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

39-18105; AD 2015-04-03] 

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

sealing sleeves that are affected by this AD. This AD was prompted by fractures of the 

high-pressure/intermediate-pressure (HP/IP) turbine support internal oil feed tube. We are 

issuing 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: This AD becomes effective [fNSERTDATE 35 DAYS AFTER DATE OF 

PUBLICATION fN THE FEDERAL REGISTER). 

ADDRESSES: See the For Further Information Contact section. 

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-2014-0561; or in person at the Docket 
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: 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; email: 

we go. wang@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 

the Federal Register on September 18, 2014 (79 FR 56025). The NPRM proposed 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 

FW 15003 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 

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Conclusion 

We reviewed the available data and determined that air safety and the public 

interest require adopting this AD as proposed. 

Costs of Compliance 

We estimate that this AD affects 69 engines installed on airplanes of U.S. registry. 

We also estimate that it will take about 8.5 hours per engine to comply with this AD. The 

average labor rate is $85 per hour. Based on these figures, we estimate the cost of this 

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 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 

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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. 1 06(g), 40113, 44701. 

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Directorate Identifier 2014-NE-12-AD. 

(a) Effective Date 

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

PUBLICATION IN THE FEDERAL REGfSTER]. 

(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, serial numbers 41693 through 42309 inclusive, 42313, 42318, 

42319, 42320, 42328, and 42330 with high-pressure/intern1ediate-pressure (HPIIP) 

turbine support internal oil feed tube sealing sleeve, part number (PIN) FW 15003, 

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

does not contain the marking 102013, 112013 or 102013L. 

(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 HP/IP turbine support internal oil 

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

(e) Actions and Compliance 

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

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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/IP turbine 

support internal oil feed tube sealing sleeves, PIN FW15003, 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. 

(f) Alternative Methods of Compliance (AMOCs) 

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

AD. Use the procedures found in 14 CFR 3 9.19 to make your request. You may email 

your request to: ANE-AD-AMOC@faa.gov. 

(g) Related Information 

(I) For more information about 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; email: wego.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/#!docketDetail;D=F AA-20 14-0561. 

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l i~tLfl~ n .. 111 n l-lUu~,~ttt·~ ~ Colleen M. D' Alessandro, 

Assistant Directorate Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

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