Airworthiness Directives; Honeywell International Inc. TPE331 Series Turboprop, and TSE331-3U Model Turboshaft Engines, 9281-9285 [E6-2574]
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Federal Register / Vol. 71, No. 36 / Thursday, February 23, 2006 / Proposed Rules
cchase on PROD1PC60 with PROPOSALS
17. Should part 715 require credit
unions that obtain a financial statement
audit and/or an ‘‘attestation on internal
controls’’ (whether as required or
voluntarily) to forward a copy of the
auditor’s report to NCUA? If so, how
soon after the audit period-end? If not,
why not?
18. Should part 715 require credit
unions to provide NCUA with a copy of
any management letter, qualification, or
other report issued by its external
auditor in connection with services
provided to the credit union? If so, how
soon after the credit union receives it?
If not, why not?
19. If credit unions were required to
forward external auditors’ reports to
NCUA, should part 715 require the
auditor to review those reports with the
Supervisory Committee before
forwarding them to NCUA?
20. Existing part 715 requires a credit
union’s engagement letter to prescribe a
target date of 120 days after the audit
period-end for delivery of the audit
report. Should this period be extended
or shortened? What sanctions should be
imposed against a credit union that fails
to include the target delivery date
within its engagement letter?
21. Should part 715 require credit
unions to notify NCUA in writing when
they enter into an engagement with an
auditor, and/or when an engagement
ceases by reason of the auditor’s
dismissal or resignation? If so in cases
of dismissal or resignation, should the
credit union be required to include
reasons for the dismissal or resignation?
22. NCUA recently joined in the final
Interagency Advisory on the Unsafe and
Unsound Use of Limitation of Liability
Provisions in External Audit
Engagement Letters, 71 FR 6847 (Feb. 9,
2006). Should credit union Supervisory
Committees be prohibited by regulation
from executing engagement letters that
contain language limiting various forms
of auditor liability to the credit union?
Should Supervisory Committees be
prohibited from waiving the auditor’s
punitive damages liability?
By the National Credit Union
Administration Board on February 16, 2006.
Mary F. Rupp,
Secretary of the Board.
[FR Doc. E6–2531 Filed 2–22–06; 8:45 am]
BILLING CODE 7535–01–P
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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]
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: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Honeywell International Inc.
TPE331 series turboprop, and TSE331–
3U model turboshaft engines. This
proposed AD would 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 would require
determining total equivalent cycles
accrued. This proposed AD results from
several reports of uncontained turbine
rotor separation on engines used in
special-use operations. We are
proposing this AD to prevent
uncontained failure of the turbine rotor
due to low-cycle-fatigue (LCF), and
damage to the aircraft.
DATES: We must receive any comments
on this proposed AD by April 24, 2006.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
PO 00000
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9281
You can get the service information
identified in this proposed 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 comments on
this proposed AD in the AD docket on
the Internet at https://dms.dot.gov.
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:
Comments Invited
We invite you to send us any written
relevant data, views, or arguments
regarding this proposal. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2006–23704; Directorate Identifier
2006–NE–02–AD’’ in the subject line of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the proposed AD. We will
consider all comments received by the
closing date and may amend the
proposed AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of the DOT
Web site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78) or you may visit https://
dms.dot.gov.
Examining the AD Docket
You may examine the docket that
contains the proposal, any comments
received and, any final disposition in
person at the DOT 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
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Federal Register / Vol. 71, No. 36 / Thursday, February 23, 2006 / Proposed Rules
ADDRESSES.
Comments will be available
in the AD docket shortly after the
Docket Management Facility receives
them.
Discussion
We received several reports of turbine
rotor separations on Honeywell
International Inc. TPE331 turboprop
series engines, resulting in metal
fragments either penetrating the engine
case or exiting the tail pipe. These
engines were in special-use operations
that typically include minor cycles
(aircraft that make multiple takeoffs and
landings without an engine shutdown).
We found that as minor cycles on
these engines accumulate, so does LCF
damage to the turbine rotors, just like
LCF damage does from a major cycle
(engine start, takeoff, landing,
shutdown). Further, the manufacturer’s
major life cycle calculations do not
address special-use operations (aircraft
that make multiple takeoffs and
landings without an engine shutdown).
Special-use operations typically include
agricultural, skydiving, and certain
cargo flight operations, where the
number of minor cycles generally ranges
between five and twenty takeoffs-andlandings (to ground idle) per major
cycle.
This proposed AD is related to the
recent FAA safety evaluation on
Mitsubishi MU–2B series airplanes.
This condition, if not corrected, could
result in LCF damage to the turbine
rotors, resulting in uncontained turbine
rotor failure and damage to the aircraft.
Relevant Service Information
We have reviewed the technical
contents of Honeywell International Inc.
Alert Service Bulletins (ASBs) No.
TPE331–A72–2111, dated November 12,
2002; No. TPE331–A72–2123, dated
February 8, 2006; No. TPE331–A72–
2130, dated September 27, 2005; and
TPE331–A–72–2131, dated September
27, 2005, that describe procedures for
determining total equivalent cycles
(major cycles plus minor cycles) for
first, second, and third-stage turbine
rotors used in special-use operations
and procedures for removing over-limit
turbine rotors from service.
We have also reviewed and approved
the technical contents of Honeywell
International Inc. Service Bulletins
(SBs) No. TPE331–72–0019, Revision
22, dated May 16, 2001; SB No.
TPE331–72–0180, Revision 31, dated
November 7, 2003; and SB No. TP331–
72–0476, Revision 27, dated September
17, 2003, and AlliedSignal Inc. SB No.
TP331–72–0117, Revision 11, dated
November 13, 1997, that describe
procedures for recording total
equivalent cycles.
currently installed in engines that were
or are in special-use operations; and
• Removing from service, turbine
rotors that were or are in special-use
operations that have reached or
exceeded their cycle life limits; and
• Using the new flight cycle counting
method that counts major and minor
cycles as accrued for all new turbine
rotors.
The proposed AD would require you
to use the service information described
previously to perform these actions.
Differences Between the Proposed AD
and the Manufacturer’s Service
Information
The proposed AD would allow
special-use operators to remove overlimit turbine rotors either according to
Table 1 of the removal schedule in the
applicable ASBs, or within nine months
after the effective date of the proposed
AD, whichever occurs later. This would
allow high-utilization agricultural
operators more time to comply with the
proposed AD within their spraying
season.
Also, the compliance time stated in
compliance paragraph 1.D. of the
applicable Honeywell ASBs is different
from the proposed AD. Also, although
the Honeywell and AlliedSignal ASBs
and SBs address only the TPE331 series,
and TSE331–3U model engines in
service, the applicability of the
proposed AD includes all certified
TPE331–1 through –12 series engines
and TSE331–3U model engines. Also,
the proposed AD provides actions for
used rotors installed on or after the
effective date of this AD.
We estimate that this proposed AD
would 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 would take about two
work hours per engine to perform the
proposed total equivalent cycles
determination and recording. We also
estimate that to perform a proposed
turbine engine removal it would take 40
work hours per engine when done at an
unscheduled turbine section inspection,
and one work hour per engine when
done at a scheduled engine turbine
section inspection. We estimate the
average labor rate to be $65 per work
hour. Required parts would cost about
$20,000 per engine. The costs associated
with this proposed 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 proposed 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.
This is one of several actions that
FAA is evaluating for unsafe conditions
on the MU–2B airplanes. We estimate
that 10 percent of the affected engines
are used on MU–2B airplanes. To date,
we have proposed the following actions:
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to exist or
develop on other products of this same
type design. We are proposing this AD,
which would require:
• Determining and recording the total
equivalent cycles for turbine rotors
Date NPRM
published
Unsafe condition
FAA–2006–23578
cchase on PROD1PC60 with PROPOSALS
Docket
Wing attach barrel nuts, bolts, and retainers
for cracks, corrosion, and fractures.
January 25, 2006
(71 FR 4072).
FAA–2006–23644
An asymmetric thrust situation in certain
flight conditions, which could result in airplane controllability problems.
February 9, 2006
(71 FR 6685).
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Costs of Compliance
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Cost impact
$65 per airplane for the inspection and $1,195 per airplane if all 8 barrel nuts needed replacement. Total
airplane cost is $1,260 per airplane. If all 397 airplanes needed all 8 barrel nuts replaced, the total
cost on U.S. operators for this proposed action
would be $500,220.
$390 per airplane to change the blade angle. The
total cost to U.S. operators for this proposed action
would be $57,720.
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Federal Register / Vol. 71, No. 36 / Thursday, February 23, 2006 / Proposed Rules
Total proposed cost impact to date
(including this NPRM) for the affected
airplanes is $47,113 per airplane. This
does not account for the following:
• The cost of any repairs or
replacements based upon the results of
inspections by the proposed actions;
and
• The loss of revenue due to the
airplane being down for work associated
with any proposed AD action.
The total cost to date on all U.S.
operators (including this NPRM) would
be $18,703,940. This is based on the
presumption that 10 airplanes would
need the actions performed as specified
by Docket No. FAA–2006–23704.
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
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Would not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD. 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, Safety.
The Proposed Amendment
Under the authority delegated to me
by the Administrator, the Federal
Aviation Administration proposes to
amend 14 CFR part 39 as follows:
9283
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
Honeywell International Inc. (formerly
AlliedSignal Inc., Garrett Engine
Division; Garrett Turbine Engine
Company; and AiResearch
Manufacturing Company of Arizona):
Docket No. FAA–2006–23704;
Directorate Identifier 2006–NE–02–AD.
Comments Due Date
(a) The Federal Aviation
Administration (FAA) must receive
comments on this airworthiness
directive (AD) action by April 24, 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 Enterprises) ..........................
ALLIED AG CAT PRODUCTIONS (formerly Schweizer) ........................
AYRES ......................................................................................................
BRITISH AEROSPACE LTD (formerly Jetstream) ..................................
CESSNA AIRCRAFT COMPANY ............................................................
CONSTRUCCIONES AERONAUTICAS, S.A. (CASA) ............................
DEHAVILLAND .........................................................................................
DORNIER .................................................................................................
FAIRCHILD ...............................................................................................
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.
cchase on PROD1PC60 with PROPOSALS
GRUMMAN AMERICAN ...........................................................................
MITSUBISHI .............................................................................................
PILATUS ...................................................................................................
POLSKIE ZAKLADY LOTNICZE SPOLKA (formerly Wytwornia Sprzetu
Komunikacyjnego).
PROP-JETS, INC. ....................................................................................
RAYTHEON AIRCRAFT (formerly Beech) ...............................................
SHORTS BROTHERS AND HARLAND, LTD .........................................
THRUSH (ROCKWELL COMMANDER) ..................................................
TWIN COMMANDER (JETPROP COMMANDER) ..................................
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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.
Sfmt 4702
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9284
Federal Register / Vol. 71, No. 36 / Thursday, February 23, 2006 / Proposed Rules
Manufacturer
Helicopter model
SIKORSKY ...............................................................................................
Unsafe Condition
(d) 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.
Compliance
(e) You are responsible for having the
actions required by this AD performed
S–55 SERIES (HELITEC CORP. S55T).
within the compliance times specified
unless the actions have already been
done.
Used Turbine Rotors Installed Before
the Effective Date of This AD
(f) For used turbine rotors installed
before the effective date of this AD, and
currently or previously used in specialuse 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
For engines
Turbine rotor
removal
schedule
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 ...........................................................
(ii) If you are unable to determine
equivalent cycles for prior special-use
operations, you must use a takeoff-toengine shutdown ratio of six to estimate
TPE331–A72–2111,
TPE331–A72–2123,
TPE331–A72–2130,
TPE331–A72–2131,
dated
dated
dated
dated
November 12, 2002 ...................
February 8, 2006 .......................
September 27, 2005 ..................
September 27, 2005 ..................
prior special-use equivalent cycles for
turbine rotors.
(iii) For each turbine rotor affected on
the Life Limited Part Log Card, record
the total equivalent cycles accrued, as
Use
Use
Use
Use
ASB
ASB
ASB
ASB
Table
Table
Table
Table
1.
1.
1.
1.
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.—SBS FOR RECORDING TOTAL EQUIVALENT CYCLES
For engines
Record using
(A) TPE331–1 through –6 series and TSE331–3U model ......................
Honeywell SB No. TPE331–72–0019, 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 ..............................................................................
AD using the applicable Turbine Rotor
Removal Schedule in Table A of this
AD.
Used Turbine Rotors Installed On or
After the Effective Date of This AD
cchase on PROD1PC60 with PROPOSALS
(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.
(h) For all new (zero cycles) turbine
rotors installed on or after the effective
date of this AD:
(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 paragraph (f) of this AD.
(2) The use of the ratio of six takeoffs
to one engine shutdown per major cycle
for unknown cycle history is not
permitted.
(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
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New (Zero Cycles) Turbine Rotors
Installed On or After the Effective Date
of This AD
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Definitions
(i) Engines used in special-use
operations are engines installed in
aircraft that make multiple takeoffs and
landings without engine shutdown.
(j) Total equivalent cycles is the
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 same as 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 the same procedure specified for
‘‘accumulated cycles’’ or ‘‘total cycles’’
in the SBs listed in Table B of this AD.
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Federal Register / Vol. 71, No. 36 / Thursday, February 23, 2006 / Proposed Rules
(m) Turbine rotors includes first,
second, and third stage seal plates, air
seals, rotor disks, wheels, and
assemblies 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 is multiple takeoffs
and landings without an engine
shutdown.
(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.
Related Information
(r) None.
Issued in Burlington, Massachusetts, on
February 15, 2006.
Ann C. Mollica,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E6–2574 Filed 2–22–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Office of the Secretary
14 CFR Part 382
RIN 2105–AD41
[OST Docket No. 2006–23999]
Accommodations for Individuals Who
Are Deaf, Hard of Hearing, or DeafBlind
Office of the Secretary,
Department of Transportation (DOT).
ACTION: Notice of Proposed Rulemaking
(NPRM).
cchase on PROD1PC60 with PROPOSALS
AGENCY:
SUMMARY: This notice of proposed
rulemaking (NPRM) proposes to amend
a previously published proposed rule
that implements the Air Carrier Access
Act (ACAA), to provide for additional
accommodations for air travelers who
are deaf, hard of hearing or deaf-blind.
This proposed rule applies to U.S. air
carriers, to foreign air carriers for their
flights into and out of the United States,
to airport facilities located in the U.S.
that are owned, controlled or leased by
carriers, and to aircraft that serve a U.S.
airport. It proposes to require U.S. and
certain foreign air carriers to provide
prompt access for individuals who
identify themselves as requiring hearing
VerDate Aug<31>2005
16:33 Feb 22, 2006
Jkt 208001
or visual assistance to the same
information provided to other
passengers in the terminal and on the
aircraft; caption safety and
informational videos, DVDs and other
audio-visual displays shown on new
and existing aircraft; caption
entertainment videos, DVDs and other
audio-visual displays on new aircraft;
ensure that individuals calling a
carrier’s TTY line for information or
reservations receive equal response time
and level of service (including queuing
or other automated response service) as
that provided to individuals calling a
non-TTY information or reservation
line; enable captioning on televisions
and audio-visual equipment located in
those portions of U.S. airports that are
owned, leased or controlled by carriers
and open to public access to the extent
that such equipment has captioning
capability on the effective date of this
rule; replace non-caption capable
televisions and audio-visual displays
with captioning capable technology in
the normal course of operations or when
relevant airport facilities undergo
substantial renovation or expansion;
and train carrier personnel to
proficiency on recognizing requests for
communication accommodations and
communicating with individuals who
have visual or hearing impairments.
DATES: Interested persons are invited to
submit comments regarding this
proposal. Comments must be received
on or before April 24, 2006.
ADDRESSES: Comments on this notice of
proposed rulemaking must refer to the
docket and notice numbers cited at the
beginning of this notice and be
submitted to the Docket Management
Facility of the Office of the Secretary
(OST), located on the Plaza Level of the
Nassif Building at the U.S. Department
of Transportation, Room PL–401, 400
Seventh Street, SW., Washington, DC
20590–0001. The DOT Docket Facility is
open to the public from 10 a.m. to 5
p.m., Monday through Friday.
Commenters may also submit comments
electronically. Instructions appear on
the Dockets Management System (DMS)
pages of the Department’s Web site
(https://dms.dot.gov).
FOR FURTHER INFORMATION CONTACT:
Omar Guerrero or Blane A. Workie,
Office of the General Counsel,
Department of Transportation, 400 7th
Street, SW., Room 4116, Washington,
DC 20590, 202–366–9342 (voice), (202)
366–0511 (TTY), 202–366–7152 (fax),
omar.guerrero@dot.gov or
blane.workie@dot.gov (e-mail).
Arrangements to receive this notice in
an alternative format may be made by
contacting the above named individuals.
PO 00000
Frm 00008
Fmt 4702
Sfmt 4702
9285
SUPPLEMENTARY INFORMATION:
Background
This NPRM concerns the issue of
accommodations for deaf, hard of
hearing and deaf-blind individuals. The
Department of Transportation
(hereinafter ‘‘Department’’ or ‘‘DOT’’)
first considered such an NPRM in 1996.
At that time, DOT issued an NPRM on
seating accommodations and stowage of
collapsible wheelchairs in which it also
requested comments on suggestions the
Department had received regarding
accommodations for deaf and hard of
hearing persons. See 61 FR 56484 (Nov.
1, 1996). Specifically, the 1996 NPRM
sought comments on the need for,
technical feasibility of, and cost of the
following accommodations: (1) The
captioning of video material shown on
aircraft (e.g., movies and other
entertainment features); (2) the
availability of telecommunications
devices for the deaf where air phone
service is provided to other passengers;
(3) the provision of assistive listening
technology for public address
announcements in the aircraft; and (4)
the provision of electronic messaging or
assistive listening technology in gate
areas. In the preamble of the final rule
that resulted from the November 1996
proposed rulemaking, however, the
Department deferred a decision on
whether to require additional
accommodations for deaf and hard of
hearing passengers. See 63 FR 10528
(March 4, 1998).
In January 2000, DOT reopened
consideration of this issue by convening
a public meeting to discuss whether the
Department should commence a
rulemaking to require certain additional
accommodations for deaf and hard of
hearing passengers under the ACAA.
See 62 FR 63279 (Nov. 19, 1999); 64 FR
66590 (Nov. 29, 1999). Later that year,
the Department determined to institute
a rulemaking on additional
accommodations for deaf and hard of
hearing individuals through the use of
a regulatory negotiation. However,
resource issues delayed the formation
and progress of a regulatory negotiation
on this issue.
Representatives from the deaf and
hard of hearing community, during the
May 2001 DOT forum regarding air
travel for people with disabilities, asked
that DOT follow-up on these early
efforts to address deaf and hard of
hearing accommodations with a
rulemaking. In response to this request,
DOT indicated that collaboration among
air carriers, airports and the disability
community would accelerate the
initiation of rulemaking addressing
these issues.
E:\FR\FM\23FEP1.SGM
23FEP1
]]>Agencies
[Federal Register Volume 71, Number 36 (Thursday, February 23, 2006)]
[Proposed Rules]
[Pages 9281-9285]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-2574]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23704; Directorate Identifier 2006-NE-02-AD]
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: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Honeywell International Inc. TPE331 series turboprop, and
TSE331-3U model turboshaft engines. This proposed AD would 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 would require determining total
equivalent cycles accrued. This proposed AD results from several
reports of uncontained turbine rotor separation on engines used in
special-use operations. We are proposing this AD to prevent uncontained
failure of the turbine rotor due to low-cycle-fatigue (LCF), and damage
to the aircraft.
DATES: We must receive any comments on this proposed AD by April 24,
2006.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
You can get the service information identified in this proposed 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 comments on this proposed AD in the AD docket
on the Internet at https://dms.dot.gov.
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:
Comments Invited
We invite you to send us any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2006-23704;
Directorate Identifier 2006-NE-02-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of the
DOT Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78) or you
may visit https://dms.dot.gov.
Examining the AD Docket
You may examine the docket that contains the proposal, any comments
received and, any final disposition in person at the DOT 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
[[Page 9282]]
ADDRESSES. Comments will be available in the AD docket shortly after
the Docket Management Facility receives them.
Discussion
We received several reports of turbine rotor separations on
Honeywell International Inc. TPE331 turboprop series engines, resulting
in metal fragments either penetrating the engine case or exiting the
tail pipe. These engines were in special-use operations that typically
include minor cycles (aircraft that make multiple takeoffs and landings
without an engine shutdown).
We found that as minor cycles on these engines accumulate, so does
LCF damage to the turbine rotors, just like LCF damage does from a
major cycle (engine start, takeoff, landing, shutdown). Further, the
manufacturer's major life cycle calculations do not address special-use
operations (aircraft that make multiple takeoffs and landings without
an engine shutdown). Special-use operations typically include
agricultural, skydiving, and certain cargo flight operations, where the
number of minor cycles generally ranges between five and twenty
takeoffs-and-landings (to ground idle) per major cycle.
This proposed AD is related to the recent FAA safety evaluation on
Mitsubishi MU-2B series airplanes. This condition, if not corrected,
could result in LCF damage to the turbine rotors, resulting in
uncontained turbine rotor failure and damage to the aircraft.
Relevant Service Information
We have reviewed the technical contents of Honeywell International
Inc. Alert Service Bulletins (ASBs) No. TPE331-A72-2111, dated November
12, 2002; No. TPE331-A72-2123, dated February 8, 2006; No. TPE331-A72-
2130, dated September 27, 2005; and TPE331-A-72-2131, dated September
27, 2005, that describe procedures for determining total equivalent
cycles (major cycles plus minor cycles) for first, second, and third-
stage turbine rotors used in special-use operations and procedures for
removing over-limit turbine rotors from service.
We have also reviewed and approved the technical contents of
Honeywell International Inc. Service Bulletins (SBs) No. TPE331-72-
0019, Revision 22, dated May 16, 2001; SB No. TPE331-72-0180, Revision
31, dated November 7, 2003; and SB No. TP331-72-0476, Revision 27,
dated September 17, 2003, and AlliedSignal Inc. SB No. TP331-72-0117,
Revision 11, dated November 13, 1997, that describe procedures for
recording total equivalent cycles.
Differences Between the Proposed AD and the Manufacturer's Service
Information
The proposed AD would allow special-use operators to remove over-
limit turbine rotors either according to Table 1 of the removal
schedule in the applicable ASBs, or within nine months after the
effective date of the proposed AD, whichever occurs later. This would
allow high-utilization agricultural operators more time to comply with
the proposed AD within their spraying season.
Also, the compliance time stated in compliance paragraph 1.D. of
the applicable Honeywell ASBs is different from the proposed AD. Also,
although the Honeywell and AlliedSignal ASBs and SBs address only the
TPE331 series, and TSE331-3U model engines in service, the
applicability of the proposed AD includes all certified TPE331-1
through -12 series engines and TSE331-3U model engines. Also, the
proposed AD provides actions for used rotors installed on or after the
effective date of this AD.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. We are proposing this AD, which would
require:
Determining and recording the total equivalent cycles for
turbine rotors currently installed in engines that were or are in
special-use operations; and
Removing from service, turbine rotors that were or are in
special-use operations that have reached or exceeded their cycle life
limits; and
Using the new flight cycle counting method that counts
major and minor cycles as accrued for all new turbine rotors.
The proposed AD would require you to use the service information
described previously to perform these actions.
Costs of Compliance
We estimate that this proposed AD would 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
would take about two work hours per engine to perform the proposed
total equivalent cycles determination and recording. We also estimate
that to perform a proposed turbine engine removal it would take 40 work
hours per engine when done at an unscheduled turbine section
inspection, and one work hour per engine when done at a scheduled
engine turbine section inspection. We estimate the average labor rate
to be $65 per work hour. Required parts would cost about $20,000 per
engine. The costs associated with this proposed 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 proposed 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.
This is one of several actions that FAA is evaluating for unsafe
conditions on the MU-2B airplanes. We estimate that 10 percent of the
affected engines are used on MU-2B airplanes. To date, we have proposed
the following actions:
----------------------------------------------------------------------------------------------------------------
Docket Unsafe condition Date NPRM published Cost impact
----------------------------------------------------------------------------------------------------------------
FAA-2006-23578............ Wing attach barrel nuts, January 25, 2006 (71 FR $65 per airplane for the
bolts, and retainers 4072). inspection and $1,195 per
for cracks, corrosion, airplane if all 8 barrel
and fractures. nuts needed replacement.
Total airplane cost is
$1,260 per airplane. If all
397 airplanes needed all 8
barrel nuts replaced, the
total cost on U.S.
operators for this proposed
action would be $500,220.
FAA-2006-23644............ An asymmetric thrust February 9, 2006 (71 FR $390 per airplane to change
situation in certain 6685). the blade angle. The total
flight conditions, cost to U.S. operators for
which could result in this proposed action would
airplane be $57,720.
controllability
problems.
----------------------------------------------------------------------------------------------------------------
[[Page 9283]]
Total proposed cost impact to date (including this NPRM) for the
affected airplanes is $47,113 per airplane. This does not account for
the following:
The cost of any repairs or replacements based upon the
results of inspections by the proposed actions; and
The loss of revenue due to the airplane being down for
work associated with any proposed AD action.
The total cost to date on all U.S. operators (including this NPRM)
would be $18,703,940. This is based on the presumption that 10
airplanes would need the actions performed as specified by Docket No.
FAA-2006-23704.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Would not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD. 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, Safety.
The Proposed Amendment
Under the authority delegated to me by the Administrator, the
Federal Aviation Administration proposes to amend 14 CFR part 39 as
follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive:
Honeywell International Inc. (formerly AlliedSignal Inc., Garrett
Engine Division; Garrett Turbine Engine Company; and AiResearch
Manufacturing Company of Arizona): Docket No. FAA-2006-23704;
Directorate Identifier 2006-NE-02-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive comments
on this airworthiness directive (AD) action by April 24, 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.
------------------------------------------------------------------------
[[Page 9284]]
------------------------------------------------------------------------
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.
Used Turbine Rotors Installed Before the Effective Date of This AD
(f) For used 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
----------------------------------------------------------------------------------------------------------------
For engines Use ASB No. Turbine rotor removal schedule
----------------------------------------------------------------------------------------------------------------
(A) TPE331-1 through -6 series and TPE331-A72-2111, dated November Use ASB Table 1.
TSE331-3U model. 12, 2002.
(B) TPE331-8 through -9 series.......... TPE331-A72-2123, dated February Use ASB Table 1.
8, 2006.
(C) TPE331-10 through -11 series........ TPE331-A72-2130, dated September Use ASB Table 1.
27, 2005.
(D) TPE331-12 series.................... TPE331-A72-2131, dated September Use ASB Table 1.
27, 2005.
----------------------------------------------------------------------------------------------------------------
(ii) If you are unable to determine equivalent cycles for prior
special-use operations, you must use a takeoff-to-engine shutdown ratio
of six to estimate prior special-use equivalent cycles for turbine
rotors.
(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.--SBs for Recording Total Equivalent Cycles
------------------------------------------------------------------------
For engines Record using
------------------------------------------------------------------------
(A) TPE331-1 through -6 series and Honeywell SB No. TPE331-72-
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:
(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 paragraph (f) of this AD.
(2) The use of the ratio of six takeoffs to one engine shutdown per
major cycle for unknown cycle history is not permitted.
Definitions
(i) Engines used in special-use operations are engines installed in
aircraft that make multiple takeoffs and landings without engine
shutdown.
(j) Total equivalent cycles is the 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
same as 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 the same procedure specified for ``accumulated
cycles'' or ``total cycles'' in the SBs listed in Table B of this AD.
[[Page 9285]]
(m) Turbine rotors includes first, second, and third stage seal
plates, air seals, rotor disks, wheels, and assemblies 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 is multiple takeoffs and landings without an
engine shutdown.
(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.
Related Information
(r) None.
Issued in Burlington, Massachusetts, on February 15, 2006.
Ann C. Mollica,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E6-2574 Filed 2-22-06; 8:45 am]
BILLING CODE 4910-13-P
