AD 2003-11-10

[Federal Register Volume 68, Number 103 (Thursday, May 29, 2003)]
[Rules and Regulations]
[Pages 31972-31973]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 03-13114]



[[Page 31972]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NE-39-AD; Amendment 39-13169; AD 2003-11-10]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. Arrius -2F 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. Arrius -2F turboshaft engines with 
certain serial number (SN) Fuel Control Units (FCUs). This amendment 
requires adjusting the FCU maximum fuel flow mechanical stop position 
to a higher fuel flow setting. This amendment is prompted by an FCU 
discovered to have a maximum fuel flow limit adjusted below the maximum 
required setting. The actions specified by this AD are intended to 
prevent reduced maximum available power during takeoff, landing, or an 
emergency, which could significantly affect helicopter performance and 
result in loss of the helicopter.

DATES: Effective July 3, 2003. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of July 3, 2003.

ADDRESSES: The service information referenced in this AD may be 
obtained from 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, 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: Antonio Cancelliere, Aerospace 
Engineer, Engine Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; 
telephone (781) 238-7751; 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. Arrius -2F turboshaft engines with certain 
SN FCUs was published in the Federal Register on February 5, 2003 (68 
FR 5856). That action proposed to require adjusting the FCU maximum 
fuel flow mechanical stop position to a higher fuel flow setting in 
accordance with Alert Service Bulletin (ASB) No. A319 73 4808, dated 
September 1, 2000.

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 334 Turbomeca S.A. Arrius -2F turboshaft 
engines of the affected design in the worldwide fleet. The FAA 
estimates that four engines installed on aircraft of U.S. registry will 
be affected by this AD, that it will take approximately three work 
hours per engine to perform the required actions, and that the average 
labor rate is $60 per work hour. Required tooling would cost 
approximately $300 per engine. Based on these figures, the total cost 
of the AD to U.S. operators is estimated to be $1,920. The manufacturer 
has advised the FAA and Direction Generale de L'Aviation Civile, which 
is the airworthiness authority for France, that the operator may be 
provided with material and tooling at no cost to the operator, thereby 
substantially reducing the cost of the AD.

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.
    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

0
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

0
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]

0
2. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2003-11-10 Turbomeca S.A.: Amendment 39-13169. Docket No. 2002-NE-
39-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to Turbomeca S.A. Arrius -2F turboshaft engines with Fuel Control 
Units (FCUs) part numbers (P/Ns) 0 319 92 832 0, 0 319 92 830 0, and 
0 319 92 825 0, with FCU serial numbers (SNs) in the following Table 
1:

                  Table 1.--Affected FCU Serial Numbers
------------------------------------------------------------------------
 
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102B....................................................    135B    166B
103B....................................................    136B    167B
104B....................................................    137B    168B
105B....................................................    138B    169B
106B....................................................    139B    171B
107B....................................................    140B    173B
108B....................................................    141B    174B
110B....................................................    142B    175B
111B....................................................    143B    176B
112B....................................................    144B    177B
113B....................................................    145B    178B
114B....................................................    146B    180B
115B....................................................    148B    181B
116B....................................................    149B    182B
118B....................................................    150B    183B
120B....................................................    153B    185B
122B....................................................    155B    186B
123B....................................................    156B    190B
124B....................................................    158B    191B
126B....................................................    159B    193B
129B....................................................    161B    199B
132B....................................................    164B     N/A
133B....................................................    165B     N/A
------------------------------------------------------------------------

    These engines are installed on, but not limited to Eurocopter 
120B ``Colibri'' 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

[[Page 31973]]

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 within 120 days 
after the effective date of this AD, unless already done.
    To prevent reduced maximum available power during takeoff, 
landing, or an emergency, which could significantly affect 
helicopter performance, and result in loss of the helicopter, do the 
following:
    (a) For FCUs listed in the applicability of this AD, adjust the 
maximum fuel flow mechanical stop position to a higher fuel flow 
setting, in accordance with paragraphs 2.A.(1) and 2.B.(1) of 
Turbomeca S.A Alert Service Bulletin (ASB) No. A319 73 4808, dated 
September 1, 2000.
    (b) Perform a ground run check and a check flight in accordance 
with paragraph 2.C.(1) of Turbomeca S.A ASB No. A319 73 4808, dated 
September 1, 2000.

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 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

    (d) Special flight permits may be issued in accordance with 
Sec. Sec.  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 actions must be done in accordance with Turbomeca S.A. 
Alert Service Bulletin No. A319 73 4808, dated September 1, 2000. 
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., 64511 Bordes Cedex, 
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 AD 2000-482(A), dated November 29, 
2000.

Effective Date

    (f) This amendment becomes effective on July 3, 2003.

    Issued in Burlington, Massachusetts, on May 20, 2003.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 03-13114 Filed 5-28-03; 8:45 am]
BILLING CODE 4910-13-P