Airworthiness Directives; Turbomeca S.A. Arriel 2B and 2B1 Turboshaft Engines

[Federal Register Volume 74, Number 79 (Monday, April 27, 2009)]
[Rules and Regulations]
[Pages 18981-18982]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-9333]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28077; Directorate Identifier 2007-NE-20-AD; 
Amendment 39-15889; AD 2009-09-03]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. Arriel 2B and 2B1 
Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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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:

    Several cases of Gas Generator Turbine (HP Turbine) blade 
rearward displacement have been detected during borescope inspection 
or in repair centre following engine disassembly. Two of them 
resulted in blade rubs between the rear face of the fir-tree roots 
and the rear bearing support cover. High HP blade rearward 
displacement can potentially result in blade release due to fatigue 
of the blade, which would cause an uncommanded in-flight engine 
shutdown.

We are issuing this AD to prevent an uncommanded in-flight engine 
shutdown which could result in an emergency autorotation landing or, at 
worst, an accident.

DATES: This AD becomes effective June 1, 2009. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in this AD as of June 1, 2009.

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 & 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 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on December 9, 2008 (73 
FR 74661). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states that:

    Several cases of Gas Generator Turbine (HP Turbine) blade 
rearward displacement have been detected during borescope inspection 
or in repair centre following engine disassembly. Two of them 
resulted in blade rubs between the rear face of the fir-tree roots 
and the rear bearing support cover.
    High HP blade rearward displacement can potentially result in 
blade release due to fatigue of the blade, which would cause an 
uncommanded in-flight engine shutdown.
    The evaluation of this condition has prompted to require a 
periodic borescope inspection in order to detect HP blade rearward 
displacement. Additionally, in case displacement is found above the 
specified limit, removal of Module 03 is required.

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.

Removal of the Arriel 2B1A Engine

    Since we issued the proposed AD, we discovered that we 
inadvertently listed the Arriel 2B1A engine in the applicability. We 
removed that model from the AD, as it is not certified for operation in 
the U.S.

Deletion of Reporting Requirement

    We deleted the Turbomeca reporting requirement from the AD, since 
we determined that the reporting requirement was unnecessary.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously.

Costs of Compliance

    We estimate that this AD will affect about 248 engines on 
helicopters of U.S. registry. We also estimate that it will take about 
2 work-hours per engine to perform the actions and that the average 
labor rate is $80 per work-hour. Based on these figures, we estimate 
the total cost of the AD to U.S. operators to be $39,680. 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:

[[Page 18982]]

    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:

2009-09-03 Turbomeca S.A.: Amendment 39-15889. Docket No. FAA-2007-
28077; Directorate Identifier 2007-NE-20-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective June 1, 
2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Turbomeca S.A. Arriel 2B and 2B1 
turboshaft engines. These engines are installed on, but not limited 
to, Eurocopter AS 350 B3 and EC 130 B4 helicopters.

Reason

    (d) Several cases of Gas Generator Turbine (HP Turbine) blade 
rearward displacement have been detected during borescope inspection 
or in repair centre following engine disassembly. Two of them 
resulted in blade rubs between the rear face of the fir-tree roots 
and the rear bearing support cover. High HP blade rearward 
displacement can potentially result in blade release due to fatigue 
of the blade, which would cause an uncommanded in-flight engine 
shutdown.

We are issuing this AD to prevent an uncommanded in-flight engine 
shutdown which could result in an emergency autorotation landing or, 
at worst, an accident.

Actions and Compliance

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

Initial Inspection

    (1) Perform an initial HP turbine borescope inspection according 
to Turbomeca S.A. Mandatory Service Bulletin (MSB) No. 292 72 2825, 
dated April 5, 2007 as follows:
    (i) For engines with fewer than 500 hours and 450 cycles since 
new or since the last HP turbine borescope inspection, inspect 
before reaching 600 hours or 500 cycles, whichever occurs first. 
Replace HP turbine modules with rearward turbine blade displacement 
greater than 0.5 mm.
    (ii) For the remaining engines, inspect within the next 100 
hours. Replace HP turbine modules with rearward turbine blade 
displacement greater than 0.5 mm.

Repetitive Inspections

    (2) Perform repetitive HP turbine borescope inspections 
according to Turbomeca S.A. MSB No. 292 72 2825, dated April 5, 
2007:
    (i) Within 600 hours or 500 cycles from the previous inspection, 
whichever occurs first, if the rearward displacement of the turbine 
blades was less than 0.2 mm. Replace HP turbine modules with 
rearward turbine blade displacement greater than 0.5 mm.
    (ii) Within 100 hours of the previous inspection if the rearward 
displacement of the turbine blades was between 0.2 mm and 0.5 mm. 
Replace HP turbine modules with rearward turbine blade displacement 
greater than 0.5 mm.

FAA AD Differences

    (f) For clarification, we restructured the actions and 
compliance wording of this AD.
    (g) We deleted the Turbomeca reporting requirement from the AD, 
since we determined that the reporting requirement was unnecessary.

Alternative Methods of Compliance (AMOCs)

    (h) 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 EASA Airworthiness Directive 2007-0109, dated April 
19, 2007, and Turbomeca S.A. MSB No. 292 72 2825, dated April 5, 
2007, for related information.
    (j) Contact James Lawrence, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & 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

    (k) You must use Turbomeca S.A. Mandatory Service Bulletin No. 
292 72 2825, dated April 5, 2007, to do the actions required by this 
AD, unless the AD specifies otherwise.
    (l) 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.
    (m) 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 April 16, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-9333 Filed 4-24-09; 8:45 am]
BILLING CODE 4910-13-P

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