DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA-2014-0561; Directorate Identifier 2014-NE-12-AD] 

RIN 2120-AA64 

Ainvorthiness Directives; Rolls-Royce pic 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 RollsRoyce plc (RR) RB211 Trent 768-60, 772-60, and 7728-60 turbofan engines. This 

proposed AD was prompted by fractures of the high-pressure/intermediate-pressure 

(HP/TP) turbine support internal oil teed tube. This proposed AD would require 

inspection of the oil feed tube sealing sleeve and removal of those oil feed tube sealing 

sleeves that fail inspection. We are proposing this AD to prevent failure of the HP/IP 

turbine support internal oil feed tube, which could result in uncontained engine failure 

and damage to the airplane. 

DATES: We must receive comments on this proposed AD by [INSERT DATE 60 

DAYS AFTER DATE OF PUBLICATION TN THE FEDERAL REGISTER]. 

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 ofTransportation, 1200 

New Jersey Avenue SE., West Building Ground Floor, Room Wl2-140, Washington, DC 

20590-0001. 
• Hand Deli very: 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. F AA-20 14-0561 ; 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: Wego Wang, Aerospace Engineer, 

Engine Certification Office, FAA, Engi ne & Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 0 1803; phone: 781-238-7134; fax: 78 1-238-7199; email : 

wego.wang@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. F AA-20 14-0561 ; Directorate Identifier 20 14-NE-12-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 infom1ation you provide. We will 

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also post a report summarizing each substantive verbal contact with FAA personnel 

conceming 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 20 I 4-0 I 68, dated 

July 16, 2014 (referred to hereinafter as "the MCAI"), to correct an unsafe condition for 

the specified products. The MCAI states: 

There have been nine occurrences of high oil consumption, 

caused by fracture of the High/Intermediate Pressure 

(HP/IP) turbine support internal oil feed tube Part Number 

(PIN) FW45909. 

The oil feed tube threaded end adaptor and sealing sleeve 

PIN FW15003 are designed to form a sliding joint which, if 

restrained, can compress the oil feed tube during thermal 

contraction of the turbine casing at the end of the flight 

cycle. On each subsequent flight, the thermal growth and 

contraction of the turbine casing relative to the oil tube, 

during the heating and cooling phases of the flight cycle, 

apply a load cycle to the tube, which may lead to low cycle 

fatigue fracture. 

This AD requires removal of certain HP/lP turbine support internal oil feed tube 

sealing sleeves to prevent oil exhaustion that could result in uncontained engine failure 

and damage to the airplane. 

You may obtain further information by examining the MCAI in the AD docket on 

the lntemet at http://www.regulations.gov by searching for and locating Docket No. 

f AA-20 14-0561. 

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 

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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 a one-time onwing or in-shop inspection of the affected engines and removal from service of all 

affected PIN FW 15003 oil feed tube sealing sleeves. 

Costs of Compliance 

We estimate that this proposed AD affects 69 engines installed on airplanes of 

U.S. registry. We also estimate that it would take about 8.5 hours per engine to comply 

with this proposed AD. 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 $49,853. 

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 ofthe Agency's 

authority. 

We are issuing this rulemaking under the authority described in "Subtitle VII. 

Part A, Subpart III, Section 4470 I : General requirements." Under that section, Congress 

charges the F !\!\ 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. 

Regulato11' 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, 

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or on the distribution of power and responsibilities among the various levels of 

government. 

For the reasons discussed above, I certify this proposed regulation: 

(I) Is not a "significant regulatory action" under Executive Order I2866, 

(2) Is not a "significant rule" under the DOT Regulatory Policies and Procedures 

( 44 FR I I 034, 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 negati ve, 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 I4 CFR part 39 as follows: 

PART 39 - AIRWORTHINESS DIRECTIVES 

I. The authority citation for part 39 continues to read as follows: 

Authority: 49 U.S.C. I06(g), 40113,44701. 

§ 39.13 !Amended] 

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

(AD): 

Rolls-Royce pic: Docket No. F AA-20 I4-0561 ; Directorate Identifier 20 14-NE-12-AD. 

(a) Comments Due Date 

We must receive comments by [INSERT DATE 60 DAYS AFTER DATE OF 

PUBUCATTON TN THE FEDERAL REGISTER]. 

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(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Rolls-Royce pic (RR) RB2 1 I Trent 768-60, 772-60, and 

7728-60 turbofan engines serial numbers 4 1693-42309 inclusive, 423 13, 42318, 42319, 

42320, 42328, and 42330 with high-pressure/intermediate-pressure (I-IP/IP) tu rbine 

support internal oil feed tube sealing sleeve part number (P/N) FWI 5003 installed that is 

marked with the prefix "BIN" followed by a six digit batch number, and does not contain 

the marki ng 102013, 11 2013 or 1020 13L. 

(d) Reason 

This AD was prompted by fractures of the HP/IP turbine support internal oil feed 

tube. We are issuing this AD to prevent failure of the HPIIP turbine support internal oil 

feed tube, which could result in uncontained engine failure and damage to the airplane. 

(c) Actions and Compliance 

Comply with this AD within the compliance times specified, unless already done. 

(I) Within 6 months after the effective date of this AD, perform on-wing or inshop inspection for, and remove from service, any affected HP/JP turbine support internal 

oil feed tube sealing sleeve. 

(2) Remove from service any HP/IP turbine support internal oil feed tube sealing 

sleeve on which markings cannot be sufficiently identified to determine whether said 

sealing sleeve is part of the affected population. 

(3) From the effective date of this AD, you may install on engines HP/JP turbine 

support internal oil feed tube sealing sleeves, PIN FW 15003, that are marked with the 

prefix " BIN" followed by a six digit batch number, provided that the part is marked with 

102013, 112013 or 102013L. 

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(f) Alternative Methods of Compliance (AMOCs) 

The Manager, Engine Certification Office, r AA, may approve AMOCs to this 

AD. Use the procedures found in 14 CrR 39. 19 to make your request. 

(g) Related Information 

( I) For more information abo u~ this AD, contact Wego Wang, Aerospace 

Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 01803; phone: 781 -238-7134; fax: 781-238-

7199; emai I: we go. wang@faa.gov. 

(2) Refer to MCAI European Aviation Safety Agency AD 2014-0168, dated July 

16,2014, 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-20 14-0561. 

Issued in Burlington, Massachusetts, on September 9, 2014. 

Acting Assistant Directorate Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

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