[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 ofthe 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 ofthe 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 ofthis 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-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 ofTransportation, 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 ofproposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to the specified products

. The NPRM was published in

2the 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 ofan 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 ofevents resulted in an engine internal fire which caused the failure ofthe IP turbine disc drive arm. This condition, ifnot 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 ofFailure 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 , 

### 32018, whichever comes first, to achieve more timely mitigation ofthe 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 ofU.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 ofthis 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 ofthe FAA Administrator. "Subtitle VII: Aviation Programs," describes in more detail the scope ofthe 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 ofcivil 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 ofthat authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.

4

### 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 ofgovernment. 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 itjustifies 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 ofthe 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.



### 5

### §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 ofthe intermediate-pressure turbine disc drive arm or burst ofthe high-pressure turbine disk, which could lead to uncontained engine failure and damage to the airplane

. (e) Actions and Compliance After the effective date ofthis 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

. 6(f) Installation Prohibition After modification ofan engine as required by paragraph (e) ofthis 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 ofan engine into the shop for maintenance involving the separation ofpairs ofmajor mating engine flanges , except that the separation ofengine flanges solely for the purposes of transportation without subsequent engine maintenance does not constitute an engine shop visit. (2) For the purpose ofthis AD, an EEC "eligible for installation" is any EEC that does not contain software standard A 14 or earlier. (h) Credit for Previous Actions Ifbefore 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 ofthis 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

. 7(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=FAA-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) ofthis 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 ofthis 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

.



### 8