Federal Register / Vol. 77, No. 240 / Thursday, December 13, 2012 / Proposed Rules 74123 

within a Corporate LLP that would 

qualify as part of the ‘‘executive and 

administrative personnel,’’ should the 

Commission issue general rules stating 

that persons holding positions with 

certain characteristics are part of the 

Corporate LLP’s restricted class? 

The Commission seeks comment on 

these and other possible approaches to 

address, if at all, the treatment of 

Corporate LLPs for purposes of the Act, 

as well as any other aspect of this 

rulemaking. 

Certification of No Effect Pursuant to 5 

U.S.C. 605(b) (Regulatory Flexibility 

Act) 

The Commission certifies that the 

attached proposed rules, if adopted, 

would not have a significant economic 

impact on a substantial number of small 

entities. The basis for this certification 

is that the proposed rules modify how 

limited liability partnerships may 

operate pursuant to Federal campaign 

finance laws. The only economic impact 

attributable to these proposed rules 

would be the costs incurred by limited 

liability partnerships that wish to 

establish and administer separate 

segregated funds. This activity is 

entirely voluntary and any costs 

associated with it would fall only on 

entities choosing to establish and 

administer a separate segregated fund. 

Therefore, the attached proposed rule 

would not have a significant impact on 

a substantial number of small entities. 

List of Subjects in 11 CFR Part 110 

Campaign funds, Political candidates, 

Political committees and parties. 

For the reasons set out in the 

preamble, Subchapter A, Chapter 1 of 

Title 11 of the Code of Federal 

Regulations is proposed to be amended 

as follows: 

PART 110—CONTRIBUTION AND 

EXPENDITURE LIMITATIONS AND 

PROHIBITIONS 

1. The authority citation for part 110 

would continue to read as follows: 

Authority: 2 U.S.C. 431(8), 431(9), 

432(c)(2), 437d, 438(a)(8), 441a, 441b, 441d, 

441e, 441f, 441g, 441h and 36 U.S.C. 510. 

§ 110.1 [Amended] 

2. In § 110.1, paragraph (e) is removed 

and reserved. 

3. Add § 110.21 to read as follows: 

§ 110.21 Partnerships. 

(a) All partnerships, except LLPs 

governed by paragraph (c) of this 

section, shall attribute a contribution by 

the partnership to both the partnership 

and each individual partner— 

(1) In direct proportion to his or her 

share of the partnership profits, 

according to instructions that the 

partnership shall provide to the political 

committee or candidate; or 

(2) By agreement of the partners, as 

long as— 

(i) Only the profits of the partners to 

whom the contribution is attributed are 

reduced (or losses increased), and 

(ii) These partners’ profits are reduced 

(or losses increased) in proportion to the 

contribution attributed to each of them. 

(b) A contribution by a partnership 

made in accordance with paragraph (a) 

of this section shall not exceed the 

limitations on contributions in 11 CFR 

110.1(b), (c), and (d). No portion of any 

such contribution may be made from the 

profits of a corporation that is a partner. 

(c) Contributions by limited liability 

partnerships (‘‘LLP’’)— 

(1) A limited liability partnership is a 

business entity that is recognized as a 

limited liability partnership under the 

laws of the State in which it is 

established. 

(2) An LLP that elects to be treated as 

a corporation by the Internal Revenue 

Service shall be considered a 

corporation for purposes of 11 CFR parts 

100, 113, 114 115, 116, and 9034, except 

that its restricted class shall consist 

solely of those persons who receive 

stock in the association pursuant to 

Internal Revenue Service rules, as well 

as their families. 

On behalf of the Commission. 

Caroline C. Hunter, 

Chair, Federal Election Commission. 

[FR Doc. 2012–30029 Filed 12–12–12; 8:45 am] 

BILLING CODE 6715–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1167; Directorate 

Identifier 2012–NE–36–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG 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 certain 

Rolls-Royce Deutschland Ltd & Co KG 

(RRD) models Tay 620–15 and Tay 650– 

15 turbofan engines. This proposed AD 

was prompted by RRD recalculating the 

Declared Safe Cyclic Life (DSCL) for 

certain low-pressure compressor (LPC) 

rotor disc assemblies operating to the 

Plan D Flight Mission. This proposed 

AD would require removing the affected 

LPC rotor disc assemblies at a new 

lower recalculated DSCL. We are 

proposing this AD to prevent failure of 

the LPC rotor disc assembly, 

uncontained engine failure, and damage 

to the airplane. 

DATES: We must receive comments on 

this proposed AD by February 11, 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 and follow 

the instructions for sending your 

comments electronically. 

• 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. 

• Fax: 202–493–2251. 

For service information identified in 

this proposed AD, contact Rolls-Royce 

Deutschland Ltd & Co KG, Eschenweg 

11–15827 Dahlewitz, BlankenfeldeMahlow, Germany; phone: +49 0 33– 

7086–1944; fax: +49 0 33–7086–3276. 

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: 

Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7779; fax: 781–238– 

7199; email: Frederick.zink@faa.gov. 

SUPPLEMENTARY INFORMATION: 


wreier-aviles on DSK5TPTVN1PROD with 
74124 Federal Register / Vol. 77, No. 240 / Thursday, December 13, 2012 / Proposed Rules 

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–2012–1167; Directorate Identifier 

2012–NE–36–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 aviation authority 

for the Member States of the European 

Community, has issued EASA AD 2012– 

0204, dated October 1, 2012 (referred to 

hereinafter as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

The Tay 650–15 and Tay 650–15/10 engine 

Time Limits Manual Chapter 05–10–01 

contains maximum approved life limitations, 

identified as Declared Safe Cyclic Life 

(DSCL) for Low Pressure Compressor (LPC) 

rotor disc assemblies Part Number (P/N) 

JR31198A and P/N JR34563A operated to the 

Plan D Flight Mission, which has been 

recalculated to a lower value. 

Decreased DSCL of LPC rotor disc 

assemblies P/N JR31198A and P/N JR34563A 

may affect these disc assemblies installed in 

Tay 650–15 and Tay 650–15/10 engines as 

well as in Tay 620–15 and Tay 620–15/20 

engines. 

Failure to take decreased DSCL of affected 

LPC rotor disc assemblies into account could 

lead to affected part failure and consequent 

release of high energy debris potentially 

resulting in damage to, and/or reduced 

control of, the aeroplane. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

RRD has issued Alert Service Bulletin 

TAY–72–A1772 dated August 9, 2012. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of Germany, 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 requires removing the 

affected LPC rotor disc assemblies at the 

new lower recalculated DSCL. 

Costs of Compliance 

We estimate that this proposed AD 

will affect 4 engines installed on 

airplanes of U.S. registry. We also 

estimate that it would require 4 hours to 

perform the actions required by this AD. 

The average labor rate is $85 per hour. 

Prorated life for the disc assembly is 

approximately $650 per disc. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$3,960. 

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 AD: 

Rolls-Royce Deutschland Ltd & Co KG (RRD) 

(formerly Rolls-Royce plc): Docket No. 

FAA–2012–1167; Directorate Identifier 

2012–NE–36–AD. 

(a) Comments Due Date 

We must receive comments by February 

11, 2013. 

(b) Affected Airworthiness Directives (ADs) 

None. 

(c) Applicability 

This AD applies to Rolls-Royce 

Deutschland Ltd & Co KG (RRD) models Tay 

620–15 and Tay 650–15 turbofan engines 

with a low-pressure compressor (LPC) rotor 

disc assembly, part number (P/N) JR31198A 

or P/N JR34563A installed. 

(d) Reason 

This AD was prompted by RRD 

recalculating the Declared Safe Cyclic Life for 

certain LPC rotor disc assemblies operating to 

the Plan D Flight Mission. We are issuing this 

AD to prevent failure of the LPC rotor disc 

assembly, uncontained engine failure, and 

loss of the airplane. 


wreier-aviles on DSK5TPTVN1PROD with 
Federal Register / Vol. 77, No. 240 / Thursday, December 13, 2012 / Proposed Rules 74125 

(e) Actions and Compliance 

Unless already done, do the following. For 

engines that have operated to the Plan D 

Flight Mission configuration, remove the LPC 

rotor disc assembly from service before 

accumulating 18,700 engine flight cycles. Do 

not return to service nor approve for return 

to service any engine with the affected discs 

installed that exceeds 18,700 engine flight 

cycles. 

(f) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(g) Related Information 

(1) For more information about this AD, 

contact Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

email: Frederick.zink@faa.gov; phone: 781– 

238–7779; fax: 781–238–7199. 

(2) Refer to European Aviation Safety 

Agency AD 2012–0204, dated October 1, 

2012, and RRD Alert Service Bulletin TAY– 

72–A1772, dated August 9, 2012, for related 

information. 

(3) For service information identified in 

this AD, contact Rolls-Royce Deutschland Ltd 

& Co KG, Eschenweg 11 Dahlewitz 15827, 

Blankenfelde-Mahlow, Germany; phone: +49 

0 33–7086–1944; fax: +49 0 33–7086–3276. 

(4) 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 

December 6, 2012. 

Robert J. Ganley, 

Acting Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–30065 Filed 12–12–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1288; Directorate 

Identifier 2012–NE–37–AD] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company 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 

General Electric Company (GE) CF34– 

8C and CF34–8E turbofan engines with 

certain part numbers (P/N) of 

operability bleed valves (OBV) installed. 

This proposed AD was prompted by 

three failure events of ring lock fuel 

fittings on the OBV. Two of those events 

led to an engine fire. This proposed AD 

would require the affected OBVs be 

removed from service and replaced with 

OBVs eligible for installation. We are 

proposing this AD to prevent failure of 

OBV ring lock fuel fittings, engine fuel 

leakage, uncontrolled fire, and damage 

to the airplane. 

DATES: We must receive comments on 

this proposed AD by February 11, 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 General 

Electric, One Neumann Way, MD Y–75, 

Cincinnati, OH; phone: 513–552–2913; 

email: geae.aoc@ge.com; and Web site: 

www.GE.com. You view 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: John 

Frost, Aerospace Engineer, Engine & 

Propeller Directorate, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7756; fax: 781– 

238–7199; email: john.frost@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– 

2012–1288; Directorate Identifier 2012– 

NE–37–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 reports of three failure 

events of OBV ring lock fuel fittings on 

GE CF34–8C turbofan engines. Two of 

those events led to an engine fire. 

Investigation revealed that the ring lock 

fittings failed due to fatigue caused by 

improper broaching of the OBV housing 

during manufacture, and, improper 

installation of the ring lock fittings 

during OBV assembly. GE CF34–8E 

turbofan engines also use the affected 

OBVs and would be affected by this 

proposed AD. This condition, if not 

corrected, could result in failure of OBV 

ring lock fuel fittings, engine fuel 

leakage, uncontrolled fire, and damage 

to the airplane. 

Relevant Service Information 

We reviewed GE Service Bulletin (SB) 

No. CF34–8C–AL S/B 75–0017, dated 

September 14 2012. We also reviewed 

GE SB No. CF34–8E–AL S/B 75–0012, 

dated September 14, 2012. These 

bulletins describe procedures for 

removing from service OBVs having an 

affected P/N. 

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 for 

all GE CF34–8C and CF34–8E turbofan 

engines with an OBV P/N 4121T67P02, 

P/N 4121T67P03, P/N 4121T67P04, 

parts manufacturer approval (PMA) P/N 

392155–2, PMA P/N 392155–3, or PMA 

P/N 392155–4 installed, removal of the 

OBV from service. 


wreier-aviles on DSK5TPTVN1PROD with