AD 2001-08-14

[Federal Register Volume 66, Number 81 (Thursday, April 26, 2001)]
[Rules and Regulations]
[Pages 20910-20912]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-10021]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-12-AD; Amendment 39-12191; AD 2001-08-14]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. Arrius Models 2B, 2B1, 
and 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 Models 2B, 2B1, and 2F 
turboshaft engines. This amendment requires the replacement of the 
right injector half manifold, left injector half manifold, and 
privilege injector pipe. This amendment is prompted by reports from the 
Direction Generale de L'Aviation Civile (DGAC), which is the 
airworthiness authority for France, of partially or totally blocked 
fuel injection manifolds, which were found during inspections at a 
repair workshop. The actions specified by this AD are intended to 
prevent engine flameout during rapid deceleration, or the inability to 
maintain the 2.5 minutes one engine inoperative (OEI) rating. The 
actions are also intended to prevent air path cracks, due to blockage 
of the fuel injection manifolds.

DATES: Effective date May 31, 2001. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of May 31, 2001.

ADDRESSES: The service information referenced in this AD may be 
obtained from Turbomeca S.A., 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; or at the Office of the Federal 
Register, 800 North Capitol Street, NW, suite 700, Washington, DC.

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: 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 Models 2B, 2B1, and 2F turboshaft 
engines was published in the Federal Register on December 6, 2000 (65 
FR 76187). That action proposed to require the replacement of the right 
injector half manifold, left injector half manifold, and privilege 
injector pipe with the engine installed on the helicopter in accordance 
with Turbomeca Alert Service Bulletin (ASB) No. A319 73 2012, Revision 
2, dated May 25, 1999, for Arrius 2B and 2B1 turboshaft engines, and 
ASB No. A319 73 4001, Revision 3, dated May 25, 1999, for Arrius 2F 
turboshaft engines.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Wording Changes

    One commenter suggests that the word ``obtain'' be substituted for 
the word ``maintain'' in various places throughout the rule.
    The FAA does not agree. The word ``maintain'' in this case refers 
to a rating which is required in the type certificate data sheet, e.g. 
the aircraft must maintain the ability to achieve 520 shaft horse power 
for 2.5 minutes with one engine inoperative in order to meet type 
design requirements.
    The commenter also states that the word ``injector'' is meaningless 
as it is used in the last sentence of the summary.
    The FAA agrees and the word ``injector'' has been removed from the 
last sentence in the summary.

Revised Alert Service Bulletins

    The manufacturer states that the most recent ASB revisions should 
be cited in the rule to capture its clarification and changes.
    The FAA partially agrees. The most recent ASB revisions, which are 
Turbomeca ASB No. A319 73 2012, Revision 3, dated July 21, 2000, and 
ASB No. A319 73 4001, Revision 4, dated October 20, 2000, have added 
the replacement of the manifold at the Turbomeca Repair Center, in 
Tarnos, France as an alternative to the on-airframe replacement. This 
AD allows operators credit for manifold replacement that was done in 
accordance with the previous revisions of the ASB's. Paragraph (a) of 
this AD has been changed to allow replacements of the manifolds with 
new or refurbished parts to be done by operators on installed engines; 
refurbishment to be done by Turbomeca's Repair Center or by any 
appropriately rated repair shop.

Change Compliance To Allow Use of Refurbished Parts

    The manufacturer states that the requirements of paragraph (c) in 
the rule should be changed to allow the use of refurbished parts.
    The FAA agrees. Paragraph (c) is changed to remove the existing 
installation limitations, and to add a definition of time-in-service.
    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes described 
previously. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Economic Impact

    There are about 130 engines of the affected design in the worldwide 
fleet. The FAA estimates that 22 engines installed on aircraft of U.S. 
registry will be affected by this AD, that it will take about 2 work 
hours per engine to accomplish the required actions, and that the 
average labor rate is $60 per work hour. Required parts will cost about 
$14,320 per engine. Based on these figures, the total cost impact of 
the AD on U.S. operators is estimated to be $317,680 for initial 
inspection and parts replacement. The manufacturer has advised the DGAC 
that the operator may exchange the removed injection manifolds, at no 
cost to the operator, thereby substantially reducing the cost impact of 
this 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

[[Page 20911]]

``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:

2001-08-14  Turbomeca S.A. Arrius Models 2B, 2B1, and 2F Turboshaft 
Engines: Amendment 39-12191. Docket No. 2000-NE-12-AD.

Applicability

    This airworthiness directive (AD) is applicable to Turbomeca 
S.A. Arrius Models 2B, 2B1, and 2F turboshaft engines. These engines 
are installed on, but not limited to Eurocopter France Model EC120B 
and Eurocopter Deutschland EC135 T1 rotorcraft.

    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 (d) 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 engine flameout and the inability to maintain the 2.5 
minutes one engine inoperative (OEI) rating due to blockage of the 
fuel injection manifolds, do the following:

Initial Replacement

    (a) If not already done in accordance with Turbomeca Alert 
Service Bulletin (ASB) No. A319 73 2012, Revision 2, dated May 25, 
1999, or ASB No. A319 73 4001, Revision 3, dated May 25, 1999, 
replace injector manifolds and borescope-inspect the flame tube and 
the high pressure turbine area within 30 days after the effective 
date of this AD, or prior to exceeding 200 hours time-in-service 
(TIS), whichever is later. Do these in accordance with Instructions 
2.A. through 2.C. of Turbomeca ASB No. A319 73 2012, Revision 3, 
dated July 21, 2000 for Arrius 2B and 2B1 turboshaft engines, and 
ASB No. A319 73 4001, Revision 4, dated October 20, 2000, for Arrius 
2F turboshaft engines, except that replacement may be done at any 
appropriately rated repair shop.

Repetitive Replacements

    (b) Thereafter, replace injector manifolds within 200 hours TIS 
since last replacement, or prior to further flight after performing 
the applicable flight manual or overhaul manual power check if the 
power check shows a negative turbine outlet temperature (TOT) margin 
or negative T4 margin.

Definition

    (c) For the purposes of this AD, time-in-service (TIS) is 
defined as the number of engine operating hours on the manifolds 
since the manifolds were new or since the manifolds were 
refurbished.

Alternative Methods of Compliance

    (d) 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, 
if any, may be obtained from the Engine Certification Office.

Special Flight Permits

    (e) 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 aircraft to a location where the 
requirements of this AD can be accomplished.

Documents That Have Been Incorporated By Reference

    (f) The inspections and replacements shall be done in accordance 
with the following Turbomeca S.A. alert service bulletins (ASB's):

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                  Document No.                     Pages     Revision                     Date
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ASB No. A319 73 2012 Total pages: 5............          5          2  May 25, 1999.
ASB No. A319 73 2012 Total pages: 5............          5          3  July 21, 2000.
ASB No. A319 73 4001 Total pages: 5............          5          3  May 25, 1999.
ASB No. A319 73 4001 Total pages: 5............          5          4  October 20, 2000.
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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 by the Direction 
Generale de L'Aviation Civile (DGAC), which is the airworthiness 
authority for France, in airworthiness directives AD 1999-217(A) and 
AD 1999-233(A).

Effective Date

    (g) This amendment becomes effective on May 31, 2001.

    Issued in Burlington, Massachusetts, on April 16, 2001.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 01-10021 Filed 4-25-01; 8:45 am]
BILLING CODE 4910-13-P