Airworthiness Directives; Honeywell International Inc. TPE331 Series Turboprop, and TSE331-3U Model Turboshaft Engines, 38054-38059 [06-5929]
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38054
Federal Register / Vol. 71, No. 128 / Wednesday, July 5, 2006 / Rules and Regulations
comments on the NPRM or on the
determination of the cost to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed.
Costs of Compliance
There are about 250 airplanes of the
affected design in the worldwide fleet.
This AD will affect about 152 airplanes
of U.S. registry. The required actions
will take about 9 work hours per
airplane, at an average labor rate of $80
per work hour. Required parts will cost
about $2,385 per airplane. Based on
these figures, the estimated cost of this
AD for U.S. operators is $471,960, or
$3,105 per airplane.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
jlentini on PROD1PC65 with RULES
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
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.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) 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.
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19:52 Jul 03, 2006
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We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
2006–13–18 McDonnell Douglas:
Amendment 39–14671. Docket No.
FAA–2006–24430; Directorate Identifier
2006–NM–048–AD.
Effective Date
(a) This AD becomes effective August 9,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to McDonnell Douglas
Model DC–9–31, DC–9–32, DC–9–32F, DC–
9–33F, DC–9–34, DC–9–34F, DC–9–41, and
DC–9–51 airplanes, certificated in any
category; as identified in Boeing Service
Bulletin DC9–28–214, dated December 16,
2005.
Unsafe Condition
(d) This AD results from fuel system
reviews conducted by the manufacturer. We
are issuing this AD to prevent point-contact
arcing or filament heating in the fuel tank,
which, in the event of a short or ground fault
inside the fuel tank, could result in a fuel
tank explosion and consequent loss of the
airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Installation
(f) Within 60 months after the effective
date of this AD, install a bonding jumper
from the boost pump volute to the fuel tank
structure, and do all applicable related
investigative and corrective actions before
further flight; by doing all the actions
specified in the Accomplishment
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Instructions of Boeing Service Bulletin DC9–
28–214, dated December 16, 2005.
Alternative Methods of Compliance
(AMOCs)
(g)(1) The Manager, Los Angeles Aircraft
Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Material Incorporated by Reference
(h) You must use Boeing Service Bulletin
DC9–28–214, dated December 16, 2005, to
perform the actions that are required by this
AD, unless the AD specifies otherwise. The
Director of the Federal Register approved the
incorporation by reference of this document
in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Contact Boeing Commercial
Airplanes, Long Beach Division, 3855
Lakewood Boulevard, Long Beach, California
90846, Attention: Data and Service
Management, Dept. C1–L5A (D800–0024), for
a copy of this service information. You may
review copies at the Docket Management
Facility, U.S. Department of Transportation,
400 Seventh Street SW., Room PL–401,
Nassif Building, Washington, DC; on the
Internet at https://dms.dot.gov; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at the NARA,
call (202) 741–6030, or go to https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on June 22,
2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 06–5871 Filed 7–3–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23704; Directorate
Identifier 2006–NE–02–AD; Amendment 39–
14674; AD 2006–14–03]
RIN 2120–AA64
Airworthiness Directives; Honeywell
International Inc. TPE331 Series
Turboprop, and TSE331–3U Model
Turboshaft Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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Federal Register / Vol. 71, No. 128 / Wednesday, July 5, 2006 / Rules and Regulations
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Honeywell International Inc. TPE331
series turboprop, and TSE331–3U model
turboshaft engines. This AD requires
implementing a new flight cycle
counting method for first, second, and
third-stage turbine rotors used in aircraft
that make multiple takeoffs and
landings without an engine shutdown,
and removing turbine rotors from
service that have reached or exceeded
their cycle life limits. This new flight
cycle counting method requires
determining total equivalent cycles
accrued. This AD results from several
reports of uncontained turbine rotor
separation on engines used in specialuse operations. We are issuing this AD
to prevent uncontained failure of the
turbine rotor due to low-cycle-fatigue
(LCF), and damage to the aircraft.
DATES: This AD becomes effective
August 9, 2006. The Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in the regulations as
of August 9, 2006.
ADDRESSES: You can get the service
information identified in this AD from
Honeywell Engines, Systems & Services,
Technical Data Distribution, M/S 2101–
201, P.O. Box 52170, Phoenix, AZ
85072–2170; telephone: (602) 365–2493
(General Aviation); (602) 365–5535
(Commercial); fax: (602) 365–5577
(General Aviation and Commercial).
You may examine the AD docket on
the Internet at https://dms.dot.gov or in
Room PL–401 on the plaza level of the
Nassif Building, 400 Seventh Street,
SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Joseph Costa, Aerospace Engineer, Los
Angeles Aircraft Certification Office,
FAA, Transport Airplane Directorate,
3960 Paramount Blvd., Lakewood, CA
90712–4137; telephone (562) 627–5246;
fax (562) 627–5210.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
a proposed AD. The proposed AD
applies to certain Honeywell
International Inc. TPE331 series
turboprop, and TSE331–3U model
turboshaft engines. We published the
proposed AD in the Federal Register on
February 23, 2006 (71 FR 9281). That
action proposed to require
implementing a new flight cycle
counting method for first, second, and
third-stage turbine rotors used in aircraft
that make multiple takeoffs and
landings without an engine shutdown,
and removing turbine rotors from
service that have reached or exceeded
their cycle life limits. This new flight
cycle counting method requires
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determining total equivalent cycles
accrued.
Examining the AD Docket
You may examine the docket that
contains the AD, any comments
received, and any final disposition in
person at the Docket Management
Facility Docket Office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The Docket
Office (telephone (800) 647–5227) is
located on the plaza level of the
Department of Transportation Nassif
Building at the street address stated in
ADDRESSES. Comments will be available
in the AD docket shortly after the DMS
receives them.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Suggestion To Delete Phrase ‘‘To
Ground Idle’’
One commenter suggests that in the
Discussion paragraph of the proposed
AD, we delete the phrase ‘‘to ground
idle’’. Doing this would reconcile the
Discussion paragraph with the
Definition paragraph (i) in the
compliance section, because touch-andgo maneuvers require the logging of
partial cycles. A touch-and-go maneuver
is a landing and takeoff without
shutdown.
We partially agree. The damage
fraction for a minor cycle identified in
the Honeywell Alert Service Bulletins is
based on landings to normal ground-idle
engine speed reductions without an
engine shutdown. Any engine
operation, such as a touch-and-go
maneuver with an engine speed
reduction to ground idle during touchdown, counts as a minor cycle. Engine
speed reductions to ground idle during
landing are an important factor in
determining the counting of a minor
cycle and, therefore, must be included
in the definition. The AD does not
repeat the proposed AD Discussion
paragraph. We agree that the wording in
our NPRM could be clearer. Therefore,
we changed Definition paragraph (i), to
include major and minor cycles, and
paragraph (o), to state that a minor
cycle, which occurs within a major
cycle, is an additional landing with an
engine speed reduction to ground idle
with no engine shutdown, followed by
a takeoff.
Request To Change Compliance Section
Paragraph (f)(1)(ii)
One commenter requests that we
change compliance section paragraph
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38055
(f)(1)(ii) from ‘‘If you are unable to
determine equivalent cycles for prior
special-use operations, you must use a
onetime takeoff-to-engine shutdown
ratio of six to estimate prior special-use
equivalent cycles for each turbine rotor’’
to ‘‘For turbine rotors known to have
prior special use operation, if you are
unable to determine equivalent cycles
for prior special-use operations, you
must use a onetime takeoff-to-engine
shutdown ratio of six to estimate prior
special-use equivalent cycles for each
turbine rotor.’’ The commenter feels that
this would clarify the phrase ‘‘unable to
determine’’ because as-written it could
be construed to mean that a rotor had
special use operation, but exact minorto-major cycle count cannot be
determined.
We partially agree. We agree with the
commenter’s application of the phrase
‘‘unable to determine’’ but we do not
agree that paragraph (f)(1)(ii) should be
changed. That paragraph must be read
in context with paragraph (f), which
clearly states ‘‘For turbine rotors
installed before the effective date of this
AD, and currently or previously used in
special-use operations:’’ However, we
did clarify paragraph (f)(1)(ii) to add the
reason why the operator or owner
would be unable to determine
equivalent cycles.
Request To Change the Phrase ‘‘Used
Turbine Rotors’’ in Compliance
Paragraph (f)
One commenter requests that we
change the phrase ‘‘used turbine rotors’’
in compliance paragraph (f) to ‘‘turbine
rotors’’ as these rotors may have had
zero cycles-since-new at installation.
We agree. The compliance action is the
same for new or used turbine rotors
installed before the effective date of the
AD. We made that change in the AD.
Request To Add a Step to Compliance
Paragraphs (f) and (g)
One commenter requests that we add
a step to compliance paragraphs (f) and
(g) to include the new counting method,
which is also referenced in paragraph
(h)(1) of the compliance section. The
commenter states that this counting
method should be used after
determining equivalent cycles, whether
the turbine rotor is new or used.
We partially agree. We agree that
operators and maintenance personnel
use the new counting method of
counting major and minor cycles when
accrued for new and used turbine rotors
after the initial assessment from the
Table 1 turbine removal schedules in
the Honeywell ASBs. This schedule
requires retiring the turbine rotors
within a specified number of equivalent
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Federal Register / Vol. 71, No. 128 / Wednesday, July 5, 2006 / Rules and Regulations
cycles, which infers that the owner or
operator use the new counting method
with minor and major cycles. We
changed compliance section paragraph
(f)(1)(ii) to read ‘‘If you are unable to
determine equivalent cycles for prior
special-use operations due to the
absence of actual data regarding the
number of takeoffs and landings per
major cycle, you must use a onetime
ratio of six takeoffs and landings per
major cycle to estimate prior special-use
equivalent cycles for each turbine
rotor’’. Also, for clarification, we
changed compliance section paragraph
(h)(1) to read ‘‘Use the new counting
method by counting and recording
minor and major cycles when accrued,
and determine equivalent cycles by the
method described in paragraph (f)(1)(i)
and (f)(1)(iii) of this AD’’.
In preparing the response to this
commenter, we decided that proposed
paragraphs (h) and (h)(2) could be
clearer. Therefore, we changed
compliance section paragraph (h) to
read ‘‘For all new (zero cycles) turbine
rotors installed on or after the effective
date of this AD used in special-use
operations:’’ and paragraph (h)(2) to
read ‘‘Using the ratio of six takeoffs and
landings per major cycle for unknown
cycle history, as referenced in paragraph
(f)(1)(ii) of this AD, is not permitted’’.
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Comment That Previous Method of
Counting Cycles Is Acceptable
One commenter states that the
previous method of counting cycles is
acceptable and that major and minor
counting is unnecessary. The
commenter cites their ‘‘lower than redline’’ engine operation temperatures are
an additional safety margin (excluding
temperatures during startups and
shutdowns).
We do not agree. The new counting
method is necessary to preclude fatigue
damage of turbine rotors and is
appropriate for most operations when
considering engine operation
temperatures and rotor speeds. We did
not change the AD based on this
comment.
Suggestion That AD Action Does Not
Target the Problem
Two commenters suggest that the AD
action does not target the problem of
why most turbine rotors fail. The
commenters state that the proposed AD
should be withdrawn.
We do not agree. The AD addresses
our safety concern that use of the
TPE331 engine beyond its original
certified intended assumption of one
cycle for each flight threatens safe
operations. We understand that the AD
does not address all causes for turbine
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rotor failure. We are investigating other
turbine rotor features that may cause
failures, and we may consider future AD
action. We did not change the AD.
Ten Percent Estimate Seems Low
One commenter states that the
proposed AD estimate of ten percent of
affected engines are used on MU–2B
airplanes, seems low, and that the
special-use industry such as skydiving,
agriculture, and some cargo, is a large
industry.
We do not agree. Ten percent of the
affected engines being used on MU–2B
airplanes, is our best estimate based on
FAA experience with special-use
operators and the MU–2 fleet size.
Root of the Problem Seems To Be in
Manufacturing
One commenter states that the root of
the problem seems to be in
manufacturing. The commenter asks if
Honeywell International Inc. will
provide a turbine rotor that can
withstand low-cycle-fatigue.
We do not agree. We investigated the
production and manufacturing of the
affected turbine rotors and found no
anomalies. Therefore, we concluded
that the existing turbine rotors were
manufactured to type design. However,
we may consider future AD action if we
find such action necessary.
Conclusion
We have carefully reviewed the
available data, including the comments
received, and determined that air safety
and the public interest require adopting
the AD with the changes described
previously. We have determined that
these changes will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Costs of Compliance
We estimate that this AD will affect
200 TPE331 series turboprop, and
TSE331–3U model turboshaft engines
installed on airplanes and helicopters of
U.S. registry. We also estimate that it
will take about two work-hours per
engine to perform the total equivalent
cycles determination and recording. We
also estimate that to replace a turbine
rotor will take 40 work-hours per engine
when done at an unscheduled
maintenance interval. We also estimate
that 38 rotors will be replaced at
unscheduled maintenance intervals. We
estimate the average labor rate to be $65
per work-hour. Required parts will cost
about $20,000 per engine. The costs
associated with this AD are dependent
on the engine mission cycle. Operators
accruing many minor and major cycles
might replace first and second stage
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turbine rotors every two years. For the
purpose of this AD, we estimate the
costs for an eight-year period with
moderate usage to be 10 minor cycles
each flight and 200 flights each year,
and the effective use of the first and
second turbine rotors to be equivalent to
2,600 cycles. Based on these figures, we
estimate the total cost to U.S. operators
to be $9,350,630.
The Agency is committed to updating
the aviation community of expected
costs associated with the MU–2B series
airplane safety evaluation conducted in
2005. As a result of that commitment,
the accumulating expected costs of all
ADs related to the MU–2B series
airplane safety evaluation may be found
at the following Web site: https://www.
faa.gov/aircraft/air_cert/
design_approvals/small_airplanes/cos/
mu2_foia_reading_library/.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
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.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
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Federal Register / Vol. 71, No. 128 / Wednesday, July 5, 2006 / Rules and Regulations
under the criteria of the Regulatory
Flexibility Act.
We prepared a summary of the costs
to comply with this AD and placed it in
the AD Docket. You may get a copy of
this summary at the address listed
under ADDRESSES.
List of Subjects in 14 CFR Part 39
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
I
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends 14 CFR part 39 as follows:
I
2006–14–03 Honeywell International Inc.
(formerly AlliedSignal Inc., Garrett
Engine Division; Garrett Turbine Engine
Company; and AiResearch
Manufacturing Company of Arizona):
Amendment 39–14674. Docket No.
FAA–2006–23704; Directorate Identifier
2006–NE–02–AD.
Manufacturer
38057
Effective Date
(a) This airworthiness directive (AD)
becomes effective August 9, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Honeywell
International Inc. TPE331–1, –1U, –1UA, –2,
–2UA, –3U, –3UW, –3W, –5, –5A, –5AB,
–5B, –5U, –6, –6A, –6U, –8, –8A, –9, –9U,
–10, –10A, –10AV, –10B, –10G, –10GP,
–10GR, –10GT, –10J, –10N, –10P, –10R,
–10T, –10U, –10UA, –10UF, –10UG,
–10UGR, –10UJ, –10UK, –10UR, –11U,
–11UA, –12, –12B, –12JR, –12UA, –12UAR,
–12UER, and –12UHR series turboprop and
TSE331–3U model turboshaft engines. These
engines are installed on, but not limited to,
the following aircraft:
Airplane model
Aero Planes, LLC (formerly McKinnon Enterprises) ................................
Allied AG Cat Productions (formerly Schweizer) .....................................
Ayres .........................................................................................................
British Aerospace Ltd (formerly Jetstream) ..............................................
Cessna Aircraft Company ........................................................................
Construcciones Aeronauticas, s.a. (CASA) .............................................
DeHavilland ..............................................................................................
Dornier ......................................................................................................
Fairchild ....................................................................................................
Grumman American .................................................................................
Mitsubishi ..................................................................................................
Pilatus .......................................................................................................
Polskie Zaklady Lotnicze Spolka (formerly Wytwornia Sprzetu
Komunikacyjnego).
Prop-Jets, Inc. ..........................................................................................
Raytheon Aircraft (formerly Beech) ..........................................................
G–21G.
G–164 series.
S–2R series.
3201 series, and HP.137 Jetstream MK.1.
441 Conquest.
C–212 series.
DH104 series 7AXC (Dove).
228 series.
SA226 AND SA227 series (Swearingen Merlin and Metro series).
G–164 series.
MU–2B series (MU–2 series).
PC–6 series (Fairchild Porter and Peacemaker).
PZL M18, PZL M18A, PZL M18B.
Shorts Brothers and Harland, Ltd. ...........................................................
Thrush (Rockwell Commander) ................................................................
Twin Commander (Jetprop Commander) .................................................
400.
C45G, TC–45G, C–45H, TC–45H, TC–45J, G18S, E18S–9700, D18S,
D18C, H18, RC–45J, JRB–6, UC–45J, 3N, 3NM, 3TM, B100, C90,
and E90.
SC7 (Skyvan) series.
S–2R.
680 and 690 series.
Manufacturer
Helicopter Model
Sikorsky ....................................................................................................
Unsafe Condition
(d) This AD results from several reports of
uncontained turbine rotor separation on
engines used in special-use operations. We
are issuing this AD to prevent uncontained
failure of the turbine rotor due to low-cyclefatigue (LCF), and damage to the aircraft.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
S–55 series (Helitec Corp. S55T).
the compliance times specified unless the
actions have already been done.
Turbine Rotors Installed Before the Effective
Date of This AD
(f) For turbine rotors installed before the
effective date of this AD, and currently or
previously used in special-use operations:
(1) Within 100 major cycles-in-service after
the effective date of this AD, or upon removal
of the turbine rotor(s) from the engine,
whichever occurs first, do the following:
(i) Determine the total equivalent cycles
accrued for turbine rotors. Use paragraph
2.A. of the Accomplishment Instructions of
the applicable Honeywell Alert Service
Bulletin (ASB) for your model engines listed
in the following Table A, to make the
determination.
TABLE A.—HONEYWELL ASBS FOR DETERMINING TOTAL EQUIVALENT CYCLES
jlentini on PROD1PC65 with RULES
For engines
Use ASB No.
(A) TPE331–1 through ¥6 series and TSE331–3U
model.
(B) TPE331–8 through –9 series ..................................
(C) TPE331–10 through–11 series ...............................
(D) TPE331–12 series ...................................................
TPE331–A72–2111, dated November 12, 2002 .........
Use ASB Table 1.
TPE331–A72–2123, dated February 8, 2006 .............
TPE331–A72–2130, dated September 27, 2005 ........
TPE331–A72–2131, dated September 27, 2005 ........
Use ASB table 1.
Use ASB Table 1.
Use ASB Table 1.
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(ii) If you are unable to determine
equivalent cycles for prior special-use
operations due to the absence of actual data
regarding the number of takeoffs and
landings per major cycle, you must use a
onetime ratio of six takeoffs and landings per
major cycle to estimate prior special-use
equivalent cycles for each turbine rotor.
(iii) For each turbine rotor affected on the
Life Limited Part Log Card, record the total
equivalent cycles accrued, as determined in
paragraphs (f)(1)(i) and (f)(1)(ii) of this AD, by
complying with the recording requirements
for your model engine listed in the following
Table B:
TABLE B.—SERVICE BULLETINS (SBS) FOR RECORDING TOTAL EQUIVALENT CYCLES
For engines
Record using
(A) TPE331–1 through –6 series and TSE331–3U model ......................
Honeywell SB No. TPE/TSE331–72–0019, Revision 22, dated May 16,
2001.
AlliedSignal SB No. TPE331–72–0117, Revision 11, dated November
13, 1997.
Honeywell SB No. TPE331–72–0180, Revision 31, dated November 7,
2003.
Honeywell SB No. TPE331–72–0476, Revision 27, dated September
17, 2003.
(B) TPE331–8 through –9 series .............................................................
(C) TPE331–10 through –11 series .........................................................
(D) TPE331–12 series ..............................................................................
(2) Remove from service turbine rotors
affected by paragraph (f) of this AD using the
applicable Turbine Rotor Removal Schedule
in Table A of this AD, or, within nine months
after the effective date of this AD, whichever
occurs later.
Used Turbine Rotors Installed On or After
the Effective Date of this AD
(g) For used turbine rotors installed on or
after the effective date of this AD, and
currently or previously used in special-use
operations:
(1) Before further flight, determine and
record total equivalent cycles using
paragraphs (f)(1)(i) through (f)(1)(iii) of this
AD.
(2) Remove from service, turbine rotors
affected by paragraph (g) of this AD using the
applicable Turbine Rotor Removal Schedule
in Table A of this AD.
New (Zero Cycles) Turbine Rotors Installed
On or After the Effective Date of This AD
(h) For all new (zero cycles) turbine rotors
installed on or after the effective date of this
AD used in special-use operations:
(1) Use the new counting method by
counting and recording minor and major
cycles when accrued, and determine
equivalent cycles by the method described in
paragraphs (f)(1)(i) and (f)(1)(iii) of this AD.
(2) Using the ratio of six takeoffs and
landings per major cycle for unknown cycle
history, as referenced in paragraph (f)(1)(ii) of
this AD, is not permitted.
Definitions
(i) An engine used in special-use
operations is defined as an engine that
accrues major and minor cycles and is
installed in an aircraft that makes multiple
takeoffs and landings without engine
shutdown.
(j) Total equivalent cycles, is that
combination of major and minor cycles as
specified in the Honeywell ASBs listed in
Table A of this AD.
(k) Total equivalent cycle life limits listed
in the ASBs, are the cycle life limits specified
in the SBs listed in Table B of this AD.
(l) The ‘‘recording of total equivalent cycles
on the Life Limited Part Log Card’’ is that
same procedure specified for ‘‘accumulated
cycles’’ or ‘‘total cycles’’ in the SBs listed in
Table B of this AD.
(m) ‘‘Turbine rotors’’ include first, second,
and third stage seal plates, air seals, rotor
disks, wheels, and assemblies, and are parts
that have part numbers specified in the ASBs
listed in Table A of this AD.
(n) A major cycle is an engine start, takeoff,
landing, and shutdown.
(o) A minor cycle, which occurs within a
major cycle, is an additional landing with an
engine speed reduction to ground idle with
no engine shutdown followed by a takeoff.
(p) A ‘‘used turbine rotor’’ is a turbine rotor
whose cycles-since-new are more than zero.
Alternative Methods of Compliance
(q) The Manager, Los Angeles Aircraft
Certification Office, has the authority to
approve alternative methods of compliance
for this AD if requested using the procedures
found in 14 CFR 39.19.
Material Incorporated by Reference
(r) You must use the service information
specified in Table C of this AD to perform the
actions required by this AD. The Director of
the Federal Register approved the
incorporation by reference of the documents
listed in Table C of this AD in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Honeywell Engines, Systems &
Services, Technical Data Distribution, M/S
2101–201, P.O. Box 52170, Phoenix, AZ
85072–2170; telephone: (602) 365–2493
(General Aviation); (602) 365–5535
(Commercial); fax: (602) 365–5577 (General
Aviation and Commercial) for a copy of this
service information. You may review copies
at the FAA, New England Region, Office of
the Regional Counsel, 12 New England
Executive Park, Burlington, MA; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
TABLE C.—INCORPORATION BY REFERENCE
Service Bulletin (SB)
Page
Honeywell SB No. TPE/TSE331–72–0019 ....................................................................
Total Pages: 16
AlliedSignal SB No. TPE331–72–0117 ..........................................................................
Total Pages: 10
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Honeywell SB No. TPE331–72–0180 ............................................................................
Total Pages: 54
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2–11
12
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2
3–10
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2–3
4–5
6–7
8–13
14
15–17
18
19
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9
11
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Date
May 16, 2001.
March 3, 2000.
May 16, 2001.
March 3, 2000.
November 13, 1997.
May 24, 1995.
November 13, 1997.
November 7, 2003.
August 23, 2002.
November 7, 2003.
August 23, 2002.
November 7, 2003.
February 23, 2001.
November 7, 2003.
February 23, 2001.
November 7, 2003.
38059
Federal Register / Vol. 71, No. 128 / Wednesday, July 5, 2006 / Rules and Regulations
TABLE C.—INCORPORATION BY REFERENCE—Continued
Service Bulletin (SB)
Page
20
21
22–24
25
26
27–54
1–2
3
4
5
6
7–14
15
16–22
23–27
28–32
33
34
35
36
37–41
42
43
44
45
46
Honeywell SB No. TPE331–72–0476 ............................................................................
Total pages: 46
Alert Service Bulletin (ASB)
Honeywell ASB No.
Total Pages: 12
Honeywell ASB No.
Total Pages: 12
Honeywell ASB No.
Total Pages: 16
Honeywell ASB No.
Total Pages: 14
Page
Revision
August 23, 2002.
November 7, 2003.
August 23, 2002.
November 7, 2003.
August 23, 2002.
November 7, 2003.
September 17, 2003.
May 24, 2002.
September 17, 2003.
May 24, 2002.
September 17, 2003.
May 24, 2002.
July 26, 2002.
May 24, 2002.
September 17, 2003.
May 24, 2002.
July 26, 2002.
May 24, 2002.
September 17, 2003.
May 24, 2002.
September 17, 2003.
May 24, 2002.
September 17, 2003.
May 24, 2002.
September 17, 2003.
May 24, 2002.
Date
ALL
Original
November 12, 2002.
TPE331–A72–2123 ........................................................................
ALL
Original
February 8, 2006.
TPE331–A72–2130 ........................................................................
ALL
Original
September 27, 2005.
TPE331–A72–2131 ........................................................................
ALL
Original
September 27, 2005.
DEPARTMENT OF TRANSPORTATION
Francis A. Favara,
Federal Aviation Administration
Manager, Engine and Propeller Directorate,
Aircraft Certification Service.
[FR Doc. 06–5929 Filed 7–3–06; 8:45 am]
14 CFR Part 39
BILLING CODE 4910–13–P
[Docket No. FAA–2005–22524; Directorate
Identifier 2005–NM–135–AD; Amendment
39–14672; AD 2006–14–01]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A330–200, A330–300, A340–200, and
A340–300 Series Airplanes, and Model
A340–541 and A340–642 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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Date
TPE331–A72–2111 ........................................................................
Issued in Burlington, Massachusetts, on
June 26, 2006.
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Model A330–200, A330–300,
A340–200, and A340–300 series
airplanes, and Model A340–541 and
A340–642 airplanes. This AD requires
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inspecting to determine if certain
emergency escape slides/slide rafts
(referred to as slide/rafts) are installed
in certain crew/passenger doors; and, if
so, performing a one-time inspection to
determine if the electrical harnesses of
the slide/rafts are properly routed, and
rerouting the harnesses if necessary.
This AD results from report that a slide/
raft failed to deploy properly during a
deployment test. We are issuing this AD
to detect and correct improper routing
of the electrical harnesses of certain
slide/rafts, which could prevent proper
deployment of the slide/rafts and delay
evacuation of passengers and flightcrew
during an emergency.
DATES: This AD becomes effective
August 9, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of August 9, 2006.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
E:\FR\FM\05JYR1.SGM
05JYR1
]]>Agencies
[Federal Register Volume 71, Number 128 (Wednesday, July 5, 2006)]
[Rules and Regulations]
[Pages 38054-38059]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-5929]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23704; Directorate Identifier 2006-NE-02-AD;
Amendment 39-14674; AD 2006-14-03]
RIN 2120-AA64
Airworthiness Directives; Honeywell International Inc. TPE331
Series Turboprop, and TSE331-3U Model Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
[[Page 38055]]
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Honeywell International Inc. TPE331 series turboprop, and
TSE331-3U model turboshaft engines. This AD requires implementing a new
flight cycle counting method for first, second, and third-stage turbine
rotors used in aircraft that make multiple takeoffs and landings
without an engine shutdown, and removing turbine rotors from service
that have reached or exceeded their cycle life limits. This new flight
cycle counting method requires determining total equivalent cycles
accrued. This AD results from several reports of uncontained turbine
rotor separation on engines used in special-use operations. We are
issuing this AD to prevent uncontained failure of the turbine rotor due
to low-cycle-fatigue (LCF), and damage to the aircraft.
DATES: This AD becomes effective August 9, 2006. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of August 9, 2006.
ADDRESSES: You can get the service information identified in this AD
from Honeywell Engines, Systems & Services, Technical Data
Distribution, M/S 2101-201, P.O. Box 52170, Phoenix, AZ 85072-2170;
telephone: (602) 365-2493 (General Aviation); (602) 365-5535
(Commercial); fax: (602) 365-5577 (General Aviation and Commercial).
You may examine the AD docket on the Internet at https://dms.dot.gov
or in Room PL-401 on the plaza level of the Nassif Building, 400
Seventh Street, SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Joseph Costa, Aerospace Engineer, Los
Angeles Aircraft Certification Office, FAA, Transport Airplane
Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; telephone
(562) 627-5246; fax (562) 627-5210.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed AD. The proposed AD applies to certain Honeywell
International Inc. TPE331 series turboprop, and TSE331-3U model
turboshaft engines. We published the proposed AD in the Federal
Register on February 23, 2006 (71 FR 9281). That action proposed to
require implementing a new flight cycle counting method for first,
second, and third-stage turbine rotors used in aircraft that make
multiple takeoffs and landings without an engine shutdown, and removing
turbine rotors from service that have reached or exceeded their cycle
life limits. This new flight cycle counting method requires determining
total equivalent cycles accrued.
Examining the AD Docket
You may examine the docket that contains the AD, any comments
received, and any final disposition in person at the Docket Management
Facility Docket Office between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone (800)
647-5227) is located on the plaza level of the Department of
Transportation Nassif Building at the street address stated in
ADDRESSES. Comments will be available in the AD docket shortly after
the DMS receives them.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Suggestion To Delete Phrase ``To Ground Idle''
One commenter suggests that in the Discussion paragraph of the
proposed AD, we delete the phrase ``to ground idle''. Doing this would
reconcile the Discussion paragraph with the Definition paragraph (i) in
the compliance section, because touch-and-go maneuvers require the
logging of partial cycles. A touch-and-go maneuver is a landing and
takeoff without shutdown.
We partially agree. The damage fraction for a minor cycle
identified in the Honeywell Alert Service Bulletins is based on
landings to normal ground-idle engine speed reductions without an
engine shutdown. Any engine operation, such as a touch-and-go maneuver
with an engine speed reduction to ground idle during touch-down, counts
as a minor cycle. Engine speed reductions to ground idle during landing
are an important factor in determining the counting of a minor cycle
and, therefore, must be included in the definition. The AD does not
repeat the proposed AD Discussion paragraph. We agree that the wording
in our NPRM could be clearer. Therefore, we changed Definition
paragraph (i), to include major and minor cycles, and paragraph (o), to
state that a minor cycle, which occurs within a major cycle, is an
additional landing with an engine speed reduction to ground idle with
no engine shutdown, followed by a takeoff.
Request To Change Compliance Section Paragraph (f)(1)(ii)
One commenter requests that we change compliance section paragraph
(f)(1)(ii) from ``If you are unable to determine equivalent cycles for
prior special-use operations, you must use a onetime takeoff-to-engine
shutdown ratio of six to estimate prior special-use equivalent cycles
for each turbine rotor'' to ``For turbine rotors known to have prior
special use operation, if you are unable to determine equivalent cycles
for prior special-use operations, you must use a onetime takeoff-to-
engine shutdown ratio of six to estimate prior special-use equivalent
cycles for each turbine rotor.'' The commenter feels that this would
clarify the phrase ``unable to determine'' because as-written it could
be construed to mean that a rotor had special use operation, but exact
minor-to-major cycle count cannot be determined.
We partially agree. We agree with the commenter's application of
the phrase ``unable to determine'' but we do not agree that paragraph
(f)(1)(ii) should be changed. That paragraph must be read in context
with paragraph (f), which clearly states ``For turbine rotors installed
before the effective date of this AD, and currently or previously used
in special-use operations:'' However, we did clarify paragraph
(f)(1)(ii) to add the reason why the operator or owner would be unable
to determine equivalent cycles.
Request To Change the Phrase ``Used Turbine Rotors'' in Compliance
Paragraph (f)
One commenter requests that we change the phrase ``used turbine
rotors'' in compliance paragraph (f) to ``turbine rotors'' as these
rotors may have had zero cycles-since-new at installation. We agree.
The compliance action is the same for new or used turbine rotors
installed before the effective date of the AD. We made that change in
the AD.
Request To Add a Step to Compliance Paragraphs (f) and (g)
One commenter requests that we add a step to compliance paragraphs
(f) and (g) to include the new counting method, which is also
referenced in paragraph (h)(1) of the compliance section. The commenter
states that this counting method should be used after determining
equivalent cycles, whether the turbine rotor is new or used.
We partially agree. We agree that operators and maintenance
personnel use the new counting method of counting major and minor
cycles when accrued for new and used turbine rotors after the initial
assessment from the Table 1 turbine removal schedules in the Honeywell
ASBs. This schedule requires retiring the turbine rotors within a
specified number of equivalent
[[Page 38056]]
cycles, which infers that the owner or operator use the new counting
method with minor and major cycles. We changed compliance section
paragraph (f)(1)(ii) to read ``If you are unable to determine
equivalent cycles for prior special-use operations due to the absence
of actual data regarding the number of takeoffs and landings per major
cycle, you must use a onetime ratio of six takeoffs and landings per
major cycle to estimate prior special-use equivalent cycles for each
turbine rotor''. Also, for clarification, we changed compliance section
paragraph (h)(1) to read ``Use the new counting method by counting and
recording minor and major cycles when accrued, and determine equivalent
cycles by the method described in paragraph (f)(1)(i) and (f)(1)(iii)
of this AD''.
In preparing the response to this commenter, we decided that
proposed paragraphs (h) and (h)(2) could be clearer. Therefore, we
changed compliance section paragraph (h) to read ``For all new (zero
cycles) turbine rotors installed on or after the effective date of this
AD used in special-use operations:'' and paragraph (h)(2) to read
``Using the ratio of six takeoffs and landings per major cycle for
unknown cycle history, as referenced in paragraph (f)(1)(ii) of this
AD, is not permitted''.
Comment That Previous Method of Counting Cycles Is Acceptable
One commenter states that the previous method of counting cycles is
acceptable and that major and minor counting is unnecessary. The
commenter cites their ``lower than red-line'' engine operation
temperatures are an additional safety margin (excluding temperatures
during startups and shutdowns).
We do not agree. The new counting method is necessary to preclude
fatigue damage of turbine rotors and is appropriate for most operations
when considering engine operation temperatures and rotor speeds. We did
not change the AD based on this comment.
Suggestion That AD Action Does Not Target the Problem
Two commenters suggest that the AD action does not target the
problem of why most turbine rotors fail. The commenters state that the
proposed AD should be withdrawn.
We do not agree. The AD addresses our safety concern that use of
the TPE331 engine beyond its original certified intended assumption of
one cycle for each flight threatens safe operations. We understand that
the AD does not address all causes for turbine rotor failure. We are
investigating other turbine rotor features that may cause failures, and
we may consider future AD action. We did not change the AD.
Ten Percent Estimate Seems Low
One commenter states that the proposed AD estimate of ten percent
of affected engines are used on MU-2B airplanes, seems low, and that
the special-use industry such as skydiving, agriculture, and some
cargo, is a large industry.
We do not agree. Ten percent of the affected engines being used on
MU-2B airplanes, is our best estimate based on FAA experience with
special-use operators and the MU-2 fleet size.
Root of the Problem Seems To Be in Manufacturing
One commenter states that the root of the problem seems to be in
manufacturing. The commenter asks if Honeywell International Inc. will
provide a turbine rotor that can withstand low-cycle-fatigue.
We do not agree. We investigated the production and manufacturing
of the affected turbine rotors and found no anomalies. Therefore, we
concluded that the existing turbine rotors were manufactured to type
design. However, we may consider future AD action if we find such
action necessary.
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
We estimate that this AD will affect 200 TPE331 series turboprop,
and TSE331-3U model turboshaft engines installed on airplanes and
helicopters of U.S. registry. We also estimate that it will take about
two work-hours per engine to perform the total equivalent cycles
determination and recording. We also estimate that to replace a turbine
rotor will take 40 work-hours per engine when done at an unscheduled
maintenance interval. We also estimate that 38 rotors will be replaced
at unscheduled maintenance intervals. We estimate the average labor
rate to be $65 per work-hour. Required parts will cost about $20,000
per engine. The costs associated with this AD are dependent on the
engine mission cycle. Operators accruing many minor and major cycles
might replace first and second stage turbine rotors every two years.
For the purpose of this AD, we estimate the costs for an eight-year
period with moderate usage to be 10 minor cycles each flight and 200
flights each year, and the effective use of the first and second
turbine rotors to be equivalent to 2,600 cycles. Based on these
figures, we estimate the total cost to U.S. operators to be $9,350,630.
The Agency is committed to updating the aviation community of
expected costs associated with the MU-2B series airplane safety
evaluation conducted in 2005. As a result of that commitment, the
accumulating expected costs of all ADs related to the MU-2B series
airplane safety evaluation may be found at the following Web site:
https://www.faa.gov/aircraft/air_cert/design_approvals/small_
airplanes/cos/mu2_foia_reading_library/.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.''Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will 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.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities
[[Page 38057]]
under the criteria of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary at the
address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
0
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration amends 14 CFR part
39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2006-14-03 Honeywell International Inc. (formerly AlliedSignal Inc.,
Garrett Engine Division; Garrett Turbine Engine Company; and
AiResearch Manufacturing Company of Arizona): Amendment 39-14674.
Docket No. FAA-2006-23704; Directorate Identifier 2006-NE-02-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective August
9, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Honeywell International Inc. TPE331-1, -
1U, -1UA, -2, -2UA, -3U, -3UW, -3W, -5, -5A, -5AB, -5B, -5U, -6, -
6A, -6U, -8, -8A, -9, -9U, -10, -10A, -10AV, -10B, -10G, -10GP, -
10GR, -10GT, -10J, -10N, -10P, -10R, -10T, -10U, -10UA, -10UF, -
10UG, -10UGR, -10UJ, -10UK, -10UR, -11U, -11UA, -12, -12B, -12JR, -
12UA, -12UAR, -12UER, and -12UHR series turboprop and TSE331-3U
model turboshaft engines. These engines are installed on, but not
limited to, the following aircraft:
------------------------------------------------------------------------
Manufacturer Airplane model
------------------------------------------------------------------------
Aero Planes, LLC (formerly McKinnon G-21G.
Enterprises).
Allied AG Cat Productions (formerly G-164 series.
Schweizer).
Ayres.................................. S-2R series.
British Aerospace Ltd (formerly 3201 series, and HP.137
Jetstream). Jetstream MK.1.
Cessna Aircraft Company................ 441 Conquest.
Construcciones Aeronauticas, s.a. C-212 series.
(CASA).
DeHavilland............................ DH104 series 7AXC (Dove).
Dornier................................ 228 series.
Fairchild.............................. SA226 AND SA227 series
(Swearingen Merlin and Metro
series).
Grumman American....................... G-164 series.
Mitsubishi............................. MU-2B series (MU-2 series).
Pilatus................................ PC-6 series (Fairchild Porter
and Peacemaker).
Polskie Zaklady Lotnicze Spolka PZL M18, PZL M18A, PZL M18B.
(formerly Wytwornia Sprzetu
Komunikacyjnego).
Prop-Jets, Inc......................... 400.
Raytheon Aircraft (formerly Beech)..... C45G, TC-45G, C-45H, TC-45H, TC-
45J, G18S, E18S-9700, D18S,
D18C, H18, RC-45J, JRB-6, UC-
45J, 3N, 3NM, 3TM, B100, C90,
and E90.
Shorts Brothers and Harland, Ltd....... SC7 (Skyvan) series.
Thrush (Rockwell Commander)............ S-2R.
Twin Commander (Jetprop Commander)..... 680 and 690 series.
------------------------------------------------------------------------
Manufacturer Helicopter Model
------------------------------------------------------------------------
Sikorsky............................... S-55 series (Helitec Corp.
S55T).
------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from several reports of uncontained turbine
rotor separation on engines used in special-use operations. We are
issuing this AD to prevent uncontained failure of the turbine rotor
due to low-cycle-fatigue (LCF), and damage to the aircraft.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
Turbine Rotors Installed Before the Effective Date of This AD
(f) For turbine rotors installed before the effective date of
this AD, and currently or previously used in special-use operations:
(1) Within 100 major cycles-in-service after the effective date
of this AD, or upon removal of the turbine rotor(s) from the engine,
whichever occurs first, do the following:
(i) Determine the total equivalent cycles accrued for turbine
rotors. Use paragraph 2.A. of the Accomplishment Instructions of the
applicable Honeywell Alert Service Bulletin (ASB) for your model
engines listed in the following Table A, to make the determination.
Table A.--Honeywell ASBs for Determining Total Equivalent Cycles
------------------------------------------------------------------------
Turbine rotor
For engines Use ASB No. removal schedule
------------------------------------------------------------------------
(A) TPE331-1 through -6 series TPE331-A72-2111, dated Use ASB Table 1.
and TSE331-3U model. November 12, 2002.
(B) TPE331-8 through -9 series TPE331-A72-2123, dated Use ASB table 1.
February 8, 2006.
(C) TPE331-10 through-11 TPE331-A72-2130, dated Use ASB Table 1.
series. September 27, 2005.
(D) TPE331-12 series.......... TPE331-A72-2131, dated Use ASB Table 1.
September 27, 2005.
------------------------------------------------------------------------
[[Page 38058]]
(ii) If you are unable to determine equivalent cycles for prior
special-use operations due to the absence of actual data regarding
the number of takeoffs and landings per major cycle, you must use a
onetime ratio of six takeoffs and landings per major cycle to
estimate prior special-use equivalent cycles for each turbine rotor.
(iii) For each turbine rotor affected on the Life Limited Part
Log Card, record the total equivalent cycles accrued, as determined
in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD, by complying with
the recording requirements for your model engine listed in the
following Table B:
Table B.--Service Bulletins (SBs) for Recording Total Equivalent Cycles
------------------------------------------------------------------------
For engines Record using
------------------------------------------------------------------------
(A) TPE331-1 through -6 series and Honeywell SB No. TPE/TSE331-72-
TSE331-3U model. 0019, Revision 22, dated May
16, 2001.
(B) TPE331-8 through -9 series......... AlliedSignal SB No. TPE331-72-
0117, Revision 11, dated
November 13, 1997.
(C) TPE331-10 through -11 series....... Honeywell SB No. TPE331-72-
0180, Revision 31, dated
November 7, 2003.
(D) TPE331-12 series................... Honeywell SB No. TPE331-72-
0476, Revision 27, dated
September 17, 2003.
------------------------------------------------------------------------
(2) Remove from service turbine rotors affected by paragraph (f)
of this AD using the applicable Turbine Rotor Removal Schedule in
Table A of this AD, or, within nine months after the effective date
of this AD, whichever occurs later.
Used Turbine Rotors Installed On or After the Effective Date of this AD
(g) For used turbine rotors installed on or after the effective
date of this AD, and currently or previously used in special-use
operations:
(1) Before further flight, determine and record total equivalent
cycles using paragraphs (f)(1)(i) through (f)(1)(iii) of this AD.
(2) Remove from service, turbine rotors affected by paragraph
(g) of this AD using the applicable Turbine Rotor Removal Schedule
in Table A of this AD.
New (Zero Cycles) Turbine Rotors Installed On or After the Effective
Date of This AD
(h) For all new (zero cycles) turbine rotors installed on or
after the effective date of this AD used in special-use operations:
(1) Use the new counting method by counting and recording minor
and major cycles when accrued, and determine equivalent cycles by
the method described in paragraphs (f)(1)(i) and (f)(1)(iii) of this
AD.
(2) Using the ratio of six takeoffs and landings per major cycle
for unknown cycle history, as referenced in paragraph (f)(1)(ii) of
this AD, is not permitted.
Definitions
(i) An engine used in special-use operations is defined as an
engine that accrues major and minor cycles and is installed in an
aircraft that makes multiple takeoffs and landings without engine
shutdown.
(j) Total equivalent cycles, is that combination of major and
minor cycles as specified in the Honeywell ASBs listed in Table A of
this AD.
(k) Total equivalent cycle life limits listed in the ASBs, are
the cycle life limits specified in the SBs listed in Table B of this
AD.
(l) The ``recording of total equivalent cycles on the Life
Limited Part Log Card'' is that same procedure specified for
``accumulated cycles'' or ``total cycles'' in the SBs listed in
Table B of this AD.
(m) ``Turbine rotors'' include first, second, and third stage
seal plates, air seals, rotor disks, wheels, and assemblies, and are
parts that have part numbers specified in the ASBs listed in Table A
of this AD.
(n) A major cycle is an engine start, takeoff, landing, and
shutdown.
(o) A minor cycle, which occurs within a major cycle, is an
additional landing with an engine speed reduction to ground idle
with no engine shutdown followed by a takeoff.
(p) A ``used turbine rotor'' is a turbine rotor whose cycles-
since-new are more than zero.
Alternative Methods of Compliance
(q) The Manager, Los Angeles Aircraft Certification Office, has
the authority to approve alternative methods of compliance for this
AD if requested using the procedures found in 14 CFR 39.19.
Material Incorporated by Reference
(r) You must use the service information specified in Table C of
this AD to perform the actions required by this AD. The Director of
the Federal Register approved the incorporation by reference of the
documents listed in Table C of this AD in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Contact Honeywell Engines, Systems &
Services, Technical Data Distribution, M/S 2101-201, P.O. Box 52170,
Phoenix, AZ 85072-2170; telephone: (602) 365-2493 (General
Aviation); (602) 365-5535 (Commercial); fax: (602) 365-5577 (General
Aviation and Commercial) for a copy of this service information. You
may review copies at the FAA, New England Region, Office of the
Regional Counsel, 12 New England Executive Park, Burlington, MA; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, call 202-
741-6030, or go to: https://www.archives.gov/federal-register/cfr/
ibr-locations.html.
Table C.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
Service Bulletin (SB) Page Revision Date
----------------------------------------------------------------------------------------------------------------
Honeywell SB No. TPE/TSE331-72-0019... 1 22 May 16, 2001.
Total Pages: 16 2-11 21 March 3, 2000.
12 22 May 16, 2001.
13-16 21 March 3, 2000.
AlliedSignal SB No. TPE331-72-0117.... 1 11 November 13, 1997.
Total Pages: 10 2 9 May 24, 1995.
3-10 11 November 13, 1997.
Honeywell SB No. TPE331-72-0180....... 1 31 November 7, 2003.
Total Pages: 54 2-3 29 August 23, 2002.
4-5 31 November 7, 2003.
6-7 29 August 23, 2002.
8-13 31 November 7, 2003.
14 27 February 23, 2001.
15-17 31 November 7, 2003.
18 27 February 23, 2001.
19 31 November 7, 2003.
[[Page 38059]]
20 29 August 23, 2002.
21 31 November 7, 2003.
22-24 29 August 23, 2002.
25 31 November 7, 2003.
26 29 August 23, 2002.
27-54 31 November 7, 2003.
Honeywell SB No. TPE331-72-0476....... 1-2 27 September 17, 2003.
Total pages: 46 3 25 May 24, 2002.
4 27 September 17, 2003.
5 25 May 24, 2002.
6 27 September 17, 2003.
7-14 25 May 24, 2002.
15 26 July 26, 2002.
16-22 25 May 24, 2002.
23-27 27 September 17, 2003.
28-32 25 May 24, 2002.
33 26 July 26, 2002.
34 25 May 24, 2002.
35 27 September 17, 2003.
36 25 May 24, 2002.
37-41 27 September 17, 2003.
42 25 May 24, 2002.
43 27 September 17, 2003.
44 25 May 24, 2002.
45 27 September 17, 2003.
46 25 May 24, 2002.
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
Alert Service Bulletin (ASB) Page Revision Date
----------------------------------------------------------------------------------------------------------------
Honeywell ASB No. TPE331-A72-2111..... ALL Original November 12, 2002.
Total Pages: 12
Honeywell ASB No. TPE331-A72-2123..... ALL Original February 8, 2006.
Total Pages: 12
Honeywell ASB No. TPE331-A72-2130..... ALL Original September 27, 2005.
Total Pages: 16
Honeywell ASB No. TPE331-A72-2131..... ALL Original September 27, 2005.
Total Pages: 14
----------------------------------------------------------------------------------------------------------------
Issued in Burlington, Massachusetts, on June 26, 2006.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 06-5929 Filed 7-3-06; 8:45 am]
BILLING CODE 4910-13-P
