[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