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[Federal Register: April 2, 2010 (Volume 75, Number 63)]
[Rules and Regulations]               
[Page 16664-16666]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr02ap10-10]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0302; Directorate Identifier 2009-NE-09-AD; 
Amendment 39-16245; AD 2009-08-08R1]
RIN 2120-AA64

 
Airworthiness Directives; Turbomeca ARRIEL 1B, 1D, 1D1, 2B, and 
2B1 Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are revising an existing 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:

    During production of Arriel 1 and Arriel 2 Power Turbine (PT) 
wheels, geometric non-conformances on blade fir tree roots have been 
detected by Turbom[eacute]ca. Potentially non-conforming PT blades 
have been traced as having been installed on Module M04 (PT) listed 
in Mandatory Service Bulletin (MSB) A292 72 0827 for Arriel 1 
engines and A292 72 2833 for Arriel 2 engines.
    The geometric non-conformities of the blades may potentially 
lead to a reduction in the fatigue resistance of PT blades to a 
lower level than their authorized in service use limit. This 
reduction of fatigue resistance can potentially result in blade 
release, which could cause an uncommanded in-flight shutdown.

    We are issuing this AD to prevent release of PT blades, which could 
result in an uncommanded in-flight shutdown and emergency autorotation 
landing.

DATES: This AD becomes effective May 7, 2010. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in this AD as of May 7, 2010.

ADDRESSES: The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

FOR FURTHER INFORMATION CONTACT: Kevin Dickert, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
kevin.dickert@faa.gov; telephone (781) 238-7117, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on December 23, 2009 
(74 FR 68194). That NPRM proposed to correct an unsafe condition for 
the specified products. The MCAI states:

    Since issuance of initial version of AD 2009-0112 additional 
information is available:

--The list of Modules M04 concerned by the restriction of the cycle 
use limit of these PT blades has been updated again: The serial 
numbers of Modules M04 which have been retrofitted are crossed out. 
However, no new affected Modules M04 have been identified. See 
figure 1 of the referenced Turbom[eacute]ca MSB.
--Additional testing and analysis had been carried out by 
Turbom[eacute]ca which allows increasing the cyclic use limit of 
these PT blades to 5 000 flight cycles.

    Therefore this AD revises AD 2009-0112 and requires establishing 
the cyclic use limit of these PT blades to 5 000 flight cycles.
    For PT blades having reached a number of flight cycles superior 
or equal to 5 000, removal of Module M04, or PT wheel assembly, or 
PT blades is required prior to next flight.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we required different actions 
in this AD from those in the MCAI in order to follow FAA policies. Any 
such differences are described in a separate paragraph of the AD. These 
requirements take precedence over the actions copied from the MCAI.

Costs of Compliance

    Based on the service information, we estimate that this AD will 
affect about 10 products of U.S. registry. We also estimate that it 
will take about 8 work-hours per product to comply with this AD. The 
average labor rate is $80 per work-hour. Required parts will cost about 
$43,000 per product. Based on

[[Page 16665]]

these figures, we estimate the cost of the AD on U.S. operators to be 
$436,400.

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.

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 provided in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, 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 removing amendment 39-15881, and 
adding the following new AD:

2009-08-08R1 Turbomeca S.A.: Amendment 39-16245. Docket No. FAA-
2009-0302; Directorate Identifier 2009-NE-09-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective May 7, 
2010.

Affected ADs

    (b) This AD revises AD 2009-08-08, Amendment 39-15881.

Applicability

    (c) This AD applies to:
    (1) Turbomeca Arriel 1B, 1D, and 1D1 turboshaft engines with the 
power turbine (PT) modules M04 installed, as listed by serial number 
(S/N) in Figure 1 of Turbomeca Alert Mandatory Service Bulletin 
(MSB) No. A292 72 0827, Version C, dated July 15, 2009; and
    (2) Turbomeca Arriel 2B and 2B1 turboshaft engines with the 
power turbine modules M04 installed, as listed by S/N in Figure 1 of 
Turbomeca Alert MSB No. A292 72 2833, Version C, dated July 15, 
2009.
    (3) These engines are installed on, but not limited to, 
Eurocopter AS 350 B, AS 350 BA, AS 350 B1, AS 350 B2, AS 350 B3, and 
EC 130 B4 helicopters.

Reason

    (d) European Aviation Safety Agency (EASA) AD No. 2009-0112R1, 
dated July 30, 2009, states:

    Since issuance of initial version of AD 2009-0112 additional 
information is available:

--The list of Modules M04 concerned by the restriction of the cycle 
use limit of these PT blades has been updated again: The serial 
numbers of Modules M04 which have been retrofitted are crossed out. 
However no new affected Modules M04 have been identified. See figure 
1 of the referenced Turbom[eacute]ca MSB.
--Additional testing and analysis had been carried out by 
Turbom[eacute]ca which allows increasing the cyclic use limit of 
these PT blades to 5,000 flight cycles.

We are issuing this AD to prevent release of PT blades, which could 
result in an uncommanded in-flight shutdown and emergency 
autorotation landing.

Actions and Compliance

    (e) Unless already done, do the following actions.
    (1) For engines with an affected Module M04 (PT module), which 
has accumulated 5,000 total PT cycles or more on the effective date 
of this AD, remove the PT blades from service before further flight.
    (2) For engines with an affected Module M04, which has 
accumulated fewer than 5,000 total PT cycles on the effective date 
of this AD, remove the PT blades from service before accumulating 
5,000 total PT cycles.
    (3) After the effective date of this AD, do not install any PT 
blades removed as specified in paragraph (e)(1) or (e)(2) of this 
AD, into any engine.

FAA AD Differences

    (f) Although the compliance section of EASA AD No. 2009-0112R1, 
dated July 30, 2009, states to replace the Module M04, or PT wheel 
assembly, or PT blades, this AD states to remove the PT blades from 
service.
    (g) Although EASA AD No. 2009-0112R1, dated July 30, 2009, 
applies to the Arriel 2B1A engine, this AD does not apply to that 
model because it has no U.S. type certificate.

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 EASA Airworthiness Directive 2009-0112R1, 
dated July 30, 2009, for related information.
    (j) Contact Kevin Dickert, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
kevin.dickert@faa.gov; telephone (781) 238-7117, fax (781) 238-7199, 
for more information about this AD.

Material Incorporated by Reference

    (k) You must use the service information specified in Table 1 of 
this AD to do the actions required by this AD, unless the AD 
specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Turbomeca, 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax 33 
05 59 74 45 15.
    (3) You may review copies at the FAA, New England Region, 12 New 
England Executive Park, Burlington, MA; or at the National Archives 
and Records Administration (NARA). For information on the 
availability of this material at NARA, call (202) 741-6030, or go 
to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

[[Page 16666]]



                                   Table 1--Material Incorporated by Reference
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        Service Bulletin No.                  Page                  Revision                     Date
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Mandatory Service Bulletin A292 72   All...................  Version C.............  July 15, 2009.
 0827.
Mandatory Service Bulletin A292 72   All...................  Version C.............  July 15, 2009.
 2833.
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    Issued in Burlington, Massachusetts, on March 16, 2010.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-6628 Filed 4-1-10; 8:45 am]
BILLING CODE 4910-13-P
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