[4910-13-PJ 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. F AA-2012-1198; Directorate Identifier 2012-NE-35-AD; Amendment 

39-17289; AD 2012-25-08] 

RIN 2120-AA64 

Ainvorthiness Directives; Rolls-Royce pic Turbofan Engines 

AGENCY: Federal Aviation Administration (FAA), DOT. 

ACTION: Final rule; request for comments. 

SUMMARY: We are adopting a new airworthiness directive (AD) for certain serial 

numbers (SINs) of Rolls-Royce pic (RR) RB211-Trent 768-60, 772-60, and 7728-60 

turbofan engines. This AD requires initial and repetitive on-wing or in-shop inspections 

of the high pressure/intermediate pressure (HP/IP) turbine bearing support oil feed tube 

outer heat shield. This AD also requires installation of a revised HP/IP turbine bearing 

support structure as terminating action to the repetitive inspections of the HP/IP turbine 

bearing support oi I feed tube outer heat shield. This AD was prompted by a report of high 

oil consumption due to an oil leak from the HP/IP turbine bearing support oil feed tube. 

We are issuing this AD to prevent failure of the HP turbine disc, uncontained engine 

failure, and damage to the airplane. 

DATES: This AD becomes effective [Insert date 15 days after date of publication in the 

FEDERAL REGISTER]. 
We must receive comments on this AD by [INSERT DATE 45 DAYS AFTER 

DATE OF PUBLICATION IN THE FEDERAL REGISTER]. 

The Director of the Federal Register approved the incorporation by reference of a 

certain publication as of [INSERT DATE 15 DAYS AFTER DATE OF PUBLICATION 

IN THE FEDERAL REGISTER]. 

The Director of the Federal Register approved the incorporation by reference of 

certain other publications as of December 14, 2007. 

ADDRESSES: You may send comments by any of the following methods: 

• Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the 

instructions for sending your comments electronically. 

• Mail: U.S. Department of Transportation, 1200 New Jersey Avenue SE., West 

Building Ground Floor, Room W12-140, Washington, DC 20590-0001. 

• Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal holidays. 

• Fax: 202-493-2251. 

For service information identified in this AD, contact Rolls-Royce plc, Corporate 

Communications, P.O. Box 31, Derby, England, DE248BJ, phone: 011-44-1332-

242424; fax: 0 11-44-1332-245418, oremail:http://www.rollsroyce.com/contact/civil_team.jsp. You may view this service information at the FAA, 

Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 

01803. For information on the availability ofthis material at the FAA, call 781-238-7125. 

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Examining the AD Docket 

You may examine the AD docket on the Internet at http://www.regulations.gov; 

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 AD, the regulatory 

evaluation, any comments received, and other information. The street address for the 

Docket Operations office (phone: 800-647-5527) is the same as the Mail address 

provided in the ADDRESSES section. Comments will be available in the AD docket 

shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Robert Morlath, Aerospace Engineer, 

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

Executive Park, Burlington, MA 01803; phone: 78 1-238 7154; fax: 781-238 7199; email: 

robert.c.morlath@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency (EASA), which is the Technical Agent for 

the Member States of the European Community, has issued EASA AD 2012-0201, dated 

September 26, 2012 (referred to after this as "the MCAr'), to correct an unsafe condition 

for the specified products. The MCAI states: 

In August 2011, a Trent 700 engine was removed for high oil 

consumption, which was found to have been caused by a small 

hole in the oil feed tube of the High Pressure I Intermediate 

Pressure (HP/IP) Bearing Support. The hole was the result of 

frettage (chafing) with a fractured outer heat shield. This is a 

known problem and recognized unsafe condition that has reemerged having been previously addressed by EASA AD 2007-

0260Rl. 

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Investigation by RR revealed a build error that, in contradiction to 

the build records, the previous configuration of outer heat shield 

(Pre-Service Bulletin (SB) 72-F117 standard) was fitted on the oil 

feed tube service pipe of the HP/IP structure. As the build error 

may have been reproduced several times, it is assumed that further 

post-SB 72-Fll7 standard structures may be in service with preSS 72-F 117 outer heat shields fitted to the oil feed tube. 

The frettage on the oil feed tube within the HP/IP turbine bearings 

support structure results from contact with the fracture edges of the 

tubes outermost heat shield, which has been found to fracture 

under thermal cycling and then to chafe against the oil tube with 

the potential to cause holes and consequent oil leaks. 

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

On November 20, 2007, we issued AD 2007-24-09 (72 FR 67568, November 29, 

2007) which corresponds with EASA AD 2007-0260R1. Our AD has a mandatory 

terminating action date of May 31, 20 I 0, however, there were, and currently are, no U.S. 

operators of the engines affected by those ADs. Those ADs are only applicable to engines 

that do not incorporate Modification Standard 72-F117. Since those ADs were issued, 

EASA has issued AD 2012-0201 that is applicable to a specific set of engines that may 

have had Modification Standard 72-F117 incorporated incorrectly. EASA did not 

supersede EASA AD 2007-0260R1 with EASA AD 2012-0201 because EASA AD 2012-

0201 only affects a very specific population of engines that, having incorporated 

Modification Standard 72-F117, either correctly or incorrectly, are no longer affected by 

EASA AD 2007-0260Rl. We are issuing our AD as a standalone document for the same 

reasons. This new AD also is applicable only to the engines specified in the MCAI, none 

of which are currently registered to U.S. operators. Also, this new AD lists certain service 

bulletins that were previously incorporated by reference in AD 2007-24-09. 

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Relevant Service Information 

RR has issued Alert Service Bulletin No. RB.211-72-AG873, dated February 27, 

2012. The actions described in this service information are intended to correct the unsafe 

condition identified in the MCAI. 

FAA's Determination and Requirements of this AD 

This product has been approved by 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 in the MCAI and 

service information referenced above. We are issuing this AD because we evaluated all 

infom1ation provided by EASA and determined the unsafe condition exists and is likely 

to exist or develop on other products of the same type design. 

FAA's Determination of the Effective Date 

No domestic operators use any of the RB211-Trent 768-60, 772-60, and 7728-60 

turbofan engines listed by SIN in this AD. Therefore, we find that notice and opportunity 

for prior public comment are unnecessary and that good cause exists for making this 

amendment efTective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves requirements affecting flight safety, and we 

did not precede it by notice and opportunity for public comment. We invite you to send 

any written relevant data, views, or arguments about this AD. Send your comments to an 

address listed under the ADDRESSES section. Include "Docket No. F AA-20 12-1198; 

Directorate Identifier 20 12-NE-35-AD" at the beginning of your comments. We 

specifically invite comments on the overall regulatory, economic, environmental, and 

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energy aspects of this AD. We will consider all comments received by the closing date 

and may amend this AD because of those comments. 

We will post all comments we receive, without change, to 

http://www.regulations.gov, including any personal information you provide. We will 

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

conceming this AD. Using the search function of the Web site, anyone can find and read 

the comments in any of our dockets, including, if provided, the name of the individual 

who sent the comment (or signed the comment on behalf of an association, business, 

labor union, etc.). You may review the DOT's complete Privacy Act Statement in the 

Federal Register published on April II , 2000 (65 FR 194 77-78). 

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. 

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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: 

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 11034, February 26, 1979); and 

3. 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. 

We prepared a regulatory evaluation of the estimated costs to comply with this 

AD and placed it in the AD docket. 

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 

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

Authority: 49 U.S.C. 106(g), 401 I3, 44701. 

§ 39.13 [Amended) 

2. The FAA amends§ 39.13 by adding the following new AD: 

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2012-25-08 Rolls-Royce pic: Amendment 39-17289; Docket No. F AA-20 12-1198; 

Directorate Identifier 2012-NE-35-AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes effective (lnsert date 15 days after 

date of publication in the FEDERAL REGISTER]. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Rolls-Royce pic (RR) RB211 Trent 768-60, 772-60, and 

772B-60 turbofan engines with serial numbers (SINs) listed in Table l to paragraph (c) of 

this AD. 

Table 1 to Paragraph (c)- Affected Engine S/Ns 

41221 41435 41446 41459 4 1465 

41425 41437 41451 41460 41466 

41428 41438 41452 41461 41468 

41430 41440 41454 41462 41469 

41431 41442 41455 41463 4 1470 

41432 41445 41456 41464 41471 

(d) Reason 

This AD was prompted by a report of high oil consumption due to an oil leak 

from the high pressure/intermediate pressure (HP/IP) turbine bearing support oil feed 

tube. We are issuing this AD to prevent a failure of the HP turbine disc, uncontained 

engine failure, and damage to the airplane. 

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(e) Actions and Compliance 

Unless already done, do the following actions. 

(t) Initial Inspection 

(l) Initially inspect the HP/lP turbine bearing support oil feed tube within the 

compliance times specified in paragraphs J.D.( 1 )(a) through 1.0.(1 )(a)(ii) of RR Alert 

Service Bulletin (ASB) No. RB.211-72-AG873, dated February 27, 2012. Perform the 

initial inspection in accordance with paragraphs 3.A (l)(a) through 3.A (l)G) ofRR ASB 

No. RB.211-72-AG873, dated February 27, 2012. 

(2) If the HP/IP turbine bearing support oil feed tube outer heat shield is not 

present, accept the module as compliant. No further action is required. 

(g) Repetitive Inspections 

If the HP/IP turbine bearing support oil feed tube outer heat shield is present, 

perform repetitive inspections of the HP/IP turbine bearing suppo11 oil feed tube, in 

accordance with paragraphs 3.A (2)(b) through 3.A (2)(f) ofRR AS8 No. RB.211-72-

AG873, dated February 27, 2012. 

(h) Mandatory Terminating Action 

As mandatory terminating action to the repetitive inspections required by this AD, 

install a revised HP/IP turbine bearing support structure, at the next 05 Module overhaul 

after the effective date of this AD, in accordance with either: 

(1) Sections 3.8 (l)(a) through 3.8 (l)(t) ofRR Service Bulletin (SB) No. 

RB.211-72-Fl17, Revision 2, dated September 25, 2006; or 

(2) Sections 3.8 (l)(a) through 3.8 (l)(e) and 3.8 (2)(a) ofRR S8 No. RB.211-

72-F227, Revision I, dated October 8, 2007. 

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(i) Definition 

For the purpose of this AD, "next 05 Module overhaul" is any time that the HP/IP 

turbine internal oil tubes have been exposed and the HP/IP turbine bearing support oil 

feed tube heat shields are subjected to visual inspection. 

(j) Alternative Methods of Compliance (AMOCs) 

The Manager, Engine Certification Office, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39. 19 to make your request. 

(k) Related Information 

(I) For more information about this AD, contact Robert Morlath, Aerospace 

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

England Executive Park, Burlington, MA 01803; phone: 781-238 7154; fax: 781-238 

7199; email: robert.c.morlath@faa.gov. 

(2) Refer to European Aviation Safety Agency AD 2012-020 1, dated September 

26, 2012, for related information. 

(I) Material Incorporated by Reference 

(1) You must use the following service information to do the actions required by 

this AD, unless the AD specifies otherwise. The Director of the Federal Register 

approved the incorporation by reference (IBR) of the following service information under 

5 U.S.C. 552(a) and 1 CFR part 51 on the date specified: 

(i) Rolls-Royce pic Alert Service Bulletin No. RB.211-72-AG873, dated February 

27, 2012, approved for IBR [INSERT DATE 15 DAYS AFTER PUBLICATION]. 

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(ii) Rolls-Royce plc Service Bulletin No. RB.211-72-Fll7, Revision 2, dated 

September 25, 2006, approved for IBR on December 14, 2007 (72 FR 67568, November 

29, 2007). 

(iii) Rolls-Royce plc Service Bulletin No. RB.211-72-F227, Revision 1, dated 

October 8, 2007, approved for IBR on December 14, 2007 (72 FR 67568, November 29, 

2007). 

(2) For service information identified in this AD, contact Rolls-Royce plc, 

Corporate Communications, P.O. Box 3 1, Derby, England, DE248BJ, phone: 011-44-

1332-242424; fax: 0 11-44-1332-245418; or email : http://www.rollsroyce.com/contact/civil_team.jsp. 

(3) 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. 

(4) You may view this service information at the National Archives and Records 

Administration (NARA). For information on the availability of this material at NARA, 

call 202-741-6030, or go to: http://www.archives.gov/(ederal-registerlcfi-librlocations. him/. 

Issued in Burlington, Massachusetts, on December 4, 2012. 

Colleen M. D' Alessandro, 

Assistant Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

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