[Federal Register Volume 61, Number 59 (Tuesday, March 26, 1996)]
[Rules and Regulations]
[Pages 13079-13081]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-7141]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-ANE-21; Amendment 39-9547; AD 96-06-10]
Airworthiness Directives; AlliedSignal, Inc. LTS101 Series
Turboshaft Engines Installed on Eurocopter France Model AS-350D and SA-
366G1 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to AlliedSignal, Inc. (formerly Textron Lycoming) LTS101
series turboshaft engines installed on Eurocopter France (formerly
Aerospatiale) Model AS-350D and SA-366G1 helicopters, that requires
incorporation of design modifications to the power turbine (PT) rotor.
This amendment is prompted by reports of PT disk failures after No. 3
bearing failures. The actions specified by this AD are intended to
prevent an uncontained engine failure due to a PT disk failure.
DATES: Effective May 28, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of May 28, 1996.
ADDRESSES: The service information referenced in this AD may be
obtained from AlliedSignal Engines, 550 Main Street, Stratford, CT
06497. This information may be examined at the Federal Aviation
Administration (FAA), New England Region, Office of the Assistant Chief
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: Eugene Triozzi, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (617)
238-7148, fax (617) 238-7199.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to AlliedSignal, Inc. (formerly
Textron Lycoming) LTS101 series turboshaft engines installed on
Eurocopter France (formerly Aerospatiale) Model AS-350D and SA-366G1
helicopters was published in the
[[Page 13080]]
Federal Register on June 30, 1995 (60 FR 21053). That action proposed
to require incorporation of a modified power turbine (PT) rotor
retention system at the next shop visit after the effective date of
this AD, but not later than April 30, 1996, in accordance with Textron
Lycoming Service Bulletin (SB) No. LTS101A-72-50-0134, Revision 1,
dated June 17, 1991, and SB No. LTS101B-72-50-0128, Revision 1, dated
June 17, 1991.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the one comment received.
The commenter states that the instructions for installation of the
PT retention system should be revised to require installation of two
parts, inadvertently omitted but necessary to enable the pneumatic
portion of the PT retention system. These parts consist of a tee-
fitting to replace an existing elbow fitting in the main fuel control,
and a pressurization line. The FAA concurs, and has revised the
accomplishment instructions of the final rule to refer to later
revisions of the applicable SB's, which reflect installation of these
additional parts. Consequently, the FAA has extended the compliance
timetable for the final rule in order to provide sufficient opportunity
for installation of the parts, and to ensure parts availability. The
FAA has determined that installation of the additional parts will not
have a substantial additional impact on accomplishment of the
requirements of this AD.
Since publication of the NPRM, the manufacturer has issued the
following revisions to the SB's, which are referenced in this final
rule: AlliedSignal Engines SB No. LTS101A-72-50-0134, Revision 2, dated
August 15, 1995; AlliedSignal Engines SB No. LTS101B-72-50-0128,
Revision 2, dated August 15, 1995; and AlliedSignal Engines SB No.
LTS101A-73-20-0166, Revision 2, dated August 1, 1995.
After careful review of the available data, including the comment
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 estimates that 20 engines installed on aircraft of U.S.
registry will be affected by the requirement to install the improved
power turbine rotor assembly and the power turbine retention system
required by this AD, that it will take approximately 10 work hours per
engine to accomplish the required actions, and that the average labor
rate is $60 per work hour. Required parts will cost approximately
$44,400 per engine. Based on these figures, the cost impact to install
the improved power turbine rotor assembly and the power turbine
retention system required by this AD on U.S. operators is estimated to
be $900,000. The FAA estimates that 60 engines installed on aircraft of
U.S. registry have previously installed the improved power turbine
rotor assembly and the power turbine retention system, in addition to
the 20 engines in the paragraph above. Therefore, a total of 80 engines
will be affected by the requirement to enable the pneumatic portion of
the PT retention system by installing the tee-fitting and
pressurization line. The FAA estimates that it will take approximately
2.5 work hours per engine to accomplish the required action. Required
parts will cost approximately $385 per engine. Based on these figures,
the total cost impact of installing the tee-fitting and pressurization
line required by the AD on U.S. operators is estimated to be $42,800.
Therefore, the revised total cost impact of this AD on all U.S.
operators is estimated to be $942,800.
The regulations adopted herein will not have substantial direct
effects 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. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
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 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
from 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 the following new
airworthiness directive:
96-06-10 AlliedSignal, Inc.: Amendment 39-9547. Docket 95-ANE-21.
Applicability: AlliedSignal, Inc. (formerly Textron Lycoming)
Models LTS101-600A-2 and -600A-3 turboshaft engines installed on
Eurocopter France (formerly Aerospatiale) Model AS-350D helicopters;
and LTS101-750B-2 turboshaft engines installed on Eurocopter France
Model SA-366G1 helicopters.
Note: This airworthiness directive (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 use the
authority provided in paragraph (c) to request approval from the
Federal Aviation Administration (FAA). This approval may address
either no action, if the current configuration eliminates the unsafe
condition, or different actions necessary to address the unsafe
condition described in this AD. Such a request should include an
assessment of the effect of the changed configuration on the unsafe
condition addressed by this AD. In no case does the presence of any
modification, alteration, or repair remove any engine from the
applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent an uncontained engine failure due to power turbine
(PT) disk failure, accomplish the following at the next shop visit
after the effective date of this airworthiness directive (AD) when
the PT rotor is removed, but not later than July 1, 1996:
(a) For LTS101-600A-2 and -600A-3 turboshaft engines installed
on Eurocopter France (formerly Aerospatiale) Model AS-350D
helicopters, incorporate improved PT rotor retention system
modifications in accordance with Section II., Accomplishment
Instructions, Paragraphs A. through AT. of AlliedSignal Engines
Service Bulletin (SB) No. LTS101A-72-50-0134, Revision 2, dated
August 15, 1995, and concurrently replace elbow fitting in fuel
control governor orifice cover Py port with tee-fitting assembly, P/
N 2543854, in accordance with Section II., Accomplishment
Instructions, Paragraphs C. (5) through C. (7) of AlliedSignal
Engines SB No. LTS101A-73-20-166, Revision 2, dated August 1, 1995.
(b) For LTS101-750B-2 turboshaft engines installed on Eurocopter
France Model SA-
[[Page 13081]]
366G1 helicopters, incorporate improved PT rotor retention system
modifications in accordance with Section II., Accomplishment
Instructions, of AlliedSignal Engines SB No. LTS101B-72-50-0128,
Revision 2, dated August 15, 1995.
(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. The
request should be forwarded through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, Engine Certification Office.
Note: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Engine Certification Office.
(e) 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 aircraft to a location where
the requirements of this AD can be accomplished.
(f) The modification of the PT rotor retention system shall be
done in accordance with the following AlliedSignal Engines SB's:
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Document No. Pages Revision Date
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LTS101A72-50-0134............................ 1-11 2 Aug. 15, 1995.
Total pages: 11.
LTS101B72-50-0128............................ 1-11 2 Aug. 15, 1995.
Total pages: 11.
LTS101A73-20-0166............................ 1-6 2 Aug. 1, 1995.
Total pages: 11.
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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 AlliedSignal Engines, 550 Main
Street, Stratford, CT 06497. Copies may be inspected at the FAA, New
England Region, Office of the Assistant Chief 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.
(e) This amendment becomes effective on May 28, 1996.
Issued in Burlington, Massachusetts, on March 11, 1996.
James C. Jones,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 96-7141 Filed 3-25-96; 8:45 am]
BILLING CODE 4910-13-U
