[Federal Register Volume 75, Number 91 (Wednesday, May 12, 2010)]
[Proposed Rules]
[Pages 26681-26683]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-11324]
=======================================================================
-----------------------------------------------------------------------
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 and 2B1
Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to revise an existing airworthiness directive (AD)
for the products listed above. This proposed 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: Since issuance of AD 2007-0109, Turbom[eacute]ca has
released modification TU166 which consists in inserting HP blade
dampers between the HP disc and the HP blade platform. Introduction of
these dampers has demonstrated to limit axial displacement of the HP
blade relative to the disk in case of blade lock rupture or opening,
therefore eliminating the need for inspection and replacement.
We are proposing this AD to prevent an uncommanded in-flight engine
shutdown which could result in an emergency autorotation landing or an
accident.
DATES: We must receive comments on this proposed AD by June 28, 2010.
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.
Contact Turbomeca, 40220 Tarnos, France; telephone 33 05 59 74 40
00, fax 33 05 59 74 45 15 for the service information identified in
this proposed AD.
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
[[Page 26682]]
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
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:
[email protected]; telephone (781) 238-7117, 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-20-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
On April 16, 2009, the FAA issued AD 2009-09-03, Amendment 39-15889
(74 FR 18981, April 27, 2009). That AD requires performing an initial
and repetitive borescope inspection of the engine for rearward
displacement of the high-pressure turbine (HP) blades.
Actions Since AD 2009-09-03 Was Issued
Since that AD was issued, 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-
0109R1, dated November 9, 2009 (referred to after this as ``the
MCAI''), to correct an unsafe condition for the specified products. The
MCAI states:
Since issuance of AD 2007-0109, Turbom[eacute]ca has released
modification TU166 which consists in inserting HP blade dampers
between the HP disc and the HP blade platform. Introduction of these
dampers has demonstrated to limit axial displacement of the HP blade
relative to the disk in case of blade lock rupture or opening,
therefore eliminating the need for inspection and replacement.
Therefore, this AD revises AD 2007-0109 by retaining the same
requirements of AD 2007-0109 except that applicability is limited to
ARRIEL 2B, 2B1 and 2B1A engines which do not incorporate
modification TU166.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Turbomeca S.A. has issued Mandatory Service Bulletin No. 292 72
2825, Version B, dated September 21, 2009. 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.
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 proposed AD
would affect about 248 products of U.S. registry. We also estimate that
it would take about 2 work-hours per product to comply with this
proposed AD. The average labor rate is $85 per work-hour. Based on
these figures, we estimate the cost of the proposed AD on U.S.
operators to be $42,160.
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:
[[Page 26683]]
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing Amendment 39-15889 and
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 June 28, 2010.
Affected Airworthiness Directives (ADs)
(b) This AD revises AD 2009-09-03, Amendment 39-15889.
Applicability
(c) This AD applies to Turbomeca S.A. Arriel 2B and 2B1
turboshaft engines that don't incorporate modification TU166. These
engines are installed on, but not limited to, Eurocopter AS 350 B3
and EC 130 B4 helicopters.
Reason
(d) This AD results from:
Since issuance of AD 2007-0109, Turbom[eacute]ca has released
modification TU166 which consists in inserting HP blade dampers
between the HP disc and the HP blade platform. Introduction of these
dampers has demonstrated to limit axial displacement of the HP blade
relative to the disk in case of blade lock rupture or opening,
therefore eliminating the need for inspection and replacement.
We are issuing this AD to prevent an uncommanded in-flight engine
shutdown which could result in an emergency autorotation landing or
an accident.
Actions and Compliance
(e) Unless already done, do the following actions:
Initial Inspection
(1) Perform an initial high-pressure (HP) turbine borescope
inspection according to Turbomeca S.A. Mandatory Service Bulletin
(MSB) No. 292 72 2825, Version B, dated September 21, 2009, or
earlier version 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, Version B, dated
September 21, 2009 or earlier version:
(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.
Optional Terminating Action
(f) Incorporating modification TU166 terminates the repetitive
inspection requirements of paragraphs (e)(2)(i) and (e)(2)(ii) of
this AD.
FAA AD Differences
(g) For clarification, we restructured the actions and
compliance wording of this AD.
(h) We deleted the Turbomeca reporting requirement from the AD.
(i) Although EASA Airworthiness Directive 2007-0109R1, dated
November 9, 2009, applies to the Arriel 2B1A engine, this AD does
not apply to that model because it has no U.S. type certificate.
Alternative Methods of Compliance (AMOCs)
(j) 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
(k) Refer to EASA Airworthiness Directive 2007-0109R1, dated
November 9, 2009, and Turbomeca S.A. MSB No. 292 72 2825, Version B,
dated September 21, 2009, or earlier version, for related
information.
(l) Contact Kevin Dickert, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
[email protected]; telephone (781) 238-7117, fax (781) 238-7199.
Issued in Burlington, Massachusetts, on May 5, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2010-11324 Filed 5-11-10; 8:45 am]
BILLING CODE 4910-13-P