[4910-13-P] 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

(Docket No. FAA-2013-0876; Directorate Identifier 2013-NE-27-AD; Amendment 

39-17895; AD 2014-14-01] 

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 pic (RR) RB211 Trent 768-60, 772-60, and 772B-60 turbofan engines. This AD 

requires modification of the engine by removing an electronic engine control (EEC) 

incorporating EEC software standard A 14 or earlier and installing an EEC eligible for 

installation. This AD was prompted by an uncontained multiple turbine blade failure on 

an RR RB211 Trent 772B turbofan engine. We are issuing this AD to prevent failure of 

the intermediate-pressure (IP) turbine disk drive arm or burst of the high-pressure turbine 

disk, which could lead to uncontained engine failure 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 pic, 

Corporate Communications, P.O. Box 31 , Derby, England, DE248BJ; phone: 011--44-

1332-242424; fax : 011--44-1332-249936; email: http://www.rolls-
royce.com/contact/civil_team.jsp; or Web site: 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 781-23 8-7125. 

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. F AA-20 13-0876; 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 

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the Federal Register on March 3, 2014 (79 FR 11722). The NPRM proposed to correct 

an unsafe condition for the specified products. The MCAI states: 

Comments 

An operator of an A330 aeroplane fitted with RR Trent 772B 

engines experienced an engine uncontained multiple turbine blade 

failure. Investigation results showed that HighPressure/Intermediate-Pressure (HP/IP) oil vent tubes may be 

affected by carbon deposit and may also be damaged by their outer 

heat shields, which in this case led to combustion inside the tube. 

The consequent chain of events resulted in an engine internal fire 

which caused the failure of the IP turbine disc drive arm. 

This condition, if not corrected, could lead to uncontained multiple 

turbine blade failures or an HP/IP turbine disc burst, possibly 

resulting in damage to, and reduced control of, the aeroplane. 

We gave the public the opportunity to participate in developing this AD. We 

considered the comments received. 

Request to Modify Description of Failure Mode 

RR requested that we define the failure mode as IP turbine disc drive arm failure 

and multiple IP turbine blade release to be consistent with descriptions in the RR service 

bulletin and the European Aviation Safety Agency (EASA) AD. 

We disagree. EASA AD 2013-0190, dated August 20, 2013 , states that the failure 

mode is multiple turbine blade failures or HP/IP turbine disc burst. We did not change 

this AD. 

Request that FAA Require the Same Compliance Date as the EASA AD 

RR requested that we modify the compliance date to be consistent with the 

compliance date required in EASA AD 2013-0190, dated August 20, 2013. 

We disagree. EASA AD 2013-0190, dated August 20, 2013 required compliance 

by December 31 , 2018. We proposed compliance at next shop visit or December 31 , 

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2018, whichever comes first, to achieve more timely mitigation of the unsafe condition. 

We did not change this AD. 

Conclusion 

We reviewed the available data, including the comments received, and determined 

that air safety and the public interest require adopting the AD as proposed. 

Costs of Compliance 

We estimate that this AD affects about 72 engines installed on airplanes of U.S. 

registry. We also estimate that it will take about 1 hour per engine to comply with this 

AD. The average labor rate is $85 per hour. There are no required parts. Based on these 

figures, we estimate the cost of this AD on U.S. operators to be $6,120. 

Authority for This Rulemaking 

Title 49 ofthe 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 44 701: 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. 

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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 

( 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. 

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§ 39.13 [Amended] 

2. The FAA amends§ 39.13 by adding the following new airworthiness directive 

(AD): 

2014-14-01 Rolls-Royce pic: Amendment 39-17895; Docket No. FAA-2013-0876; 

Directorate Identifier 2013-NE-27-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 plc (RR) RB211 Trent 768-60, 772-60, and 

772B-60 turbofan engines prior to engine serial number 42066. 

(d) Reason 

This AD was prompted by an uncontained multiple turbine blade failure on an RR 

RB211 Trent 772B turbofan engine. We are issuing this AD to prevent failure of the 

intermediate-pressure turbine disc drive arm or burst of the high-pressure turbine disk, 

which could lead to uncontained engine failure and damage to the airplane. 

(e) Actions and Compliance 

After the effective date of this AD, at the next engine shop visit or by December 

31 , 2018, whichever occurs first, modify the engine by removing any electronic engine 

control (EEC) that incorporates EEC software standard A14 or earlier and installing an 

EEC eligible for installation. 

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(f) Installation Prohibition 

After modification of an engine as required by paragraph (e) of this AD, do not 

install an EEC with software standard A14 or earlier into that engine. 

(g) Definitions 

(1) For the purpose ofthis 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 does not constitute an engine shop 

visit. 

(2) For the purpose of this AD, an EEC "eligible for installation" is any EEC that 

does not contain software standard A 14 or earlier. 

(h) Credit for Previous Actions 

If before the effective date ofthis AD you removed from an engine any EEC that 

had EEC software standard A14 or earlier and your engine no longer has an EEC with 

soft~are standard A14 or earlier, you have met the requirements of this AD. 

(i) Alternative Methods of Compliance (AMOCs) 

The Manager, Engine Certification Office, FAA, may approve AMOCs to this 

AD. Use the procedures found in 14 CFR 39.19 to make your request. 

(j) 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. 

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(2) Refer to MCAI European Aviation Safety Agency AD 2013-0190, dated 

August 20, 2013 , for more information. You may examine the MCAI in the AD docket 

on the Internet at http://www.regulations.gov/# !docketDetail;D=F AA-2013-0876. 

(3) RR Alert Service Bulletin No. RB.211-73-AG829, dated April 18, 2012, 

which is not incorporated by reference in this AD, can be obtained from Rolls-Royce pic, 

using the contact information in paragraph (j)(4) of this AD. 

( 4) For service information identified in this AD, contact Rolls-Royce pic, 

Corporate Communications, P.O. Box 31 , Derby, England, DE248BJ; phone: 011-44-

1332-242424; fax: 011-44-1332-249936; email: http://www.rollsroyce.com/contact/civil_team.jsp; or Web site: 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 . 

(k) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on June 30, 2014. 

Colleen M. D' Alessandro, 

Assistant Directorate Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

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