76402 Federal Register / Vol. 80, No. 236 / Wednesday, December 9, 2015 / Proposed Rules 

Issued in Burlington, Massachusetts, on 

December 3, 2015. 

Colleen M. D’Alessandro, 

Directorate Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–30948 Filed 12–8–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4076; Directorate 

Identifier 2015–NE–30–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc 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 plc (RR) RB211–22B and 

RB211–524 turbofan engines with lowpressure turbine (LPT) support roller 

bearing, part number (P/N) LK30313 or 

P/N UL29651, installed. This proposed 

AD was prompted by a report of a 

breach of the turbine casing and release 

of engine debris. This proposed AD 

would require removal of certain LPT 

support roller bearings installed in RR 

RB211–22B and RB211–524 engines. We 

are proposing this AD to prevent failure 

of the LPT support roller bearing, loss 

of radial position following LPT blade 

failure, uncontained part release, 

damage to the engine, and damage to the 

airplane. 

DATES: We must receive comments on 

this proposed AD by February 8, 2016. 

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. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: 202–493–2251. 

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–2015– 

4076; 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 proposed AD, the 

mandatory continuing airworthiness 

information (MCAI), the regulatory 

evaluation, any comments received, and 

other information. The 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: 

Brian Kierstead, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7772; fax: 781–238– 

7199; email: brian.kierstead@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–4076; Directorate Identifier 

2015–NE–30–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on 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 with FAA 

personnel concerning this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2015– 

0187, dated September 9, 2015 (referred 

to hereinafter as ‘‘the MCAI’’), to correct 

an unsafe condition for the specified 

products. The MCAI states: 

An RB211–524G2–T engine experienced an 

in-service event that resulted in breach of a 

turbine casing and some release of core 

engine debris through a hole in the engine 

nacelle. The investigation of the event 

determined the primary cause to have been 

fracture and release of a Low Pressure (LP) 

turbine stage 2 blade. The blade release 

caused secondary damage to the LP turbine, 

producing significant out-of-balance forces. 

The event engine was fitted with an LP 

turbine support bearing where the roller 

retention cage is constructed from two halves 

that are riveted together. The LP turbine 

imbalance resulted in an overload of the LP 

turbine support bearing and caused 

separation of the riveted, two-piece roller 

retention cage. Radial location of the LP 

turbine shaft was lost, allowing further 

progression of the event that resulted in a 

breach of the IP turbine casing. 

RR introduced a modified LPT 

support roller bearing that can 

withstand greater loads when an LPT 

turbine blade release occurs, thereby 

preventing LPT rotor movement. You 

may obtain further information by 

examining the MCAI in the AD docket 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

4076. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of the United 

Kingdom, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the European 

Community, EASA has notified us of 

the unsafe condition described in the 

MCAI. We are proposing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other products of the 

same type design. This proposed AD 

would require removal from service of 

the affected LPT support bearings. 

Costs of Compliance 

We estimate that this proposed AD 

affects 9 engines installed on airplanes 

of U.S. registry. We also estimate it 

would take 0 hours to comply with this 

proposed AD since the proposed actions 

required by the AD would be performed 

during a shop visit, when major engine 

flanges are separated, which requires 

the removal of the LPT support roller 

bearing. Therefore, no additional time is 

needed to remove it. Parts would cost 

about $8,184 per engine. The average 

labor rate is $85 per hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $73,656. 

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 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 80, No. 236 / Wednesday, December 9, 2015 / Proposed Rules 76403 

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. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Rolls-Royce plc: Docket No. FAA–2015– 

4076; Directorate Identifier 2015–NE– 

30–AD. 

(a) Comments Due Date 

We must receive comments by February 8, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Rolls-Royce plc RB211– 

22B–02, RB211–22B (MOD 72–8700), RB211– 

524B–02, RB211–524B–B–02, RB211–524B2– 

19, RB211–524B2–B–19, RB211–524B3–02, 

RB211–524B4–02, RB211–524B4–D–02, 

RB211–524C2–19, RB211–524C2–B–19, 

RB211–524D4–19, RB211–524D4–B–19, 

RB211–524D4X–19, RB211–524D4X–B–19, 

RB211–524D4–39, RB211–524D4–B–39, 

RB211–524G2–19, RB211–524G3–19, 

RB211–524–G2–T–19, RB211–524G3–T–19, 

RB211–524H–36, RB211–524H2–19, RB211– 

524H–T–36, and RB211–524H2–T–19 

turbofan engines, all serial numbers, with 

low-pressure turbine (LPT) support roller 

bearing, part number (P/N) LK30313 or P/N 

UL29651, installed. 

(d) Reason 

This AD was prompted by a report of a 

breach of the turbine casing and release of 

engine debris through a hole in the engine 

nacelle. We are issuing this AD to prevent 

failure of the LPT support roller bearing, loss 

of radial position following LPT blade 

failure, uncontained part release, damage to 

the engine, and damage to the airplane. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. At the next shop visit or within 24 

months after the effective date of this AD, 

whichever occurs first, remove from service 

LPT support roller bearing, P/N LK30313 or 

P/N UL29651, and replace with a part 

eligible for installation. 

(f) Installation Prohibition 

After the effective date of this AD, do not 

install an LPT support roller bearing, P/N 

LK30313 or P/N UL29651, onto any engine. 

(g) Definition 

For the purpose of this AD, a ‘‘shop visit’’ 

is defined as 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 does not constitute an engine 

shop visit. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. You may email your 

request to: ANE-AD-AMOC@faa.gov. 

(i) Related Information 

(1) For more information about this AD, 

contact Brian Kierstead, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7772; fax: 781–238–7199; 

email: brian.kierstead@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2015–0187, dated 

September 9, 2015, for more information. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2015–4076. 

Issued in Burlington, Massachusetts, on 

December 2, 2015. 

Colleen M. D’Alessandro, 

Directorate Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–30947 Filed 12–8–15; 8:45 am] 

BILLING CODE 4910–13–P 

ENVIRONMENTAL PROTECTION 

AGENCY 

40 CFR Part 52 

[EPA–R05–OAR–2014–0362; FRL–9939–76– 

Region 5] 

Air Plan Approval; Ohio; Regional 

Haze Glatfelter BART SIP Revision 

AGENCY: Environmental Protection 

Agency (EPA). 

ACTION: Proposed rule. 

SUMMARY: The Environmental Protection 

Agency (EPA) is proposing to extend the 

compliance date for the Best Available 

Retrofit Technology (BART) emission 

limits for sulfur dioxide (SO2) at the 

P.H. Glatfelter Company (Glatfelter) 

facility submitted as part of its State 

Implementation Plan (SIP) Revision on 

April 14, 2014. Specifically, EPA is 

proposing to extend the compliance 

date for the SO2 emission limits 

applicable to Boilers No. 7 and No. 8 at 

Glatfelter by 25 months, from December 

31, 2014, to January 31, 2017. We have 

reviewed this SIP revision and 

concluded that it meets the 

requirements of the Clean Air Act and 

the regional haze rule and because 

BART requirements continue to be met. 

DATES: Comments must be received on 

or before January 8, 2016. 

ADDRESSES: Submit your comments, 

identified by Docket ID No. EPA–R05– 

OAR–2014–0362, by one of the 

following methods: 

1. www.regulations.gov: Follow the 

on-line instructions for submitting 

comments. 

2. Email: aburano.douglas@epa.gov. 

3. Fax: (312) 408–2279. 

4. Mail: Douglas Aburano, Chief, 

Attainment Planning and Maintenance 

Section, Air Programs Branch (AR–18J), 

U.S. Environmental Protection Agency, 

77 West Jackson Boulevard, Chicago, 

Illinois 60604. 

5. Hand Delivery: Douglas Aburano, 

Chief, Attainment Planning and 

Maintenance Section, Air Programs 

Branch (AR–18J), U.S. Environmental 

Protection Agency, 77 West Jackson 

Boulevard, Chicago, Illinois 60604. 

Such deliveries are only accepted 

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