Airworthiness Directives; Turbomeca S.A. Arrius 2F Turboshaft Engines

[Federal Register Volume 73, Number 128 (Wednesday, July 2, 2008)]
[Rules and Regulations]
[Pages 37793-37795]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-14311]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28053; Directorate Identifier 2007-NE-18-AD; 
Amendment 39-15590; AD 2008-13-27]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. Arrius 2F Turboshaft 
Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

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:

    This AD is issued following a case of non-commanded in-flight 
engine shut-down which occurred on an ARRIUS 2F turboshaft engine, 
following the seizing of the gas generator. The result may be an 
emergency autorotation landing or, at worst, an accident.
    Investigations of this event have revealed that the seizing of 
the gas generator was caused by the fracture of the separator cage 
of the gas generator front bearing, due to high-cycle fatigue cracks 
initiated in the lubrication slots of the separator cage.

We are issuing this AD to prevent uncommanded shutdown of the engine, 
which could lead to an accident.

DATES: This AD becomes effective August 6, 2008. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in this AD as of August 6, 2008.

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: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
[email protected]; telephone (781) 238-7176; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR

[[Page 37794]]

part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on August 28, 2007 (72 
FR 49236). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states that:

    This AD is issued following a case of non-commanded in-flight 
engine shut-down which occurred on an Arrius 2F turboshaft engine, 
following the seizing of the gas generator. The result may be an 
emergency autorotation landing, or, at worst, an accident.
    Investigations of this event have revealed that the seizing of 
the gas generator was caused by the fracture of the separator cage 
of the gas generator front bearing, due to high-cycle fatigue cracks 
initiated in the lubrication slots of the separator cage.
    Modification Tf 12 introduces a new gas generator front bearing 
without lubrication slots on the separator cage.

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.

Change to the Compliance End Date

    We have changed the compliance time from ``at the next shop visit 
after the effective date of the AD, but no later than April 30, 2008'' 
to ``at the next shop visit after the effective date of this AD, but no 
later than 30 days after the effective date of this AD'' to allow the 
operators more time to complete the requirements of this AD.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

Differences Between This AD and the MCAI or Service Information

    The Mandatory Continuing Airworthiness Information (MCAI) and 
service information require the operators to comply with the 
requirements at the next shop visit after the effective date of the AD, 
but no later than April 30, 2008. We require compliance at the next 
shop visit after the effective date of this AD, but no later than 30 
days after the effective date of this AD.

Costs of Compliance

    We estimate that this AD will affect 61 engines of U.S. registry. 
We also estimate that it will take about 10 work-hours per engine to 
comply with this AD. The average labor rate is $80 per work-hour. 
Required parts will cost about $111,440. Based on these figures, we 
estimate the cost of this AD to the U.S. operators to be $6,846,640. 
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 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 adding the following new AD:

2008-13-27 Turbomeca S.A.: Amendment 39-15590. Docket No. FAA-2007-
28053; Directorate Identifier 2007-NE-18-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective August 
6, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Turbomeca S.A. Arrius 2F turboshaft 
engines that have not incorporated Turbomeca Modification Tf 12A. 
These engines are installed on, but not limited to, Eurocopter 
EC120B helicopters.

Reason

    (d) European Aviation Safety Agency (EASA) AD No. 2007-0057, 
dated March 1, 2007, states:
    This AD is issued following a case of non-commanded in-flight 
engine shut-down which occurred on an Arrius 2F turboshaft engine, 
following the seizing of the gas generator. The result may be an 
emergency autorotation landing, or, at worst, an accident.
    Investigations of this event have revealed that the seizing of 
the gas generator was caused by the fracture of the separator cage 
of the gas generator front bearing, due to high-cycle fatigue cracks 
initiated in the lubrication slots of the separator cage.
    Modification Tf12 introduces a new gas generator front bearing 
without lubrication slots on the separator cage.

We are issuing this AD to prevent uncommanded shutdown of the 
engine, which could lead to an accident.

Actions and Compliance

    (e) Unless already done, do the following actions.

[[Page 37795]]

    (1) At the next engine shop visit after the effective date of 
this AD, but no later than 30 days after the effective date of this 
AD, replace the engine module 02 with a module that incorporates 
Turbomeca Modification Tf 12A. Turbomeca Modification Tf 12A 
installs into the engine module 02 a new gas generator front bearing 
without lubrication slots on the separator cage.
    (2) Use the Instructions to be Incorporated section of Turbomeca 
Mandatory Service Bulletin No. 319 72 4012, Update No. 1, dated 
September 19, 2006, to do the actions in paragraph (e)(1) of this 
AD.

FAA AD Differences

    (f) The Mandatory Continuing Airworthiness Information (MCAI) 
and service information require the operators to comply with the 
requirements at the next shop visit after the effective date of the 
AD, but no later than April 30, 2008. We require compliance at the 
next shop visit after the effective date of this AD, but no later 
than 30 days after the effective date of this AD.

Other FAA AD Provisions

    (g) 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

    (h) Refer to EASA AD 2007-0057, dated March 1, 2007, for related 
information.
    (i) Contact James Lawrence, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
[email protected]; telephone (781) 238-7176; fax (781) 238-
7199, for more information about this AD.

Material Incorporated by Reference

    (j) You must use Turbomeca Mandatory Service Bulletin No. 319 72 
4012, Update No. 1, dated September 19, 2006, 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.

    Issued in Burlington, Massachusetts, on June 18, 2008.
Diane Cook,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E8-14311 Filed 7-1-08; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T03:29:25.866492+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

0748efe887e0889d476f765723601e46cc57248a6f2450dedd59a5136ec6a20b

Text SHA-256

0198cb1f1d7b5a2acd58262675bb96034690a6b8cb6f8cf153f88effbc98b73c