AD 2002-14-26

[Federal Register Volume 67, Number 140 (Monday, July 22, 2002)]
[Rules and Regulations]
[Pages 47682-47684]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-18203]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-35-AD; Amendment 39-12826; AD 2002-14-26]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. Arriel Models 1A, 1A1, 
1B, 1D, and 1D1 Turboshaft Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to Turbomeca S.A. Arriel models 1A, 1A1, 1B, 1D, and 1D1 
turboshaft engines. This action requires installation of containment 
shield rings around the free turbine blade area, and installation of a 
double support around the gearbox free turbine bearing housing. This 
amendment is prompted by two reports of the cantilevered axis of the 
free turbine moving from its design position and inducing blade 
trajectories outside the current design free turbine containment area. 
This condition can lead to uncontainment of the free turbine during an 
overspeed

[[Page 47683]]

event. The actions specified in this AD are intended to prevent 
uncontainment of the free turbine during an overspeed event, resulting 
in damage to the helicopter.

DATES: Effective August 6, 2002. The incorporation by reference of 
certain publications listed in the rule is approved by the Director of 
the Federal Register as of August 6, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before September 20, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2001-NE-35-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8:00 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. Comments may also be sent via 
the Internet using the following address: ``<a href="/cdn-cgi/l/email-protection#d1e8fcb0bfb4fcb0b5b2bebcbcb4bfa591b7b0b0ffb6bea7"><span class="__cf_email__" data-cfemail="e9d0c488878cc4888d8a8684848c879da98f8888c78e869f">[email&#160;protected]</span></a>''. 
Comments sent via the Internet must contain the docket number in the 
subject line.
    The service information referenced in this AD may be obtained from 
Turbomeca S.A., 40220 Tarnos, France; telephone: (33) 05 59 64 40 00; 
Fax: (33) 05 59 64 60 80. This information may be examined, by 
appointment, at the FAA, New England Region, Office of the Regional 
Counsel, 12 New England Executive Park, Burlington, MA; or at the 
Office of the Federal Register, 800 North Capitol Street, NW, suite 
700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace 
Engineer, Engine Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park; Burlington, MA 01803-5299, 
telephone (781) 238-7175; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The Direction Generale de L'Aviation Civile 
(DGAC), which is the airworthiness authority for France, recently 
notified the FAA that an unsafe condition may exist on Turbomeca S.A. 
Arriel models 1A, 1A1, 1B, 1D, and 1D1 turboshaft engines. The DGAC 
advises that two reports were received of the cantilevered axis of the 
free turbine moving from its design position and inducing blade 
trajectories outside the current design, free turbine containment area. 
This condition can lead to uncontainment of the free turbine during an 
overspeed event.

Manufacturer's Service Information

    Turbomeca S.A. has issued service bulletin (SB) No. A292 72 0206, 
Update 2, dated October 23, 2000, which specifies installation of 
modification TU 254, containment shield ring made of INCO 625 material, 
SB No. A292 72 0207, Update 2, dated October 23, 2000, which specifies 
installation of modification TU 255, additional containment shield ring 
made of Z10CNT 18-11 material, and SB No. 292 72 0208, Update 2, dated 
May 13, 1996, which specifies installation of modification TU 259, 
double support around the reduction gearbox free turbine bearing 
housing, to maintain bearing centering. The DGAC classified these SB's 
as mandatory and issued AD 1995-069(A)R3, dated March 7, 2001, to 
assure the airworthiness of these Turbomeca S.A. engines in France.

Bilateral Airworthiness Agreement

    This engine model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. The FAA has examined the findings of 
the DGAC, reviewed all available information, and determined that AD 
action is necessary for products of this type design that are 
certificated for operation in the United States.

FAA's Determination of an Unsafe Condition and Required Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on other Turbomeca S.A. Arriel models 1A, 1A1, 1B, 1D, 
and 1D1 turboshaft engines of the same type design, this AD is being 
issued to prevent uncontainment of the free turbine during an overspeed 
event, resulting in damage to the helicopter. This AD requires 
installation of containment shield rings around the free turbine blade 
area, and installation of a double support around the gearbox free 
turbine bearing housing to maintain bearing centering. The actions must 
be done in accordance with the SB's described previously.

Immediate Adoption of This AD

    Since there are currently no domestic operators of this engine 
model affected by the adoption of this rule, notice and opportunity for 
prior public comment are unnecessary. Therefore, a situation exists 
that allows the immediate adoption of this regulation, and good cause 
exists for making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications should identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NE-35-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it 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. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this final rule.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and is not a ``significant regulatory action'' 
under Executive Order 12866. It has been determined further that this 
action involves an emergency regulation

[[Page 47684]]

under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 
1979). If it is determined that this emergency regulation otherwise 
would be significant under DOT Regulatory Policies and Procedures, a 
final regulatory evaluation will be prepared and placed in the Rules 
Docket. A copy of it, if filed, may be obtained from the Rules Docket 
at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new 
airworthiness directive:

2002-14-26  Turbomeca S.A.: Amendment 39-12826. Docket No. 2001-NE-
35-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to Turbomeca S.A. Arriel models 1A, 1A1, 1B, 1D, and 1D1 turboshaft 
engines. These engines are installed on, but not limited to, Astar 
AS350D; Eurocopter AS350B, BA, B1, L1, and B2N; and Fennic AS550U2 
helicopters.

    Note 1: This AD applies to each engine identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For engines that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (c) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Compliance with this AD is required as indicated, 
unless already done.
    To prevent uncontainment of the free turbine during an overspeed 
event, resulting in damage to the helicopter, do the following:
    (a) For Arriel engine models 1A and 1A1 that have incorporated 
modification TU 13, but have not incorporated modification TU 99 and 
modification TU 215, and for Arriel engine models 1B and 1D that 
have not incorporated modification TU 99 and modification TU 215, do 
the following within 30 days after the effective date of this AD:
    (1) Install containment shield ring in accordance with the 
Instructions to be Incorporated, paragraphs 2A. through 2C, 
(modification TU 254) of service bulletin (SB) No. A292 72 0206, 
Update 2, dated October 23, 2000.
    (2) Install double support around the reduction gearbox free 
turbine bearing housing, in accordance with Instructions for 
Incorporation, paragraphs 2A. through 2C, (modification TU 259) of 
SB No. 292 72 0208, Update 2, dated May 13, 1996.
    (b) For Arriel engine models 1A and 1A1 that have incorporated 
modification TU 13 and modification TU 99, but have not incorporated 
modification TU 215, and Arriel engine models 1B, 1D, and 1D1 that 
have incorporated modification TU 99, but have not incorporated 
modification TU 215, do the following within 30 days after the 
effective date of this AD:
    (1) Install additional containment shield ring, in accordance 
with the Instructions to be Incorporated, paragraphs 2A. through 2C, 
(modification TU 255) of SB No. A292 72 0207, Update 2, dated 
October 23, 2000.
    (2) Install double support around the reduction gearbox free 
turbine bearing housing, in accordance with Instructions for 
Incorporation, paragraphs 2A. through 2C, (modification TU 259) of 
SB No. 292 72 0208, Update 2, dated May 13, 1996.

Alternative Methods of Compliance

    (c) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Engine Certification Office (ECO). 
Operators must submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, ECO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the ECO.

Special Flight Permits

    (d) Special flight permits may be issued in accordance with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the helicopter to a location where the 
requirements of this AD can be done.

Documents That Have Been Incorporated by Reference

    (e) The modifications must be done in accordance with the 
following Turbomeca S.A. mandatory service bulletins (MSB's):

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              Document No.                          Pages              Revision                Date
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MSB No. A292 72 0206, Total pages: 8...  All.......................            2  Oct. 23, 2000.
MSB No. A292 72 0207, Total pages: 7...  All.......................            2  Oct. 23, 2000.
MSB No. 292 72 0208, Total pages: 8....  All.......................            2  May 13, 1996.
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This incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Turbomeca S.A., 40220 Tarnos, 
France; telephone: (33) 05 59 64 40 00; fax: (33) 05 59 64 60 80. 
Copies may be inspected, by appointment, at the FAA, New England 
Region, Office of the Regional Counsel, 12 New England Executive 
Park, Burlington, MA; or at the Office of the Federal Register, 800 
North Capitol Street, NW, suite 700, Washington, DC.

    Note 3: The subject of this AD is addressed in Direction 
Generale de L'Aviation Civile airworthiness directive AD 1995-
069(A)R3.

Effective Date

    (f) This amendment becomes effective on August 6, 2002.

    Issued in Burlington, Massachusetts, on July 8, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 02-18203 Filed 7-19-02; 8:45 am]
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