[Federal Register Volume 67, Number 220 (Thursday, November 14, 2002)]
[Rules and Regulations]
[Pages 68932-68934]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-29003]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NE-31-AD; Amendment 39-12950; AD 2002-23-06]
RIN 2120-AA64
Airworthiness Directives; Textron Lycoming AEIO-540, IO-540,
LTIO-540, O-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 an emergency airworthiness directive
(AD) that was sent previously to all known U.S. owners and operators of
Textron Lycoming (T/L) AEIO-540, IO-540, LTIO-540, O-540, and TIO-540
series reciprocating engines. That action requires replacing certain
zinc-plated crankshaft gear retaining bolts. This action still requires
replacing certain zinc-plated crankshaft gear retaining bolts, but
expands the population of affected engines. This amendment is prompted
by two recent failures of zinc-plated crankshaft gear retaining bolts,
and a reassessment of the extent to which the suspect bolts may still
be present in the field. The actions specified by this AD are intended
to prevent loss of all engine power and possible forced landing.
DATES: Effective November 19, 2002. The incorporation by reference of
certain publications listed in the regulations is approved by the
Director of the Federal Register as of November 19, 2002.
Comments for inclusion in the Rules Docket must be received on or
before January 13, 2003.
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-31-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.
The applicable service information may be obtained from Lycoming, a
Textron Company, 652 Oliver Street, Williamsport, PA 10071; telephone
(570) 323-6181. This information may also be obtained electronically on
``http://www.lycoming.textron.com''. 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.
FOR FURTHER INFORMATION CONTACT: Norm Perenson, Aerospace Engineer, New
York Aircraft Certification Office, FAA, Engine and Propeller
Directorate, 10 Fifth Street, 3rd floor, Valley Stream, NY 11581-1200;
telephone (516) 256-7537; fax (516) 568-2716.
SUPPLEMENTARY INFORMATION: On October 1, 2002, the Federal Aviation
Administration (FAA) issued emergency airworthiness directive (AD)
2002-20-51 that applies to Textron Lycoming AEIO-540, IO-540, LTIO-540,
O-540, and TIO-540 series reciprocating engines. AD 2002-20-51 requires
replacing zinc-plated cranshaft gear retaining bolts, part number (P/N)
STD-2209, with new cadmium-plated bolts P/N STD-2209. That action was
prompted by two recent failures of zinc-plated crankshaft gear
retaining bolts with one failure resulting in two fatalities. Since
1999, when the FAA issued AD 99-03-05 that requires the removal of
zinc-plated bolts from O-540-F series engines installed on Robinson R44
helicopters, five failures have occurred on fixed-wing airplanes. That
condition, if not corrected, could result in loss of all engine power
and possible forced landing.
Since that AD was issued, the manufacturer has introduced gear bolt
replacement kit, 05K19987, for use in replacing suspect bolts, and has
determined that some of the bolts that were recalled on November 10,
1998, were not returned to T/L and may have been installed into engines
after November 10, 1998. Based on that determination, the manufacturer
has issued Lycoming Service Bulletin (SB) No. 554, Supplement 3, to
increase the time period during which these bolts might have been
installed in affected engines and to have maintenance facilities return
to T/L, all crankshaft gear retaining bolts, part number STD-2209,
except those that are included as
[[Page 68933]]
part of a gear bolt replacement kit, 05K19987.
Manufacturer's Service Information
The FAA has reviewed and approved the technical contents of
Lycoming SB No. 554, dated September 30, 2002, that describes
procedures for replacing the existing crankshaft gear retaining bolt.
FAA's Determination of an Unsafe Condition and Required Actions
Since the unsafe condition described is likely to exist or develop
on other Textron Lycoming AEIO-540, IO-540, O-540, LTIO-540, and TIO-
540 series reciprocating engines of the same type design, the FAA
issued emergency AD 2002-20-51 to prevent loss of all engine power and
possible forced landing. This AD supersedes AD 2002-20-51, and requires
replacing the crankshaft gear retaining bolt:
[sbull] Before further flight on engines that have been overhauled
or have had the gear retaining bolt replaced between November 27, 1996
and November 10, 1998, and that have not complied with emergency AD
2002-20-51 by using a bolt from the gear bolt replacement kit,
05K19987, and
[sbull] Within 10 hours time-in-service (TIS) or 7 days after the
effective date of this AD, on engines that have complied with AD 2002-
20-51, but did not install a bolt from gear bolt replacement kit,
05K19987, and
[sbull] Within 10 hours time-in-service (TIS) or 7 days after the
efective date of this AD, on engines that have been overhauled in the
field, that have had the gear retaining bolt replaced in the field
between November 10, 1998, and the effective date of this AD, or have
been repaired by Lycoming between November 27, 1996 and November 10,
1998.
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 October 1, 2002, to all
known U.S. owners and operators of Textron Lycoming AEIO-540, IO-540,
O-540, LTIO-540, and TIO-540 series reciprocating engines. These
conditions still exist. Since a situation exists that requires the
immediate adoption of this regulation, it is found that notice and
opportunity for prior public comment hereon are impracticable, and that
good cause exists for making this amendment effective in less than 30
days.
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-31-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:
[sbull] 2002-23-06 Textron Lycoming: Amendment 39-12950. Docket
2002-NE-31-AD. Supersedes emergency AD 2002-20-51.
Applicability: This airworthiness directive (AD) is applicable
to all Textron Lycoming AEIO-540, IO-540, LTIO-540, O-540, and TIO-
540 series reciprocating engines with crankshaft gear retaining
bolts, part number (P/N) STD-2209 installed, except O-540-F series
engines to which AD 99-03-05 applies and on which the bolt has not
been subsequently replaced with a bolt other than one included in
gear bolt replacement kit 05K19987, and engines with single-drive
dual magnetos. These engines are installed on, but not limited to
the following aircraft:
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Aero Commander. (500), (500-B), (500-E), (500-U)
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Aero Mercantil. Gavilan.
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Aerofab. Renegade 250.
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Bellanca Aircraft. Aries T-250
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Britten-Norman. (BN-2).
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Cessna Aircraft. Skylane C-182, Stationair C-206, Turbo Skylane T182T,
Turbo Stationair T-206
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Christen. Pitts (S-2S), (S-2B).
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Commander Aircraft. 114TC, 114B
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[[Page 68934]]
DeHavilland. (DH-114-2X)
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Dornier. (DO-28-B1)
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Evangel-Air.
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Extra-Flugzeugbau. Extra 300.
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Found Bros. (FBA-2C), Centennial (100)
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Gippsland. GA-200.
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Helio. Military (H-250).
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King Engineering. Angel.
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Maule. MT-7-260, M-7-260, MX-7-235, MT-7-235, M7-235, Star
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Rocket (MX-7-235), Super Rocket (M-6-235), Super Std. Rocket (M-7-235).
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Mooney Aircraft. ``TLS'' M20M.
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Moravan. Zlin-50L
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Pilatus Britten-Norman. Islander (BN-2A-26), Islander (BN-2A-27),
Islander II (BN-2B-26), Islander (BN-2A-21), Trislander (BN-2A-Mark III-
2), Islander (BN-2B).
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Piper Aircraft. 700P Aerostar, Aerostar 600A, Aerostar 601B, Aerostar
601P, Apache (PA-23 ``235''), Aztec (PA-23 ``250''), Aztec (PA-23
``250''), Comanche (PA-24 ``250''), Comanche (PA-24 ``260''), Aztec F,
Aztec C (PA-23 ``250''), Cherokee (PA-24 ``250''), Cherokee (PA-28
``235''), Cherokee Six (PA-32 ``260''), Cherokee Six (PA-32-300).
``LANCE'', Comanche (PA-24 ``150''), Comanche (PA-24 ``250''), Comanche
(PA-24), Comanche (PA-24 ``260''), Comanche 260, Mirage (PA-46-350P),
Navajo (PA-31), Navajo (PA-31-300), Navy Aztec (PA-23 ``250''), Pawnee
(PA-24 ``235''), Pawnee (PA-25 ``260''), Saratoga (PA-32-300), Brave
300, Sequoia 602P, T-1020, T35, Turbo Aztec (PA-23-250), Turbo Saratoga
TC (PA-32-301T)
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S.O.C.A.T.A. Rallye 235CA., Rallye 235GT, Rallye 235C, TB-20
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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 (h) 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 loss of all engine power and possible forced landing,
do the following:
Engines That Have Complied With Emergency AD 2002-20-51
(a) For AEIO-540, LTIO-540, IO-540, O-540, and TIO-540 series
engines that have complied with emergency AD 2002-20-51 by
installing a bolt included in bolt replacement kit 05K19987, no
further action is required.
(b) For AEIO-540, LTIO-540, IO-540, O-540, and TIO-540 series
engines that have complied with emergency AD 2002-20-51 but did not
install a bolt included in bolt replacement kit 05K19987, within 10
hours time-in-service or 10 days after the effective date of this
AD, whichever is earlier, replace the crankshaft gear retaining bolt
with a new bolt included in gear bolt replacement kit, 05K19987,
supplied by Textron Lycoming. Information on replacing the retaining
bolt may be found in Lycoming SB No. 554, dated September 30, 2002.
Engines Listed by Serial Number (SN)
(c) For AEIO-540, LTIO-540, IO-540, O-540, and TIO-540 engines
with a single-drive dual magneto, and all O-540-F engines to which
AD 99-03-05 applies and on which the bolt has not been subsequently
replaced with a bolt other than one included in gear bolt
replacement kit 05K19987, including any O-540-F engines that are
listed by SN in Table 1 of Lycoming SB No. 554, dated September 30,
2002, no further action is required.
(d) Before further flight, for all other engines, replace the
crankshaft gear retaining bolt with a new bolt included in gear bolt
replacement kit, 05K19987, supplied by Textron Lycoming if your
engine SN is listed in Table 1 of Lycoming SB No. 554, dated
September 30, 2002. Information on replacing the retaining bolt may
be found in Lycoming SB No. 554, dated September 30, 2002.
Bolts That Have Been Replaced During Field Maintenance or Field
Overhaul
(e) Replace the crankshaft gear retaining bolt with a new bolt
supplied as part of gear bolt replacement kit 05K19987, supplied by
Textron Lycoming, within 10 hours time-in-service or 7 days after
the effective date of this AD, whichever is earlier,if:
(1) The bolt on your O-540-F series was replaced after
compliance with AD 99-03-05 with a bolt that was not included in
bolt replacement kit 05K19987. Information on replacing the
retaining bolt may be found in Lycoming SB No. 554, dated September
30, 2002.
(2) The bolt on your AEIO, LTIO, IO, O, or TIO-540 series engine
was replaced during field maintenance or field overhaul between
November 27, 1996 and the effective date of this AD, or if your
engine was repaired between November 27, 1996 and November 10, 1998,
at Lycoming. Information on replacing the retaining bolt may be
found in Lycoming SB No. 554, dated September 30, 2002.
Recording Gear Bolt Replacement Kit Number
(f) After the effective date of this AD, record the number of
the gear bolt replacement kit, 05K19987, in the engine records when
recording compliance with this AD.
Prohibition Against Installing Gear Retaining Bolts P/N STD-2209
(g) After the effective date of this AD, do not install any
crankshaft gear retaining bolt, P/N STD-2209, except one that is
included in a Lycoming gear bolt replacement kit, 05K19987, onto any
engine listed in this AD.
Alternative Methods of Compliance
(h) 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 (NYACO). Operators must submit their requests through an
appropriate FAA Maintenance Inspector, who may add comments and then
send it to the Manager, NYACO.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the NYACO.
Special Flight Permits
(i) 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 aircraft to a location where
the requirements of this AD can be done.
Documents That Have Been Incorporated by Reference
(j) Engine serial numbers are listed in Table 1 of Lycoming
Service Bulletin No. 554, dated September 30, 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, a Textron Company, 652
Oliver Street, Williamsport, PA 17701; telephone (570) 323-6181.
This information may also be obtained electronically on ``http://www.lycoming.textron.com''. 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
(k) This amendment becomes effective November 19, 2002.
Issued in Burlington, Massachusetts, on November 8, 2002.
Francis A Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 02-29003 Filed 11-13-02; 8:45 am]
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