5452 Federal Register / Vol. 80, No. 21 / Monday, February 2, 2015 / Rules and Regulations 

* * * * * 

WISCONSIN 

* * * * * 

Southwestern Wisconsin 

Survey Area 

Wisconsin: 

Chippewa 

Eau Claire 

La Crosse 

Monroe 

Trempealeau 

Area of Application. Survey area plus: 

Minnesota: 

Fillmore 

Houston 

Winona 

Wisconsin: 

Barron 

Buffalo 

Clark 

Crawford 

Dunn 

Florence 

Forest 

Jackson 

Juneau 

Langlade 

Lincoln 

Marathon 

Marinette 

Menominee 

Oneida 

Pepin 

Portage 

Price 

Richland 

Rusk 

Shawano 

Taylor 

Vernon 

Vilas 

Waupaca 

Wood 

* * * * * 

[FR Doc. 2015–01938 Filed 1–30–15; 8:45 am] 

BILLING CODE 6325–39–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0961; Directorate 

Identifier 2011–NE–22–AD; Amendment 39– 

18090; AD 2015–02–22] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Corporation Turboprop and Turboshaft 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2012–14– 

06 for certain Rolls-Royce Corporation 

(RRC) 250–C20, –C20B, and –C20R/2 

turboshaft engines. AD 2012–14–06 

required a one-time visual inspection 

and fluorescent-penetrant inspection 

(FPI) on certain 3rd-stage and 4th-stage 

turbine wheels for cracks in the turbine 

blades. This new AD replaces the onetime visual inspection and FPI with 

repetitive visual inspections and FPIs. 

This AD also adds certain engine 

models to the applicability. This AD 

was prompted by the determination that 

the one-time inspections required by AD 

2012–14–06 should be changed to 

repetitive inspections. We are issuing 

this AD to prevent failure of 3rd-stage 

and 4th-stage turbine wheel blades, 

which could cause engine failure and 

damage to the aircraft. 

DATES: This AD is effective March 9, 

2015. 

ADDRESSES: For service information 

identified in this AD, contact RollsRoyce Corporation, 450 South Meridian 

Street, Indianapolis, IN 46225–1103; 

phone: 888–255–4766 or 317–230–2720; 

email: helicoptercustsupp@rollsroyce.com; Internet: www.rollsroyce.com. You may view this 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.govby searching for 

and locating Docket No. FAA–2011– 

0961; 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: John 

Tallarovic, Aerospace Engineer, Chicago 

Aircraft Certification Office, FAA, 2300 

E. Devon Ave., Des Plaines, IL 60018; 

phone: 847–294–8180; fax: 847–294– 

7834; email: john.m.tallarovic@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2012–14–06, 

Amendment 39–17120 (77 FR 40479, 

July 10, 2012), (‘‘AD 2012–14–06’’). AD 

2012–14–06 applied to certain RRC 

250–C20, –C20B, and –C20R/2 

turboshaft engines. The NPRM 

published in the Federal Register on 

October 2, 2014 (79 FR 59463). The 

NPRM was prompted by determination 

that the one-time inspections required 

by AD 2012–14–06 should be changed 

to repetitive inspections. The NPRM 

proposed to replace the one-time visual 

inspection and FPI with repetitive 

visual inspections and FPIs, and also to 

require a visual inspection and FPI after 

any engine hot start. The NPRM also 

proposed to add certain engine models 

to the applicability. We are issuing this 

AD to prevent failure of 3rd-stage and 

4th-stage turbine wheel blades, which 

could cause engine failure and damage 

to the aircraft. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 59463, 

October 2, 2014) and the FAA’s 

response to each comment. 

Request To Remove a Certain Proposed 

Inspection Requirement 

RRC requested that we remove the 

requirement to inspect the 3rd-stage and 

4th-stage turbine wheels after a hot start 

because they are already prohibited 

from further use after a hot start by the 

maintenance instructions. 

We agree. Maintenance instructions 

clearly direct replacement of 3rd-stage 

and 4th-stage turbine wheels following 

a hot start. We removed from this AD 

the requirement to perform a visual 

inspection and an FPI on the affected 

turbine wheels after any hot start. 

Request To Limit Applicability 

RRC requested that we restrict 

applicability of the AD to only those 

affected engines that are installed on 

MD helicopters because the majority of 

failures have occurred on MD 

helicopters. 

We disagree. Failures have occurred 

in installations on other than MD 

helicopters. Also, the FAA cannot 

ensure that parts once used on MD 

helicopters have not been subsequently 

installed on other engines or helicopter 

models. We did not change this AD. 

Request To Delete a Certain Reference 

RRC requested that we remove, from 

the Actions Since AD 2012–14–06 Was 

Published paragraph, reference to 3rdstage turbine wheel failures by replacing 

the words ‘‘3rd-stage and’’ with the 

words ‘‘two additional’’ because 

additional failures only occurred in 4thstage turbine wheels. 


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Federal Register / Vol. 80, No. 21 / Monday, February 2, 2015 / Rules and Regulations 5453 

We agree. The new failures since AD 

2012–14–06 was published were in 4thstage turbine wheels. However, the 

paragraph, Actions Since AD 2012–14– 

06 was Published, which appeared in 

the NPRM (October 2, 2014 79 FR 

59463), does not appear in this final 

rule. We did not change this AD. 

Request To Revise a Certain Paragraph 

RRC requested that we add the word 

‘‘potential’’ before the word ‘‘failures’’ 

in the Actions Since AD 2012–14–06 

Was Published paragraph. 

We agree. However, the paragraph, 

Actions Since AD 2012–14–06 Was 

Published, which appeared in the 

NPRM (October 2, 2014 79 FR 59463), 

does not appear in this final rule. We 

did not change this AD. 

Request To Revise the Costs of 

Compliance 

RRC requested that we change, in the 

Costs of Compliance paragraph, the 

estimated time to conduct the 

inspection from one hour to two hours. 

We agree. We changed our estimate in 

this AD to reflect two hours of labor to 

conduct the inspection. 

Request To Revise the Labor Rate 

RRC requested that we change, in the 

Costs of Compliance paragraph, the 

labor rate from $85 per hour to $116 per 

hour. 

We disagree. The rate of $85 per hour 

is provided by the FAA Office of 

Aviation Policy and Plans for us to use 

when estimating the labor costs of 

complying with AD requirements. We 

did not change this AD. 

Request To Revise the Costs of 

Compliance 

RRC requested that we add the word 

‘‘initial’’ before the stated cost in the 

Costs of Compliance paragraph. 

We partially agree. We did not insert 

the word ‘‘initial’’, but we clarified that 

our estimate of costs of compliance are 

for one inspection, whether initial or 

recurring. 

Request To Revise a Definition 

RRC requested that we change our 

definition of a hot start. 

We partially agree. We agree with the 

suggested changes because they clarify 

the definition of a hot start. However, in 

our reply to a prior comment, we agreed 

to remove the inspection requirements 

associated with a hot start. Therefore, 

we have deleted all requirements in this 

AD to conduct inspections after hot 

starts, and have deleted the Definition 

paragraph. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously. 

We have determined that these minor 

changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

59463, October 2, 2014) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 59463, 

October 2, 2014). 

We also determined that these 

changes will not significantly increase 

the economic burden on any operator or 

increase the scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 3,769 

engines installed on aircraft of U.S. 

registry. We also estimate that it will 

take about 2 hours per engine to comply 

with the inspection requirement of this 

AD. The average labor rate is $85 per 

hour. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators for one inspection to be 

$640,730. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this 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 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) 

2012–14–06, Amendment 39–17120 (77 

FR 40479, July 10, 2012), and adding the 

following new AD: 

2015–02–22 Rolls-Royce Corporation: 

Amendment 39–18090; Docket No. 

FAA–2011–0961; Directorate Identifier 

2011–NE–22–AD. 

(a) Effective Date 

This AD is effective March 9, 2015. 

(b) Affected ADs 

This AD supersedes AD 2012–14–06, 

Amendment 39–17120 (77 FR 40479, July 10, 

2012). 

(c) Applicability 

This AD applies to Rolls-Royce 

Corporation (RRC) 250–B17, –B17B, –B17C, 

–B17D, –B17E, –B17F, –B17F/1, –B17F/2 

turboprop engines; and 250–C20, –C20B, 

–C20F, –C20J, –C20R, –C20R/1, –C20R/2, 

–C20R/4, –C20S, and –C20W turboshaft 

engines; with either a 3rd-stage turbine 

wheel, part number (P/N) 23065818, or a 4thstage turbine wheel, P/N 23055944, installed. 

(d) Unsafe Condition 

This AD was prompted by investigations 

that revealed that not all 3rd-stage and 4thstage turbine wheel blade failures were 

identified by the one-time inspections 

required by AD 2012–14–06, Amendment 

39–17120 (77 FR 40479, July 10, 2012). We 

determined that to address the unsafe 

condition, repetitive inspections are 


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5454 Federal Register / Vol. 80, No. 21 / Monday, February 2, 2015 / Rules and Regulations 

required, triggered by hours since last 

inspection (HSLI). We are issuing this AD to 

prevent failure of 3rd-stage and 4th-stage 

turbine wheel blades, which could cause 

engine failure and damage to the aircraft. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. After the effective date of this AD: 

(1) Within 1,750 HSLI, remove the affected 

turbine wheels and perform a visual 

inspection and a fluorescent-penetrant 

inspection (FPI) on the removed turbine 

wheels for cracks at the trailing edge of the 

turbine blades near the fillet at the rim. 

(2) Any time the power turbine is 

disassembled, perform a visual inspection 

and an FPI on the affected turbine wheels for 

cracks at the trailing edge of the turbine 

blades, near the fillet at the rim. 

(3) Thereafter, re-inspect every 1,750 HSLI. 

(4) Do not return to service any turbine 

wheels that have cracks detected. 

(f) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Chicago Aircraft 

Certification Office, may approve AMOCs for 

this AD. Use the procedures found in 14 CFR 

39.19 to make your request. 

(g) Related Information 

(1) For more information about this AD, 

contact John Tallarovic, Aerospace Engineer, 

Chicago Aircraft Certification Office, FAA, 

2300 E. Devon Ave., Des Plaines, IL 60018; 

phone: 847–294–8180; fax: 847–294–7834; 

email: john.m.tallarovic@faa.gov. 

(2) RRC Alert Commercial Engine Bulletin 

(CEB) No. CEB–A–1407, Revision 3, dated 

May 19, 2014, and Alert CEB No. CEB–A–72– 

4098, Revision 3, dated May 19, 2014 

(combined into one document), which are 

not incorporated by reference in this AD, can 

be obtained from RRC, using the contact 

information in paragraph (g)(3) of this AD. 

(3) For service information identified in 

this AD, contact Rolls-Royce Corporation 

Customer Support, 450 South Meridian 

Street, Indianapolis, IN 46225–1103; phone: 

888–255–4766 or 317–230–2720; email: 

helicoptercustsupp@rolls-royce.com; 

Internet: www.rolls-royce.com. 

(4) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA 01803. For information on the 

availability of this material at the FAA, call 

781–238–7125. 

(h) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

January 20, 2015. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2015–01371 Filed 1–30–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0049; Directorate 

Identifier 2014–SW–037–AD; Amendment 

39–18096; AD 2015–02–27] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Previously Eurocopter 

France) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2013–19– 

19 for certain Eurocopter France Model 

AS332C, AS332L, AS332L1, AS332L2, 

and EC225LP helicopters. AD 2013–19– 

19 required replacing certain serialnumbered main gearbox (MGB) bevel 

gear vertical shafts and inspecting and 

replacing, if necessary, each MGB bevel 

gear vertical shaft (shaft). This new AD 

requires the same actions as AD 2013– 

19–19 but corrects an error in the term 

used to identify an inspection 

qualification and updates the type 

certificate holder’s name. This AD is 

prompted by two incidents of 

emergency ditching after warning 

indications of loss of MGB oil pressure. 

These actions are intended to detect a 

cracked shaft, which could result in loss 

of MGB oil pressure, loss of the MGB 

lubrication system, and subsequent loss 

of control of the helicopter. 

DATES: This AD is effective February 17, 

2015. 

We must receive comments on this 

AD by April 3, 2015. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

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

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

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 AD, the European 

Aviation Safety Agency (EASA) AD, the 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

Office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

For service information identified in 

this AD, contact Airbus Helicopters, 

Inc., 2701 N. Forum Drive, Grand 

Prairie, TX 75052; telephone (972) 641– 

0000 or (800) 232–0323; fax (972) 641– 

3775; or at http://

www.airbushelicopters.com/techpub. 

You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

FOR FURTHER INFORMATION CONTACT: 

James Blyn, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

james.blyn@faa.gov. 

SUPPLEMENTARY INFORMATION: 

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 prior to it becoming effective. 

However, we invite you to participate in 

this rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit them only one time. We will file 

in the docket all comments that we 

receive, as well as a report summarizing 

each substantive public contact with 

FAA personnel concerning this 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

Discussion 

On September 9, 2013, we issued AD 

2013–19–19 (78 FR 60188, October 1, 

2013), which required replacing certain 


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