Federal Register / Vol. 76, No. 201 / Tuesday, October 18, 2011 / Proposed Rules 64283 

be considered for a Proposed Determination. 

Before a vote of the Council with respect to 

a particular nonbank financial company, the 

Council members will review information 

relevant to the consideration of the nonbank 

financial company for a Proposed 

Determination. After this review, the Council 

may, by a vote of two-thirds of its members 

(including an affirmative vote of the Council 

Chairperson), make a Proposed 

Determination with respect to the nonbank 

financial company. Following a Proposed 

Determination, the Council intends to issue 

a written notice of the Proposed 

Determination to the nonbank financial 

company, which will include an explanation 

of the basis of the Proposed Determination. 

The Council expects to notify any nonbank 

financial company in the Stage 3 Pool if the 

nonbank financial company, either before or 

after a Proposed Determination of such 

nonbank financial company, ceases to be 

considered for determination. Any nonbank 

financial company that ceases to be 

considered at any time in the Council’s 

determination process may be considered for 

Proposed Determination in the future at the 

Council’s discretion. 

A nonbank financial company that is 

subject to a Proposed Determination may 

request a hearing to contest the Proposed 

Determination in accordance with section 

113(e) of the Dodd-Frank Act. If the nonbank 

financial company requests a hearing in 

accordance with the procedures set forth in 

section 1310.21(c) of the proposed rule, the 

Council will set a time and place for such 

hearing. The Council will (after a hearing, if 

a hearing is requested), determine by a vote 

of two-thirds of the voting members of the 

Council (including the affirmative vote of the 

Chairperson) whether to subject such 

company to supervision by the Board of 

Governors and prudential standards. The 

Council will provide the nonbank financial 

company with written notice of the Council’s 

final determination, including an explanation 

of the basis for the Council’s decision. In 

accordance with section 113(h) of the DoddFrank Act, a nonbank financial company that 

is subject to a final determination may bring 

an action in U.S. district court for an order 

requiring that the determination be 

rescinded. 

Dated: October 11, 2011. 

Alastair Fitzpayne, 

Executive Secretary, Department of the 

Treasury. 

[FR Doc. 2011–26783 Filed 10–17–11; 8:45 am] 

BILLING CODE 4810–25–P–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28059; Directorate 

Identifier 2007–NE–13–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc (RR) Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to all RR RB211–Trent 553– 

61, 553A2–61, 556–61, 556A2–61, 

556B–61, 556B2–61, 560–61, 560A2–61, 

768–60, 772–60, 772B–60, 875–17, 877– 

17, 884–17, 884B–17, 892–17, 892B–17, 

and 895–17 turbofan engines. The 

existing AD currently requires 

inspecting the intermediate-pressure 

(IP) compressor rotor shaft rear balance 

land for cracks. Since we issued that 

AD, we received reports of one RB211– 

Trent 700 and two additional RB211– 

Trent 800 IP compressor rotor shafts 

that have been found cracked. This 

proposed AD would continue to require 

initial inspections, add additional 

inspections, and an optional terminating 

action. The cracking identified above 

could lead to IP compressor rotor shaft 

failure, uncontained engine failure, and 

damage to the airplane. We are 

proposing this AD to correct the unsafe 

condition on these products. 

DATES: We must receive comments on 

this proposed AD by December 2, 2011. 

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 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 e-mail from http:// 

www.rolls-royce.com/contact/ 

civil_team.jsp. You may review copies 

of the referenced 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 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: 

Alan Strom, Aerospace Engineer, Engine 

Certification Office, FAA, 12 New 

England Executive Park, Burlington, 

MA; phone: 781–238–7143; fax: 781– 

238–7199; e-mail: 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–2007–28059; Directorate Identifier 

2007–NE–13–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 

On August 25, 2008, we issued AD 

2008–18–08, Amendment 39–15665 (73 

FR 52201, September 9, 2008), for all 

Rolls-Royce plc RB211–Trent 553–61, 

553A2–61, 556–61, 556A2–61, 556B–61, 

556B2–61, 560–61, 560A2–61, 768–60, 

772–60, 772B–60, 875–17, 877–17, 884– 

17, 884B–17, 892–17, 892B–17, and 

895–17 turbofan engines. That AD 

requires a onetime eddy current 

inspection (ECI) of the rear balance land 

of the IP compressor rotor shaft for 

cracks. That AD resulted from reports of 


srobinson on DSK4SPTVN1PROD with PROPOSALS
64284 Federal Register / Vol. 76, No. 201 / Tuesday, October 18, 2011 / Proposed Rules 

cracking on the rear balance land of IP 

compressor rotor shafts. We issued that 

AD to detect cracking on the rear 

balance land of the IP compressor rotor 

shaft. Cracking on the rear balance land 

on the IP compressor rotor shaft can 

lead to failure of the rotor shaft and 

damage to the engine. 

Actions Since Existing AD Was Issued 

Since we issued AD 2008–18–08, (73 

FR 52201, September 9, 2008), RR 

reports that they have introduced an 

optional terminating action to the 

repetitive inspections required by that 

AD. RR also reported that for those 

operators not adopting the optional 

terminating action, improved inspection 

methods for the RB211–Trent 700 and 

RB211–Trent 800 turbofan engines are 

necessary. Also, EASA issued AD 2010– 

0266, dated December 21, 2010, and AD 

2010–0266R1, dated January 6, 2011, to 

require repetitive on-wing and in-shop 

ECIs on RB211–Trent 700 and RB211– 

Trent 800 engines and repetitive in-shop 

visual inspections on the RB211–Trent 

500, RB211–Trent 700, and RB211– 

Trent 800 engines. EASA issued their 

ADs because RR had reported finding 

additional cracks on the IP compressor 

rotor shaft of two in-service RB211– 

Trent 800 engines and on one in-service 

RB211–Trent 700 engine. The cracking 

had initiated from frettage marks caused 

by balance weights. RR reports that 

stress analysis has shown that the 

cracking presents a possible threat to the 

rotor integrity. We evaluated the data 

supplied by EASA and RR, and concur 

that the improved inspections for cracks 

on the balance land of the IP compressor 

rotor shaft are required. We have 

evaluated the optional terminating 

action and determined it to be effective. 

These cracks, if present, could result 

in an unsafe condition leading to IP 

compressor rotor shaft failure and 

damage to the engine. 

Relevant Service Information 

We reviewed RR Alert Service 

Bulletins (ASB) No. RB.211–72–AF260, 

Revision 5, dated July 7, 2011, ASB No. 

RB.211–72–AG085, Revision 2, dated 

July 7, 2011, ASB No. RB.211–72– 

AG264, Revision 5, dated March 21, 

2011, ASB No. RB.211–72–AG270, 

Revision 4, dated March 21, 2011, and 

Service Bulletin No. RB.211–72–G448, 

Revision 3, dated July 7, 2011 which 

provide information for the inspections 

required by this AD. 

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 these same 

type designs. 

Proposed AD Requirements 

This proposed AD would require: 

• For the RB211–Trent 700 and 

RB211–Trent 800 engines, on wing 

initial and repetitive borescope 

inspections and when in the shop, 

repetitive ECIs for cracks on the rear 

balance land; and 

• For the RB211–Trent 500 engines, 

initial and repetitive in-shop visual 

inspections or ECIs for cracks on the 

rear balance land. 

This proposed AD would also add an 

optional terminating action to the 

repetitive inspection requirements for 

the RB211–Trent 700 and RB211–Trent 

800 engines. 

Costs of Compliance 

We estimate that this proposed AD 

would affect about 136 engines installed 

on airplanes of U.S. registry. We also 

estimate that it would take about 6 

work-hours per engine to perform the 

proposed inspections and that the 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

total cost of the proposed AD to U.S. 

operators to be $69,360. 

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 have 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 that the 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, 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—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 

removing airworthiness directive (AD) 

2008–18–08, Amendment 39–15665 (73 

FR 52201, September 9, 2008), and 

adding the following new AD: 

Rolls-Royce plc: Docket No. FAA–2007– 

28059; Directorate Identifier 2007–NE– 

13–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by December 2, 2011. 

(b) Affected ADs 

This AD supersedes AD 2008–18–08, 

Amendment 39–15665, (73 FR 52201, 

September 9, 2008). 

(c) Applicability 

This AD applies to Rolls-Royce plc (RR) 

RB211–Trent 553–61, 553A2–61, 556–61, 

556A2–61, 556B–61, 556B2–61, 560–61, 

560A2–61, 768–60, 772–60, 772B–60, 875– 

17, 877–17, 884–17, 884B–17, 892–17, 892B– 

17, and 895–17 turbofan engines. 

(d) Unsafe Condition 

We are superseding AD 2008–18–08 

because additional cracking on RB211–Trent 

700 and RB211–Trent 800 intermediatepressure (IP) compressor rotor shafts has 

been found since that AD was issued. This 

cracking could lead to IP compressor rotor 

shaft failure, uncontained engine failure, and 

damage to the airplane. 


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Federal Register / Vol. 76, No. 201 / Tuesday, October 18, 2011 / Proposed Rules 64285 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) RB211-Trent 700 Series Engines—Rear 

Balance Land Inspections 

(1) On-Wing Inspections 

Perform on-wing inspections as follows: 

(i) Within 625 cycles-in-service (CIS) after 

the effective date of this AD, borescope 

inspect the IP compressor rotor shaft rear 

balance land. Use RR Alert Service Bulletin 

(ASB) No. RB.211–72–AG270, Revision 4, 

dated March 21, 2011, sections 3.A.(2)(a) 

through 3.A.(2)(c) and 3.A.(3)(a) through 

3.A.(3)(c), or 3.B.(2)(a) through 3.B.(2)(c) and 

3.B.(4)(a) through 3.B.(4)(c), to do the 

inspection. 

(ii) Thereafter, repeat the inspection within 

every 625 cycles-since-last inspection (CSLI). 

You may count CSLI from the last borescope 

inspection or the last eddy current 

inspection, whichever has occurred last. 

(2) In-Shop Inspections 

At each shop visit, eddy current inspect 

(ECI) and visually inspect the IP compressor 

rotor shaft rear balance land, and visually 

inspect the balance weights. Use RR ASB No. 

RB.211–72–AG085, Revision 2, dated July 7, 

2011, sections 3.A. through 3.D.(3)(b)(v), 

except paragraphs 3.D.(3)(a)(ii) and 

3.D.(3)(b)(iii) to do the inspections. 

(3) RB211-Trent 800 Series Engines—Rear 

Balance Land Inspections 

(1) On-Wing Inspections 

(i) Within 475 CIS after the effective date 

of this AD, borescope inspect the IP 

compressor rotor shaft rear balance land. Use 

RR ASB No. RB.211–72–AG264, Revision 5, 

dated March 21, 2011, sections 3.B.(2)(a) 

through 3.B.(2)(c) and 3.B.(4)(a) through 

3.B.(4)(c) to do the inspection. 

(ii) Thereafter, repeat the inspection within 

every 475 CSLI. You may count CSLI from 

the last borescope inspection or the last eddy 

current inspection, whichever has occurred 

last. 

(2) In-Shop Inspections 

At each shop visit, ECI and visually inspect 

the IP compressor rotor rear shaft balance 

land, and visually inspect the balance 

weights. Use RR ASB No. RB.211–72–AG085, 

Revision 2, dated July 7, 2011, sections 3.A. 

through 3.D.(3)(b)(v), except paragraphs 

3.D.(3)(a)(ii) and 3.D.(3)(b)(iii), to do the 

inspections. 

(h) RB211-Trent 500 Series Engines—InShop Rear Balance Land Inspections 

At each shop visit, ECI the IP compressor 

rotor shaft and visually inspect the balance 

weights. Use RR ASB No. RB.211–72–AF260, 

Revision 5, dated July 7, 2011 sections 3.A. 

through 3.B.(3)(a)(iii) to do the visual 

inspection, or RR SB No. RB.211–72–G448, 

Revision 3, dated July 7, 2011 section 3.D.(1) 

through 3.D.(14) to do the ECI. 

(i) Definition 

For the purposes of this AD, a shop visit 

is defined as introduction of an engine into 

a shop, and disassembly sufficient to expose 

the IP compressor module rear face. 

(j) Optional Terminating Action for RB211- 

Trent 700 and RB211-Trent 800 Engines 

(1) Modifying an RB211-Trent 700 engine 

as specified in RR SB No. RB.211–72–G402, 

Revision 2, dated July 7, 2011, or RR SB No. 

RB.211–72–G402, Revision 1, dated January 

11, 2011, is terminating action for paragraph 

(f)(2) of this AD. 

(2) Modifying an RB211-Trent 800 engine 

as specified in RR SB No. RB.211–72–G401, 

Revision 2, dated July 5, 2011, or SB No. 

RB.211–72–G401, Revision 1, dated January 

11, 2011, is terminating action for paragraph 

(h)(2) of this AD. 

(k) Previous Credit 

(1) For RB211-Trent 700 series engines: 

(i) On-wing inspections done before the 

effective date of this AD using RR ASB No. 

RB.211–72–AG270, Revision 1, dated 

December 14, 2009, or Revision 2, dated 

December 21, 2010, or Revision 3, dated 

February 25, 2011, meet the inspection 

requirements in paragraph (f) of this AD. 

(ii) In-shop inspections done before the 

effective date of this AD using RR ASB No. 

RB.211–72–AG085, Revision 1, dated 

September 27, 2010, meet the inspection 

requirements in paragraph (g) of this AD. 

(2) For RB211-Trent 800 series engines: 

(i) On-wing inspections done before the 

effective date of this AD using RR ASB No. 

RB.211–72–AG264, Revision 3, dated 

December 21, 2010, or Revision 4, dated 

February 25, 2011, meet the inspection 

requirements in paragraph (h) of this AD. 

(ii) In-shop inspections done before the 

effective date of this AD using RR ASB No. 

RB.211–72–AG085, Revision 1, dated 

September 27, 2010, meet the inspection 

requirements in paragraph (i) of this AD. 

(3) For RB211-Trent 500 series engines: 

(i) In-shop visual inspections done before 

the effective date of this AD using RR ASB 

No. RB.211–72–AF260, Revision 4, dated 

July 28, 2009, meet the inspection 

requirements in paragraph (j) of this AD. 

(ii) In-shop ECIs done before the effective 

date of this AD using RR ASB No. RB.211– 

72–G448, Revision 2, dated December 23, 

2010, meet the ECI requirements in 

paragraph (j) of this AD. 

(l) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures in 14 CFR 39.19 to request an 

AMOC. 

(m) Related Information 

(1) For more information about this AD, 

contact Alan Strom, Aerospace Engineer, 

Engine Certification Office, FAA, 12 New 

England Executive Park, Burlington, MA; 

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

e-mail: alan.strom@faa.gov. 

(2) 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: 011–44–1332–245418; or e-mail 

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

civil_team.jsp. You may review copies of the 

referenced 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 

October 6, 2011. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–26821 Filed 10–17–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0948; Directorate 

Identifier 2009–NE–30–AD] 

RIN 2120–AA64 

Airworthiness Directives; Thielert 

Aircraft Engines GmbH (TAE) Models 

TAE 125–02–99 and TAE 125–01 

Reciprocating Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to revise an 

existing airworthiness directive (AD) for 

the products listed above. This 

proposed AD results from mandatory 

continuing airworthiness information 

(MCAI) issued by an aviation authority 

of another country to identify and 

correct an unsafe condition on an 

aviation product and from a comment 

received from the European Aviation 

Safety Agency (EASA) on AD 2010–06– 

12, (75 FR 12439, March 16, 2010). The 

MCAI describes the unsafe condition as: 

As a consequence of occurrences and 

service experience, Thielert Aircraft Engines 

GmbH has introduced a new rail pressure 

control valve part number (P/N) 05–7320– 

E000702 and has amended the Airworthiness 

Limitation Section (ALS) of the Operation & 

Maintenance Manual OM–02–02 to include a 

replacement of the rail pressure control 

valve. Failure of this part could result in inflight shutdowns of the engine(s). 

TAE has also amended the ALS of the 

Operation & Maintenance Manual OM– 

02–01 to include a replacement of the 

rail pressure valve. We are proposing 

this AD to prevent engine in-flight 

shutdown, possibly resulting in reduced 

control of the aircraft. 

DATES: We must receive comments on 

this proposed AD by November 17, 

2011. 

ADDRESSES: You may send comments by 

any of the following methods: 


srobinson on DSK4SPTVN1PROD with PROPOSALS