[Federal Register Volume 61, Number 177 (Wednesday, September 11, 1996)]
[Rules and Regulations]
[Pages 47802-47804]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-22922]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-ANE-72; Amendment 39-9749; AD 96-19-01]
RIN 2120-AA64
Airworthiness Directives; Allison 250 Series Turbine 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 Allison 250 series turbine engines. This action
requires initial and repetitive visual inspections of all engine
filters for metal particles resulting from premature wear of two
bearings produced under Parts Manufacture Approval (PMA) by Superior
Air Parts, Inc. In addition, this AD requires replacement of those
bearings with bearings that incorporate improved retainers, which
constitutes terminating action to the inspection requirements of this
AD. This amendment is prompted by a report of a failure during a ground
test of an engine with bearings manufactured by Superior Air Parts,
Inc. The actions specified in this AD are intended to prevent bearing
failure due to bearing separator instability, which can result in
subsequent turbine and engine failure.
DATES: Effective September 26, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of September 26, 1996.
Comments for inclusion in the Rules Docket must be received on or
before November 12, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 95-ANE-72, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may also be
submitted to the Rules Docket by using the following Internet address:
epd-adcomments@mail.hq.faa.gov''. All comments must contain the
Docket No. in the subject line of the comment.
The service information referenced in this AD may be obtained from
Superior Air Parts, Inc., 14280 Gillis Rd., Dallas, TX 75244-3792;
telephone (800) 487-4884, fax (214) 490-8471. This information may be
examined 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.
FOR FURTHER INFORMATION CONTACT: Richard D. Karanian, Aerospace
Engineer, Special Certification Office, FAA, Rotorcraft Directorate,
2601 Meacham Blvd., Fort Worth, TX 76137-4298; telephone (817) 222-
5195, fax (817) 222-5136.
SUPPLEMENTARY INFORMATION: The Federal Aviation Administration (FAA)
received a report of a chip detector light on an Allison 250 turboshaft
engine during a helicopter flight. The pilot returned to base and the
ground crew commenced with an inspection to determine the cause. Metal
particles, including silver flakes, were discovered on the chip
detector; however, a preliminary inspection failed to determine where
the metal particles originated. In accordance with the applicable
service instruction, an engine ground run was initiated. Approximately
two hours into the ground run, the engine began to vibrate. The ground
run was discontinued and the engine was disassembled. An inspection
revealed that the No. 5 bearing, part number (P/N) A6871505, produced
under Parts Manufacture Approval (PMA) by Superior Air Parts, Inc., had
failed. In addition, the FAA has received reports of 5 more incidents
where metal particles were found, resulting in the removal of four No.
5 bearings, P/N A6871505, and one No. 8 bearing, P/N A23007152. This
condition, if not corrected, could result in bearing failure due to
bearing separator instability, which can result in subsequent turbine
and engine failure.
The FAA has reviewed and approved the technical contents of
Superior Turbine Service Bulletin (SB) No. T95-SB001, Revision A, dated
September 29, 1995, and SB No. T95-SB002, Revision A, dated September
29, 1995, that describe procedures for initial and repetitive visual
inspections of all engine filters for metal particles resulting from
wear of bearing ball retainer.
Since an unsafe condition has been identified that is likely to
exist or develop on other Allison 250 series turbine engines of the
same type design, this AD is being issued to prevent bearing failure.
This AD requires an initial visual inspection within 20 days after the
effective date of this AD, followed by repetitive inspections at
intervals not to exceed 25 hours time in service (TIS) since last
inspection for the first 300 hours TIS of engine operation. After
accumulating greater than 300 hours TIS of engine operation, the
inspections must be accomplished at intervals not to exceed 100 hours
TIS since last inspection. The repetitive inspections must be performed
until engine overhaul, or repair or maintenance when disassembly
permits replacement of the bearing, whichever occurs first. At that
time, remove the No. 5 bearing, Superior P/N A6871505, and replace with
a serviceable No. 5 bearing, Allison P/N 6871505; and remove the No. 8
bearing, Superior P/N A23007152, and replace with a serviceable No. 8
bearing, Allison P/N 23031478. The Allison bearings incorporate
improved retainers, and Superior Air Parts, Inc. no longer manufactures
replacement bearings. Replacement with these serviceable bearings
constitutes terminating action to the inspection requirements of this
AD. The actions are required to be accomplished in accordance with the
SBs 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
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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 95-ANE-72.'' 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 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 USC 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
96-19-01 Allison: Amendment 39-9749. Docket 95-ANE-72.
Applicability: Allison Model 250-B15G,-B17F, -B17F/1, -B17F/2, -
C20, -C20B, -C20F, -C20J, -C20S, -C20W, -R, -C20R/1, -C20R/2, -C20R/
4, -C28B, -C28C, -C30, -C30P, -C30M, and -C30G turbine engines, with
Superior Air Parts, Inc. Parts Manufacture Approval (PMA) bearings,
Part Number (P/N) A6871505 and P/N A23007152, installed. These
engines are installed on but not limited to the following aircraft:
Aerospace Technologies of Australia PTY Ltd. N-22 and N-24; Agusta
S.p.A A109 series, SF600 series; Beech Aircraft Corp. A36 and T34
(Tradewind Turbines conversion); Bell Helicopter Textron Model 47
(Soloy Conversion), OH58 series, 206 series, 230, 430; Cessna 206
and 207 (Soloy Conversions); Enstrom Helicopter Corp. TH28, 480;
Eurocopter Deutschland GmbH BO105 series; Eurocopter France AS355
series; Flugzeugwerke Altenrheim AG (FFA) AS202 series; Hiller
Aviation UH12 series (Soloy Conversions); Maule Aerospace Technology
Corp. MX-7 series; McDonnell Douglas Helicopter Co. OH6 series, 500
series, MD500 series, MD520N series, MD530 series; Partenavia
Costruzioni Aeronautiche S.p.A P68 series; Pilatus Britten-Norman
Ltd. BN-2T; and Sikorsky Aircraft Division S76 series.
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 request
approval for an alternative method of compliance in accordance with
paragraph (e) 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: Required as indicated, unless accomplished
previously.
To prevent bearing failure due to bearing separator instability,
which can result in subsequent turbine and engine failure,
accomplish the following:
(a) For engines with No. 5 bearings, Superior P/N A6871505,
installed, accomplish the following:
(1) Within 20 days after the effective date of this AD, perform
an initial visual inspection of all engine filters for metal
particles in accordance with Superior Turbine Service Bulletin (SB)
No. T95-SB001, Revision A, dated September 29, 1995. If any engine
filter contains metal particles that exceed the return to service
criteria described in that SB, prior to further flight, remove the
No. 5 bearing, Superior P/N A6871505, and replace with a serviceable
No. 5 bearing, Allison P/N 6871505.
(2) Thereafter, for engines with No. 5 bearing, Superior P/N
A6871505, installed, perform visual inspections of all engine
filters for metal particles in accordance with Superior Turbine SB
No. T95-SB002, dated September 29, 1995, and, if necessary, replace
with serviceable parts, at intervals not to exceed the following:
(i) For engines with 300 hours or less TIS since overhaul, or
TSN if never overhauled, perform inspections at intervals not to
exceed 25 hours TIS since last inspection.
(ii) For engines with more than 300 hours TIS since new or
overhaul, whichever is lesser, perform inspections at intervals not
to exceed 100 hours TIS since last inspection.
(b) For engines with No. 8 bearings, Superior P/N A23007152,
installed, accomplish the following:
(1) Within 20 days after the effective date of this AD, perform
an initial visual inspection of all engine filters for metal
particles in accordance with Superior Turbine SB No. T95-SB002,
Revision A, dated September 29, 1995. If any engine filter contains
metal particles that exceed the return to service criteria described
in that SB, prior to further flight, remove the No. 8 bearing,
Superior P/N A23007152, and replace with a serviceable No. 8
bearing, Allison P/N 23031478.
(2) Thereafter, for engines with No. 8 bearing, Superior P/N
A23007152, installed, perform visual inspections of all engine
filters for metal particles in accordance with Superior Turbine SB
No. T95-SB002, dated September 29, 1995, and, if necessary, replace
with serviceable parts, at intervals not to exceed the following:
(i) For engines with 300 hours or less TIS since overhaul, or
TSN if never overhauled, perform inspections at intervals not to
exceed 25 hours TIS since last inspection.
(ii) For engines with more than 300 hours TIS since new or
overhaul, whichever is lesser, perform inspections at intervals not
to exceed 100 hours TIS since last inspection.
(c) At the next engine overhaul, or repair or maintenance when
disassembly permits replacement of the bearing, after the effective
date of this AD, whichever occurs first, remove the No. 5 bearing,
Superior P/N A6871505, and replace with a serviceable No. 5 bearing,
Allison P/N 6871505; and remove the No. 8 bearing, Superior P/N
A23007152, and replace with a serviceable No. 8 bearing, Allison P/N
23031478.
(d) Installation of serviceable bearings in accordance with
paragraph (c) of this AD, constitutes terminating action to the
inspection requirements of this AD.
(e) 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, Special 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, Special Certification Office.
Note: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Special Certification Office.
(f) Special flight permits may be issued in accordance with
sections 21.197 and 21.199
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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.
(g) The actions required by this AD shall be done in accordance
with the following Superior Turbine service documents:
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Document No. Pages Revision Date
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SB No. T95-SB001......................... 1-2 A Sept. 29, 1995.
Total pages: 2.
SB No. T95-SB002......................... 1-2 A Sept. 29, 1995.
Total pages: 2.
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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 Superior Air Parts, Inc., 14280
Gillis Rd., Dallas, TX 75244-3792; telephone (800) 487-4884, fax
(214) 490-8471. 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.
(h) This amendment becomes effective on September 26, 1996.
Issued in Burlington, Massachusetts, on August 30, 1996.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 96-22922 Filed 9-10-96; 8:45 am]
BILLING CODE 4910-13-U
