[Federal Register Volume 62, Number 66 (Monday, April 7, 1997)]
[Rules and Regulations]
[Pages 16477-16479]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-8476]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-ANE-43; Amendment 39-9977; AD 97-01-04]
RIN 2120-AA64
Airworthiness Directives; Textron Lycoming and Superior Air
Parts, Inc.
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule, request for comments.
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SUMMARY: This document publishes in the Federal Register an amendment
adopting Airworthiness Directive (AD) 97-01-04 that was sent previously
to all known U.S. owners and operators of certain Textron Lycoming TIO-
540, LTIO-540, and IO-540 series reciprocating engines with certain
Superior Air Parts, Inc. Parts Manufacture Approval (PMA) replacement
cylinder assemblies installed by individual letters. This AD requires
removal from service of affected cylinder assemblies for higher time
cylinder assemblies and replacement with serviceable parts, and initial
and repetitive dye penetrant inspections for mid-time cylinder
assemblies, or replacement with serviceable parts. This amendment is
prompted by a report of an inflight engine failure of a Textron
Lycoming TIO-540 reciprocating engine with affected Superior Air Parts,
Inc. PMA cylinder assemblies installed. The actions specified by this
AD are intended to prevent cylinder head separation, inflight loss of
power, possible engine failure, and fire.
DATES: Effective April 22, 1997 to all persons except those persons to
whom it was made immediately effective by priority letter AD 97-01-04,
issued on December 27, 1996, which contained the requirements of this
amendment.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 22, 1997.
Comments for inclusion in the Rules Docket must be received on or
before June 6, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 96-ANE-43, 12 New England
Executive Park, Burlington, MA 01803-5299.
The applicable service information may be obtained from Superior
Air Parts, Inc., 14280 Gillis Road, Dallas, TX 75244-3792; telephone
(800) 400-5949, fax (972) 702-8723. 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: M. Monica Merritt, Aerospace Engineer,
Special Certification Office, FAA, Rotorcraft Directorate, 2601 Meacham
Blvd., Ft. Worth, TX 76137-4298; telephone (817) 222-5196, fax (817)
222-5136.
SUPPLEMENTARY INFORMATION: On December 27, 1996, the Federal Aviation
Administration (FAA) issued priority letter airworthiness directive
(AD) 97-01-04, applicable to Textron Lycoming Models TIO-540-A2C, -J2B,
-F2BD, -J2BD, -N2BD, -R2AD, -S1AD, and LTIO-540-J2B, -F2BD, -J2BD,
N2BD, -R2AD, and IO-540-M1B5D reciprocating engines, with Superior Air
Parts, Inc. Parts Manufacture Approval (PMA) part number SL54000-A1, -
A2, -A2P, -A20P, and A21P series replacement cylinder assemblies
installed, with serial numbers 001 through 650. That action was
prompted by a report from the Australian Civil Aviation Authority (CAA)
of a New Piper Company Model PA31-350 aircraft, with a Textron Lycoming
TIO-540 engine installed, that suffered an inflight engine failure. An
examination
[[Page 16478]]
of the engine revealed that a Superior Air Parts, Inc. PMA part numbers
SL54000 series replacement cylinder assembly experienced a cylinder
head separation. A soap leak check of the other 5 cylinders detected
bubbles in 2 cylinders indicating a crack. Superior Air Parts has
reported 12 fractured cylinders from the field. The cause of the
cylinder head fractures and separations appears to be that the design
of the PMA cylinder wall thickness is too thin. This condition, if not
corrected, could result in cylinder head separation, inflight loss of
power, possible engine failure, and fire.
The FAA has reviewed and approved the technical contents of
Superior Air Parts, Inc. Mandatory Service Bulletin (MSB) No. 96-002,
Revision A, dated December 17, 1996, that describes procedures for dye
penetrant inspections of cylinder assemblies for cracking.
Since the unsafe condition described is likely to exist or develop
on other engines of the same type design, the FAA issued priority
letter AD 97-01-04 to prevent cylinder head separation, inflight loss
of power, possible engine failure, and fire. The AD requires removal of
cylinders from engines with 300 or more hours Time in Service (TIS)
since installation of the affected cylinder assemblies on the effective
date of this AD within 5 hours TIS after the effective date of this AD,
and replacement with serviceable parts. For engines with 245 hours or
more TIS since installation of the affected cylinder assemblies on the
effective date of this AD, this AD requires an initial dye penetrant
inspection within 5 hours TIS after the effective date of this AD,
followed by repetitive dye penetrant inspections at intervals not to
exceed 25 hours TIS until reaching the 300 hours TIS limit, upon which
the cylinder assemblies must be removed from service. Instead of the
dye penetrant inspections, operators may optionally remove affected
cylinder assemblies and replace with serviceable parts. Cylinder
assemblies with less than 245 hours TIS since installation of the
affected cylinder assemblies on the effective date of this AD must
begin the dye penetrant inspections upon reaching 250 hours TIS since
installation of the affected cylinder assemblies. The actions are
required to be accomplished in accordance with the MSB described
previously.
Since it was found that immediate corrective action was required,
notice and opportunity for prior public comment thereon were
impracticable and contrary to the public interest, and good cause
existed to make the AD effective immediately by individual letters
issued on December 27, 1996, to all known U.S. owners and operators of
certain Textron Lycoming TIO-540, LTIO-540, and IO-540 series
reciprocating engines with certain Superior Air Parts, Inc. PMA
replacement cylinder assemblies installed. These conditions still
exist, and the AD is hereby published in the Federal Register as an
amendment to Section 39.13 of part 39 of the Federal Aviation
Regulations (14 CFR part 39) to make it effective to all persons.
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 96-ANE-43.'' 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 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
97-01-04 Textron Lycoming and Superior Air Parts, Inc.: Amendment
39-9977. Docket 96-ANE-43.
Applicability: Textron Lycoming Models TIO-540-A2C, -F2BD, -J2B,
-J2BD, -N2BD, -R2AD, -S1AD, and LTIO-540-J2B, -F2BD, -J2BD, N2BD, -
R2AD, and IO-540-M1B5D reciprocating engines, with Superior Air
Parts, Inc. Parts Manufacture Approval (PMA) part numbers SL54000-
A1, -A2, -A2P, -A20P, and A21P replacement cylinder assemblies
installed, with serial numbers 001 through 650. These engines are
installed on but not limited to the following aircraft: Bellanca DW-
1 (Eagle), The New Piper Aircraft Co. PA-31 and PA-32 series, Riley
Aircraft Cessna 310 conversion, and Twin Commander Aircraft Corp.
700 series.
Note 1: 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
[[Page 16479]]
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 cylinder head separation, inflight loss of power,
possible engine failure, and fire, accomplish the following:
(a) Within 5 hours Time in Service (TIS) after the effective
date of this AD, for engines with 300 or more hours TIS since
installation of the affected cylinder assemblies on the effective
date of this AD, remove from service affected cylinder assemblies
and replace with serviceable parts.
(b) Within 5 hours TIS after the effective date of this AD, for
engines with 245 hours but less than 300 hours TIS since
installation of the affected cylinder assemblies on the effective
date of this AD, accomplish the following:
(1) Perform an initial dye penetrant inspection for cracks in
accordance with Superior Air Parts, Inc. Mandatory Service Bulletin
(MSB) No. 96-002, Revision A, dated December 17, 1996, or remove and
replace with a serviceable part.
(2) Thereafter, perform repetitive dye penetrant inspections for
cracks at intervals not to exceed 25 hours TIS since last
inspection, in accordance with Superior Air Parts, Inc. MSB No. 96-
002, Revision A, dated December 17, 1996, or remove and replace with
a serviceable part.
(3) Prior to further flight, remove from service cylinder
assemblies found cracked during dye penetrant inspections and
replace with serviceable parts.
(4) Upon accumulating 300 hours TIS since installation of the
affected cylinder assemblies, prior to further flight remove from
service affected cylinder assemblies and replace with serviceable
parts.
(c) For engines with less than 245 hours TIS since installation
of the affected cylinder assemblies on the effective date of this
AD, accomplish the following:
(1) Upon accumulating 250 hours TIS since installation of the
affected cylinder assemblies, perform an initial dye penetrant
inspection for cracks in accordance with Superior Air Parts, Inc.
MSB No. 96-002, Revision A, dated December 17 , 1996, or remove and
replace with a serviceable part.
(2) Thereafter, perform repetitive dye penetrant inspections for
cracks at intervals not to exceed 25 hours TIS since last
inspection, in accordance with Superior Air Parts, Inc. MSB No. 96-
002, Revision A, dated December 17 , 1996, or remove and replace
with a serviceable part.
(3) Prior to further flight, remove from service cracked
cylinder assemblies and replace with serviceable parts.
(4) Upon accumulating 300 hours TIS since installation of the
affected cylinder assemblies, prior to further flight remove from
service affected cylinder assemblies and replace with serviceable
parts.
(d) For the purpose of this AD, a serviceable part is defined as
a cylinder assembly other than a Superior Air Parts, Inc. PMA part
number SL54000 -A1, -A2, -A2P, -A20P, and A21P replacement cylinder
assembly, with serial numbers 001 through 650.
(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 Maintenance
Inspector, who may add comments and then send it to the Manager,
Special Certification Office.
Note 2: 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 in accordance with Sections 21.197
and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and
21.199) may not be issued.
(g) The actions required by this AD shall be accomplished in
accordance with the following Superior Air Parts, Inc. MSB:
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Document No. Pages Revision Date
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96-002................................. 1-4 A December 17, 1996.
Total pages 4.
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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 Road, Dallas, TX 75244-3792; telephone (800) 400-5949, fax
(972) 702-8723. 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 April 22, 1997, to all
persons except those persons to whom it was made immediately
effective by priority letter AD 97-01-04, issued December 27, 1996,
which contained the requirements of this amendment.
Issued in Burlington, Massachusetts, on March 26, 1997.
James C. Jones,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 97-8476 Filed 4-4-97; 8:45 am]
BILLING CODE 4910-13-U
