[Federal Register Volume 67, Number 183 (Friday, September 20, 2002)]
[Rules and Regulations]
[Pages 59139-59156]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-24030]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NE-03-AD; Amendment 39-12883; AD 2002-19-03]
RIN 2120-AA64
Airworthiness Directives; Textron Lycoming IO-540, LTIO-540 and
TIO-540 Series 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) 2002-17-53 that was sent previously to all known U.S. owners and
operators of Textron Lycoming LTIO-540 and TIO-540 series engines,
rated at 300 horsepower (HP) or higher. That action requires, before
further flight, replacing certain serial-numbered crankshafts that were
hammer forged with crankshafts that were press forged. That AD was
prompted by reports of crankshaft failures in LTIO-540 and TIO-540
engines, rated at 300 HP or higher. This amendment expands the suspect
population of engines to include engines with crankshafts that were
manufactured between March 1997 and the present and all IO-540 engines
with crankshafts that were manufactured between March 1997 and the
present that have been modified by supplemental type certificate (STC)
by installing a turbocharger system. The actions specified by this AD
are intended to prevent failure of the crankshaft, which could result
in total engine power loss, in-flight engine failure and possible
forced landing.
DATES: Effective September 20, 2002.
The incorporation by reference of certain publications listed in
the rule is approved by the Director of the Federal Register as of
September 20, 2002.
Comments for inclusion in the Rules Docket must be received on or
before November 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. 2002-NE-
[[Page 59140]]
03-AD, 12 New England Executive Park, Burlington, MA 01803-5299.
Comments may be inspected at this location, by appointment, between 8
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.
FOR FURTHER INFORMATION CONTACT: Rocco Viselli or Norm Perenson,
Aerospace Engineer, New York Aircraft Certification Office, FAA, Engine
and Propeller Directorate, 10 Fifth Street, Third Floor, Valley Stream,
NY 11581-1200; telephone (516) 256-7531 or (516) 256-7537; fax (516)
568-2716.
SUPPLEMENTARY INFORMATION: On August 16, 2002, the FAA issued emergency
AD 2002-17-53, applicable to Textron Lycoming LTIO-540 and TIO-540
series engines, rated at 300 HP or higher, to supersede emergency AD
2002-04-51 issued on February 11, 2002. AD 2002-17-53 requires
replacing certain crankshafts that were manufactured using a hammer-
forged process with crankshafts that were manufactured using a press-
forged process. That action was prompted by reports of 17 crankshaft
failures in LTIO-540 and TIO-540 engines, rated at 300 HP or higher,
which were assembled with certain crankshafts that were manufactured
using a hammer-forged process. The FAA is continuing the investigation
into the cause of the crankshaft failures, and further regulatory
action may follow. This action is prompted by an additional crankshaft
failure that was outside the population of crankshafts covered by AD
2002-17-53. This AD requires the same replacement of certain
crankshafts before further flight, and includes material testing of
certain crankshafts manufactured between March 1997 and the present.
This AD also expands the applicability to include all IO-540 engines
with crankshafts that were manufactured between March 1997 and the
present that have been modified by STC by installing a turbocharger
system. This condition, if not corrected, could result in crankshaft
failure, which could result in total engine power loss, in-flight
engine failure and possible forced landing.
Manufacturer's Service Information
The FAA has reviewed the technical contents of Lycoming Mandatory
Service Bulletin (MSB) No. 552, dated August 16, 2002, that provide
tables of the affected engine and crankshaft serial numbers (SN's).
FAA's Determination of an Unsafe Condition and Required Actions
Since an unsafe condition has been identified that is likely to
exist or develop on other Textron Lycoming LTIO-540 and TIO-540
engines, rated at 300 HP or higher, and on IO-540 engines that have
been modified by STC by installing a turbocharger system with certain
crankshafts installed, this AD requires removal of certain crankshafts
before further flight and material testing of certain other
crankshafts.
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 August 16, 2002, to all
known U.S. owners and operators of Textron Lycoming LTIO-540 and TIO-
540 engines, rated at 300 HP or higher. 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 No. 2002-NE-03-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:
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:
[[Page 59141]]
2002-19-03 Textron Lycoming: Amendment 39-12883. Docket No. 2002-NE-
03-AD. Supersedes Emergency AD 2002-17-53.
Applicability
This AD is applicable to all Textron Lycoming LTIO-540 and TIO-
540 engines, rated at 300 horsepower (HP) or greater and all IO-540
engines, rated at any HP, that have been modified by supplemental
type certificate (STC) listed in Table 1 of this AD, by installing a
turbocharger system. These engines are used on, but not limited to
Piper Navajo (PA 31, PA 31-350, and PA 31-325), Piper Saratoga (PA
32-301T, PA 32R-301T), Piper Aerostar (PA 60-700P), Piper Malibu
Mirage (PA 46-350P), Piper Mojave (PA 31P-350) Appalachian Aircraft
Corporation Gavilan (EL-1), and Cessna T-206 airplanes.Table 1
follows:
Table 1.--List of STC Numbers
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SA000214DE SA00356DE SA01925AT SA09650SC
SA469NE SA2062WE SA2118NM SE2122WE
SA2123NM SA257CE SA2657WE SA2082WE
SA305SO SA3513WE SA3719SW SA385WE
SA4942NM SA529WE SA530WE SA539WE
SA5699NM SA811WE SA840WE SA909WE
SA978WE SE00357DE SE01949AT SE1657NM
SE978NM SE17WE SE21WE SE22WE
SE4157NM SE5869SW SE40WE SE60WE
SE6WE SE7734SW SE81WE SA01925AT
SA1648NM SA4156NM SA1747CE SE4941NM
SA2656WE SA000214DE ................ ................
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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 (g) 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 crankshaft failure, which could result in total
engine power loss, in-flight engine failure and possible forced
landing, do the following:
LTIO-540 Engines, TIO-540 Engines, Rated at 300 HP or Greater
(a) If your engine SN is listed in Table 1 of Lycoming Mandatory
Service Bulletin (MSB) No. 552, dated August 16, 2002, remove the
crankshaft before further flight.
(b) If your engine SN is listed in Table 2 of this AD, do the
following; Table 2 follows:
[[Page 59142]]
[GRAPHIC] [TIFF OMITTED] TR20SE02.044
(1) Contact Lycoming, 652 Oliver Street, Williamsport, PA 17701,
U.S.A.; telephone (570) 323-6181, within 10 hours time-in-service (TIS)
to arrange for a crankshaft material test.
(2) Operation of the engine beyond 10 hours TIS after the effective
date of this AD or while the material is being tested is not permitted.
(3) If your crankshaft fails the material testing, remove the
crankshaft before further flight.
(4) If your crankshaft passes the material testing, the crankshaft
may be returned to service.
(c) If your engine SN is listed in Table 3 of this AD, do the
following; Table 3 follows:
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(1) Contact Lycoming, 652 Oliver Street, Williamsport, PA 17701,
U.S.A.; telephone (570) 323-6181, contact Lycoming, 652 Oliver Street,
Williamsport, PA 17701, U.S.A.; telephone (570) 323-6181 within 50
hours time-in-service (TIS) or 6 months after the effective date of
this AD, whichever occurs earlier, to arrange for a crankshaft material
test.
(2) Operation of the engine beyond 50 hours TIS or 6 months after
the effective date of this AD, whichever occurs earlier, or while the
material is being tested is not permitted.
(3) If your crankshaft fails the material testing, remove the
crankshaft before further flight.
(4) If your crankshaft passes the material testing, the crankshaft
may be returned to service.
IO-540 Engines Modified by STC by Installing a Turbocharger System and
All Engines That Have Been Overhauled
(d) If your engine was manufactured, overhauled or had the
crankshaft replaced after March 1, 1997, and your engine SN is not
covered in paragraphs (a), (b), or (c) of this AD, do the following:
[[Page 59150]]
(1) Determine the SN of your crankshaft.
(2) If your crankshaft SN is listed in Table 2 of Lycoming MSB 552,
dated August 16, 2002, remove the crankshaft before further flight.
(3) If your crankshaft SN is listed in Table 4 of this AD, do the
following; Table 4 follows:
[GRAPHIC] [TIFF OMITTED] TR20SE02.052
(i) Contact Lycoming, 652 Oliver Street, Williamsport, PA 17701,
U.S.A.; telephone (570) 323-6181, within 10 hours time-in-service (TIS)
to arrange for a crankshaft material test.
(ii) Operation of the engine beyond 10 hours TIS after the
effective date of this AD or while the material is being tested is not
permitted.
(iii) If your crankshaft fails the material testing, remove the
crankshaft before further flight.
(iv) If your crankshaft passes the material testing, the crankshaft
may be returned to service.
(4) If your crankshaft SN is listed in Table 5 of this AD, do the
following; Table 5 follows:
[[Page 59151]]
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[GRAPHIC] [TIFF OMITTED] TR20SE02.054
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[GRAPHIC] [TIFF OMITTED] TR20SE02.058
BILLING CODE 4910-13-C
(i) Contact Lycoming, 652 Oliver Street, Williamsport, PA 17701,
U.S.A.; telephone (570) 323-6181, contact Lycoming, 652 Oliver Street,
Williamsport, PA 17701, U.S.A.; telephone (570) 323-6181 within 50
hours time-in-service (TIS) or 6 months after the effective date of
this AD, whichever occurs earlier, to arrange for a crankshaft material
test.
(ii) Operation of the engine beyond 50 hours TIS or 6 months after
the effective date of this AD, whichever occurs earlier, or while the
material is being tested is not permitted.
(iii) If your crankshaft fails the material testing, remove the
crankshaft before further flight.
(iv) If your crankshaft passes the material testing, the crankshaft
may be returned to service.
Disposition of Crankshafts That Have Passed the Material Test
(e) A crankshaft that has passed the Lycoming material testing may
be returned to service.
Disposition of Crankshafts That Have Failed the Material Test
(f) After the effective date of this AD, do not install in any
engine, any crankshaft that has failed the material test.
Denial of Alternative Methods of Compliance
(g) An alternative method of compliance to perform material testing
on crankshafts listed by SN in Table 2 of Lycoming MSB 552, dated
August 16, 2002, will not be approved.
Special Flight Permits
(h) Special flight permits may be issued in accordance with
Sec. Sec. 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where the
requirements of this AD can be done.
Documents That Have Been Incorporated By Reference
(i) The actions must be done in accordance with the following
Lycoming Mandatory Service Bulletin No. 552, dated August 16, 2002.
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 Lycoming, 652 Oliver Street, Williamsport,
PA 17701, U.S.A. Copies may be inspected 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
(j) This amendment becomes effective September 20, 2002.
Issued in Burlington, Massachusetts, on September 16, 2002.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 02-24030 Filed 9-19-02; 8:45 am]
BILLING CODE 4910-13-P