AD 2001-12-19

[Federal Register Volume 66, Number 120 (Thursday, June 21, 2001)]
[Rules and Regulations]
[Pages 33164-33166]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-15392]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-15-AD; Amendment 39-12275; AD 2001-12-19]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. Artouste II and Artouste 
III Series Turboshaft Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), that 
is applicable to Turbomeca S.A. Artouste II and Artouste III series 
turboshaft engines. This amendment requires installation of 
modification TU 24, TU 167, or TU 164, depending on the specific engine 
series. These modifications will prevent uncommanded partial closing or 
total closing of the electrical fuel cock, which will prevent 
uncommanded in-flight engine shutdown. From the effective date of this 
AD, and until the modification is installed, this amendment will also 
limit the duration of the engine operating cycle. This amendment is 
prompted by reports of unexpected power loss during test flights. The 
actions specified by this AD are intended to prevent unexpected power 
loss, which could result in an uncommanded in-flight engine shutdown, 
autorotation, and forced landing.

DATES: Effective date July 26, 2001. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of July 26, 2001.

ADDRESSES: The service information referenced in this AD may be 
obtained from Turbomeca S.A, Turbomeca S.A.64511 Bordes Cedex, France; 
telephone 33 05 59 64 40 00, fax 33 05 59 64 60 80. This information 
may be examined 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.

[[Page 33165]]


FOR FURTHER INFORMATION CONTACT: Glorianne Niebuhr, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7132; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an AD that is 
applicable to Turbomeca Artouste II and Artouste III series turboshaft 
engines was published in the Federal Register on May 31, 2000 (65 FR 
34602). That action proposed to require installation of modification TU 
24, TU 167, or TU 164, depending on the specific engine series, in 
accordance with Turbomeca Artouste II Service Bulletin (SB) No. 223 72 
0070, dated January 21, 1999; Turbomeca Artouste III SB No. 218 80 
0098, dated January 14, 1999; or Turbomeca Artouste III SB No. 218 80 
0093, Revision 2, dated January 14, 1999.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.
    There are approximately 3,102 Turbomeca S.A. Artouste II and 
Artouste III series turboshaft engines of the affected design in the 
worldwide fleet. The FAA estimates that 213 engines installed on 
helicopters of US registry would be affected by this proposed AD, that 
it would take approximately two work hours per engine to accomplish the 
proposed actions, and that the average labor rate is $60 per work hour. 
Required parts would cost approximately $630 per engine. Based on these 
figures, the total cost impact of the proposed AD on US operators is 
estimated to be $159,750. The manufacturer has advised the Direction 
Generale de L'Aviation Civile (DGAC), which is the airworthiness 
authority for France, that it may provide modification TU 24, TU 164, 
or TU 167 at no cost to the operator, thereby substantially reducing 
the cost impact of this proposed rule.

Regulatory Impact

    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.
    For the reasons discussed above, I certify that this action (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) if promulgated, 
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. A final evaluation has been prepared for 
this action and it is contained in the Rules Docket. A copy of it may 
be obtained by contacting 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 a new airworthiness directive 
to read as follows:

2001-12-19  Turbomeca S.A.: Amendment 39-12275. Docket No. 2000-NE-
15-AD.

Applicability

    This airworthiness directive (AD) is applicable to Turbomeca 
S.A. Artouste II and Artouste III series turboshaft engines. These 
engines are installed on, but not limited to, Alouette II SE 3130, 
Alouette II SE 313 B, Eurocopter SA 315 LAMA, and SA 316 Alouette 
III series 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 (h) 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

    Required as indicated, unless accomplished previously.
    To prevent unexpected power loss, which could result in an 
uncommanded in-flight engine shutdown, autorotation, and forced 
landing, accomplish the following:

For Artouste II Engines

    (a) As of the effective date of this AD, the duration of the 
operating cycle (start-up to shutdown) is limited to two hours total 
until modification TU 24 is installed in accordance with Turbomeca 
Artouste II Service Bulletin (SB) 218 80 0070, Section 2, dated 
January 21, 1999.
    (b) At the next shop visit, within 30 days, or within 120 cycles 
after the effective date of this AD, whichever occurs first, install 
modification TU 24 in accordance with Turbomeca Artouste II SB 218 
80 0070, Section 2, dated January 21, 1999.

For Artouste III B and Artouste III B1 Engines

    (c) As of the effective date of this AD, the duration of the 
operating cycle (start-up to shutdown) is limited to two hours total 
until modification TU 167 is installed in accordance with Turbomeca 
Artouste III SB 218 80 0093, Revision 2, Section 2, dated January 
14, 1999.
    (d) At the next shop visit, within 30 days, or within 120 cycles 
after the effective date of this AD, whichever occurs first, install 
modification TU 167 in accordance with Turbomeca Artouste III 
Service Bulletin 218 80 0093, Revision 2, Section 2, dated January 
14, 1999.

For Artouste III D Engines

    (e) As of the effective date of this AD, the duration of the 
operating cycle (start-up to shutdown) is limited to two hours total 
until modification TU 164 is installed in accordance with Turbomeca 
Artouste III Service Bulletin 218 80 0098, Section 2, dated January 
14, 1999.
    (f) At the next shop visit, within 30 days, or within 120 cycles 
after the effective date of this AD, whichever occurs first, install 
modification TU 164 in accordance with Turbomeca Artouste III 
Service Bulletin 218 80 0098, Section 2, dated January 14, 1999.

Definition

    (g) For the purpose of this AD, a shop visit is defined as any 
time when the engine is removed from the helicopter for maintenance.

Alternative Methods of Compliance

    (h) 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. 
Operators shall submit their request through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Engine Certification Office.


[[Page 33166]]


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

Special Flight Permits

    (i) Special flight permits may be issued in accordance with 
sections 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 accomplished.

Documents That Have Been Incorporated by Reference

    (j) The inspection shall be done in accordance with the 
following Turbomeca service bulletins (SBs):

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             Document No.                       Pages                 Revision                    Date
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SB Artouste II SB 223 72 0070; Total   All...................  Original..............  Jan. 21, 1999.
 pages: 16.
SB Artouste III SB 218 80 0093; Total  All...................  2.....................  Jan. 14, 1999.
 pages: 18.
SB Artouste III SB 218 80 0098; Total  All...................  Original..............  Jan. 14, 1999.
 pages: 10.
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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 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 (DGAC) Airworthiness Directive (AD) 
1999-005(A), dated January 13, 1999, and AD 1999-090(A), dated 
February 24, 1999.

Effective Date

    (k) This amendment becomes effective on July 26, 2001.

    Issued in Burlington, Massachusetts, on June 11, 2001.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 01-15392 Filed 6-20-01; 8:45 am]
BILLING CODE 4910-13-P