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[Federal Register Volume 65, Number 105 (Wednesday, May 31, 2000)]
[Proposed Rules]
[Pages 34602-34604]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-13567]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-15-AD]
RIN 2120-AA64

Airworthiness Directives; Turbomeca Artouste II and Artouste III 
Series Turboshaft Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

DATES: Comments must be received by July 31, 2000.

ADDRESSES: Submit comments to the Federal Aviation Administration 
(FAA), New England Region, Office of the Regional Counsel, Attention: 
Rules Docket No. 2000-NE-15-AD, 12 New England Executive Park, 
Burlington, MA 01803-5299. Comments may also be submitted to the Rules 
Docket by using the following Internet address: ``[email protected]''. Comments may be inspected at this location between 
8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal 
holidays.
    The service information referenced in the proposed rule may be 
obtained from Turbomeca, 40220 Tarnos, 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.

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:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications should identify the Rules Docket number 
and be submitted to the address specified above. All communications 
received on or before the closing date for comments, specified above, 
will be considered before taking action on the proposed rule. The 
proposals contained in this notice may be changed in light of the 
comments received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NE-15-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, New England Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 2000-NE-15-AD, 12 New England Executive 
Park, Burlington, MA 01803-5299.

Discussion

    The Director General de L'Aviation Civile (DGAC), which is the 
airworthiness authority for France, recently notified the Federal 
Aviation Administration (FAA) that an unsafe condition may exist on 
Turbomeca Artouste II and Artouste III series turboshaft engines. The 
DGAC advises that it has received reports of unexpected power loss in 
service. This power loss is due to closing of the electrical fuel cock. 
This condition, if not corrected, could result in unexpected power 
loss, which could result in an uncommanded in-flight engine shutdown, 
autorotation, and forced landing.

Service Information

    Turbomeca has issued Artouste II Service Bulletin (SB) No. 223 72 
0070, dated January 21, 1999, that specifies procedures for installing 
modification TU 24, which provides an equipped relay inside the control 
unit. Turbomeca has also issued Artouste III SB No. 218 80 0098, dated 
January 14, 1999 and SB No. 218 80 0093, Revision 2, dated January 14, 
1999 which state similar requirements and specify procedures for 
installation of modifications TU 164 and TU 167 respectively. The DGAC 
classified these SB's as mandatory and issued Airworthiness Directive 
(AD) 1999-005(A), dated January 13, 1999, and AD 1999-090(A), dated 
February 24, 1999, in order to ensure the airworthiness of these 
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.

[[Page 34603]]

Proposed Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on other engines used on helicopters of the same type 
design registered in the United States, the proposed AD would require 
installation of modification TU 24, TU 164 or TU 167 at the earliest of 
the following:
     The next shop visit after the effective date of this AD, 
or
     Within 30 days after the effective date of this AD, or
     Within 120 cycles-in-service after the effective date of 
this AD.
    The actions would be required to be accomplished in accordance with 
the SB's described previously. This proposal will also limit the 
duration of the engine operating cycle, from the effective date of this 
AD, to a two-hour cycle (engine start/stop) until the modifications are 
installed.

Economic Analysis

    There are approximately 3,102 engines of the affected design in the 
worldwide fleet. The FAA estimates that 213 engines installed on 
aircraft of US registry would be affected by this proposed AD, that it 
would take approximately 2 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 DGAC that it 
may provide modifications TU 164 and TU 167 at no cost to the operator, 
thereby substantially reducing the cost impact of this proposed rule.

Regulatory Impact

    This proposal 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 proposal.
    For the reasons discussed above, I certify that 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) 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 copy of the draft 
regulatory evaluation prepared for this action 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, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:

Turbomeca: Docket No. 2000-NE-15-AD.

    Applicability: This airworthiness directive (AD) applies to 
Turbomeca Artouste II and Artouste III B, B1 and D 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 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 Service 
Bulletin 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 Service Bulletin 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.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive,

[[Page 34604]]

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.

    Issued in Burlington, Massachusetts, on May 23, 2000.

Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 00-13567 Filed 5-30-00; 8:45 am]
BILLING CODE 4910-13-U
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