40820 Federal Register / Vol. 77, No. 133 / Wednesday, July 11, 2012 / Proposed Rules 

For the Nuclear Regulatory Commission. 

Gregory Suber, 

Acting Deputy Director, Environmental 

Protection and Performance Assessment 

Directorate, Division of Waste Management 

and Environmental Protection, Office of 

Federal and State Materials and 

Environmental Management Programs. 

[FR Doc. 2012–16657 Filed 7–10–12; 8:45 am] 

BILLING CODE 7590–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0482; Directorate 

Identifier 2012–NE–14–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) RB211–524G2–19; 

RB211–524G2–T–19; RB211–524G3–19; 

RB211–524G3–T–19; RB211–524H2–19; 

RB211–524H2–T–19; RB211–524H–36; 

RB211–524H–T–36; RB211–535E4–37; 

RB211–535E4–B–37; RB211–535E4–B– 

75; and RB211–535E4–C–37 turbofan 

engines. This proposed AD was 

prompted by an investigation by RR 

concluding that certain intermediatepressure (IP) turbine discs produced 

before 1997 by a certain supplier may 

contain steel inclusions. This proposed 

AD would require removal of the 

affected IP turbine discs to inspect them 

for steel inclusions, and removal from 

service if the discs fail the inspection. 

This proposed AD would also require 

removal from service of some IP turbine 

discs at reduced life limits. We are 

proposing this AD to prevent 

uncontained IP turbine disc failure, 

engine failure, and damage to the 

airplane. 

DATES: We must receive comments on 

this proposed AD by September 10, 

2012. 

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 proposed AD, contact Rolls-Royce 

plc, Corporate Communications, P.O. 

Box 31, Derby, England, DE248BJ; 

phone: 011–44–1332–242424; fax: 011– 

44–1332–245418 or email from http:// 

www.rolls-royce.com/contact/ 

civil_team.jsp, or download the 

publication from https:// 

www.aeromanager.com. You may 

review copies of the referenced 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; 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: 

Alan Strom, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7143; fax: 781–238– 

7199; email: alan.strom@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–2012–0482; Directorate Identifier 

2012–NE–14–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– 

0060, dated April 18, 2012 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

The inspection of several intermediate 

pressure (IP) turbine discs at past engine 

overhauls identified the presence of steel 

inclusions in these parts. Further 

investigation concluded that all affected parts 

were manufactured from billets produced 

before 1997 at a certain supplier who also 

melted steel in the same furnaces. Initial 

engineering evaluation concluded that the 

lives of the parts would not be affected by the 

presence of the said steel inclusions. This 

evaluation has been recently repeated, 

utilising improved structural analysis, and it 

is now concluded that the currently 

published lives of the components cannot be 

supported for some discs with a steel 

inclusion. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

RR has issued RB211–524G, 524H, 

and 535E4 Propulsion Systems Alert 

Service Bulletin No. RB.211–72–AG493, 

Revision 1, dated November 11, 2011. 

The actions described in this service 

information are intended to confirm the 

presence or absence of steel inclusions 

on the affected IP turbine discs, and to 

require removal of certain discs at new 

lower life limits. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

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 


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Federal Register / Vol. 77, No. 133 / Wednesday, July 11, 2012 / Proposed Rules 40821 

and is likely to exist or develop on other 

products of the same type design. 

This proposed AD would require 

removal of the affected IP turbine discs 

to inspect them for steel inclusions, and 

if found, this AD would require removal 

from service. This proposed AD would 

also impose a new lower life limit on 

affected IP turbine discs. 

Costs of Compliance 

We estimate that this proposed AD 

would affect about 200 engines installed 

on airplanes of U.S. registry. We also 

estimate that it would take about 12.5 

work-hours per engine to inspect an IP 

turbine disc. The average labor rate is 

$85 per work-hour. In addition, 77 discs 

must be removed earlier than the 

existing Airworthiness Limitation 

Section requires. A prorated 

replacement IP turbine disc would cost 

about $9,925 per engine. We also 

estimate the cost of replacing a disc if 

it fails the inspection would be 

$225,000. Based on these figures, we 

estimate the cost of the proposed AD on 

U.S. operators to be $976,725. 

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 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 airworthiness 

directive (AD): 

Rolls-Royce plc: Docket No. FAA–2012– 

0482; Directorate Identifier 2012–NE– 

14–AD. 

(a) Comments Due Date 

We must receive comments by September 

10, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

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

RB211–524G2–19; RB211–524G2–T–19; 

RB211–524G3–19; RB211–524G3–T–19; 

RB211–524H2–19; RB211–524H2–T–19; 

RB211–524H–36; RB211–524H–T–36; 

RB211–535E4–37; RB211–535E4–B–37; 

RB211–535E4–B–75; and RB211–535E4–C– 

37 turbofan engines. 

(d) Reason 

This AD was prompted by an investigation 

by RR concluding that certain intermediatepressure (IP) turbine discs produced before 

1997 by a certain supplier may contain steel 

inclusions. We are issuing this AD to prevent 

uncontained IP turbine disc failure, engine 

failure, and damage to the airplane. 

(e) Actions and Compliance 

Unless already done, do the following 

actions. 

(f) Disc Inspection 

After the effective date of this AD, use 

Appendix 1 and Appendix 2 of RR RB211– 

524G, 524H, and 535E4 Propulsion Systems 

Alert Service Bulletin (ASB) No. RB.211–72– 

AG493, Revision 1, dated November 11, 

2011; to determine if the IP turbine disc is 

below or above the inspection threshold. 

(1) If below the inspection threshold then 

clean, demagnetize, and perform a 

Superconductive Quantitative Inductive 

Device (SQUID) inspection of the disc at the 

next shop visit or before the disc reaches the 

inspection threshold, whichever is later. Use 

Appendix 4 of RR RB211–524G, 524H, and 

535E4 Propulsion Systems ASB No. RB.211– 

72–AG493, Revision 1, dated November 11, 

2011, to perform the SQUID inspection. 

(2) If above the inspection threshold, clean, 

demagnetize and perform a SQUID 

inspection of the disc if in the shop or, at the 

next shop visit, whichever occurs first. Use 

Appendix 4 of RR RB211–524G, 524H, and 

535E4 Propulsion Systems ASB No. RB.211– 

72–AG493, Revision 1, dated November 11, 

2011, to perform the SQUID inspection. 

(3) Do not return to service any disc that 

fails the inspection required by this AD. 

(g) Disc Life Reduction 

(1) After the effective date of this AD, use 

Appendix 2 of RR RB211–524G, 524H, and 

535E4 Propulsion Systems ASB No. RB.211– 

72–AG493, Revision 1, dated November 11, 

2011, to determine the new lower life of 

affected IP turbine disc(s). 

(2) Remove from service any disc at the 

next shop visit or before it exceeds its new 

lower life limit, whichever is later, as found 

in Appendix 2 of RR RB211–524G, 524H, and 

535E4 Propulsion Systems ASB No. RB.211– 

72–AG493, Revision 1, dated November 11, 

2011. 

(3) Do not return to service any disc that 

exceeds its new lower life limit, as found in 

Appendix 2 of RR RB211–524G, 524H, and 

535E4 Propulsion Systems ASB No. RB.211– 

72–AG493, Revision 1, dated November 11, 

2011. 

(h) Definition of Shop Visit 

For purposes of this AD, a shop visit is 

defined as induction into the shop where the 

IP and low pressure (LP) turbine module is 

removed from the engine, and any casing is 

removed from the IP and LP turbine module. 

(i) 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. 

(j) Related Information 

(1) For more information about this AD, 

contact Alan Strom, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7143; fax: 781–238–7199; 

email: alan.strom@faa.gov. 

(2) European Aviation Safety Agency AD 

2012–0060, dated April 18, 2012, and RollsRoyce plc RB211–524G, 524H, and 535E4 

Propulsion Systems ASB No. RB.211–72– 

AG493, Revision 1, dated November 11, 

2011, pertain to the subject of this AD. 

(3) For service information identified in 

this AD, contact Rolls-Royce plc, Corporate 

Communications, P.O. Box 31, Derby, 


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40822 Federal Register / Vol. 77, No. 133 / Wednesday, July 11, 2012 / Proposed Rules 

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

242424; fax: 011–44–1332–245418 or email 

from http://www.rolls-royce.com/contact/ 

civil_team.jsp, or download the publication 

from https://www.aeromanager.com. You 

may review copies of the referenced 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 

June 25, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–16856 Filed 7–10–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0546; Directorate 

Identifier 2012–NE–15–AD] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Division 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 Pratt 

& Whitney PW4050, PW4052, PW4056, 

PW4060, PW4060A, PW4060C, 

PW4062, PW4062A, PW4152, PW4156, 

PW4156A, PW4158, PW4160, PW4460, 

PW4462, and PW4650 turbofan engines, 

including models with any dash number 

suffix. This proposed AD was prompted 

by 16 reports of damaged or failed 3rd 

stage low-pressure turbine (LPT) duct 

segments. This proposed AD would 

require removing from service certain 

part numbers (P/Ns) of 3rd stage LPT 

duct segments. We are proposing this 

AD to prevent failure of the 3rd stage 

LPT duct segments, which could lead to 

LPT rotor damage, uncontained engine 

failure, and damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by September 10, 

2012. 

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 Pratt & 

Whitney, 400 Main St., East Hartford, 

CT 06108; phone: 860–565–8770; fax: 

860–565–4503. You may review copies 

of the referenced 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; 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: 

James Gray, Aerospace Engineer, Engine 

& Propeller Directorate, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7742; fax: 781– 

238–7199; email: james.e.gray@faa.gov. 

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– 

2012–0546; Directorate Identifier 2012– 

NE–15–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 

We received 16 reports of damaged or 

failed 3rd stage LPT duct segments that 

resulted in 5 in-flight shutdowns, two of 

which were uncontained engine 

failures. The 3rd stage LPT duct 

segment assembly has seal plates that 

are attached with rivets. During normal 

engine operation, vibration may cause 

these seal plates to loosen or fall off, 

which allows hot gaspath air to enter 

the cavity behind the duct. This can 

cause the 3rd stage LPT duct segment to 

distort, fall into the gaspath, and 

damage the downstream LPT rotor 

blades. This condition, if not corrected, 

could result in failure of the 3rd stage 

LPT duct segments, which could lead to 

LPT rotor damage, uncontained engine 

failure, and damage to the airplane. 

Relevant Service Information 

We reviewed Pratt & Whitney EngineDuct Segment, Third Stage LPT 

Assembly Service Bulletin (SB) No. 

PW4ENG 72–488, Revision 3, dated 

August 13, 2009. The SB lists the part 

numbers of parts to be removed and 

parts to be installed. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

removal from service of 3rd stage LPT 

duct segments P/Ns 50N095; 50N095– 

001; 50N235; 50N235–001; 50N494–01; 

50N494–001; 50N495–01; and 50N495– 

001, at the next piece-part exposure 

after the effective date of the proposed 

AD. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 151 engines installed on 

airplanes of U.S. registry. We estimate 

that no additional labor costs would be 

incurred to perform the required work 

as the work is done when the 3rd stage 

LPT duct segments are at piece-part 

exposure. The average labor rate is $85 

per work-hour. Required parts would 

cost about $44,441 per engine. Based on 

these figures, we estimate the total cost 

of the AD to U.S. operators to be 

$6,710,591. 

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. 


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