Federal Register / Vol. 76, No. 70 / Tuesday, April 12, 2011 / Rules and Regulations 20231 

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: http:// 

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 

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 http:// 

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. 


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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. 

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 AD is . . . Then remove the power turbine rotor from the engine . . . 

(1) Fewer than 5,000 cycles-since-new (CSN) .. Between 5,000 and 5,500 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 AD is . . . Then remove the power turbine 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; 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 


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