[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: 
``[email protected]''. 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