[Federal Register: July 5, 2006 (Volume 71, Number 128)]
[Rules and Regulations]
[Page 38054-38059]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr05jy06-3]
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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.
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[[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 http://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:
http://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: http://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