[Federal Register: December 9, 2008 (Volume 73, Number 237)]
[Proposed Rules]
[Page 74661-74663]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09de08-16]
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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]
RIN 2120-AA64
Airworthiness Directives; Turbomeca S.A. Arriel 2B, 2B1, and 2B1A
Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) provided by the aviation
authority of France to identify and correct an unsafe condition on an
aviation product. The MCAI states the following:
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 proposing this AD to prevent an uncommanded in-flight engine
shutdown which could result in an emergency autorotation landing or, at
worst, an accident.
DATES: We must receive comments on this proposed AD by January 8, 2009.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, 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 proposed 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: Christopher Spinney, Aerospace
Engineer, Engine Certification Office, FAA, Engine & Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803; e-
mail: christopher.spinney@faa.gov; telephone (781) 238-7175; fax (781)
238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-
28077; Directorate Identifier 2007-NE-27-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on 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 proposed 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).
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2007-0109, dated April 19, 2007 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The EASA AD states:
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.
You may obtain further information by examining the EASA AD in the AD
docket.
Relevant Service Information
Turbomeca S.A. has issued Mandatory Service Bulletin No. 292 72
[[Page 74662]]
2825, Original Issue, dated April 5, 2007. The actions described in
this service information are intended to correct the unsafe condition
identified in the EASA AD.
FAA's Determination and Requirements of This Proposed 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 EASA AD and service information referenced
above. We are proposing 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 proposed AD would require inspecting for HP blade rearward
displacement.
Costs of Compliance
We estimate that this proposed AD would affect about 248 engines on
helicopters of U.S. registry. We also estimate that it would take about
2 work-hours per engine to perform the proposed actions and that the
average labor rate is $80 per work-hour. Based on these figures, we
estimate the total cost of the proposed 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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 proposed
regulation:
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 proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Turbomeca S.A.: Docket No. FAA-2007-28077; Directorate Identifier
2007-NE-20-AD.
Comments Due Date
(a) We must receive comments by January 8, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Turbomeca S.A. Arriel 2B, 2B1, and 2B1A
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.
(3) After each inspection, the compliance certificate must be
sent to Turbomeca S.A. within 7 days, according to Sec. 2.D(1)(c)
of Turbomeca S.A. MSB No. 292 72 2825, dated April 5, 2007.
FAA AD Differences
(f) We modified the drawdown times to be more consistent with
the compliance times.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) 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.
(2) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
Related Information
(h) 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.
(i) Contact Christopher Spinney, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA
[[Page 74663]]
01803; e-mail: christopher.spinney@faa.gov; telephone (781) 238-
7175; fax (781) 238-7199, for more information about this AD.
Issued in Burlington, Massachusetts, on December 2, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E8-29102 Filed 12-8-08; 8:45 am]
BILLING CODE 4910-13-P