[Federal Register Volume 59, Number 86 (Thursday, May 5, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-10365]
[[Page Unknown]]
[Federal Register: May 5, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 93-ANE-80; Amendment 39-8897; AD 94-09-08]
Airworthiness Directives; Allied-Signal Inc., Garrett Engine
Division, TPE331 Series Turboprop and Model TSE331-3U Turboshaft
Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule, request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to certain Allied-Signal Inc., Garrett Engine Division,
TPE331 series turboprop and Model TSE331-3U turboshaft engines. This
action requires inspection of certain third stage turbine stator
assemblies, and replacement, if necessary, with serviceable assemblies.
This amendment is prompted by reports of six third stage turbine stator
assemblies assembled with inner seal supports made of incorrect
material that results in a significantly reduced cyclic life. The
actions specified by this AD are intended to prevent an uncontained
failure of the third stage turbine wheel.
DATES: May 20, 1994.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of May 20, 1994.
Comments for inclusion in the Rules Docket must be received on or
before July 5, 1994.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 93-ANE-80, 12 New England
Executive Park, Burlington, MA 01803-5299.
The service information referenced in this AD may be obtained from
AlliedSignal, Inc., Aviation Services Division, Data Distribution Dept.
64-3/2102-IM, P.O. Box 29003, Phoenix, AZ 85038-9003. This information
may be examined at the FAA, New England Region, Office of the Assistant
Chief Counsel, Burlington, MA; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Joseph Costa, Aerospace Engineer, Los
Angeles Aircraft Certification Office, FAA, Transport Airplane
Directorate, 3229 East Spring Street, Long Beach, CA 90806-2425;
telephone (310) 988-5246, fax (310) 988-5210.
SUPPLEMENTARY INFORMATION: The Federal Aviation Administration (FAA)
has received reports of six third stage turbine stator assemblies
assembled with inner seal supports made of incorrect material that
significantly reduces the cyclic life of the assembly. The manufacturer
has identified part serial numbers of 150 third stage turbine stator
assemblies that may contain the inner seal supports made of Hastelloy S
material. These assemblies were repaired at the Garrett General
Aviation Service Division (GGASD) facility in Phoenix, Arizona between
November 1988 and May 1991. Fatigue failure of the inner seal support
has resulted in the seal support moving aft and contacting the third
stage turbine wheel. This condition, if not corrected, can result in an
uncontained failure of the third stage turbine wheel.
The FAA has reviewed and approved the technical contents of
AlliedSignal Aerospace Alert Service Bulletin (ASB) No. TPE331-A72-
0906, dated October 15, 1993, that describes procedures for inspecting
the third stage turbine stator assemblies, and replacing, if necessary,
with serviceable assemblies.
Since an unsafe condition has been identified that is likely to
exist or develop on other engines of this same type design, this AD is
being issued to prevent an uncontained failure of the third stage
turbine wheel. This AD requires inspection of third stage turbine
stator assemblies to determine the acceptability of the inner seal
supports, and replacement, if necessary, with serviceable assemblies.
The actions are required to be accomplished in accordance with the
service bulletin described previously.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications should identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 93-ANE-80.'' The postcard will be date stamped and
returned to the commenter.
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.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and is not a ``significant regulatory action''
under Executive Order 12866.
It has been determined further that this action involves an
emergency regulation under DOT Regulatory Policies and Procedures (44
FR 11034, February 26, 1979). If it is determined that this emergency
regulation otherwise would be significant under DOT Regulatory Policies
and Procedures, a final regulatory evaluation will be prepared and
placed in the Rules Docket. A copy of it, if filed, 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 14 CFR part
39 of the Federal Aviation Regulations 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:
94-09-08 Allied-Signal Inc., Garrett Engine Division: Amendment 39-
8897. Docket 93-ANE-80.
Applicability: Allied-Signal Inc., Garrett Engine Division,
Model TPE331-1, -2, -2UA, -3U, -3UW, -5, -5A, -6, and -6A turboprop
and Model TSE331-3U turboshaft engines incorporating third stage
stator turbine assemblies, Part Number (P/N) 868379-3, repaired at
the Garrett General Aviation Service Division (GGASD) facility in
Phoenix, Arizona, between November 1988 and May 1991, and identified
by serial numbers listed in AlliedSignal Aerospace Alert Service
Bulletin (ASB) No. TPE331-A72-0906, dated October 15, 1993. These
engines are installed on but not limited to Mitsubishi MU-2B series
(MU-2 series); Construcciones Aeronauticas, S.A. (CASA) C-212
series; Fairchild SA226 series (Swearingen Merlin and Metro series);
Prop-Jets, Inc. Model 400; Twin Commander 680 and 690 (Jetprop
Commander), Rockwell Commander S-2R, Shorts Brothers and Harland,
Ltd. SC7 (Skyvan), Dornier 228 series, Beech 18 and 45 series and
Models JRB-6, 3N, 3NM, 3TM, and B100, Pilatus PC-6 series (Fairchild
Porter, Peacemaker), De Havilland Model DH 104 series 7AXC (Dove),
and Ayres S-2R series airplanes; and Sikorsky S-55 series
helicopters.
Compliance: Required as indicated, unless accomplished
previously.
To prevent an uncontained failure of the third stage turbine
wheel, accomplish the following:
(a) Inspect suspect third stage turbine stator assemblies, P/N
868379-3, and replace, if necessary, with serviceable assemblies, in
accordance with the Accomplishment Instructions of AlliedSignal
Aerospace ASB No. TPE331-A72-0906, dated October 15, 1993, and the
following schedule:
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Third stage turbine
stator cycles in
service since repair Inspection schedule
by GGASD
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900 or more cycles.. Within 50 cycles in service after the effective
date of this AD.
450 to 899 cycles... Within 150 cycles in service after the effective
date of this AD, but not to exceed 950 cycles in
service since repair by GGASD.
Less than 450 cycles Prior to accumulating 600 cycles in service since
repair by GGASD.
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Note: The FAA has determined that cracking of third stage
turbine stator assemblies is related to operating cycles, rather
than operating hours.
(b) If cycles cannot be determined, calculate cycles by
multiplying third stage turbine stator assembly hours time in
service by 1.5.
(c) An alternative method of compliance or adjustment of the
initial compliance time that provides an acceptable level of safety
may be used if approved by the Manager, Los Angeles Aircraft
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, Los Angeles Aircraft
Certification Office.
Note: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Los Angeles Aircraft Certification
Office.
(d) Special flight permits may be issued in accordance with 14
CFR 21.197 and 21.199 to operate the aircraft to a location where
the requirements of this AD can be accomplished.
(e) The inspection, and replacement, if necessary, of the third
stage turbine stator assembly, shall be accomplished in accordance
with the following ASB, which also identifies third stage turbine
stator assemblies, P/N 868379-3, repaired at GGASD between November
1988 and May 1991, by serial number:
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Document No. Pages Date
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AlliedSignal Aerospace ASB No. TPE331-A72- 1-10 Oct. 15, 1993.
0906.
Total pages: 10.
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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., Aviation Services
Division, Data Distribution Dept. 64-3/2102-IM, P.O. Box 29003,
Phoenix, AZ 85038-9003. 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.
(f) This amendment becomes effective on May 20, 1994.
Issued in Burlington, Massachusetts, on April 19, 1994.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 94-10365 Filed 5-4-94; 8:45 am]
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