AD 2002-21-15

[Federal Register Volume 67, Number 204 (Tuesday, October 22, 2002)]
[Rules and Regulations]
[Pages 64798-64799]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-26790]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NE-53-AD; Amendment 39-12922; AD 2002-21-15]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. TPE331 
Series Turboprop and TSE331-3U Series 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 Honeywell International Inc. (formerly AlliedSignal 
Inc., Garrett Engine Division, Garrett Turbine Engine Company, and 
AiResearch Manufacturing Company of Arizona) TPE331 series turboprop 
and TSE331-3U series turboshaft engines. This amendment requires 
replacing second stage turbine stator assemblies, part numbers (P/N's) 
894528-1, -2, -3, -5, -6, -10, and -11, with serviceable turbine stator 
assemblies. This amendment is prompted by reports of six uncontained 
separations of the second stage turbine wheels associated with 
obstructed internal cooling holes or passage in the vanes of the second 
stage turbine stator which may result in contact and rub into the 
turbine rotor. The actions specified by this AD are intended to prevent 
uncontained turbine rotor separation and damage to the aircraft.

DATES: Effective November 26, 2002.

ADDRESSES: Information regarding this action 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.

FOR FURTHER INFORMATION CONTACT: Joseph Costa, Aerospace Engineer, 
Federal Aviation Administration, Transport Airplane Directorate, Los 
Angeles Aircraft Certification Office, 3960 Paramount Blvd., Lakewood, 
CA 90712-4137; Telephone (562) 627-5246, Fax (562) 627-5210.

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 Honeywell International Inc. (formerly AlliedSignal Inc., 
Garrett Engine Division, Garrett Turbine Engine Company, and AiResearch 
Manufacturing Company of Arizona) TPE331 series turboprop and TSE331-3U 
series turboshaft engines was published in the Federal Register on 
February 19, 2002 (67 FR 7318). That action proposed to require 
replacing second stage turbine stator assemblies, P/N's 894528-1, -2, -
3, -5, -6, -10, and -11, with serviceable turbine stator assemblies.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comment received.
    One commenter states that the proposal incorrectly identifies some 
of the areas of fatigue damage as the second and third stage turbine 
wheels, and instead should have identified the first and second stage 
turbine wheels. The FAA agrees and has corrected the final rule.
    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 has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Economic Analysis

    There are approximately 4,700 engines of the affected design in the 
worldwide fleet. The FAA estimates that 2,350 engines installed on 
aircraft of U.S. registry would be affected by this AD, that it would 
take approximately 4.0 work hours per engine to do the actions, and 
that the average labor rate is $60 per work hour. Required replacement 
parts will cost approximately $8,000 per engine. Based on these 
figures, the total cost of the AD on U.S. operators is estimated to be 
$14,958,000.

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, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the

[[Page 64799]]

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:

2002-21-15 Honeywell International Inc.: Amendment 39-12922. Docket 
No. 99-NE-53-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to Honeywell International Inc. (formerly AlliedSignal Inc., Garrett 
Engine Division, Garrett Turbine Engine Company, and AiResearch 
Manufacturing Company of Arizona) TPE331-1, -2, -2UA, -3U, -3UW, -5, 
-5A, -5AB, -5B, -6, and -6A series turboprop and TSE331-3U series 
turboshaft engines with second stage turbine stator assemblies, part 
numbers (P/N's) 894528-1, -2, -3, -5, -6, -10, and -11. These 
engines are installed on, but not limited to Ayres S-2R series; 
Beech 18 and 45 series and model JRB-6, 3N, 3NM, 3TM, and B100 
airplanes; Construcciones Aeronauticas, S.A. (CASA) C-212; De 
Havilland DH104 series 7AXC (Dove); Dornier 228 series; Fairchild 
SA226 series (Swearingen Merlin and Metro series); Grumman American 
G-164 series; Mitsubishi MU-2 and MU-2B series; Pilatus PC-6 series 
(Fairchild Porter and Peacemaker); Prop-Jets, Inc. Model 400; 
Rockwell Commander S2-R; Schweizer G-164 series; Shorts Brothers and 
Harland, Ltd. SC7 (Skyvan); and Twin Commander 680 and 690 series 
(Jetprop Commander) airplanes; and Sikorsky S-55 series (Helitec 
Corp. S55T) 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 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 as indicated, 
unless already done.
    To reduce fatigue damage of the second stage turbine stator 
inner seal support, rotating knife seal, and the first and second 
stage turbine wheels which may result in an uncontained rotor 
failure and damage to the aircraft, do the following:
    (a) Replace second stage turbine stator assemblies, P/N's 
894528-1, -2, -3, -5, -6, -10, and -11, with a new or reworked 
second stage turbine stator assembly at the next removal of the 
second stage turbine stator assembly from the engine or at the next 
turbine section inspection, but do not exceed 3,100 engine operating 
hours since last turbine section inspection. Information for 
replacing second stage turbine stator assemblies is available in 
Honeywell International Inc. Alert Service Bulletin (ASB) TPE331-
A72-2082 dated May 16, 2001. Information for reworking second stage 
turbine stator assemblies is available in Honeywell International 
Inc. SB TPE331-72-2085RWK dated May 16, 2001.
    (b) After the effective date of this AD, do not install any 
second stage turbine stator assembly P/N's 894528-1, -2, -3, -5, -6, 
-10, and -11.

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, Los Angles Aircraft Certification 
Office (LAACO). Operators must submit their request through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, LAACO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the LAACO.

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 aircraft to a location where 
the requirements of this AD can be done.

Effective Date

    (e) This amendment becomes effective on November 26, 2002.
    Issued in Burlington, Massachusetts, on October 15, 2002.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 02-26790 Filed 10-21-02; 8:45 am]
BILLING CODE 4910-13-P