Federal Register / Vol. 76, No. 70 / Tuesday, April 12, 2011 / Rules and Regulations 20229 

necessary. For each calendar year, FSIS 

will calculate the overtime rate for 

inspection service, per hour per 

program employee, using the following 

formula: The quotient of dividing the 

Office of Field Operations plus Office of 

International Affairs inspection program 

personnel’s previous fiscal year’s 

regular direct pay by previous fiscal 

year’s regular hours, plus the quotient 

multiplied by the calendar year’s 

percentage of cost of living increase 

multiplied by 1.5, plus the benefits rate, 

plus the travel and operating rate, plus 

the overhead rate, plus the allowance 

for bad debt rate. FSIS calculates the 

benefits rate, the travel and operating 

rate, the overhead rate, and the 

allowance for bad debt using the 

formulas set forth in § 592.510(b), and 

the cost of living increases and 

percentage of inflation factors set forth 

in § 592.510(c). 

■ 12. In § 592.530, remove the second 

sentence and add three sentences in its 

place to read as follows: 

§ 592.530 Holiday rate. 

* * * The official plant must, in 

advance of such holiday work, request 

that the inspector in charge furnish 

inspection services during such period 

and must pay the Agency for such 

holiday work at the hourly rate. For 

each calendar year, FSIS will calculate 

the holiday rate for inspection service, 

per hour per program employee, using 

the following formula: The quotient of 

dividing the Office of Field Operations 

plus Office of International Affairs 

inspection program personnel’s 

previous fiscal year’s regular direct pay 

by previous fiscal year’s regular hours, 

plus the quotient multiplied by the 

calendar year’s percentage of cost of 

living increase, multiplied by 2, plus the 

benefits rate, plus the travel and 

operating rate, plus the overhead rate, 

plus the allowance for bad debt rate. 

FSIS calculates the benefits rate, the 

travel and operating rate, the overhead 

rate, and the allowance for bad debt 

using the formulas set forth in 

§ 592.510(b), and the cost of living 

increases and percentage of inflation 

factors set forth in § 592.510(c). 

Done in Washington, DC, on April 7, 2011. 

Alfred V. Almanza, 

Administrator. 

[FR Doc. 2011–8699 Filed 4–11–11; 8:45 am] 

BILLING CODE 3410–DM–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0233; Directorate 

Identifier 98–ANE–10–AD; Amendment 

39–16660; AD 2011–08–10] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc (RR) RB211–Trent 768–60 and 

Trent 772–60 Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

RR RB211–Trent 700 series turbofan 

engines. That AD currently requires, for 

the step aside gearbox (SAGB), 

repositioning of the oil metering jet up 

into the oil distributor within the bevel 

gearshaft, followed by initial and 

repetitive visual inspections of the 

magnetic chip detector (MCD). Since we 

issued that AD, RR has demonstrated 

that the repositioning of the oil metering 

jet eliminates the need for the repetitive 

inspections. This AD changes the 

applicability from RB211–Trent 700 

series turbofan engines, to RB211–Trent 

768–60 and Trent 772–60 turbofan 

engines. This AD also eliminates the 

visual inspections of the MCD from the 

AD requirements. This AD was 

prompted by RR demonstrating that the 

repositioning of the oil metering jet 

eliminates the need for the repetitive 

inspections, by the need to correct the 

AD applicability, and by the need to 

eliminate the visual inspections of the 

MCD. We are issuing this AD to prevent 

in-flight engine shutdowns caused by 

SAGB driving bevel gearshaft ball 

bearing failure. 

DATES: This AD is effective April 27, 

2011. 

The Director of the Federal Register 

previously approved the incorporation 

by reference of a certain publication 

listed in this AD as of October 1, 1998 

(63 FR 49416, September 16, 1998). 

We must receive any comments on 

this AD by May 27, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

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. 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 street address for 

the Docket Office (phone: 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Alan Strom, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

telephone 781–238–7143; fax 781–238– 

7199; e-mail: alan.strom@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On September 8, 1998, we issued AD 

98–19–12, Amendment 39–10754 (63 

FR 49416, September 16, 1998), for RR 

RB211–Trent 700 series turbofan 

engines. That AD requires, for the 

SAGB, repositioning of the oil metering 

jet up into the oil distributor within the 

bevel gearshaft, followed by initial and 

repetitive visual inspections of the 

MCD. That AD resulted from reports of 

uncommanded engine shutdowns 

caused by failure of the SAGB driving 

bevel gearshaft ball bearing due to oil 

starvation. We issued that AD to prevent 

in-flight engine shutdowns caused by 

SAGB driving bevel gearshaft ball 

bearing failure. 

Actions Since AD Was Issued 

Since we issued AD 98–19–12, RR has 

demonstrated that the repositioning of 

the oil metering jet eliminates the need 

for the repetitive inspections. Also, 

since we issued that AD, Rolls Royce 

put into service, its RB211–Trent 772B– 


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20230 Federal Register / Vol. 76, No. 70 / Tuesday, April 12, 2011 / Rules and Regulations 

60 model turbofan engine, which does 

not have the unsafe condition that AD 

sought to correct. Since the AD 

applicability states that it is for RB211– 

Trent 700 series turbofan engines, that 

applicability includes the RB211–Trent 

772B–60 engines, and it shouldn’t. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

AD Requirements 

This AD retains the oil metering jet 

repositioning requirements of AD 

98–19–12. This AD also eliminates the 

initial and repetitive visual inspections 

of the MCD, required by AD 98–19–12. 

This AD also corrects the applicability 

from RB211–Trent 700 series turbofan 

engines, to, RB211–Trent 768–60 

turbofan engines prior to serial No. 

41052, and RB211–Trent 772–60 

turbofan engines prior to serial No. 

41052. 

FAA’s Justification and Determination 

of the Effective Date 

Since no domestic operators use 

RB211–Trent 768–60 or RB211–Trent 

772–60 turbofan engines, we find that 

notice and opportunity for prior public 

comment are unnecessary and that good 

cause exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the docket number 

FAA–2011–0233 and Directorate 

Identifier 98–ANE–10–AD at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD affects no 

engines installed on airplanes of U.S. 

registry. The elimination of visual 

inspection requirements by this AD, 

adds no additional economic burden. 

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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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 

removing airworthiness directive (AD) 

98–19–12, Amendment 39–10754 (63 

FR 49416, September 16, 1998), and 

adding the following new AD: 

2011–08–10 Rolls-Royce plc: Amendment 

39–16660; Docket No. FAA–2011–0233; 

Directorate Identifier 98–ANE–10–AD. 

Effective Date 

(a) This AD is effective April 27, 2011. 

Affected ADs 

(b) This AD supersedes AD 98–19–12, 

Amendment 39–10754. 

Applicability 

(c) This AD applies to Rolls-Royce plc (RR) 

RB211–Trent 768–60 turbofan engines prior 

to serial No. 41052, and RB211–Trent 772– 

60 turbofan engines prior to serial No. 41052. 

Unsafe Condition 

(d) This AD was prompted by RR 

demonstrating that the repositioning of the 

oil metering jet eliminates the need for the 

repetitive inspections, by the need to correct 

the AD applicability, and by the need to 

eliminate the visual inspections of the MCD. 

We are issuing this AD to prevent in-flight 

engine shutdowns caused by step aside 

gearbox (SAGB) driving bevel gearshaft ball 

bearing failure. 

Compliance 

(e) Comply with this AD before further 

flight, unless already done. 

Repositioning of the Oil Metering Jet 

(f) Reposition the oil metering jet up into 

the oil distributor within the bevel gearshaft, 

using RR Service Bulletin No. RB.211 72– 

C270, dated June 1, 1997. 

Alternative Methods of Compliance 

(AMOCs) 

(g) The Manager, Engine Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(h) For more information about this AD, 

contact Alan Strom, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

telephone 781–238–7143; fax 781–238–7199; 

e-mail: alan.strom@faa.gov. 

Material Incorporated by Reference 

(i) You must use Rolls-Royce plc Service 

Bulletin No. RB.211 72–C270, dated June 1, 

1997, to do the actions required by this AD. 

(1) The Director of the Federal Register 

previously approved the incorporation by 

reference of this service information under 5 


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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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