[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                
----------------------------------------------------------------------------------------------------------------
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]
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