CODE 4910-13-P

