[Federal Register: April 27, 2009 (Volume 74, Number 79)]
[Rules and Regulations]
[Page 18981-18982]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr27ap09-3]
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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:
james.lawrence@faa.gov; 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:
james.lawrence@faa.gov; 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