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
20510 Federal Register / Vol. 78, No. 66 / Friday, April 5, 2013 / Proposed Rules 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street 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: 

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. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2013–0029; Directorate Identifier 2013– 

NE–01–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 because of 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 we receive 

about 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 2012– 

0265, dated December 18, 2012 (referred 

to herein after as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified product. The MCAI states: 

Flight Profiles (FP) define the limits of 

engine operation within which the engine 

will qualify for use of an associated set of 

Critical Parts life limits. The Rolls-Royce 

RB211–535E4–B–37 engine previously had 

only one such FP and associated set of life 

limits published in the applicable RR Time 

Limits Manual. 

However, a recent review of operational 

flight data has revealed that some engines 

may have been operated beyond the currently 

valid datum FP. 

Failure to account for the correct rate of 

fatigue damage associated with engine 

operation may lead to Critical Parts failure, 

possibly resulting in release of high energy 

debris, damage to the aeroplane and/or injury 

to occupants. 

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. 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–AG875, dated December 13, 2012. 

The Alert NMSB introduces two new 

datum flight profiles (Flight Profile D 

and Flight Profile E) and the life-limited 

part lives that are 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 parts using a drawdown plan. 

Differences Between the AD and the 

MCAI or Service Information 

This AD differs from EASA AD 2012– 

0265, 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. 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 377 engines installed 

on airplanes of U.S. registry. Of these 

377 engines, we estimate 95 engines 

operate to Flight Profile D or E. The 

average labor rate is $85 per work hour. 

We do not estimate any labor cost is 

associated with this proposed AD 

because the affected parts are replaced 

at the next shop visit. Prorated cost of 

parts adjusted to Flight Profile D 

operation, would cost about $77,672 per 

engine. Prorated cost of parts adjusted to 

Flight Profile E operation, would cost 

about $204,981 per engine. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$11,834,655. 

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), 

(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. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 66 / Friday, April 5, 2013 / Proposed Rules 20511 

1The Commission voted 2–1 to approve 

publication of this proposed rule. Chairman Inez M. 

Tenenbaum and Commissioner Robert S. Adler 

voted to approve publication, and Commissioner 

Nancy A. Nord voted against publication. 

Commissioner’s statements concerning this or any 

other Commission action may be viewed by clicking 

on a specific Commissioner’s name and selecting 

‘‘Statements’’ on the Commission’s Web site at 

http://www.cpsc.gov/en/About-CPSC/ 

Commissioners/, or obtained from the 

Commission’s Office of the Secretary. 

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 airworthiness 

directive (AD): 

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

0029; Directorate Identifier 2013–NE– 

01–AD. 

(a) Comments Due Date 

We must receive comments by June 4, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Rolls-Royce plc (RR) 

RB211–535E4–B–37 series turbofan engines. 

(d) Unsafe Condition 

This AD was prompted by recalculating the 

life of certain life limited parts operated to 

certain flight profiles. We are issuing this AD 

to prevent the failure of critical rotating parts, 

which could result in uncontained failure of 

the engine and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Within 30 days after the effective date 

of this AD for engines that have operated to 

Flight Profile D or E, recalculate the life of 

the low-pressure (LP) turbine disc stage 2, 

intermediate-pressure (IP) compressor rotor 

shaft (stage 1 to 6), high-pressure (HP) 

compressor rear rotor shaft assembly, and HP 

turbine disc installed on that engine. Use the 

part lives, prorated life formulas, and flight 

profiles in Appendices 2, 4, and 5 of RR Alert 

Non-Modification Service Bulletin (NMSB) 

No. RB.211–72–AG875, dated December 13, 

2012, to make that calculation. 

(2) Within 30 days after the effective date 

of this AD for engines that will operate to 

Flight Profile D or E, assign the Maximum 

Approved Lives defined in Appendix 2 of RR 

Alert NMSB No. RB.211–72–AG875, dated 

December 13, 2012, to the LP turbine disc 

Stage 2, IP compressor rotor shaft (stage 1 to 

6), HP compressor rear rotor shaft assembly, 

and HP turbine disc based on the flight 

profile that will be flown. 

(3) For engines that have only operated to, 

and will continue to operate to, Flight Profile 

C, as defined in Appendix 5 of RR Alert 

NMSB No. RB.211–72–AG875, dated 

December 13, 2012, no further action is 

required by this AD. 

(4) For engines that incorporate an LP 

turbine disc stage 2, IP compressor rotor shaft 

(stage 1 to 6), HP compressor rear rotor shaft 

assembly, or HP turbine disc whose part life 

is defined by paragraph (e)(1) of this AD that 

have an engine shop visit (ESV) after the 

effective date of this AD, remove each part 

from service before the part exceeds the part 

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

(5) For those engines that incorporate an 

LP turbine disc stage 2, IP compressor rotor 

shaft (stage 1 to 6), HP compressor rear rotor 

shaft assembly, or HP turbine disc whose part 

life is defined by paragraph (e)(1) of this AD, 

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 

After the effective date of this AD, any LP 

turbine disc stage 2, IP compressor rotor shaft 

(stage 1 to 6), HP compressor rear rotor shaft 

assembly, or HP turbine disc whose part life 

is defined by paragraph (e)(1) of this AD that 

is re-installed in any engine after the effective 

date of this AD must be removed from service 

before the part exceeds the part life assigned 

in paragraph (e)(2) of this AD. 

(g) Definitions 

For the purpose of this AD, 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 an ESV. 

(h) 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. 

(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; 

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

238–7754; fax: 781–238–7199. 

(2) Refer to EASA AD 2012–0265, dated 

December 18, 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. 2013–07935 Filed 4–4–13; 8:45 am] 

BILLING CODE 4910–13–P 

CONSUMER PRODUCT SAFETY 

COMMISSION 

16 CFR Parts 1112 and 1226 

[Docket No. CPSC–2013–0014] 

Safety Standard for Soft Infant and 

Toddler Carriers 

AGENCY: Consumer Product Safety 

Commission. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: The Danny Keysar Child 

Product Safety Notification Act, Section 

104 of the Consumer Product Safety 

Improvement Act of 2008 (CPSIA), 

requires the United States Consumer 

Product Safety Commission 

(Commission or CPSC) to promulgate 

consumer product safety standards for 

durable infant or toddler products. 

These standards are to be ‘‘substantially 

the same as’’ applicable voluntary 

standards or more stringent than the 

voluntary standard if the Commission 

concludes that more stringent 

requirements would further reduce the 

risk of injury associated with the 

product. The Commission is proposing 

a safety standard for soft infant and 

toddler carriers in response to the 

direction under Section 104(b) of the 

CPSIA.1

DATES: Submit comments by June 19, 

2013. 

ADDRESSES: Comments related to the 

Paperwork Reduction Act aspects of the 

marking, labeling, and instructional 

literature of the proposed rule should be 

directed to the Office of Information and 

Regulatory Affairs, OMB, Attn: CPSC 

Desk Officer, FAX: 202–395–6974, or 

emailed to 

oira_submission@omb.eop.gov. 

Other comments, identified by Docket 

No. CPSC–2013–0014, may be 

submitted electronically or in writing: 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS