Airworthiness Directives; Honeywell International Inc. LTS101 Series Turboshaft Engines and LTP101 Series Turboprop Engines, 20231-20232 [2011-8470]

Download as PDF Federal Register / Vol. 76, No. 70 / Tuesday, April 12, 2011 / Rules and Regulations U.S.C. 552(a) and 1 CFR part 51, as of October 1, 1998 (63 FR 49416, September 16, 1998). (2) For service information identified in this AD, contact Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United Kingdom; telephone 44 1332 242424; fax 44 1332 249936; e-mail: tech.help@rolls-royce.com. (3) You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. For information on the availability of this material at the FAA, call 781–238–7125. Issued in Burlington, Massachusetts, on April 5, 2011. Peter A. White, Acting Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2011–8469 Filed 4–11–11; 8:45 am] BILLING CODE 4910–13–P referenced service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–1185; Directorate Identifier 2009–NE–24–AD; Amendment 39–16656; AD 2011–08–06] Robert Baitoo, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712–4137; phone: 562–627–5245; fax: 562–627–5210; e-mail: robert.baitoo@faa.gov. SUPPLEMENTARY INFORMATION: RIN 2120–AA64 Discussion Airworthiness Directives; Honeywell International Inc. LTS101 Series Turboshaft Engines and LTP101 Series Turboprop Engines We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That SNPRM published in the Federal Register on December 17, 2010 (75 FR 78937). The original notice of proposed rulemaking (74 FR 67829, December 21, 2009) proposed to require removing power turbine blades, part number (P/N) 4–141–084–06 from service, using a drawdown schedule. The SNPRM proposed to require expanding and clarifying the applicability to include more engine models and power turbine blade P/Ns that could have the unsafe condition, and clarifying the applicability by specifying power turbine rotor P/Ns instead of the blade P/Ns. Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires removing certain power turbine rotors from service using a specific drawdown schedule. This AD was prompted by reports of fatigue cracks in the airfoil of the power turbine blades. 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. DATES: This AD is effective May 17, 2011. ADDRESSES: For service information identified in this AD, contact Honeywell International Inc., P.O. Box 52181, Phoenix, AZ 85072–2181; phone: 800– 601–3099 (U.S.A.) or 602–365–3099 (International); or go to: https:// portal.honeywell.com/wps/portal/aero. You may review copies of the erowe on DSK5CLS3C1PROD with RULES SUMMARY: VerDate Mar<15>2010 15:01 Apr 11, 2011 Jkt 223001 Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the SNPRM. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting the AD as proposed. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 20231 Costs of Compliance We estimate that this AD will affect 240 engines installed on aircraft of U.S. registry. We also estimate that it will take about 30 work-hours per engine to perform the actions, and that the average labor rate is $85 per work-hour. If all removed power turbine rotors get replaced, required parts will cost about $70,000 per engine. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $17,412,000. 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 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), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. E:\FR\FM\12APR1.SGM 12APR1 20232 Federal Register / Vol. 76, No. 70 / Tuesday, April 12, 2011 / Rules and Regulations Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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 (AD): ■ 2011–08–06 Honeywell International Inc. (Formerly AlliedSignal, Textron Lycoming): Amendment 39–16656; Docket No. FAA–2009–1185; Directorate Identifier 2009–NE–24–AD. Effective Date (a) This AD is effective May 17, 2011. Affected ADs (b) None. power and prevent continued safe flight or safe landing. 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. Compliance 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 (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 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 ...................................... erowe on DSK5CLS3C1PROD with RULES (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. Related Information (j) Contact Robert Baitoo, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA VerDate Mar<15>2010 15:01 Apr 11, 2011 Jkt 223001 90712–4137; phone: 562–627–5245; fax: 562– 627–5210; e-mail: robert.baitoo@faa.gov, 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. PO 00000 Frm 00016 Fmt 4700 Sfmt 9990 Issued in Burlington, Massachusetts, on March 30, 2011. Peter A. White, Acting Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2011–8470 Filed 4–11–11; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\12APR1.SGM 12APR1

Agencies

[Federal Register Volume 76, Number 70 (Tuesday, April 12, 2011)]
[Rules and Regulations]
[Pages 20231-20232]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-8470]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-1185; Directorate Identifier 2009-NE-24-AD; 
Amendment 39-16656; AD 2011-08-06]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD requires removing certain power turbine 
rotors from service using a specific drawdown schedule. This AD was 
prompted by reports of fatigue cracks in the airfoil of the power 
turbine blades. 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.

DATES: This AD is effective May 17, 2011.

ADDRESSES: For service information identified in this AD, contact 
Honeywell International Inc., P.O. Box 52181, Phoenix, AZ 85072-2181; 
phone: 800-601-3099 (U.S.A.) or 602-365-3099 (International); or go to: 
https://portal.honeywell.com/wps/portal/aero. You may review copies of 
the referenced service information at the FAA, Engine & Propeller 
Directorate, 12 New England Executive Park, Burlington, MA. For 
information on the availability of this material at the FAA, call 781-
238-7125.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (phone: 800-647-5527) is Document Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Robert Baitoo, Aerospace Engineer, Los 
Angeles Aircraft Certification Office, FAA, Transport Airplane 
Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; phone: 562-
627-5245; fax: 562-627-5210; e-mail: robert.baitoo@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 to include an AD that would apply to the specified 
products. That SNPRM published in the Federal Register on December 17, 
2010 (75 FR 78937). The original notice of proposed rulemaking (74 FR 
67829, December 21, 2009) proposed to require removing power turbine 
blades, part number (P/N) 4-141-084-06 from service, using a drawdown 
schedule. The SNPRM proposed to require expanding and clarifying the 
applicability to include more engine models and power turbine blade P/
Ns that could have the unsafe condition, and clarifying the 
applicability by specifying power turbine rotor P/Ns instead of the 
blade P/Ns.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the SNPRM.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting the AD as proposed.

Costs of Compliance

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

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

    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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

[[Page 20232]]

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA 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 (AD):

2011-08-06 Honeywell International Inc. (Formerly AlliedSignal, 
Textron Lycoming): Amendment 39-16656; Docket No. FAA-2009-1185; 
Directorate Identifier 2009-NE-24-AD.

Effective Date

    (a) This AD is effective May 17, 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.

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 effective date of this   Then remove the power turbine rotor from
         AD is . . .                        the engine . . .
------------------------------------------------------------------------
(1) Fewer than 5,000 cycles-   Between 5,000 and 5,500 CSN.
 since-new (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 effective date of this   Then remove the power turbine rotor from
         AD is . . .                        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; phone: 562-627-5245; 
fax: 562-627-5210; e-mail: robert.baitoo@faa.gov, 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 March 30, 2011.
Peter A. White,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-8470 Filed 4-11-11; 8:45 am]
BILLING CODE 4910-13-P