Federal Register / Vol. 78, No. 66 / Friday, April 5, 2013 / Proposed Rules 20507 

(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. 

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—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

Rolls-Royce plc: Docket No. FAA–2013– 

0143; Directorate Identifier 2013–NE– 

06–AD. 

(a) Comments Due Date 

We must receive comments by June 4, 

2013. 

(b) Affected Airworthiness Directives (ADs) 

None. 

(c) Applicability 

This AD applies to: 

(1) All Rolls-Royce plc (RR) RB211–524G2– 

19; –524G3–19; –524H2–19; and –524H–36 

turbofan engines. 

(2) RR RB211–524B–02; –524B2–19; 

–524B3–02; –524B4–02; –524C2–19; 

–524D4–19; –524D4–B–19; and –524D4–39 

that have incorporated RR Service Bulletin 

(SB) No. RB.211–72–7221, dated December 7, 

1984. 

(3) All RR RB211–535C–37; –535E4–37; 

–535E4–B–37, and –535E4–B–75 turbofan 

engines, except those engines that have 

incorporated RR SB No. RB.211–72–C230, 

dated November 16, 1999, or Revision 1, 

dated November 22, 2012. 

(4) This AD does not apply to engines 

listed in paragraphs (c)(1) through (c)(3): 

(i) That have installed a front combustion 

liner (FCL) metering panel delivered from RR 

after April 23, 2011; or 

(ii) That were inspected before the effective 

date of this AD using RR Alert NonModification Service Bulletin (NMSB) No. 

RB.211–72–AF572, dated October 15, 2007, 

or Revision 1, dated October 8, 2008, or 

Revision 2, dated April 2, 2009, or RR 

Repeater Technical Variance No. 75295, Issue 

1, dated April 20, 2007. 

(d) Reason 

This AD was prompted by the discovery of 

a cracked and distorted FCL metering panel, 

made from the wrong material. We are 

issuing this AD to prevent hot gas burning 

through the engine casing, which could 

result in an under-cowl fire and damage to 

the airplane. 

(e) Actions and Compliance 

Unless already done, do the following 

actions. 

(1) At the next engine shop visit or within 

625 flight cycles, whichever occurs first after 

the effective date of this AD, perform a onetime inspection of the FCL metering panel to 

determine if it was made from N75 material, 

and replace it if made from N75 material, 

with one made from C263 material. 

(2) To inspect RB211–524 series turbofan 

engines, use Section 3., Accomplishment 

Instructions, of Alert NMSB No. RB.211–72– 

AG183, Revision 3, dated December 6, 2012, 

except reporting requirement paragraph 2 of 

Appendices 1 and 2 of that Alert NMSB. 

(3) To inspect RB211–535 series turbofan 

engines, use Section 3., Accomplishment 

Instructions, of Alert NMSB No. RB.211–72– 

AG046, Revision 3, dated December 6, 2012, 

except reporting requirement paragraph 2 of 

Appendices 1 and 2 of that Alert NMSB. 

(f) Definitions 

For the purpose of this AD, a shop visit is 

the induction of an engine into the shop for 

maintenance or overhaul. The separation of 

engine flanges solely for the purposes of 

transporting the engine without subsequent 

engine maintenance does not constitute an 

engine shop visit. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. 

(h) Related Information 

(1) For more information about this AD, 

contact Robert Green, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

email: robert.green@faa.gov; phone: 781– 

238–7754; fax: 781–238 7199. 

(2) Refer to European Aviation Safety 

Agency AD 2012–0215R1, dated January 4, 

2013, RR Alert NMSB No. RB.211–72– 

AG183, Revision 3, dated December 6, 2012, 

and Alert NMSB No. RB.211–72–AG046, 

Revision 3, dated December 6, 2012, for 

related information. 

(3) For service information identified in 

this AD, contact Rolls-Royce plc, Corporate 

Communications, P.O. Box 31, Derby, 

England, DE248BJ; phone: 011–44–1332– 

242424; fax: 011–44–1332–249936 or email 

from http://www.rolls-royce.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. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

March 29, 2013. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–07930 Filed 4–4–13; 8:45 am] 

BILLING CODE 4910–13–P 

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 

plc 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 

Rolls-Royce 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-cyclefatigue life analysis for the low pressure 

turbine (LPT) stage 2 discs. This 

proposed AD would require removal of 

affected parts 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 June 4, 2013. 

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 W12–140, 

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 plc, 

Corporate Communications, P.O. Box 

31, Derby, England, DE248BJ; phone: 

011–44–1332–242424; fax: 011–44– 

1332–249936; or email from http:// 

www.rolls-royce.com/contact/ 

civil_team.jsp; or download the 

publication from https:// 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
20508 Federal Register / Vol. 78, No. 66 / Friday, April 5, 2013 / Proposed Rules 

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 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; 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 available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Robert Green, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

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 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. 

Using the search function of the Web 

site, anyone can find and read the 

comments in any of our dockets, 

including, if provided, the name of the 

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 April 11, 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 December 18, 2012, to 

correct an unsafe condition for the 

specified products. That mandatory 

continuing airworthiness information 

(MCAI) states: 

A recent re-evaluation of Critical Part lives 

carried out by Rolls-Royce revealed changes 

to the thermal profile and stresses in certain 

features of the low pressure turbine (LPT) 

Stage 2 disc. These changes have resulted in 

a reduction of the cyclic life of the 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, which 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.211– 

72–AH029, dated December 13, 2012. 

The NMSB introduces new LPT stage 2 

disc part lives that will be the 

drawdown plan retirement thresholds. 

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 design. This 

proposed AD would require removal of 

affected LPT stage 2 discs using a 

drawdown plan. 

Differences Between the AD and the 

MCAI or Service Information 

This AD differs from EASA AD 2012– 

0266, dated December 18, 2012, as 

follows: The EASA AD specifies 

replacing the affected critical parts 

during the module disassembly if the 

subsequent, anticipated 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.211–72–AH029, 

dated December 13, 2012. We specify 

replacing at next shop visit (defined by 

the separation of a major flange). 

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 scheduled shop visits. Prorated 

cost of the parts adjusted for lost life is 

about $8,290 per engine. Based on these 

figures, 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 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. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism 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 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); 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 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 66 / Friday, April 5, 2013 / Proposed Rules 20509 

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. 

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—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

Rolls-Royce plc: Docket No. FAA–2013– 

0052; Directorate Identifier 2013–NE– 

02–AD. 

(a) Comments Due Date 

We must receive comments by June 4, 

2013. 

(b) Affected Airworthiness Directives (ADs) 

None. 

(c) Applicability 

This AD applies to all Rolls-Royce plc (RR) 

RB211–535E4–37, RB211–535E4–B–37, 

RB211–535E4–C–37, and RB211–535E4–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. 

(e) Actions and Compliance 

(1) Within 30 days after the effective date 

of this AD, re-calculate the cyclic life since 

new of each LPT stage 2 disc. Use the part 

lives and prorated life formulas in 

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

RB.211–72–AH029, dated December 13, 

2012, 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, 

2012, to the LPT stage 2 disc based on the 

flight profile that will be flown. 

(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 maximum 

approved life assigned in paragraph (e)(2) of 

this AD. 

(4) For those engines that do not have an 

ESV after the effective 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.211–72–D365, Revision 5, dated 

December 13, 2012, 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 performed 

prior to reinstallation requires the separation 

of a pair of major mating engine module 

flanges. Separation of flanges solely for the 

purpose of shipment without subsequent 

internal maintenance is not a shop visit. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs to this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(i) Related Information 

(1) For more information about this AD, 

contact Robert Green, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7754; fax: 781–238–7199; 

email: Robert.Green@faa.gov. 

(2) Refer to European Aviation Safety 

Agency Airworthiness Directive 2012–0266, 

dated December 18, 2012, and RR Alert 

NMSB No. RB.211–72–AH029, dated 

December 13, 2012, for related information. 

(3) For service information identified in 

this AD, contact Rolls-Royce plc, Corporate 

Communications, P.O. Box 31, Derby, 

England, DE248BJ; phone: 011–44–1332– 

242424; fax: 011–44–1332–249936; or email 

from http://www.rolls-royce.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 of 

this material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

March 28, 2013. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–07931 Filed 4–4–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0029; Directorate 

Identifier 2013–NE–01–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc 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 

Rolls-Royce plc (RR) RB211–535E4–B– 

37 series turbofan engines. This 

proposed AD was prompted by 

recalculating the life of certain life 

limited parts operated to certain flight 

profiles. This proposed AD would 

require removal of affected parts using 

a drawdown plan. We are proposing this 

AD to prevent the failure of critical 

rotating parts, which could result in 

uncontained failure of the engine and 

damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by June 4, 2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Rolls-Royce 

plc, Corporate Communications, P.O. 

Box 31, Derby, England, DE248BJ; 

phone: 011–44–1332–242424; fax: 011– 

44–1332–249936 or email from http:// 

www.rolls-royce.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. For information on the availability 

of this material at the FAA, call 781– 

238–7125. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS