Airworthiness Directives; Textron Lycoming Reciprocating Engines

[Federal Register Volume 67, Number 117 (Tuesday, June 18, 2002)]
[Rules and Regulations]
[Pages 41315-41318]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-14696]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-36-AD; Amendment 39-12779; AD 2002-12-07]
RIN 2120-AA64


Airworthiness Directives; Textron Lycoming Reciprocating Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment supersedes emergency airworthiness directive 
(AD) 2000-18-53 that was sent previously to all known U.S. owners and 
operators of certain Textron Lycoming reciprocating engines. That 
action required before further flight after receipt of that emergency 
AD, replacement of the oil filter converter plate gasket or the 
converter plate kit. That action also required, within 10 hours time-
in-service (TIS) or within 3 days after the effective date of that 
emergency AD, inspection of the oil filter base for signs of oil 
leakage and evidence of gasket extrusion. That action also required 
replacement of the converter plate gasket at intervals not to exceed 50 
hours TIS since the last replacement of the gasket. This amendment 
requires the same replacements and inspection, and introduces the 
installation of an improved design gasket or converter plate kit as 
terminating action for the repetitive gasket replacements. The actions 
specified in this AD are intended to prevent complete loss of engine 
oil and subsequent seizing of the engine and possibility of fire, 
caused by oil leakage between the converter plate and accessory 
housing.

DATES: Effective July 3, 2002. The incorporation by reference of 
certain publications listed in the rule is approved by the Director of 
the Federal Register as of July 3, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before August 19, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2000-NE-36-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8:00 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. Comments may also be sent via 
the Internet using the following address: [email protected]. 
Comments sent via the Internet must contain the docket number in the 
subject line. The service information referenced in this AD may be 
obtained from Textron Lycoming, 652 Oliver Street, Williamsport, PA 
17701, U.S.A. telephone (570) 323-6181. Information regarding this 
action may be examined, by appointment, at the FAA, New England Region, 
Office of the Regional 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: Rocco Viselli, Aerospace Engineer, New 
York Aircraft Certification Office, FAA, Engine and Propeller 
Directorate, 10 Fifth Street, 3rd Floor, Valley Stream, NY 11581-1200; 
telephone (516) 256-7531, fax (516) 568-2716.

SUPPLEMENTARY INFORMATION: On September 5, 2000, the Federal Aviation 
Administration (FAA) issued Emergency airworthiness directive (AD) 
2000-18-53, applicable to certain Textron Lycoming reciprocating 
engines. That AD requires the following:
    <bullet> For engines with more than 50 hours time-since-new (TSN), 
time-since-overhaul (TSO), or time-since-last replacement of the oil 
filter plate gasket, replacement of the oil filter converter plate 
gasket part number (P/N) LW-13388, or the converter plate kit P/N LW-
13904.
    <bullet> For engines with fewer than 50 hours TSN, TSO, or time-
since-last replacement of the oil filter converter plate gasket P/N LW-
13388, or the converter plate kit P/N LW-13904, inspection of the oil 
filter base for signs of oil leakage and evidence of gasket extrusion.
    <bullet> Replacement of converter plate gasket P/N LW-13388 at 
intervals not to exceed 50 hours TIS since the last replacement of the 
gasket. The actions are required to be done in accordance

[[Page 41316]]

with Textron Lycoming Mandatory Service Bulletin (MSB) 543A, dated 
August 30, 2000 and Textron Lycoming Service Instruction No. 1453, 
dated May 9, 1991.

That AD was prompted by reports of certain oil filter converter plate 
gaskets, P/N LW-13388, extruding from the seat of the oil filter 
converter plate. The protruding or swelling of the gasket allows oil to 
leak from between the plate and accessory housing. The actions 
specified in that AD are intended to prevent complete loss of engine 
oil and subsequent seizing of the engine and possible fire, caused by 
oil leakage between the converter plate and accessory housing.
    Since emergency AD 2000-18-53 was issued, Textron Lycoming has 
issued a service bulletin supplement that relieves the requirements of 
MSB 543A and that eliminates the need for gasket replacement every 50 
ours TSN, TSO, or time since the last replacement.

Manufacturer's Service Information

    The FAA has reviewed and approved the technical contents of the 
following Textron Lycoming Service Information:
    <bullet> MSB 543A, dated August 30, 2000, and SI No. 1453, dated 
May 9, 1991, that provide instructions for replacing the oil filter 
converter plate gasket P/N LW-13388, or the converter plate kit P/N LW-
13904.
    <bullet> Supplement No. 1 to MSB 543A, dated October 4, 2000, that 
describes procedures for replacing the oil filter converter plate 
gasket P/N LW-13388, or the converter plate kit P/N LW-13904, with a 
new improved design.

FAA's Determination of an Unsafe Condition and Required Actions

    Since the unsafe condition described is likely to exist or develop 
on other engines of the same type design, the FAA issued emergency AD 
2000-18-53 to prevent complete loss of engine oil and subsequent 
seizing of the engine and possible fire, caused by oil leakage between 
the converter plate and accessory housing. This AD requires for engines 
listed that were shipped from the factory between April 1, 1999 and 
October 4, 2000, and any engine listed that had the oil filter 
converter plate gasket replaced with gasket P/N LW-13388, and, any 
engine listed that had the oil filter converter plate replaced with 
converter plate kit P/N LW-13904, the following:
    <bullet> Before further flight after the effective date of this AD, 
for engines with more than 50 hours TSN or TSO, or time-since-last 
replacement of the oil filter plate gasket P/N LW-13388, replacement of 
the oil filter converter plate gasket or the converter plate kit 
P/N LW-13904.
    <bullet> Within 10 hours TIS or within 3 days after the effective 
date of this AD, whichever occurs earlier, for engines with fewer than 
50 hours TSN, TSO, or time-since-last replacement of the oil filter 
converter plate gasket P/N LW-13388, or the converter plate kit P/N LW-
13904, inspection of the oil filter base for signs of oil leakage and 
evidence of gasket extrusion.
    <bullet> Replacement of the converter plate gasket P/N LW-13388 at 
intervals not to exceed 50 hours TIS since the last replacement of the 
gasket.
    <bullet> As terminating action to the repetitive gasket replacement 
specified in this AD, replacement of the oil filter converter plate 
gasket or the oil filter converter plate with a converter plate kit, in 
accordance with Part II and Part III of Textron Lycoming Supplement 1 
to MSB 543A, dated October 4, 2000.

The actions must be done in accordance with the service information 
described previously.

Immediate Adoption of This AD

    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 on September 5, 2000 to 
all known U.S. owners and operators of the affected Textron Lycoming 
reciprocating engines. 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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NE-36-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it would not have a substantial 
direct effect 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. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this final rule.
    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:

[[Page 41317]]

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 a new airworthiness 
directive, Amendment 39-12779, to read as follows:

2002-12-07  Textron Lycoming: Amendment 39-12779. Docket No. 2000-
NE-36-AD. Supersedes AD 2000-18-53.

    Applicability: This airworthiness directive (AD) is applicable 
to the reciprocating engine models in the following Table, that were 
shipped from the factory between April 1, 1999 and October 4, 2000, 
or rebuilt, or overhauled, or had the oil filter converter plate kit 
part number (P/N) LW-13904 or gasket P/N LW13388 replaced:

                       Engine Applicability Table
------------------------------------------------------------------------
 
------------------------------------------------------------------------
O-320...................  -H1AD, -H1BD, -H2AD, -H2BD, -H3AD, -H3BD
------------------------------------------------------------------------
(L)O-360................  -A1AD, -A1F6D, -A1G6D, -A1LD, -A3AD, -A4AD, -
                           A5AD, -E1A6D
------------------------------------------------------------------------
IO-360..................  -A1B6D, -A1D6D, -A3B6D, -A3D6D, -C1E6D, -J1AD,
                           -J1A6D
------------------------------------------------------------------------
(L)TO-360...............  -A1A6D, -C1A6D, -E1A6D, -F1A6D
------------------------------------------------------------------------
TIO-360.................  -C1A6D
------------------------------------------------------------------------
(L)HIO-360..............  -E1AD, -E1BD, -F1AD
------------------------------------------------------------------------
O-540...................  -H1A5D, -H1B5D, -H2A5D, -H2B5D, -J1A5D, -
                           J1B5D, -J1C5D, -J1D5D, -J2A5D, -J2B5D, -
                           J2C5D, -J2D5D, -J3A5D, -J3C5D, -L3C5D
------------------------------------------------------------------------
IO-540..................  -C4D5D, -K1A5D, -K1B5D, -K1E5D, -K1F5D, -
                           K1G5D, -K1J5D, -L1A5D, -L1B5D, -M1A5D, -
                           M1B5D, -M2A5D, -T4A5D, -T4B5D, -T4C5D, -
                           U1A5D, -U1B5D, -V4A5D, -W1A5D, -W3A5D
------------------------------------------------------------------------
(L)TIO-540..............  -K1AD, -S1AD, -AA1AD, -AB1AD, -AB1BD, -F2BD, -
                           J2BD, -N2BD, -R2AD, -T2AD, -V2AD
------------------------------------------------------------------------
AEIO-540................  -L1B5D
------------------------------------------------------------------------
TIO-541.................  -E Series
------------------------------------------------------------------------
TIGO-541................  -D1A, -D1B, -E1A
------------------------------------------------------------------------
IO-720..................  -A1BD, -B1BD, -C1BD, -D1BD, -D1CD
------------------------------------------------------------------------


    Note 1: This 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 (f) 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

    Compliance with this AD is required as indicated, unless already 
done.
    To prevent complete loss of engine oil and subsequent seizing of 
the engine and possibility of fire, caused by oil leakage between 
the converter plate and accessory housing, do the following:
    (a) For engines with more than 50 hours time-since-new (TSN), 
time-since-overhaul (TSO), or time since the last replacement of the 
oil filter converter plate gasket, P/N LW-13388, or the converter 
plate kit, P/N LW-13904, replace the converter plate gasket or 
converter plate kit in accordance with paragraphs 1 and 2 of Textron 
Lycoming Mandatory Service Bulletin (MSB) 543A, dated August 30, 
2000, and Textron Lycoming Service Instruction (SI) No. 1453, dated 
May 9, 1991, or Part II of Supplement No. 1 to MSB 543A, dated 
October 4, 2000, before further flight.
    (b) For engines with fewer than 50 hours TSN, TSO, or time since 
the last replacement of the oil filter converter plate gasket, P/N 
LW-13388, or the oil converter plate, P/N LW-13904, inspect the 
gasket within 10 hours time-in-service (TIS) or within 3 days after 
the effective date of this AD, whichever occurs earlier, for the 
following:
    (1) Inspect the oil filter base for both:
    (i) Signs of oil leakage between the oil filter base and the 
accessory housing; and
    (ii) Any evidence of the gasket extruding beyond the perimeter 
of the base.
    (2) If there is any oil leakage, or if the seal is damaged, 
extruded, displaced, or deteriorated, replace the converter plate 
gasket or converter plate kit in accordance with paragraphs 1 and 2 
of Textron Lycoming MSB 543A, dated August 30, 2000, and Textron 
Lycoming SI No. 1453, dated May 9, 1991, or Part II of Supplement 
No. 1 to MSB 543A, dated October 4, 2000, before further flight.
    (c) Thereafter, replace the converter plate gasket, P/N LW-
13388, or the oil converter plate kit, P/N LW-13904, at intervals 
not to exceed 50 hours TIS since the last replacement.
    (d) Before October 1, 2003, replace the oil filter converter 
plate gasket or oil filter converter plate kit, in accordance with 
Part II or Part III respectively, of Supplement No. 1 to MSB 543A, 
dated October 4, 2000.

Terminating Action

    (e) Replacement of oil filter converter plate gasket, or oil 
filter converter plate in accordance with Part II or Part III of 
Textron Lycoming Supplement 1 to MSB 543A, dated October 4, 2000, 
constitutes terminating action to the repetitive gasket replacement 
specified in paragraph (c) of this AD.

Alternative Methods of Compliance

    (f) 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, New York Aircraft Certification 
Office. Operators must submit their requests through an appropriate 
FAA Maintenance Inspector, who may add comments and then send it to 
the Manager, New York Aircraft 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 New York Aircraft Certification 
Office.

Special Flight Permits

    (g) Special flight permits may be issued in accordance with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the airplane to a

[[Page 41318]]

location where the requirements of this AD can be done.

Documents That Have Been Incorporated by Reference

    (h) The inspections and replacements must be done in accordance 
with the following Textron Lycoming mandatory service bulletin 
(MSB), MSB supplement, and Service Instruction (SI):

----------------------------------------------------------------------------------------------------------------
          Document No.                    Pages                 Revision                       Date
----------------------------------------------------------------------------------------------------------------
MSB No. 543A, Total pages: 2....  All.................  Revision A..............  August 30, 2000.
MSB No. 543A, Supplement No. 1,   All.................  Original................  October 4, 2000.
 Total pages: 3.
SI No. 1453, Total pages: 1.....  All.................  Original................  May 9, 1991.
----------------------------------------------------------------------------------------------------------------

The incorporations by reference were 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 Textron Lycoming, 652 Oliver Street, 
Williamsport, PA 17701, U.S.A. telephone: 570-323-6181. This 
information may be examined, by appointment, at the FAA, New England 
Region, Office of the Regional 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.

Effective Date

    (i) This amendment becomes effective July 3, 2002.

    Issued in Burlington, Massachusetts, on June 4, 2002.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 02-14696 Filed 6-17-02; 8:45 am]
BILLING CODE 4910-13-P

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