DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA-2013-0052; Directorate Identifier 2013-NE-02-AD] 

RIN 2120-AA64 

Airworthiness Directives; Rolls-Royce pic Turbofan Engines 

AGENCY: Federal Aviation Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking (NPRM). 

[4910-13-P] 

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all RollsRoyce plc (RR) RB211-535E4-37, RB211-535E4-B-37, RB211-535E4-C-37, and 

RB211-535E4-B-75 turbofan engines. This proposed AD was prompted by RR updating 

the low-cycle-fatigue life analysis for the low pressure turbine (LPT) stage 2 discs. This 

proposed AD would require removal of affected pmts using a drawdown plan. We are 

proposing this AD to prevent LPT stage 2 disc failure , which could result in uncontained 

engine damage 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 and follow the 

instructions for sending your comments electronically. 
• Mail: Docket Management Facility, U.S. Department of Transportation, 1200 

New Jersey Avenue SE., West Building Ground Floor, Room W12-1 40, 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 pic, Corporate 

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

242424; fax: 011-44-1332-249936; or email from http://www.rollsroyce.com/contact/civil_team.jsp; or download the publication from 

https://www.aeromanager.com. 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. 

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 proposed 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 avail able in the AD docket 

shortl y after receipt. 

FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, 

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

2 
Executive Park, Burlington, MA 01803 ; phone: 781-238-7754; fax: 781-238-7199; email: 

Robert. Green@faa. gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

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 . FAA-2013-0052; Directorate Identifier 2013-NE-02-AD" at the 

beginning of your comments. We specificall y 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 pers01mel 

concerning this proposed AD. Using the search function of the Web site, anyone can find 

and read the comments in any of our dockets, including, ifprovided, the name ofthe 

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 April11 , 2000 (65 FR 19477-78). 

Discussion 

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

the Member States of the European Community, has issued EASA AD 2012-0266, dated 

3 
December 18, 20 12, to correct an unsafe condition for the specified products. That 

mandatory continuing airworthiness info rmation (MCAI) states: 

A recent re-evaluation of Critical Part li ves carri ed out by RollsRoyce revealed changes to the thermal profil e and stresses in 

certain features of the low pressure turbine (LPT) Stage 2 disc. 

These changes have resulted in a reduction ofthe cyclic life ofthe 

LPT stage 2 discs. 

Operation of an engine equipped with a Critical Part that has 

exceeded its cyclic life may result in Critical Part failure, 

consequent release of high energy debris, damage to the aeroplane 

and/or injury to occupants. 

We are proposing this AD to prevent LPT stage 2 disc failure, whi ch could result in 

uncontained engine damage and damage to the airplane. You may obtain further 

information by examining the MCAI in the AD docket. 

Relevant Service Information 

RR has issued Alert Non-Modification Service Bulletin (NMSB) No. RB.2 11-72-

AH029, dated December 13, 201 2. The NMSB introduces new LPT stage 2 disc part 

li ves that will be the drawdown plan retirement tlu·esholds. 

FAA's Determination and Requirements of this Proposed AD 

This product has been approved by the aviation authority ofthe United Kingdom 

and is approved fo r 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 ex ists and is likely to exist or develop on other products of the same type 

design. This proposed AD would require removal of affected LPT stage 2 discs using a 

drawdown plan. 

4 
Differences Between the AD and the MCAI or Service Inf01·mation 

This AD differs from EASA AD 201 2-0266, dated December 18,201 2, as 

follows: The EASA AD specifies replacing the affected critical parts during the modul e 

disassembly if the subsequent, anti cipated time on wing (time before next shop visit) plus 

current life of the part will exceed the new provisional lives published in the RR Alert 

NMSB No. RB.2 ll-72-AH029, dated December 13, 201 2. We specify replacing at next 

shop visit (defin ed by the separation of a major fl ange). 

Costs of Compliance 

We estimate that this proposed AD would affect about 220 engines installed on 

airplanes of U.S. registry. The average labor rate is $85 per hour. We do not estimate any 

labor cost associated with this proposed AD because the affected parts are replaced 

during schedul ed shop visits. Prorated cost of the parts adjusted for lost life is about 

$8,290 per engine. Based on these fi gures, we estimate the cost of the proposed AD on 

U.S. operators to be $ 1,823 ,800. 

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 fli ght of civil aircraft in air commerce by 

prescribing regulations fo r practices, methods, and procedures the Administrator finds 

5 
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. 

Regulatory Findings 

We determined that this proposed AD would not have federa lism implications 

under Executive Order 13132. This proposed AD would 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 

goverm11ent. 

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

(1) Is not a " significant regulatory actio n" under Executive Order 12866; 

(2) Is not a " significant rule" under the DOT Regulatory Policies and Procedures 

( 44 FR 11 034, February 26, 1979); and 

(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. 

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

proposed 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. 

6 
The Proposed Amendment 

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

proposes to amend 14 CFR part 39 as fo llows: 

PART 39- AIRWORTHINESS DIRECTIVES 

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

Authority: 49 U.S.C. 106(g), 4011 3, 44701. 

§ 39.13 [Amended] 

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

Rolls-Royce pic: Docket No. FAA-201 3-0052; Directorate Identifier 20 13-NE-02-AD. 

(a) Comments Due Date 

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

PUBLICATION IN THE FEDERAL REGISTER]. 

(b) Affected Airworthiness Directives (ADs) 

None. 

(c) Applicability 

This AD applies to all Rolls-Royce plc (RR) RB211-535E4-37, RB211 -535E4-B37, RB2 11-535E4-C-37, and RB211-53 5E4-B-75 turbofan engines. 

(d) Reason 

This AD was prompted by RR updating the low-cycle-fatigue life analysis for the 

low pressure turbine (LPT) stage 2 discs. We are issuing this AD to prevent LPT stage 2 

disc failure, which could result in uncontained engine damage and damage to the 

airplane. 

7 
(e) Actions and Compliance 

(1) Within 30 days after the effecti ve date of this AD, re-calculate the cycli c life 

since new of each LPT stage 2 disc. Use the part li ves and prorated life fo rmulas in 

Appendices 1, 2, and 3 of RR Alert Non-Modification Service Bulletin (NMSB) No. 

RB.211-72-AH029, dated December 13 , 201 2, to make that calculation. 

(2) Assign the Maximum Approved Lives defined in Appendix 1 of Alert NMSB 

No. RB.211-72-AH029, dated December 13, 201 2, to the LPT stage 2 disc based on the 

flight profi le that will be fl own. 

(3) For engines that have an engine shop visit (ESV) after the effective date of 

this AD, remove the LPT stage 2 disc from service before the part exceeds the max imum 

approved life assigned in paragraph (e)(2) of this AD. 

(4) For those engines that do not have an ESV after the effecti ve date of this AD 

before the part exceeds the part life assigned in paragraph (e)(2) of this AD, remove the 

part from service at the next ESV. 

(f) Installation Prohibition 

With the exception of parts that can be reworked using RR Service Bulletin No . 

RB.2 11-72-D365, Revision 5, dated December 13, 201 2, do not reinstall any part 

removed per this AD into any engine. 

(g) Definitions 

For the purpose of this AD, an ESV is whenever engine maintenance perfo rmed 

prior to reinstallation requires the separation of a pair of major mating engine modul e 

flanges. Separation of flanges solely for the purpose of shipment without subsequent 

internal maintenance is not a shop visit. 

8 
(h) Alternative Methods of Compliance (AMOCs) 

The Manager, Engine Certification Offi ce, FAA, may approve AMOCs to this 

AD. Use the procedures fo und in 14 CFR 39.1 9 to make your request. 

(i) Related Information 

(1) For more information about this AD, contact Robert Green, Aerospace 

Engineer, Engine Certification Office, FAA, Engine & Propell er Directorate, 12 New 

England Executi ve Park, Burlington, MA 01803; phone: 781-23 8-7754; fax: 781-23 8-

71 99; email : Robert.Green@faa.gov. 

(2) Refer to European Aviation Safety Agency Airworthiness Directive 20 12-

0266, dated December 18, 20 12, and RR Alert NMSB No. RB.2 11-72-AH029, dated 

December 13, 201 2, for related info rmation. 

(3) For service info rmation 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- 249936; or email from http://www.rollsroyce.com/contact/civil_team.jsp; or download the publication from 

https://www.aeromanager.com. You may view this service info rmation at the FAA, 

Engine & Propell er Directorate, 12 New England Executive Park, Burlington, MA 

01803. For information on the availability ofthis material at the FAA, call 781-238-71 25 . 

9 
Issued in Burlington, Massachusetts, on March 28, 20 13. 

Coll een M. D' Alessandro, 

Assistant Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

10