Federal Register / Vol. 79, No. 191 / Thursday, October 2, 2014 / Proposed Rules 59461 

& 440) airplanes, certificated in any category, 

all manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 71, Powerplant. 

(e) Reason 

This AD was prompted by reports of 

dislodged engine fan cowl panels. We are 

issuing this AD to prevent damage to the 

fuselage and flight control surfaces from 

dislodged engine fan cowl panels. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Fastener Installation 

Within 6,000 flight hours after the effective 

date of this AD: Install attaching hardware on 

the left and right fan cowl access panels and 

the nacelle attaching structures, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

601R–71–034, Revision B, dated August 1, 

2014. 

(h) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using Bombardier Service 

Bulletin 601R–71–034, dated March 31, 2014; 

or Service Bulletin 601R–71–034, Revision A, 

dated April 28, 2014. This service 

information is not incorporated by reference 

in this AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7300; fax 516–794–5531. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, New York ACO, ANE–170, 

Engine and Propeller Directorate, FAA; or 

Transport Canada Civil Aviation (TCCA); or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–20, dated 

July 9, 2014, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2014–0750. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. You may view this 

service information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on 

September 24, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–23550 Filed 10–1–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0462; Directorate 

Identifier 2014–NE–06–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Corporation Turboprop and Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Rolls-Royce Corporation (RRC) AE 2100 

series turboprop engines and AE 3007A 

and 3007C series turbofan engines. This 

proposed AD was prompted by reports 

of pitting in the wheel bores and 

subsequent RRC analysis that concluded 

that lower life limits are needed for the 

affected turbine wheels. This proposed 

AD would reduce the approved life 

limits of the affected turbine wheels. 

This proposed AD would also require an 

eddy current inspection (ECI) of certain 

RRC engines with affected turbine 

wheels. We are proposing this AD to 

prevent uncontained failure of the 

turbine wheels, damage to the engine, 

and damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by December 1, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Rolls-Royce 

Corporation, 450 South Meridian Street, 

Mail Code NB–01–06, Indianapolis, IN 

46225, phone: 317–230–1667; email: 

CMSEindyOSD@rolls-royce.com; 

Internet: www.rolls-royce.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.gov by searching for 

and locating Docket No. FAA–2014– 

0462; 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 proposed 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: Kyri 

Zaroyiannis, Aerospace Engineer, 

Chicago Aircraft Certification Office, 

Small Airplane Directorate, FAA, 2300 

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

phone: 847–294–7836; fax: 847–294– 

7834; email: kyri.zaroyiannis@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2014–0462; Directorate Identifier 2014– 

NE–06–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 


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59462 Federal Register / Vol. 79, No. 191 / Thursday, October 2, 2014 / Proposed Rules 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 

Discussion 

Inspections during the manufacturing 

process revealed higher than normal 

pitting in the bore of certain turbine 

wheels due to a permanganate cleaning 

process. Analysis and subsequent 

testing by RRC of these affected turbine 

wheels indicated that these wheels, 

because of the potential for pitting in 

the wheel bores, could not be operated 

safely up to their published life limits. 

For RRC AE 2100 series turboprop 

engines, the affected turbine wheels are 

identified as 1st stage gas generator 

turbine wheels and as 4th stage turbine 

wheels. For the RRC AE 3007A and 

3007C series turbofan engines, the 

affected turbine wheels are identified as 

high-pressure turbine (HPT) stage 1 and 

stage 2 wheels. Operation of the affected 

wheels above the new lower limits 

represents an unsafe condition. 

We are also proposing an ECI for 

certain RRC AE 3007A engines with 

affected turbine wheels because our risk 

analysis shows that these engines are 

operated in a more stringent 

environment and therefore require 

periodic inspections to ensure these 

engines are operated safely. 

This condition, if not corrected, could 

result in uncontained failure of the 

turbine wheels, damage to the engine, 

and damage to the airplane. 

Relevant Service Information 

We reviewed RRC Alert Service 

Bulletin (ASB) No. AE 2100D2–A–72– 

085, dated July 25, 2013; RRC ASB No. 

AE 2100D3–A–72–277, dated July 25, 

2013; RRC ASB No. AE 2100P–A–72– 

019, dated July 25, 2013; RRC ASB No. 

AE 3007A–A–72–407, Revision 1, dated 

August 29, 2014; RRC ASB No. AE 

3007A–A–72–408, Revision 1, dated 

August 29, 2014; and RRC ASB No. AE 

3007C–A–72–316, dated December 6, 

2013. RRC ASB No. AE 3007A–A–72– 

408 provides instructions on performing 

an ECI of affected HPT stage 2 wheels. 

The other RRC ASBs list the lower 

approved life limits of the affected 

turbine wheels. 

FAA’s Determination 

We are proposing 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. 

Proposed AD Requirements 

This proposed AD would require an 

ECI of certain RRC engines with affected 

turbine wheels, and reduce the life 

limits of the affected turbine wheels. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 664 engines installed on 

airplanes of U.S. registry. We also 

estimate that it would take about 1 hour 

to perform an ECI in the bore of the 

turbine wheel for affected engines. The 

average labor rate is $85 per work-hour. 

We estimate the pro-rated replacement 

cost would be $30,688 for a 1st stage gas 

generator turbine wheel; $63,693 for an 

HPT stage 1 wheel; $13,941 for an HPT 

stage 2 wheel; and $13,186 for a 4th 

stage turbine wheel. We also estimate 

that these parts would be replaced 

during an engine shop visit at no 

additional labor cost. Based on these 

figures, we estimate the total cost of the 

AD to U.S. operators to be $11,317,969. 

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 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 this proposed regulation: 

(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), 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction, 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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. Amend § 39.13 by adding the 

following new airworthiness directive 

(AD): 

Rolls Royce Corporation (Formerly Allison 

Engine Company): Docket No. FAA– 

2014–0462; Directorate Identifier 2014– 

NE–06–AD. 

(a) Comments Due Date 

We must receive comments by December 1, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Rolls-Royce 

Corporation (RRC) AE 2100D2, 2100D2A, 

2100D3, and 2100P turboprop engines and 

AE 3007A1, A1/1, A1/3, A1E, A1P, A2, A3, 

C, C1, and C2 turbofan engines: 

(1) With an installed 1st stage gas generator 

turbine wheel, part number (P/N) 23079946, 

23088906, or 23089692, all serial numbers 

(S/Ns) listed in Table 2 and Table 3 of RRC 

Alert Service Bulletin (ASB) No. AE 2100D2– 

A–72–085, dated July 25, 2013; and in Table 

2 and Table 3 of RRC ASB No. AE 2100D3– 

A–72–277, dated July 25, 2013. 

(2) With an installed high-pressure turbine 

(HPT) stage 1 or HPT stage 2 wheel, P/N 

23079946, 23088906, 23088784, 23084520, 

23084781, 23088817, or 23088818, all S/Ns 

listed in Table 1 through Table 7 of RRC ASB 


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Federal Register / Vol. 79, No. 191 / Thursday, October 2, 2014 / Proposed Rules 59463 

No. AE 3007A–A–72–407, Revision 1, dated 

August 29, 2014, except those S/Ns excluded 

by Table 1, Table 2, Table 4, and Table 5 of 

RRC ASB No. AE 3007A–A–72–407, Revision 

1, dated August 29, 2014. 

(3) With an installed HPT stage 2 wheel, 

P/N 23084520 or 23088818, all S/Ns listed in 

Table 1 and Table 2 of RRC ASB No. AE 

3007C–A–72–316, dated December 6, 2013, 

except those S/Ns excluded by Table 1 of 

RRC ASB No. AE 3007C–A–72–316, dated 

December 6, 2013. 

(4) With an installed 4th stage turbine 

wheel, P/N 23083536, all S/Ns listed in Table 

2 of RRC ASB No. AE 2100P–A–72–019, 

dated July 25, 2013. 

(d) Unsafe Condition 

This AD was prompted by reports of 

pitting in the wheel bores and subsequent 

RRC analysis that concluded that lower life 

limits are needed for the affected turbine 

wheels. We are issuing this AD to prevent 

uncontained failure of the turbine wheels, 

damage to the engine, and damage to the 

airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) For all RRC AE 3007A1, A1/1, A1/3, 

A1E, A1P, and A3 series engines with an 

HPT stage 2 wheel P/N and S/N identified in 

RRC ASB No. AE 3007A–A–72–408, Revision 

1, dated August 29, 2014, at each shop visit 

after the effective date of this AD, eddy 

current inspect the bore of the affected HPT 

stage 2 wheels. Use RRC ASB AE 3007A–A– 

72–408, Revision 1, August 29, 2014, to do 

the inspection. Do not return to service any 

wheel that fails the inspection required by 

this AD. 

(2) Thirty days after the effective date of 

this AD, do not return to service any engine 

that has a turbine wheel with a P/N and an 

S/N listed in any of the following RR ASBs 

whose wheel life exceeds the new life limits 

identified in the RR ASBs: 

RRC ASB No. AE 2100D2–A–72–085, dated 

July 25, 2013; 

RRC ASB No. AE 2100D3–A–72–277, dated 

July 25, 2013; 

RRC ASB No. AE 2100P–A–72–019, dated 

July 25, 2013; 

RRC ASB No. AE 3007A–A–72–407, 

Revision 1, dated August 29, 2014; or 

RRC ASB No. AE 3007C–A–72–316, dated 

December 6, 2013. 

(f) Installation Prohibition 

Thirty days after the effective date of this 

AD, do not install an affected wheel, as 

identified in paragraph (c) of this AD, into 

any RRC AE 3007C2 engine. 

(g) Definition 

For the purpose of this AD, an ‘‘engine 

shop visit’’ is the induction of an engine into 

the shop for maintenance involving the 

separation of pairs of major mating engine 

flanges, except that the separation of engine 

flanges solely for the purposes of 

transportation without subsequent engine 

maintenance is not an engine shop visit. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Chicago Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Use the procedures 

found in 14 CFR 39.19 to make your request. 

(i) Related Information 

(1) For more information about this AD, 

contact Kyri Zaroyiannis, Aerospace 

Engineer, Chicago Aircraft Certification 

Office, Small Airplane Directorate, FAA, 

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

phone: 847–294–7836; fax: 847–294–7834; 

email: kyri.zaroyiannis@faa.gov. 

(2) RRC ASB No. AE 2100D2–A–72–085, 

dated July 25, 2013; RRC ASB No. AE 

2100D3–A–72–277, dated July 25, 2013; RRC 

ASB No. AE 2100P–A–72–019, dated July 25, 

2013; RRC ASB No. AE 3007A–A–72–407, 

Revision 1, dated August 29, 2014; RRC ASB 

No. AE 3007A–A–72–408, Revision 1, dated 

August 29, 2014; and RRC ASB No. AE 

3007C–A–72–316, dated December 6, 2013, 

which are not incorporated by reference in 

this AD, can be obtained from RRC using the 

contact information in paragraph (i)(3) of this 

AD. 

(3) For service information identified in 

this AD, contact Rolls-Royce Corporation, 

450 South Meridian Street, Mail Code NB– 

01–06, Indianapolis, IN 46225, phone: 317– 

230–1667; email: CMSEindyOSD@rollsroyce.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. For information on the availability of 

this material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

September 25, 2014. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–23561 Filed 10–1–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0961; Directorate 

Identifier 2011–NE–22–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Corporation Turboprop and Turboshaft 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2012–14– 

06, which applies to certain Rolls-Royce 

Corporation (RRC) 250–C20, –C20B, and 

–C20R/2 turboshaft engines. AD 2012– 

14–06 currently requires a one-time 

visual inspection and fluorescentpenetrant inspection (FPI) on certain 

3rd-stage and 4th-stage turbine wheels 

for cracks in the turbine blades. Since 

we issued AD 2012–14–06, we 

determined that the one-time inspection 

required by AD 2012–14–06 should be 

changed to repetitive inspections and 

that we should add an inspection after 

any engine hot start. We also identified 

additional engine models subject to the 

unsafe condition. This proposed AD 

would replace the one-time visual 

inspection and FPI with repetitive 

visual inspections and FPIs, and would 

also require inspection and FPI after any 

engine hot start. This proposed AD 

would also add certain engine models to 

the applicability. We are proposing 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: We must receive comments on 

this proposed AD by December 1, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Rolls-Royce 

Corporation, 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. 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.gov by 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 proposed AD, the 

regulatory evaluation, any comments 


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