[4910-13-P) 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA-2015-0593; Directorate Identifier 2015-NE-08-AD; Amendment 

39-18254; AD 2015-17-21] 

RIN 2120-AA64 

Ainvorthiness 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 all Rolls-Royce 

plc (RR) RB211-535E4-37, RB211-535E4-B-37, and RB2ll-535E4-C-37 turbofan 

engines. This AD requires reducing the cyclic life limits for certain high-pressure turbine 

(HPT) disks, removing those disks that have exceeded the new life limit, and replacing 

them with serviceable parts. This AD was prompted by RR updating the life limits for 

ce11ain HPT disks. We are issuing this AD to prevent failure of the HPT disk, which 

could result in uncontained disk 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]. 

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

certain publication listed in this AD as of [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 3 1, Derby, England, DE24 8BJ; phone: 011--44-

1332- 242424; fax: 01 1--44- 1332- 249936; email: http://www.rollsroyce.com/contact/civil_team.jsp; Internet: https://www.aeromanager.com. You may 

view this service infonnation at the FAA, Engine & Propeller Directorate, 12 New 

England Executi ve Park, Burlington, MA. For info rmation on the avail ability of this 

material at the FAA, call781-238-7125. lt is also available on the Internet at 

http://www.regulations.gov by searching for and locating Docket No. FAA-2015-0593. 

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 15-0593; 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 add ress for the Docket Office (phone : 800-647-5527) is Document 

Management Facility, U.S. Department of Transportation, Docket Operations, M-30, 

West Building Ground Floor, Room W 12- 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, Burli ngton, MA 01803; phone: 781-238-7134; fax: 781-238-7199; emai l: 

we go. wang@ faa.gov. 

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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 April 29, 2015 (80 FR 23737). The NPRM proposed to correct an 

unsafe condition for the specified products. The MCAI states: 

Comments 

An engineering analysis, carried out by RR, of the lives of critical 

parts ofthe RB211-535E4-37 engine, has resulted in reduced 

cyclic life limits for certain high pressure (HP) turbine discs. The 

reduced limits are published in the RR RB211-535E4-37 Time 

Limits Manual (TLM): 05-10-01-800-000, current Revision dated 

July 2014. 

Operation of critical parts beyond these reduced cyclic life limits 

may result in part failure, possibly resulting in the release of highenergy debris, which may cause damage to the aeroplane and/or 

inj ury to the occupants. 

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

received no conunents on the NPRM (80 FR 23737, April 29, 2015). 

Conclusion 

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

interest require adopting this AD as proposed. 

Related Ser-vice Information under 1 CFR Part 51 

We reviewed RR Non-Modification Service Bulletin (NMSB) No. RB.211-72-

0188, Revision No.1 , dated October 30,2013, and RR RB21 1-535£4-37, Time Limits 

Manual (TLM): 05-10-01-800-000, Revision dated July 1, 2014; and RR 

RB211-535E4-37, TLM: 05-00-01-800-000, Revision dated July 1, 2014 (referred to 

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hereafter as ' the TLM'). The NMSB describes the updated lifing analysis ofthe affected 

1--IPT disks. The TLM provides revised li fe limits for the affected HPT disks. Tllis service 

information is reasonably available because the interested parties have access to it 

through their normal course of business or see ADDRESSES for other ways to access this 

service infom1ation. 

Costs of Compliance 

We estimate that this AD affects 650 engines installed on airplanes of U.S. 

registry. We also estimate that it would take about 0 hours per engine to comply with this 

AD. The average labor rate js $85 per hour. The pro-rated cost of required parts would be 

about $12,2 13 per engine. Based on these figures, we estimate the cost of this AD on 

U.S. operators to be $7,938,450. 

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 of the Agency's 

authority. 

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

Pa1t 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 fi nds 

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 rulcmaking 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, J 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 II 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 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 

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

Authority: 49 U.S.C. 106(g), 40113, 44701. 

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§ 39.13 [Amended] 

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

(AD): 

2015-17-21 Rolls-Royce pic: Amendment 39-18254; Docket No. FAA-2015-0593; 

Directorate Identifier 20 15-NE-08-AD. 

(a) Effective Date 

Tllis 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), RB211-535E4-37, RB211-535E4-

B-37, and RB211-535E4-C-37 turbofan engines. 

(d) Reason 

This AD was prompted by RR updating the life limits for certain high-pressure 

turbine (HPT) disks. We are issuing this AD to prevent failure of the HPT disk, which 

could result in uncontained disk release, damage to the engine, and damage to the 

airplane. 

(e) Actions and Compliance 

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

(1) After the effective date of this AD, use RR RB211-535E4-37, Time Limits 

Manual (TLM): 05-10-01-800-000, Revision dated July I, 2014 (referred to hereafter as 

'the TLM'), to determine the new life limits for the affected engine models and 

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configurations, with the exception of those engine models mentioned in paragraph (e)(2) 

of this AD. 

(2) For RR RB211-S3SE4-B-37 or RB2 I 1-S3SE4-C-37 engines with an affected 

HPT disk that was previously installed on an RB211-535E4-37 engine operated under 

Flight Plan A, use Task 05-00-01-800-000 in the TLM to re-calculate equivalent cycles 

since new to obtain the new life limit. 

(3) If an affected engine model has an HPT disk install ed with part number (P/N) 

UL27681 or UL39767, remove the affected 1-IPT disk before the accumulated cyclic life 

exceeds either 19,500 flight cycles (FCs) under f-light Plan A, or 14,700 FCs under Flight 

Plan B, or within 25 FCs after the etiective date of this AD, whichever occurs later. 

(4) For all affected engines, other than those specified in paragraph (e)(3) of this 

AD, remove each HPT disk before exceeding its applicable life limit as specified in the 

TLM. 

(5) Install an HPT disk eligible for installation. 

(f) Definition 

For the purpose of this AD, a part eligible for install ation is one with a PIN listed 

in the T LM with a total accumulated cyclic life that is less than the applicable life limit 

specified in the TLM. 

(g) 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. 

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(h) Related Information 

(1) For more infonnation 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 2014-0249R1 , dated 

February 18, 2015, for more information. You may examine the MCAJ in the AD docket 

on the Internet at http://www.regulations.gov by searching for and locating it in Docket 

No. F AA-2015-0593. 

(i) Material Incorporated by Reference 

( 1) The Director of the Federal Register approved the incorporation by reference 

(JBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51 . 

(2) You must use this service information as applicable to do the actions required 

by this AD, unless the AD specifies otherwise. 

(i) Rolls-Royce plc RB211-535E4-37, Time Limits Manual: 05-10-01-800-000, 

Revision dated July 1, 2014. 

(ii) Reserved. 

(3) For RR service information identified in this AD, contact Rolls-Royce pic, 

Corporate Communications, P.O. Box 31 , Derby, England, DE24 8BJ; phone: 011-44-

1332- 242424; fax: 011-44-1332-249936; email: http://www.rollsroyce.com/contact/civil_ team.j sp; Internet: https://www.aeromanager.com .. 

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(4) You may view this service information at FAA, Engine & Propeller 

D.irectorate, 12 New England Executi ve Park, Burlington, MA. For information on the 

availability of this materi al at the FAA, call 781-238-7125. 

(5) 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.archi ves.gov/federal-register/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on August 21, 2015. 

Colleen M. D' Alessandro, 

Directorate Manager, Engine & Propeller Directorate, 

Aircraft Certilication Service. 

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