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

RIN 2120-AA64 

Airworthiness 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 all RollsRoyce pic (RR) RB21 1-535E4-37, RB211-535E4-B-37, and RB211-535E4-C-37 

turbofan engines. This proposed AD was prompted by RR updating the life limits for 

certain high-pressure turbine (HPT) disks. This proposed AD would require reducing the 

cyclic life limits for certain HPT disks, removing those disks that have exceeded the new 

life limit, and replacing them with serviceable parts. We are proposing 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: We must receive comments on this proposed AD by [INSERT DATE 60 

DAYS AFTER DATE OF PUBLICATION IN 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. 
Monday through Friday, except Federal holidays. 

• Fax: 202-493-2251. 

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

Corporate Communications, P. 0. Box 31, Derby, England, DE24 8BJ; phone: 0 11-44-

1332-242424; fax: 011--44-1332- 249936; email: http://www.rollsroyce.com/contact/civi l_team.jsp; Internet: https://www.aeromanager.com. 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. 

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-2015-0593; 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, Engine & Propeller Directorate, 12 New England 

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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 15-0593; Directorate Identifier 20 15-NE-08-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 information you provide. We will 

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

concerning 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 2014-0249R1, 

dated February 18,2015 (referred to hereinafter as "the MCAI"), to correct an unsafe 

condition for the specified products. The MCAI states: 

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 

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

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

F AA-2015-0593. 

Related Service Information under 1 CFR Part 51 

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

0188, Revision No. I, dated October 30,2013, and RR RB211-535E4-37, Time Limits 

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

RB211-535E4-37, TLM: 05-00-01-800-000, Revision dated July 1, 2014. The NMSB 

describes the updated lifing analysis of the affected HP turbine disks. The TLMs provide 

revised life limits for the affected HP turbine disks. This 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 information. 

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 

in the MCAI and service information referenced above. 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 

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We estimate that this proposed 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 proposed AD. The average labor rate is $85 per hour. Pro-rated cost of required 

parts cost would be about $12,213 per engine. Based on these figures, we estimate the 

cost of this proposed AD on U.S. operators to be $7,938,450. 

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

government. 

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

(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) Wi 11 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. 

The Proposed Amendment 

Accordingly, under the authority delegated to me by the Administrator, the FAA 

proposes to amend 14 CFR part 39 as follows: 

PART 39 - AIRWORTHlNESS 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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(a) Comments Due Date 

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

PUBLICATION IN THE FEDERAL REGISTER). 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Rolls-Royce pic (RR), RB211-535E4-37, RB21 1-535E4-

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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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 installed with PIN UL27681 or 

UL39767, remove the affected HPT disk before the accumulated cyclic life exceeds 

either 19,500 flight cycles (FCs) under Flight Plan A, or 14,700 FCs under Flight Plan B, 

or within 25 FCs after the effective date of this AD, whichever occurs later. 

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

(t) Definition 

For the purpose of this AD, a part eligible for installation is one with a part 

number listed in the TLM 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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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 MCAI in the AD docket 

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

No. FAA-2015-0593. 

(3) RR Non-Modification Service Bulletin No. RB.211-72-G188, Revision No. 1, 

dated October 30,2013, and RR RB211-535E4-37, 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, which are not incorporated by reference in this AD, can be obtained from 

Rolls-Royce plc, using the contact information in paragraph (h)(4) of this proposed AD. 

(4) For service information identified in this proposed AD, contact Rolls-Royce 

plc, 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.jsp; Internet: https:/ /www .aero manager .com. 

(5) You may view this service infom1ation 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. 

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