[4910-13-P] 

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 pic Turbofan Engines 

AGENCY: Federal Aviation Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new airworthiness directive (AD) for certain RollsRoyce plc (RR) RB211-524 turbofan engines with certain part number (PIN) lowpressure turbine (LPT) stage 3 turbine blades installed. This AD requires implementation 

of a life limit for certain PIN 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 [INSERT DATE 35 DAYS AFTER DATE OF 

PUBLICATION IN THE FEDERAL REGISTER]. 

ADDRESSES: 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.rollsroyce.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 ofthis 

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. F AA-20 14-0904; 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. 

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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: 

Comments 

Since 2006, a number of low pressure turbine (LPT) Stage 3 blade 

failures have been reported, each resulting in engine in-flight shutdown. 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. 

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. 

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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: 

(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 

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( 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 pic: Amendment 39-18129; Docket No. FAA-2014-0904; 

Directorate Identifier 2014-NE-14-AD. 

(a) Effective Date 

This AD becomes effective [INSERT DATE 35 DAYS AFTER DATE OF 

PUBLICATION IN THE FEDERAL REGISTER]. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Rolls-Royce pic (RR) RB21 1-524B-02, RB2 11-524B-B02, RB211-524B2-19, RB211-524B2-B-19, RB211 -524B3-02, RB2 11-524C2-19, and 

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RB211-524C2-B-19 turbofan engines with low-pressure turbine (LPT) stage 3 turbine 

blade, part number (PIN) 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, PIN 

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, PIN 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, PIN 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. 

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(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) 

ofthis 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.rollsroyce.com/contact/civil_ team.j sp; 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 ofthis material at the FAA, call 781-238-7125 . 

(h) Material Incorporated by Reference 

None. 

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' ' . 

Issued in Burlington, Massachusetts, on March 26, 2015. 

Colleen M. D' Alessandro, 

Assistant Directorate Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

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