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contains regulatory documents having general

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are keyed to and codified in the Code of

Federal Regulations, which is published under

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Rules and Regulations Federal Register

18083 

Vol. 80, No. 64 

Friday, April 3, 2015 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0904; Directorate 

Identifier 2014–NE–14–AD; Amendment 39– 

18129; AD 2015–07–01] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Rolls-Royce plc (RR) RB211–524 

turbofan engines with certain part 

number (P/N) low-pressure turbine 

(LPT) stage 3 turbine blades installed. 

This AD requires implementation of a 

life limit for certain P/N LPT stage 3 

turbine blades and replacement of 

affected blades that reach or exceed the 

life limit. This AD was prompted by 

reports of LPT stage 3 turbine blade 

failures, release of blades, and 

subsequent in-flight shutdowns. We are 

issuing this AD to prevent failure of LPT 

stage 3 turbine blades and subsequent 

release of blade debris, which could 

lead to failure of one or more engines, 

loss of thrust control, and damage to the 

airplane. 

DATES: This AD becomes effective May 

8, 2015. 

ADDRESSES: For service information 

identified in this AD, contact RollsRoyce plc, Corporate Communications, 

P.O. Box 31, Derby, England, DE24 8BJ; 

phone: 011–44–1332–242424; fax: 011– 

44–1332–249936; email: http://

www.rolls-royce.com/contact/civil_

team.jsp; Internet: https://

www.aeromanager.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. It is also available on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2014–0904. 

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– 

0904; 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 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 

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: 

Kenneth Steeves, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7765; fax: 781–238– 

7199; email: kenneth.steeves@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on December 2, 2014 (79 FR 

71363). The NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Since 2006, a number of low pressure 

turbine (LPT) Stage 3 blade failures have 

been reported, each resulting in engine inflight shut-down. Engineering analysis on 

those occurrences indicates that blades with 

an accumulated life of 11,000 flight cycles 

(FC) or more have an increased risk of failure. 

This condition, if not detected and 

corrected, could lead to release of LPT Stage 

3 blade debris and consequent (partial or 

complete) loss of engine power, possibly 

resulting in reduced control of the aeroplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. The 

commenter supports the NPRM (79 FR 

71363, December 2, 2014). 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 2 

engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 120 hours per engine to 

comply with this AD. The average labor 

rate is $85 per hour. Parts cost is zero. 

Based on these figures, we estimate the 

cost of this AD on U.S. operators to be 

$20,400. 

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 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 this AD: 


asabaliauskas on DSK5VPTVN1PROD with RULES
18084 Federal Register / Vol. 80, No. 64 / Friday, April 3, 2015 / Rules and Regulations 

(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. 

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): 

2015–07–01 Rolls-Royce plc: Amendment 

39–18129; Docket No. FAA–2014–0904; 

Directorate Identifier 2014–NE–14–AD. 

(a) Effective Date 

This AD becomes effective May 8, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

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

RB211–524B–02, RB211–524B–B–02, 

RB211–524B2–19, RB211–524B2–B–19, 

RB211–524B3–02, RB211–524C2–19, and 

RB211–524C2–B–19 turbofan engines with 

low-pressure turbine (LPT) stage 3 turbine 

blade, part number (P/N) LK55386, LK86483, 

or LK86503, installed. 

(d) Reason 

This AD was prompted by reports of LPT 

stage 3 turbine blade failure, release of 

blades, and subsequent in-flight shutdown. 

We are issuing this AD to prevent failure of 

LPT stage 3 turbine blades and subsequent 

release of blade debris, which could lead to 

failure of one or more engines, loss of thrust 

control, and damage to the airplane. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Remove from service before further 

flight any LPT stage 3 turbine blade, P/N 

LK55386, LK86483, or LK86503, that exceeds 

11,000 flight cycles since new. 

(2) If you cannot determine the 

accumulated flight cycles, remove any LPT 

stage 3 turbine blade, P/N LK55386, 

LK86483, or LK86503, within 200 flight 

cycles after the effective date of this AD. 

(3) After the effective date of this AD, do 

not install any LPT stage 3 turbine blade, P/ 

N LK55386, LK86483, or LK86503, on any 

engine if the blade has accumulated 11,000 

or more flight cycles since new. 

(f) 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. 

(g) Related Information 

(1) For more information about this AD, 

contact Kenneth Steeves, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7765; fax: 781–238– 

7199; email: kenneth.steeves@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2014–0210, dated 

September 19, 2014, for more information. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0904-0002. 

(3) RR Alert Non-Modification Service 

Bulletin No. RB.211–72–AH790, Revision 1, 

dated November 5, 2014, which is not 

incorporated by reference in this AD, can be 

obtained from Rolls-Royce plc, using the 

contact information in paragraph (g)(4) of this 

AD. 

(4) For service information identified in 

this AD, contact Rolls-Royce plc, Corporate 

Communications, P.O. Box 31, Derby, 

England, DE24 8BJ; phone: 011–44–1332– 

242424; fax: 011–44–1332–249936; email: 

http://www.rolls-royce.com/contact/civil_

team.jsp; Internet: https://

www.aeromanager.com. 

(5) 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. 

(h) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

March 26, 2015. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2015–07492 Filed 4–2–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 95 

[Docket No. 31012; Amdt. No. 519] 

IFR Altitudes; Miscellaneous 

Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This amendment adopts 

miscellaneous amendments to the 

required IFR (instrument flight rules) 

altitudes and changeover points for 

certain Federal airways, jet routes, or 

direct routes for which a minimum or 

maximum en route authorized IFR 

altitude is prescribed. This regulatory 

action is needed because of changes 

occurring in the National Airspace 

System. These changes are designed to 

provide for the safe and efficient use of 

the navigable airspace under instrument 

conditions in the affected areas. 

DATES: Effective Date: 0901 UTC, April 

30, 2015. 

FOR FURTHER INFORMATION CONTACT: 

Harry Hodges, Flight Procedure 

Standards Branch (AMCAFS–420), 

Flight Technologies and Programs 

Division, Flight Standards Service, 

Federal Aviation Administration, Mike 

Monroney Aeronautical Center, 6500 

South MacArthur Blvd. Oklahoma City, 

OK 73169 (Mail Address: P.O. Box 

25082 Oklahoma City, OK 73125) 

telephone: (405) 954–4164. 

SUPPLEMENTARY INFORMATION: This 

amendment to part 95 of the Federal 

Aviation Regulations (14 CFR part 95) 

amends, suspends, or revokes IFR 

altitudes governing the operation of all 

aircraft in flight over a specified route 

or any portion of that route, as well as 

the changeover points (COPs) for 

Federal airways, jet routes, or direct 

routes as prescribed in part 95. 

The Rule 

The specified IFR altitudes, when 

used in conjunction with the prescribed 

changeover points for those routes, 

ensure navigation aid coverage that is 

adequate for safe flight operations and 

free of frequency interference. The 

reasons and circumstances that create 

the need for this amendment involve 

matters of flight safety and operational 

efficiency in the National Airspace 

System, are related to published 

aeronautical charts that are essential to 

the user, and provide for the safe and 

efficient use of the navigable airspace. 

In addition, those various reasons or 


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