AD 95-16-04

[Federal Register Volume 60, Number 149 (Thursday, August 3, 1995)]
[Rules and Regulations]
[Pages 39637-39638]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-18551]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-ANE-64; Amendment 39-9323; AD 95-16-04]


Airworthiness Directives; AlliedSignal, Inc. (Formerly Textron 
Lycoming) LTS101 Series Turboshaft and LTP101 Series Turboprop Engines

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. LTS101 series turboshaft and LTP101 
series turboprop engines, that requires replacement of cast material 
axial compressor rotors with wrought material axial compressor rotors 
that have improved fatigue characteristics and material properties. 
This amendment is prompted by 36 reports of axial compressor blade 
failures on cast rotors. The actions specified by this AD are intended 
to prevent engine power loss and inflight engine shutdown.

DATES: Effective October 2, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of October 2, 1995.

ADDRESSES: The service information referenced in this AD may be 
obtained from AlliedSignal, Inc., 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 and LTP101 series turboprop 
engines was published in the Federal Register on January 4, 1995 (60 FR 
393). That action proposed to require replacing cast material axial 
compressor rotors with wrought material axial compressor rotors that 
have improved fatigue characteristics and material properties, in 
accordance with Textron Lycoming Service Bulletin No. LT 101-72-30-
0088, Revision 5, dated September 25, 1992.
    On October 28, 1994, AlliedSignal Inc. purchased the turbine engine 
product line of Textron Lycoming, and this final rule has been revised 
to refer to the engine by its new name.
    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 with the change described previously.
    There are approximately 200 engines of the affected design in the 
worldwide fleet. The FAA estimates that 100 engines installed on 
aircraft of U.S. registry will be affected by this AD, that it will 
take approximately 50 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 $6,500 per engine, on a prorated cost 
basis. Based on these figures, the total cost impact of the AD on U.S. 
operators is estimated to be $955,000.
    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. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.
Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

95-16-04  AlliedSignal, Inc.: Amendment 39-9323. Docket 94-ANE-64.

    Applicability: AlliedSignal, Inc. (formerly Textron Lycoming) 
LTS101 turboshaft and LTP101 turboprop engines installed on but not 
limited to Aerospatiale AS 350 and SA366G, Bell 222, and 
Messerschmitt-Bolkow-Blohm (MBB) BK117 helicopters; Piaggio P166-DL3 
and Airtractor AT302 airplanes. NOTE: This AD applies to each 

[[Page 39638]]
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 (b) to request approval from the 
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 engine power loss and inflight engine shutdown, 
accomplish the following:
    (a) Remove from service Part Numbers (P/N) 4-101-006- 20, -21, -
24, -26, -35, -36, and -40 cast material axial compressor rotors, as 
follows:
    (1) For axial compressor rotors P/N 4-101-006-35 with serial 
number suffix ``E,'' remove in accordance with Textron Lycoming 
Service Bulletin (SB) No. LT 101-72-30-0088, Revision 5, dated 
September 25, 1992, within 50 hours time in service (TIS), or 60 
days after the effective date of this AD, whichever occurs first.
    (2) For axial compressor rotors P/N 4-101-006-35 with serial 
number suffix other than ``E,'' and all other axial compressor 
rotors with P/N listed in paragraph (a) of this airworthiness 
directive (AD), remove in accordance with Textron Lycoming SB No. LT 
101-72-30-0088, Revision 5, dated September 25, 1992, as follows:
    (i) For axial compressor rotors that have accumulated 600 hours 
or less TIS since new, remove within 100 hours TIS, or 120 days 
after the effective date of this AD, whichever occurs first.
    (ii) For axial compressor rotors that have accumulated more than 
600 but less than or equal to 1,200 hours TIS since new, remove 
within 300 hours TIS, or 240 days after the effective date of this 
AD, whichever occurs first.
    (iii) For axial compressor rotors that have accumulated more 
than 1,200 but less than or equal to 2,400 hours TIS since new, 
remove within 600 hours TIS, or 360 days after the effective date of 
this AD, whichever occurs first.
    (iv) For axial compressor rotors that have accumulated more than 
2,400 hours TIS since new, remove within 1,200 hours TIS, or 720 
days after the effective date of this AD, whichever occurs first.
    (3) Replace with a serviceable wrought material axial compressor 
rotor P/N 4-101-006-28, -32, -39, or -41, as applicable, in 
accordance with Textron Lycoming SB No. LT 101-72-30-0088, Revision 
5, dated September 25, 1992.
    (b) 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.

    (c) 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.
    (d) The actions required by this AD shall be done in accordance 
with the following SB:

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          Document No.            Pages   Revision          Date        
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Textron Lycoming SB No. LT 101-      1-4         5  September 25, 1992. 
 72-30-0088.                                                            
Total Pages: 5.                                                         
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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, Inc., 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 October 2, 1995.

    Issued in Burlington, Massachusetts, on July 20, 1995.
James C. Jones,

Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.

[FR Doc. 95-18551 Filed 7-31-95; 10:37 am]

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