[Federal Register Volume 67, Number 28 (Monday, February 11, 2002)]
[Proposed Rules]
[Pages 6210-6212]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-3160]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-10-AD]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. Arriel Models 2 S1, 2 B, 
and 2 C Turboshaft Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The Federal Aviation Administration (FAA) proposes to adopt a 
new airworthiness directive (AD) that is applicable to Turbomeca S.A. 
Arriel models 2 S1, 2 B, and 2 C turboshaft engines. This proposal 
would require initial and repetitive visual inspections for fuel leaks, 
and replacement of fuel pumps that are found leaking fuel. In addition, 
this proposal would require removal from service fuel pumps that are 
found with pump wall thickness below minimum. This proposal is prompted 
by a manufacturing investigation of pump bodies found to have below 
minimum material thickness, which could cause fuel leakage through 
thin, porous walls, reducing fuel pump fire resistance. The actions 
specified by the proposed AD are intended to prevent fuel leakage, 
which may cause engine fires that could lead to an in-flight engine 
shutdown, damage to the helicopter, and forced landing.

DATES: Comments must be received by April 12, 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-10-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8 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: [email protected]. 
Comments sent via the Internet must contain the docket number in the 
subject line.
    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, by 
appointment, at the FAA, New England Region, Office of the Regional 
Counsel, 12 New England Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT: James Rosa, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone: (781) 
238-7152; 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 in triplicate 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 action 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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NE-10-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRM's

    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. 2001-NE-10-AD, 12 New England Executive 
Park, Burlington, MA 01803-5299.

Discussion

    The Direction Generale de L'Aviation Civile (DGAC), which is the 
airworthiness authority for France, has notified the FAA that an unsafe 
condition may exist on Turbomeca S.A. Arriel models 2 S1, 2 B, and 2 C 
turboshaft engines. The DGAC advises that it has received a 
manufacturer's report of 44 fuel metering HP/LP fuel pump assemblies 
that are suspected to

[[Page 6211]]

have pump body material wall thickness being below the minimum material 
thickness. This condition, if not corrected, may cause fuel leakage, 
which may cause engine fires that could lead to an in-flight engine 
shutdown, damage to the helicopter, and forced landing.

Manufacturer's Service Information

    Turbomeca has issued Service Bulletin (SB) No. 292 73 2803, dated 
July 2, 1999, that specifies procedures for initial and repetitive 
visual inspection for fuel leaks and serial number records inspections 
to locate 44 fuel metering HP/LP pump assemblies. These assemblies are 
suspected of having pump body material wall thickness below minimum 
material thickness and require initial and repetitive visual 
inspections, plus terminating action in the form of pump replacement or 
confirmation of correct pump body material wall thickness. The DGAC 
classified this service bulletin as mandatory and issued AD 99-285(A) 
in order to assure the airworthiness of these engines in France.

Bilateral Agreement Information

    This engine model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
Sec. 21.29 of Title 14 of the Code of Federal 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.

Proposed Requirements of This AD

    Since an unsafe condition has been identified that is likely to 
exist or develop on other Turbomeca S.A. Arriel models 2 S1, 2 B, and 2 
C turboshaft engines of the same type design that are used on 
helicopters registered in the United States, the proposed AD would 
require initial and repetitive visual inspections for fuel leaks, and 
replacement of fuel pumps that are found leaking fuel. In addition, 
this proposal would require removal from service fuel pumps that are 
found with pump wall thickness below minimum. This proposal would also 
require that pumps with correct body material wall thickness have the 
letter ``x'' added to the end of the SN on the pump. Except for the 
letter ``x'' marking, the actions would be required to be done in 
accordance with the service bulletin described previously.

Economic Analysis

    There are approximately 44 engines of the affected design in the 
worldwide fleet. It is unknown by the FAA how many engines are 
installed on aircraft of U.S. registry that would be affected by this 
proposed AD. The FAA estimates that it would take approximately 1.5 
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 $59,000 per engine. Based on these figures, the total 
cost effect of the proposed AD is estimated to be $59,090 per engine. 
Assuming all 44 engines are installed on aircraft of U.S. registry, the 
total cost effect is estimated to be $2,599,960. The manufacturer has 
advised the DGAC that affected pumps may be exchanged free of charge, 
thereby substantially reducing the potential cost effect of this 
proposed rule.

Regulatory Impact

    This proposed 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 proposed rule.
    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. 2001-NE-10-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to Turbomeca S.A. Arriel models 2 S1, 2 B, and 2 C turboshaft 
engines. These engines are installed on, but not limited to Sikorsky 
S76, Eurocopter France ``Ecureuil'' AS 350 B3, and Eurocopter France 
``Dauphin'' AS 365 N3 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 are affected, the owner/operator must request approval for 
an alternative method of compliance in accordance with paragraph (e) 
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 fuel leakage, which may cause engine fires that could 
lead to an in-flight engine shutdown, damage to the helicopter, and 
forced landing, do the following:

Inspections and Actions

    (a) For the fuel metering high pressure/low pressure (HP/LP) 
pump assemblies listed by serial number (SN) in Appendix 1 of 
Turbomeca Service Bulletin (SB) No. 292 73 2803, dated July 2, 1999, 
do the following:
    (1) After the last flight of each day, within five minutes of 
engine shutdown, perform a visual inspection of the floor of the 
helicopter engine bay for fuel leaks.
    (2) If evidence of a fuel leak is observed, inspect the fuel 
metering HP/LP pump assembly for leakage and if leakage is observed, 
replace with a serviceable pump assembly before further flight.
    (3) If visual inspection of the floor of the helicopter engine 
bay for fuel leaks reveals no leaks, do either of the following:
    (i) Continue repetitive visual inspections of the floor of the 
helicopter engine bay for fuel leaks in accordance with paragraph 
(a)(1) of this AD, and perform repetitive visual inspections of the 
fuel metering HP/LP pump assembly for fuel leaks at intervals not to 
exceed 50 hours of operation. If evidence of fuel leaking is 
observed, replace the pump assembly with a serviceable pump assembly 
before further flight, in accordance with

[[Page 6212]]

Turbomeca SB No. 292 73 2803, dated July 2, 1999; or
    (ii) Remove the pump assembly and inspect to determine if pump 
body material wall thickness is below the minimum material 
thickness, in accordance with Section 2 of Turbomeca SB No. 292 73 
2803, dated July 2, 1999. If pump body material wall thickness is at 
or above the minimum material thickness, mark the pump assembly by 
adding a letter ``x'' to the end of the SN.
    (b) Replace the fuel metering HP/LP pump assembly if listed by 
SN in Appendix 1 of Turbomeca Service Bulletin (SB) No. 292 73 2803, 
dated July 2, 1999, with a serviceable pump assembly by December 31, 
2006.

Definition

    (c) For the purposes of this AD, a serviceable pump assembly is 
a fuel metering HP/LP pump assembly not listed by SN in Appendix 1 
of Turbomeca SB No. 292 73 2803, dated July 2, 1999, or a fuel 
metering HP/LP pump assembly listed by SN in Appendix 1 whose pump 
body material wall thickness has been determined by inspection to be 
at or above the minimum material thickness, and marked in accordance 
with paragraph (a)(3)(ii) of this AD.

Terminating Action

    (d) Replacement, or verification of correct wall thickness of a 
fuel metering HP/LP pump assembly that is listed in Appendix 1 of 
Turbomeca SB No. 292 73 2803, dated July 2, 1999, with a serviceable 
pump assembly as defined in paragraph (c) of this AD, is considered 
terminating action for the inspection requirements specified in 
paragraph (a) of this AD.

Alternative Methods of Compliance

    (e) 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 request 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

    (f) Special flight permits may be issued in accordance 
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.

    Note 3: The subject of this AD is addressed in Direction 
Generale de L'Aviation Civile (DGAC) Airworthiness Directive AD 99-
285(A), dated July 13, 1999.


    Issued in Burlington, Massachusetts, on February 1, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 02-3160 Filed 2-8-02; 8:45 am]
BILLING CODE 4910-13-U