[Docket No. FAA-2015-4076; Directorate Identifier 2015-NE-30-AD; Amendment 

39-18483; AD 2016-08-07] 

RlN 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 plc (RR) RB211-22B and RB211-524 turbofan engines with low-pressure turbine 

(LPT) support roller bearing, part number (PIN) LK30313 or PIN UL29651, installed. 

This AD requires removal of certain LPT support roller bearings installed in RR RB211-

22B and RB211-524 engines. This AD was prompted by a report of a breach of the 

turbine casing and release of engine debris through a hole in the engine nacelle. We are 

issuing this AD to prevent failure of the LPT support roller bearing, loss of radial position 

following LPT blade failure, tmcontained part release, damage to the engine, and damage 

to the airplane. 

DATES: This AD becomes effective [INSERT DATE 35 DAYS AFTER DATE OF 

PUBLICATION IN 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-2015-4076; 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: Brian Kierstead, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, 

Burlington, MA 01803; phone: 781-238-7772; fax: 781-238-7199; email: 

brian.kierstead@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 December 9, 2015 (80 FR 76402). The NPRM proposed to 

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

An RB211-524G2-T engine experienced an in-service event that 

resulted in breach of a turbine casing and·some release of core 

engine debris through a hole in the engine nacelle. The 

investigation of the event determined the primary cause to have 

been fracture and release of a Low Pressure (LP) turbine stage 2 

blade. The blade release caused secondary damage to the LP 

turbine, producing significant out-of-balance forces. The event 

engine was fitted with an LP turbine support bearing where the 

roller retention cage is constructed from two halves that are riveted 

together. The LP turbine imbalance resulted in an overload of the 

LP turbine support bearing and caused separation of the riveted, 

two -piece roller retention cage. Radial location of the LP turbine 

shaft was lost, allowing further progression of the event that 

resulted in a breach of the IP turbine casing. 

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

considered the comments received. 

Support for the NPRM (80 FR 76402, December 9, 2015) 

Boeing concurred with the NPRM. 

Request to Change Compliance 

Orbital ATK and Lockheed Martin requested that the compliance time be based 

on LPT blade cycles instead of calendar time. Orbital ATK cites correspondence with the 

U.S. Rolls-Royce representative who recommends a 15,000 cycles-since-new (CSN) 

duration for the LPT blade design life. Since there is no calendar time driving the unsafe condition, Orbital ATK believes this is a good mitigation factor for low utilization rate operators. Orbital ATK believes that routine borescope inspections of the LPT blades and 

removal of the engine prior to reaching an LPT blade limit of 15,000 CSN offers an 

equivalent level of safety. 

We partially agree. We agree that the failure mode of the bearing support is not a 

time-based dependency. However, a compliance time of24 months is specified to allow 

for a shop visit interval. We have determined that removal of the LPT support roller 

bearing addresses the unsafe condition. Operators with unique circmnstances may apply 

for an alternative method of compliance using the procedures listed in this AD. We did 

not change this AD. 

Request to Change Costs of Compliance 

Lockheed Martin requested an adjustment to the estimated costs of compliance. 

The costs to low utilization operators would be significantly increased by imposing an 

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utilization operators to the shop faster. Operators with unique circumstances may apply 

for an alternative method of compliance using the procedures listed in this AD. 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 this AD as proposed. 

Costs of Compliance 

We estimate that this AD affects 9 engines installed on airplanes of U.S. registry. 

We also estimate it will take 0 hours to comply with this AD. Removing the LPT support 

roller bearing is required during a shop visit; therefore, no additional time is needed for removal. Required parts cost about $8,184 per engine. 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 

$73,656. 

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 

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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" m1der 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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Directorate Identifier 2015-NE-30-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 Rolls-Royce plc RB211-22B-02, RB211-22B (MOD 72-

8700), RB211-524B-02, RB211-524B-B-02, RB211-524B2-19, RB211-524B2-B-l9, 

Rli211-524B3-02, RB2ll-524B4-02, RB211-524B4-D-02, RB211-524C2-19, RB211-

524C2-B-19, RB211-524D4-19, RB211-524D4-B-19, RB211-524D4X-19, RB211-

524D4X-B-19, RB211-524D4-39, RB211-524D4-B-39, RB211-524G2-l9, RB211-

524G3-19, RB2ll-524-G2-T-l9, RB211-524G3-T-19, RB211-524H-36, RB211-524H2-

19, RB211-524H-T-36, and RB211-524H2-T-19 turbofan engines, all serial nmnbers, 

with low-pressure turbine (LPT) support roller bearing, part number (PIN) LK30313 or 

PIN UL29651, installed. 

(d) Reason 

This AD was prompted by a report of a breach of the turbine casing and release of 

engine debris through a hole in the engine nacelle. We are issuing this AD to prevent 

failure of the LPT support roller bearing, loss of radial position following LPT blade 

failure, uncontained part release, damage to the engine, and damage to the airplane. 

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UL29651, and replace with a part eligible for installation. 

(f) Installation Prohibition 

After the effective date of this AD, do not install an LPT support roller bearing, 

PIN LK30313 or PIN UL29651, onto any engine. 

(g) Definition 

For the purpose of this AD, a "shop visit" is defined as 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. 

(h) Alternative Methods of Compliance (AMOCs) 

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

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

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

(i) Related Information 

(1) For more information about this AD, contact Brian Kierstead, Aerospace 

Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 

District Avenue, Burlington, MA 01803; phone: 781-238-7772; fax: 781-238-7199; 

email: brian.kierstead@faa.gov. 

(2) Refer to MCAI European Aviation Salety Agency AD 2015-0187, dated 

September 9, 2015, for more infonnation. You may examine the MCAI in the AD docket 

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Issued in Burlington, Massachusetts, on April4, 2016. 

Colleen M. D' Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

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