AD 2002-16-25

[Federal Register Volume 67, Number 163 (Thursday, August 22, 2002)]
[Rules and Regulations]
[Pages 54338-54339]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-21355]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-10-AD; Amendment 39-12864; AD 2002-16-25]
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: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), that 
is applicable to Turbomeca S.A. Arriel models 2 S1, 2 B, and 2 C 
turboshaft engines. This amendment requires initial and repetitive 
visual inspections for fuel leaks, and replacement of fuel pumps that 
are found leaking fuel. In addition, this amendment requires that fuel 
pumps found with pump wall thickness below minimum be removed from 
service. This amendment 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 this 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: Effective September 26, 2002. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of September 26, 2002.

ADDRESSES: The service information referenced in this AD 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 Federal Aviation Administration (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: Richard Woldan, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7136; 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 S.A. Arriel models 2 S1, 2 B, and 2 C 
turboshaft engines was published in the Federal Register on February 
11, 2002 (67 FR 6210). That action proposed to require initial and 
repetitive visual inspections for fuel leaks, and replacement of fuel 
pumps that are found leaking fuel. In addition, that action proposed to 
require that fuel pumps found with pump wall thickness below minimum be 
removed from service. These proposed actions would be done in 
accordance with Turbomeca Service Bulletin (SB) No. 292 73 2803, dated 
July 2, 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.

Economic Analysis

    There are approximately 44 engines of the affected design in the 
worldwide fleet. It is unknown how many engines are installed on 
aircraft of U.S. registry that would be affected by this AD. The FAA 
estimates that it would take approximately 1.5 work hours per engine to 
accomplish the 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 of the AD is estimated to be $59,090 
per engine. Assuming all 44 engines are installed on aircraft of U.S. 
registry, the total cost is estimated to be $2,599,960. The 
manufacturer has advised the Direction Generale de L'Aviation Civile 
(DGAC), which is the airworthiness authority for France, that affected 
pumps may be exchanged free of charge, thereby substantially reducing 
the potential cost of this rule.

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in

[[Page 54339]]

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) 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:

2002-16-25  Turbomeca S.A.: Amendment 39-12864. 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 is 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 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 with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the aircraft to a location where the 
requirements of this AD can be done.

Documents That Have Been Incorporated by Reference

    (g) The inspections and removals must be done in accordance with 
Turbomeca SB No. 292 73 2803, dated July 2, 1999. 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, 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 99-
285(A), dated July 13, 1999.

Effective Date

    (h) This amendment becomes effective on September 26, 2002.

    Issued in Burlington, Massachusetts, on August 14, 2002.
Mark C. Fulmer,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 02-21355 Filed 8-21-02; 8:45 am]
BILLING CODE 4910-13-P