[Federal Register Volume 63, Number 32 (Wednesday, February 18, 1998)]
[Proposed Rules]
[Pages 8149-8151]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-3797]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 63, No. 32 / Wednesday, February 18, 1998 /
Proposed Rules
[[Page 8149]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-ANE-42-AD]
RIN 2120-AA64
Airworthiness Directives; Superior Air Parts, Inc., Piston Pins
Installed on Textron Lycoming Reciprocating Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to Superior Air Parts, Inc., piston
pins installed on Textron Lycoming reciprocating engines. This proposal
would require removal from service of defective piston pins, and
replacement with serviceable parts. This proposal is prompted by
reports of numerous piston pin fractures. The actions specified by the
proposed AD are intended to prevent the piston pin from puncturing the
engine crankcase by the connecting rod, resulting in the loss of oil
leading to total power failure and possible fire, or freeing the
connecting rod, possibly puncturing the cylinder or jamming the engine
crankshaft, resulting in catastrophic engine failure.
DATES: Comments must be received by March 20, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 97-ANE-42-AD, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may also be sent
via the Internet using the following address: ``9-ad-
[email protected]''. Comments sent via the Internet must contain
the docket number in the subject line. Comments may be inspected at
this location between 8:00 a.m. and 4:30 p.m., Monday through Friday,
except Federal holidays.
FOR FURTHER INFORMATION CONTACT: Paul Madej, Aerospace Engineer,
Special Certification Office, FAA, Rotorcraft Directorate, 2601 Meacham
Blvd., Ft. Worth, TX 76137-4298; telephone (817) 222-4635, fax (817)
222-5785.
SUPPLEMENTARY INFORMATION:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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 above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with
the substance of this proposal 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 97-ANE-42-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, New England Region, Office of the Assistant Chief Counsel,
Attention: Rules Docket No. 97-ANE-42-AD, 12 New England Executive
Park, Burlington, MA 01803-5299.
Discussion
The Federal Aviation Administration (FAA) received numerous reports
of fractured Parts Manufacturer Approval (PMA) Superior Air Parts, Inc.
piston pins, Part Number (P/N) 13444-1, installed on Textron Lycoming
IO-540, O-320, IO-720, LTIO-540, IGSO-540, IO-360, LO-360, and O-360
series reciprocating engines. The investigation reveals that some of
these piston pins shipped from Superior Air Parts, Inc. between August
24, 1993, through April 22, 1996, may contain subsurface manufacturing
imperfections, such as higher impurity levels, retained austenite, and
grind burns. The higher impurity levels may provide a stress riser and
grind burns or retained austenite may cause weaker material to give way
to fatigue cracks, which may propagate to failure. Failure of the
piston pin may cause puncturing of the engine crankcase by the
connecting rod resulting in the loss of oil leading to total power
failure and possible fire. Failure of the piston pin may free the
connecting rod, possibly puncturing the cylinder or cause jamming of
the engine crankshaft resulting in catastrophic engine failure.
Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, the
proposed AD would require within 20 hours time in service after the
effective date of this AD, removal from service of defective piston
pins, and replacement with serviceable parts.
The FAA estimates that 19,000 engines installed on aircraft of U.S.
registry would be affected by this proposed AD, that it would take
approximately 6 work hours per engine to accomplish the proposed
actions, and that the average labor rate is $60 per work hour. Required
parts would cost approximately $200 per engine. Based on these figures,
the total cost impact of the proposed AD on U.S. operators is estimated
to be $10,640,000.
The regulations proposed herein would 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
proposal would not have sufficient federalism implications to warrant
the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action''
[[Page 8150]]
under Executive Order 12866; (2) is not a ``significant rule'' under
the DOT Regulatory Policies and Procedures (44 FR 11034, February 26,
1979); and (3) if promulgated, will not have a significant economic
impact, positive or negative, on a substantial number of small entities
under the criteria of the Regulatory Flexibility Act. A copy of the
draft regulatory evaluation prepared for this action is contained in
the Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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:
Superior Air Parts, Inc., Piston Pins Installed on Textron Lycoming
Reciprocating Engines: Docket No. 97-ANE-42-AD.
Superior Air Parts, Inc. Parts Manufacturer Approval (PMA) piston
pins, Part Number (P/N) 13444-1, installed on Textron Lycoming O-
320-B1A, B1B, B2C, B2A, B2B, B3A, B3B, B3C, D1A, D1B, D1C, D2A, D2B,
D2C, D1D, D1F, D2G, D2J, D3G, E2A, D2F, D2H, H1AD, H2AD, H1BD, H2BD,
H3BD;
LIO-320-B1A, B2A
IO-320-B1A, B2A, C1A, B1C, D1A, B1B, D1B, D1AD, C1B, D2A, D2B, A2C,
E2A;
AIO-320-B1B, C1B;
O-340-A
O-360-B2A, C1A, C1C, C1F, C2A, C2C, C2E, D2A, F1A6, A1A, A2A, A3A,
A1C, A1D, A2D, A2E, C2D, D2B, A1AD, A1F6, A1F6D, A1G6, A1G6D, A1LD,
A2F, A2G, A3AD, A4A, A4G, A4J, A4K, A4M, A3AD, C1G, A5AD, E1A6D,
F1A6;
LO-360-A1C6D, C1A6D, E1AD, E1A6D, E2A6D, E1BD, E2BD;
IVO-360-A1A, VO-360-A1A, A1B, B1A, B1B;
LTO-360-E1A6D;
C1E6
TO-360-A1G6D, E1A6D, C1A6D;
HO-360-B1A, B1B, A1A;
HIO-360-A1A, A1B, B1A, C1A, C1B, D1A, E1AD, E1BD, F1AD;
IO-360-C1A, C1B, C1C, C1C6, C1D6, C1E6, C1E6D, C1F, A1A, A1B, A1B6,
A1B6D, A1C, A1D6, A1D6D, A2A, A2B, A2C, A3B6D, A3D6D, B1A, B1B, B1C,
B1D, B1E, B1F, B1F6, B2E, B2F, B2F6, B4A, D1A, E1A, F1A, J1AD,
J1A6D, K2A, A1D;
AIO-360-A1A, A1B, A2A, A2B, B1B;
LHIO-360-C1A, C1B, F1AD;
LIO-360-C1E6;
TIO-360-A1B, C1A6D;
AEIO-360-A1E, B1G6, H1A, A1A, A1B, A1B6, A1C, A1D, A1E, A2A, A2B,
A2C, B1B, B1D, B1F, B1F6, B2F, B2F6, B4A;
GO-480-B, B1A6, B1B, B1C, B1D, D1A, F6, F1A6, F2A6, F4A6, C1B6,
C1D6;
G1A6, G1D6, G1H6, G1J6, G2D6, G2F6,G1B6, C2, G1E6, G1F6, G1G6, D1A,
E1A6, F2D6, F3A6, F3B6, F4B6, C2C6, C2D6, C2E6, G1J6;
GSO-480-A1A6, A1C6, A2A6, B1A6, B1B6, B1C6, B1E6, B1F6, B1G6, B1J6,
B2C6, B2D6, B2G6, B2H6 B1B3;
IGSO-480-A1A6, A1B6, A1C6, A1D6, A1E6, A1F6, A1G6;
IGO-480-A1B6, A1A6;
O-540-B2B5, B2C5, B4B5, E4A5, E4B5, E4C5, G1A5, H1A5D, H1A5, H2A5,
H1B5D, H2B5D, A1A, A1A5, A1B5, A1C5, A1D, A1D5, A2B, A3D5, A4A5,
A4B5, A4C5, A4D5, B4A5, A1D5, A2B, A3D5, B1A5, B2A5, E4B5, E4C5,
F1A5, F1B5, B2B5, G2A5, B1B5, D1A5, L3C5D;
IO-540-A1A5, B1A5, B1B5, B1C5, C2C, C1B5, C1C5, C4B5, C4C5, D4A5,
D4B5, D4C5, E1A5, E1B5, E1C5, G1A5, G1B5, G1C5, G1D5, G1E5, G1F5,
J4A5, K1A5, K1B5, K1C5, K1D5, K1E5, M1A5, M1A5D, N1A5, P1A5, R1A5,
K1E5D, D4A5, K1A5D, K1B5D, K1F5, K1F5D, K1G5, K1G5D, K1H5, K1J5,
K1J5D, L1A5, S1A5, T4A5D, T4B5D, L1C5, C4D5D, U4A5D, T4C5D, U1A5D,
U1B5D;
TIO-540-A1A, A1B, A2A, A2B, A2C, C1A, E1A, G1A, H1A, J2B, F2BD,
J2BD, N2BD, R2AD, S1AD, AA1AD, AB1AD, U2A, C1AD, AF1A, AE2A;
LTIO-540-J2B, F2BD, J2BD, N2BD, R2AD, U2A;
IGO-540-A1A, A1C, B1A, B1C, A1B, B1B;
IGSO-540-A1A, A1C, A1D, A1E, A1H, B1A, B1C, A1H;
AEIO-540-L1B5, L1B5D, D4B5, D4A5, D4C5;
VO-540-A1A, A2A, B1A, B2A, B1B3, B1C, B2C, D1D, B2D, B2G, B1F, B1B,
B1E, B2E, C1A, C2A, C1B, C1C3, B1H3, C2C;
TIVO-540-A2A;
TIO-541-A1A, E1A4, E1B4, E1C4, E1D4;
TIGO-541-E1A, B1A, C1A, D1A, D1B, G1AD; and
IO-720-A1A, A1B, B1B, C1B, D1B, B1BD, D1CD series reciprocating
engines, and which were overhauled or had cylinder head maintenance
performed by a repair facility other than Textron Lycoming after
August 24, 1993. These engines are installed on but not limited to
the following aircraft: Aero Bero AB-180;
Aero Commander;
Aero Lark 100;
Aero Victa R-2;
Aromot P-56;
Aviolight P66D;
Beagle A-109, Airedale D5-160, Husky D5-180, J1-U;
Raytheon Beech 76, 95, B-95, M-23;
Bellanca 8GCBC FP;
Bolkow 207, K1-107C;
C.A.A.R.P. S.A.N. M-23III;
Center Regente DR-253;
Cessna 172, 172RG, 177;
Champion Citabria;
Christen Husky A-1;
Daetwyler MD3-160;
DeHavilland DHA-3MK3;
Dinfia (1A-51);
Doyn-Cessna (170, 170A, 170B, 172, 172A, 172B);
Earl Horton Pawnee (Piper PA-25);
FFA Bravo AS-202/15;
Fuji F-200;
General Aviation Pinguino;
Grob G115;
Grumman AA-5;
GY-100-135;
Gyroflug Speed Canard;
Hi Sheer Wing;
Hughes 269A;
Hughes Tool YH-2HU;
InterMntn. Call Air A-6;
Kingsford-Smith J5-6;
Lake C-2, LA-4, 4A, 4P;
Malmo MF, -10, -10B;
Maule MX-7-180;
MBB BO-209C;
Mooney 20B (M20B, M20D, M20E);
Nash Petrel;
Neifa 1PD-5901;
Norman Aeroplace NAC-1 Freelance;
The New Piper, Inc. PA-44; PA-23, PA-22, PA-22S, PA-24, PA-28, PA-
28S, PA-30, PA-30T, PA-39;
Partenavia (P-66) P-66, P-66B, P-66C, 131APM;
Pezetel 150;
Procaer F-15-A;
Regente N-591;
Robin DR400-140B, DR400-180, -180R, DR-340, DR-360, R-1180T, R-3140,
R-3170;
Robinson R-22;
SAAB 91-D;
SOCATA. TB9, TB10, MS-886, MS-892, MS-893, Rallye 180Gt, RS-180;
Siai-Marchetti S, -202, -205;
Slingsby T67, T67C, T67M;
Societe Aero. Normande Mousquetaire (D-140), Jodel D-140C;
Std. Helicopter;
Sud Gardan GY-180, GY80-160;
Teal III TSC 1A3;
Uirapuru Aerotec 122;
Valmet PIK-23;
Wassmer WA-50A, -40, 52;
Note 1: Shipping records, engine logbooks, work orders, and
parts invoices check may allow an owner or operator to determine if
this AD applies.
Note 2: 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 (d) 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
[[Page 8151]]
request should include specific proposed actions to address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent the piston pin from puncturing the engine crankcase
by the connecting rod, resulting in the loss of oil leading to total
power failure and possible fire, or freeing the connecting rod,
possibly puncturing the cylinder or jamming the engine crankshaft,
resulting in catastrophic engine failure, accomplish the following:
(a) If an engine has not had a piston pin installed after August
23, 1993, or if an engine has had a piston pin installed after
August 23, 1993, but it was installed by Textron Lycoming, then no
action is required.
(b) For engines that had a piston pin installed after August 23,
1993, by an entity other than Textron Lycoming, within 20 hours time
in service (TIS) after the effective date of this AD, determine if a
suspect PMA Superior Air Parts, Inc. piston pin, P/N 13444-1, could
have been installed. If unable to verify that a suspect piston pin
was not installed using a records check, disassemble the engine in
accordance with the applicable Maintenance Manual or Overhaul
Manual, visually inspect or verify for suspect piston pins, and
accomplish the following:
(1) If it is determined that suspect PMA Superior Air Parts,
Inc. piston pins, P/N 13444-1, could have been installed, remove
from service defective piston pins and replace with serviceable
piston pins.
(2) If it is determined that suspect PMA Superior Air Parts,
Inc. piston pins, P/N 13444-1, could not have been installed, no
further action is required.
(c) For the purpose of this AD, a serviceable piston pin is any
piston pin that has been verified not to be a PMA Superior Air
Parts, Inc. piston pin, P/N 13444-1, shipped from Superior Air
Parts, Inc., from August 24, 1993, through April 22, 1996.
Installation of a PMA Superior Air Parts Inc. piston pin, P/N 13444-
1, that cannot be verified to be outside of the suspect shipping
period range, is prohibited after the effective date of this AD.
(d) 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.
Operators shall submit their requests through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Special Certification Office.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Special Certification Office.
(e) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the aircraft to a location where
the inspection may be performed.
Issued in Burlington, Massachusetts, on February 6, 1998.
James C. Jones,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 98-3797 Filed 2-17-98; 8:45 am]
BILLING CODE 4910-13-P