Airworthiness Directives; Honeywell International LTS101 Series Turboshaft Engines and LTP101 Series Turboprop Engines, 78937-78939 [2010-31782]

Download as PDF 78937 Federal Register / Vol. 75, No. 242 / Friday, December 17, 2010 / Proposed Rules Number represented by label or test Maximum number within tolerances Number represented by label or test Maximum number within tolerances Number represented by label or test Maximum number within tolerances (X) (Y) (X) (Y) (X) (Y) 32 33 41 42 66 67 79 80 100 ................................... 116 ................................... 10. In § 201.74, paragraph (a) is amended by removing the last sentence, and paragraph (c) is amended by adding a sentence at the end of the paragraph to read as follows: § 201.74 seed. Labeling of all classes of certified * * * * * (c) * * * The seed lot number or other identification number, the kind, and variety name (if certified to variety) shall appear on the official label and/or directly on the container in a position to be viewed in conjunction with the official certification label. * * * * * 11. In § 201.75, paragraph (c), the last sentence is revised to read as follows: § 201.75 Interagency certification. * * * * * (c) * * * The seed lot number or other identification number, the kind, and variety name (if certified to variety) shall appear on the official label and/or directly on the container in a position to be viewed in conjunction with the official certification label. Dated: December 10, 2010. Robert C. Keeney, Acting Administrator, Agricultural Marketing Service. [FR Doc. 2010–31573 Filed 12–16–10; 8:45 am] BILLING CODE 3410–02–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–1185; Directorate Identifier 2009–NE–24–AD] srobinson on DSKHWCL6B1PROD with PROPOSALS RIN 2120–AA64 Airworthiness Directives; Honeywell International LTS101 Series Turboshaft Engines and LTP101 Series Turboprop Engines Federal Aviation Administration, DOT. ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. AGENCY: This supplemental NPRM revises an earlier proposed SUMMARY: VerDate Mar<15>2010 16:28 Dec 16, 2010 Jkt 223001 airworthiness directive (AD), for Honeywell International LTS101–600A series and LTS101–700D–2 turboshaft engines, and LTP101–600A–1A and LTP101–700A–1A turboprop engines with power turbine blades, part number (P/N) 4–141–084–06, installed. That proposed AD would have required removing power turbine blades, P/N 4–141–084–06 from service, using a drawdown schedule specified in that proposed AD. That proposal was prompted by reports of fatigue cracks in the airfoil of the power turbine blade. This action revises the proposed rule by expanding and clarifying the applicability to include more engine models and power turbine blade P/Ns that could have the unsafe condition, and by clarifying the applicability by specifying power turbine rotor P/Ns instead of the blade P/Ns. The actions specified by this proposed AD are intended to prevent fracture of the power turbine blade airfoil, which could result in sudden loss of engine power and prevent continued safe flight or safe landing. DATES: We must receive any comments on this proposed AD by February 15, 2011. Use one of the following addresses to comment on this proposed AD. • Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. Contact Honeywell International Inc., P.O. Box 52181, Phoenix, AZ 85072– 2181; telephone (800) 601–3099 (U.S.A.) or (602) 365–3099 (International); or go to: https://portal.honeywell.com/wps/ portal/aero, for a copy of the service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Robert Baitoo, Aerospace Engineer, Los Angeles Aircraft Certification Office, ADDRESSES: PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712–4137; e-mail: robert.baitoo@faa.gov; telephone (562) 627–5245; 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– 2009–1185; Directorate Identifier 2009– NE–24–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:// www.regulations.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 Web site, anyone can find and read the comments in any of our dockets, including, if provided, 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). Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. E:\FR\FM\17DEP1.SGM 17DEP1 78938 Federal Register / Vol. 75, No. 242 / Friday, December 17, 2010 / Proposed Rules Discussion The FAA proposed to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to add an AD, applicable to Honeywell International LTS101– 600A series and LTS101–700D–2 turboshaft engines, and LTP101–600A– 1A and LTP101–700A–1A turboprop engines. We published the proposed AD in the Federal Register on December 21, 2009 (74 FR 67829). That action proposed to require removing power turbine blades, P/N 4–141–084–06, from service using a specific drawdown schedule. That NPRM was prompted by reports of fatigue cracks in the airfoil of the power turbine blade. That condition, if not corrected, could result in fracture of the power turbine blade airfoil, which could result in sudden loss of engine power. Since we issued that NPRM, Honeywell International Inc. informed us that power turbine blades, P/N 4– 141–084–03, could also have the unsafe condition. Those blades are used in power turbine rotors P/Ns 4–141–290– 02 and 4–141–290–16. Based on the information we received from Honeywell International Inc., we also determined that specifying the applicability by power turbine rotors P/N is clearer than by specifying the blade P/N. Comments We provided the public the opportunity to participate in the development of that proposed AD. We have considered the comments received on the original NPRM. srobinson on DSKHWCL6B1PROD with PROPOSALS Proposed AD Should Apply to Engines on Multi-Engine Helicopters One commenter, the National Transportation Safety Board (NTSB) asks us to consider adding to the applicability of the proposed AD, engines that also use the affected P/N turbine rotor blade, and are installed on multi-engine helicopters. The NTSB states that loss of power in one of the two engines is a safety issue. We agree with the NTSB that the fracture of a power turbine airfoil of an LTS101 series turboshaft engine installed on a twin-engine helicopter is a safety issue. We added Honeywell International Inc. LTS101–650B–1, LTS101–650C–3, LTS101–650C–3A, LTS101–750B–1, LTS101–750B–2, LTS101–750C–1, and LTS101–850B–2 turboshaft engines that are installed on twin-engine helicopters to the applicability of the proposed AD. We also added to the applicability, paragraph (g), and Table 1 of the proposed AD, Honeywell International VerDate Mar<15>2010 16:28 Dec 16, 2010 Jkt 223001 Inc. LTP101–600A–1A and LTP101– 700A–1A turboprop engines that use the same blades. The NTSB also requested that we reduce the drawdown schedule for the affected blades to remove the at risk power turbine rotor blades sooner. We don’t agree. Our risk assessment for the unsafe condition doesn’t justify accelerating the drawdown schedules. Editorial Changes to Table 1 and Table 1 of the Proposed AD We changed Table 1 and Table 2 in the proposed AD to eliminate arbitrary step changes. Since these changes expand the scope of the originally proposed rule, we determined that reopening the comment period is appropriate. FAA’s Determination of an Unsafe Condition and Proposed Actions Since an unsafe condition has been identified that is likely to exist or develop on other Honeywell International Inc. LTS101–600A–2, –3, –3A, LTS101–700D–2, LTS101–650B–1, LTS101–650C–3, LTS101–650C–3A, LTS101–750B–1, LTS101–750B–2, LTS101–750C–1, and LTS101–850B–2 turboshaft engines; and LTP101–600A– 1A and LTP101–700A–1A turboprop engines of the same type design, the proposed AD would require removing from service, power turbine rotors, P/Ns 4–141–290–01, –02, –03, –05, –06, –11, –12, –13, –14, or –16, using the compliance drawdown schedule specified in Table 1, and Table 2 of this AD. Costs of Compliance We estimate that this proposed AD would affect 240 engines installed on aircraft of U.S. registry. We also estimate that it would take about 30 work-hours per engine to perform the proposed actions, and that the average labor rate is $85 per work-hour. Required parts would cost about $70,000 per engine. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $17,412,000. 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 AD: PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 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. 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, Safety. The Proposed Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: Honeywell International Inc. (Formerly AlliedSignal, Textron Lycoming): Docket No. FAA–2009–1185; Directorate Identifier 2009–NE–24–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by February 15, 2011. Affected ADs (b) None. Applicability (c) This AD applies to Honeywell International LTS101–600A–2, –3, –3A, LTS101–700D–2, LTS101–650B–1, LTS101– 650C–3, LTS101–650C–3A, LTS101–750B–1, LTS101–750B–2, LTS101–750C–1, and LTS101–850B–2 turboshaft engines; and LTP101–600A–1A and LTP101–700A–1A turboprop engines with power turbine rotor, part number (P/N) 4–141–290–01, –02, –03, –05, –06, –11, –12, –13, –14, or –16, installed. These engines are installed on, but not limited to, Eurocopter AS350 and BK117 series and Bell 222 series helicopters; and Page Thrush, Air Tractor AT–302, and Pacific Aero 08–600, Piaggio P166 DL3, and Riley International R421 airplanes. E:\FR\FM\17DEP1.SGM 17DEP1 Federal Register / Vol. 75, No. 242 / Friday, December 17, 2010 / Proposed Rules Unsafe Condition (d) This AD results from reports of fatigue cracks in the airfoil of the power turbine blade. We are issuing this AD to prevent fracture of the power turbine blade airfoil, which could result in sudden loss of engine power and prevent continued safe flight or safe landing. the compliance times specified unless the actions have already been done. (f) For engines with power turbine rotors, P/Ns 4–141–290–11, –12, –13, and –14, marked with ‘‘ORI T41881,’’ on the aft hub in the vicinity of the P/N, no further action is required. Compliance (e) You are responsible for having the actions required by this AD performed within 78939 Removing Power Turbine Rotors From LTS101–600A–2, –3, –3A, and LTS101– 700D–2 Turboshaft Engines and LTP101– 600A–1A and LTP101–700A–1A Turboprop Engines (g) For LTS101–600A–2, –3, –3A, and LTS101–700D–2 turboshaft engines and LTP101–600A–1A and LTP101–700A–1A turboprop engines, remove power turbine rotors, P/Ns 4–141–290–01, –02, –03, –05, –06, –11, –12, –13, –14, or –16, using the cycles specified in Table 1 of this AD: TABLE 1—DRAWDOWN CYCLES FOR LTS101–600A–2, –3, –3A, AND LTS101–700D–2 TURBOSHAFT ENGINES AND LTP101–600A–1A AND LTP101–700A–1A TURBOPROP ENGINES If power turbine rotor time on the effective date of this AD is * * * Then remove the power turbine rotor from the engine * * * (1) Fewer than 5,000 cycles-since-new (CSN) ........................................ (2) 5,000 to 7,899 CSN ............................................................................ Between 5,000 and 5,500 CSN. Within 500 cycles-in-service (CIS) after the effective date of this AD or before exceeding 8,000 CSN, whichever occurs first. Within 100 CIS after the effective date of this AD or before exceeding 10,050 CSN, whichever occurs first. Within 50 CIS after the effective date of this AD. (3) 7,900 to 9,999 CSN ............................................................................ (4) 10,000 or more CSN ........................................................................... Removing Power Turbine Rotors From LTS101–650B–1, –650C–3,—650C–3A, –750B–1, –2, –750C–1, and –850B–2 Engines (h) Remove power turbine rotors, P/Ns 4–141–290–01, –02 –03, –05, –06, –11, –12, –13, –14, or –16, using the cycles specified in Table 2 of this AD: TABLE 2—DRAWDOWN CYCLES FOR LTS101–650B–1, –650C–3,–650C–3A, –750B–1, –2, –750C–1, AND –850B–2 ENGINES If power turbine rotor time on the effective date of this AD is * * * Then remove the power turbine rotor from the engine * * * (1) Fewer than 5,500 CSN ....................................................................... (2) 5,500 to 7,999 CSN ............................................................................ Between 5,000 and 7,200 CSN. Within 1,700 CIS after the effective date of this AD or before exceeding 8,950 CSN, whichever occurs first. Within 950 CIS after the effective date of this AD or before exceeding 10,400 CSN, whichever occurs first. Within 400 CIS after the effective date of this AD. (3) 8,000 to 9,999 CSN ............................................................................ (4) 10,000 or more CSN ........................................................................... Alternative Methods of Compliance (i) The Manager, Los Angles 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. [FR Doc. 2010–31782 Filed 12–16–10; 8:45 am] BILLING CODE 4910–13–P Related Information srobinson on DSKHWCL6B1PROD with PROPOSALS Issued in Burlington, Massachusetts, on December 13, 2010. Thomas A. Boudreau, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. (j) Contact Robert Baitoo, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712–4137; e-mail: robert.baitoo@faa.gov; telephone (562) 627–5245; fax (562) 627– 5210, for more information about this AD. (k) Honeywell International Inc. Service Bulletins LT 101–71–00–0252 and LTS101– 71–00–0253, pertain to the subject of this AD. Contact Honeywell International Inc., P.O. Box 52181, Phoenix, AZ 85072–2181; telephone (800) 601–3099 (U.S.A.) or (602) 365–3099 (International); or go to: https:// portal.honeywell.com/wps/portal/aero, for a copy of this service information. DEPARTMENT OF LABOR Employment and Training Administration 20 CFR Part 641 RIN 1205–AB60 Senior Community Service Employment Program; Notice of Proposed Rulemaking, Additional Indicator on Volunteer Work; Correction Employment and Training Administration, Labor. AGENCY: VerDate Mar<15>2010 16:28 Dec 16, 2010 Jkt 223001 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 ACTION: Proposed rule; correction. This document corrects an expiration date cited in the Notice of Proposed Rulemaking (NPRM) of the Senior Community Service Employment Program (SCSEP), Additional Indicator on Volunteer Work that was published on November 23, 2010. The NPRM updates the SCSEP regulations to add an indicator to measure the number of exiting participants who enter volunteer work. The relevant Office of Management and Budget (OMB) Control Number for SCSEP’s approved information collection is 1205–0040. The NPRM stated that the expiration date for 1205–0040 was October 31, 2010. However, that date is incorrect. The information collection is now pending with OMB, as the Department has requested a 3-year extension on the expiration of the approval date for it. Therefore 1205–0040 remains current on a month-by-month basis until OMB acts on the current information SUMMARY: E:\FR\FM\17DEP1.SGM 17DEP1

Agencies

[Federal Register Volume 75, Number 242 (Friday, December 17, 2010)]
[Proposed Rules]
[Pages 78937-78939]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-31782]

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-1185; Directorate Identifier 2009-NE-24-AD]
RIN 2120-AA64

Airworthiness Directives; Honeywell International LTS101 Series
Turboshaft Engines and LTP101 Series Turboprop Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.

-----------------------------------------------------------------------

SUMMARY: This supplemental NPRM revises an earlier proposed
airworthiness directive (AD), for Honeywell International LTS101-600A
series and LTS101-700D-2 turboshaft engines, and LTP101-600A-1A and
LTP101-700A-1A turboprop engines with power turbine blades, part number
(P/N) 4-141-084-06, installed. That proposed AD would have required
removing power turbine blades, P/N 4-141-084-06 from service, using a
drawdown schedule specified in that proposed AD. That proposal was
prompted by reports of fatigue cracks in the airfoil of the power
turbine blade. This action revises the proposed rule by expanding and
clarifying the applicability to include more engine models and power
turbine blade P/Ns that could have the unsafe condition, and by
clarifying the applicability by specifying power turbine rotor P/Ns
instead of the blade P/Ns. The actions specified by this proposed AD
are intended to prevent fracture of the power turbine blade airfoil,
which could result in sudden loss of engine power and prevent continued
safe flight or safe landing.

DATES: We must receive any comments on this proposed AD by February 15,
2011.

ADDRESSES: Use one of the following addresses to comment on this
proposed AD.
Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 1200 New Jersey Avenue, SE., West Building Ground
Floor, Room W12-140, Washington, DC 20590-0001.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Fax: (202) 493-2251.
Contact Honeywell International Inc., P.O. Box 52181, Phoenix, AZ
85072-2181; telephone (800) 601-3099 (U.S.A.) or (602) 365-3099
(International); or go to: https://portal.honeywell.com/wps/portal/aero, for a copy of the service information identified in this proposed
AD.

FOR FURTHER INFORMATION CONTACT: Robert Baitoo, Aerospace Engineer, Los
Angeles Aircraft Certification Office, FAA, Transport Airplane
Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; e-mail:
robert.baitoo@faa.gov; telephone (562) 627-5245; 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-2009-1185; Directorate
Identifier 2009-NE-24-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://www.regulations.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 Web site, anyone can find and read the comments in any
of our dockets, including, if provided, 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).

Examining the AD Docket

You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
the same as the Mail address provided in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.

[[Page 78938]]

Discussion

The FAA proposed to amend part 39 of the Federal Aviation
Regulations (14 CFR part 39) to add an AD, applicable to Honeywell
International LTS101-600A series and LTS101-700D-2 turboshaft engines,
and LTP101-600A-1A and LTP101-700A-1A turboprop engines. We published
the proposed AD in the Federal Register on December 21, 2009 (74 FR
67829). That action proposed to require removing power turbine blades,
P/N 4-141-084-06, from service using a specific drawdown schedule. That
NPRM was prompted by reports of fatigue cracks in the airfoil of the
power turbine blade. That condition, if not corrected, could result in
fracture of the power turbine blade airfoil, which could result in
sudden loss of engine power.
Since we issued that NPRM, Honeywell International Inc. informed us
that power turbine blades, P/N 4-141-084-03, could also have the unsafe
condition. Those blades are used in power turbine rotors P/Ns 4-141-
290-02 and 4-141-290-16. Based on the information we received from
Honeywell International Inc., we also determined that specifying the
applicability by power turbine rotors P/N is clearer than by specifying
the blade P/N.

Comments

We provided the public the opportunity to participate in the
development of that proposed AD. We have considered the comments
received on the original NPRM.

Proposed AD Should Apply to Engines on Multi-Engine Helicopters

One commenter, the National Transportation Safety Board (NTSB) asks
us to consider adding to the applicability of the proposed AD, engines
that also use the affected P/N turbine rotor blade, and are installed
on multi-engine helicopters. The NTSB states that loss of power in one
of the two engines is a safety issue.
We agree with the NTSB that the fracture of a power turbine airfoil
of an LTS101 series turboshaft engine installed on a twin-engine
helicopter is a safety issue. We added Honeywell International Inc.
LTS101-650B-1, LTS101-650C-3, LTS101-650C-3A, LTS101-750B-1, LTS101-
750B-2, LTS101-750C-1, and LTS101-850B-2 turboshaft engines that are
installed on twin-engine helicopters to the applicability of the
proposed AD. We also added to the applicability, paragraph (g), and
Table 1 of the proposed AD, Honeywell International Inc. LTP101-600A-1A
and LTP101-700A-1A turboprop engines that use the same blades.
The NTSB also requested that we reduce the drawdown schedule for
the affected blades to remove the at risk power turbine rotor blades
sooner.
We don't agree. Our risk assessment for the unsafe condition
doesn't justify accelerating the drawdown schedules.

Editorial Changes to Table 1 and Table 1 of the Proposed AD

We changed Table 1 and Table 2 in the proposed AD to eliminate
arbitrary step changes.
Since these changes expand the scope of the originally proposed
rule, we determined that reopening the comment period is appropriate.

FAA's Determination of an Unsafe Condition and Proposed Actions

Since an unsafe condition has been identified that is likely to
exist or develop on other Honeywell International Inc. LTS101-600A-2, -
3, -3A, LTS101-700D-2, LTS101-650B-1, LTS101-650C-3, LTS101-650C-3A,
LTS101-750B-1, LTS101-750B-2, LTS101-750C-1, and LTS101-850B-2
turboshaft engines; and LTP101-600A-1A and LTP101-700A-1A turboprop
engines of the same type design, the proposed AD would require removing
from service, power turbine rotors, P/Ns 4-141-290-01, -02, -03, -05, -
06, -11, -12, -13, -14, or -16, using the compliance drawdown schedule
specified in Table 1, and Table 2 of this AD.

Costs of Compliance

We estimate that this proposed AD would affect 240 engines
installed on aircraft of U.S. registry. We also estimate that it would
take about 30 work-hours per engine to perform the proposed actions,
and that the average labor rate is $85 per work-hour. Required parts
would cost about $70,000 per engine. Based on these figures, we
estimate the total cost of the proposed AD to U.S. operators to be
$17,412,000.

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 AD:
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. 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, Safety.

The Proposed Amendment

Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part 39 of the Federal Aviation Regulations (14 CFR part 39) as
follows:

PART 39--AIRWORTHINESS DIRECTIVES

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive:

Honeywell International Inc. (Formerly AlliedSignal, Textron
Lycoming): Docket No. FAA-2009-1185; Directorate Identifier 2009-NE-
24-AD.

Comments Due Date

(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by February 15,
2011.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Honeywell International LTS101-600A-2, -
3, -3A, LTS101-700D-2, LTS101-650B-1, LTS101-650C-3, LTS101-650C-3A,
LTS101-750B-1, LTS101-750B-2, LTS101-750C-1, and LTS101-850B-2
turboshaft engines; and LTP101-600A-1A and LTP101-700A-1A turboprop
engines with power turbine rotor, part number (P/N) 4-141-290-01, -
02, -03, -05, -06, -11, -12, -13, -14, or -16, installed. These
engines are installed on, but not limited to, Eurocopter AS350 and
BK117 series and Bell 222 series helicopters; and Page Thrush, Air
Tractor AT-302, and Pacific Aero 08-600, Piaggio P166 DL3, and Riley
International R421 airplanes.

[[Page 78939]]

Unsafe Condition

(d) This AD results from reports of fatigue cracks in the
airfoil of the power turbine blade. We are issuing this AD to
prevent fracture of the power turbine blade airfoil, which could
result in sudden loss of engine power and prevent continued safe
flight or safe landing.

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.
(f) For engines with power turbine rotors, P/Ns 4-141-290-11, -
12, -13, and -14, marked with ``ORI T41881,'' on the aft hub in the
vicinity of the P/N, no further action is required.

Removing Power Turbine Rotors From LTS101-600A-2, -3, -3A, and LTS101-
700D-2 Turboshaft Engines and LTP101-600A-1A and LTP101-700A-1A
Turboprop Engines

(g) For LTS101-600A-2, -3, -3A, and LTS101-700D-2 turboshaft
engines and LTP101-600A-1A and LTP101-700A-1A turboprop engines,
remove power turbine rotors, P/Ns 4-141-290-01, -02, -03, -05, -06,
-11, -12, -13, -14, or -16, using the cycles specified in Table 1 of
this AD:

Table 1--Drawdown Cycles for LTS101-600A-2, -3, -3A, and LTS101-700D-2
Turboshaft Engines and LTP101-600A-1A and LTP101-700A-1A Turboprop
Engines
------------------------------------------------------------------------
If power turbine rotor time on the Then remove the power turbine
effective date of this AD is * * * rotor from the engine * * *
------------------------------------------------------------------------
(1) Fewer than 5,000 cycles-since-new Between 5,000 and 5,500 CSN.
(CSN).
(2) 5,000 to 7,899 CSN................. Within 500 cycles-in-service
(CIS) after the effective date
of this AD or before exceeding
8,000 CSN, whichever occurs
first.
(3) 7,900 to 9,999 CSN................. Within 100 CIS after the
effective date of this AD or
before exceeding 10,050 CSN,
whichever occurs first.
(4) 10,000 or more CSN................. Within 50 CIS after the
effective date of this AD.
------------------------------------------------------------------------

Removing Power Turbine Rotors From LTS101-650B-1, -650C-3,--650C-3A, -
750B-1, -2, -750C-1, and -850B-2 Engines

(h) Remove power turbine rotors, P/Ns 4-141-290-01, -02 -03, -
05, -06, -11, -12, -13, -14, or -16, using the cycles specified in
Table 2 of this AD:

Table 2--Drawdown Cycles for LTS101-650B-1, -650C-3,-650C-3A, -750B-1, -
2, -750C-1, and -850B-2 Engines
------------------------------------------------------------------------
If power turbine rotor time on the Then remove the power turbine
effective date of this AD is * * * rotor from the engine * * *
------------------------------------------------------------------------
(1) Fewer than 5,500 CSN............... Between 5,000 and 7,200 CSN.
(2) 5,500 to 7,999 CSN................. Within 1,700 CIS after the
effective date of this AD or
before exceeding 8,950 CSN,
whichever occurs first.
(3) 8,000 to 9,999 CSN................. Within 950 CIS after the
effective date of this AD or
before exceeding 10,400 CSN,
whichever occurs first.
(4) 10,000 or more CSN................. Within 400 CIS after the
effective date of this AD.
------------------------------------------------------------------------

Alternative Methods of Compliance

(i) The Manager, Los Angles 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

(j) Contact Robert Baitoo, Aerospace Engineer, Los Angeles
Aircraft Certification Office, FAA, Transport Airplane Directorate,
3960 Paramount Blvd., Lakewood, CA 90712-4137; e-mail:
robert.baitoo@faa.gov; telephone (562) 627-5245; fax (562) 627-5210,
for more information about this AD.
(k) Honeywell International Inc. Service Bulletins LT 101-71-00-
0252 and LTS101-71-00-0253, pertain to the subject of this AD.
Contact Honeywell International Inc., P.O. Box 52181, Phoenix, AZ
85072-2181; telephone (800) 601-3099 (U.S.A.) or (602) 365-3099
(International); or go to: https://portal.honeywell.com/wps/portal/aero, for a copy of this service information.

Issued in Burlington, Massachusetts, on December 13, 2010.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2010-31782 Filed 12-16-10; 8:45 am]
BILLING CODE 4910-13-P

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