11172 Federal Register / Vol. 76, No. 40 / Tuesday, March 1, 2011 / Proposed Rules 

b. Revise paragraphs II(a)(2)(viii)(A), 

II(a)(2)(viii)(B) introductory text, 

II(b)(1)(iv), II(b)(2)(ii), and II(b)(4); 

b. Remove paragraph II(c)(3) and 

remove and reserve paragraph II(c)(4); 

and 

c. Add new paragraph II(c)(3). 

The revisions and addition read as 

follows: 

Appendix C to Part 704—Risk-Based 

Capital Credit Risk-Weight Categories 

* * * * * 

Part II: Risk-Weightings 

(a) * * * 

(2) * * * 

(viii) * * * 

(A) A qualifying securities firm must meet 

the minimum credit quality standards as 

established by the corporate credit union’s 

board of directors or demonstrate at least a 

strong capacity to meet its financial 

obligations, even under adverse economic 

conditions, for the projected life of the 

exposure, whichever requirement is more 

stringent. Alternatively, a qualifying 

securities firm may rely on the 

creditworthiness of its parent consolidated 

company, if the parent consolidated 

company guarantees the claim. 

(B) A collateralized claim on a qualifying 

securities firm does not have to comply with 

the requirements of paragraph (a) if the claim 

arises under a contract that: 

* * * * * 

(b) * * * 

(1) * * * 

(iv) Unused portions of ABCP liquidity 

facilities that do not meet the definition of an 

eligible ABCP liquidity facility. The resulting 

credit equivalent amount is assigned to the 

risk category appropriate to the assets to be 

funded by the liquidity facility based on the 

assets or the obligor, after considering any 

collateral or guarantees. 

* * * * * 

(2) * * * 

(ii) Unused portions of commitments 

(including home equity lines of credit and 

eligible ABCP liquidity facilities) with an 

original maturity exceeding one year except 

those listed in paragraph II(b)(5) of this 

Appendix. For eligible ABCP liquidity 

facilities, the resulting credit equivalent 

amount is assigned to the risk category 

appropriate to the assets to be funded by the 

liquidity facility based on the assets or the 

obligor, after considering any collateral or 

guarantees. 

* * * * * 

(4) 10 percent credit conversion factor 

(Group D). Unused portions of eligible ABCP 

liquidity facilities with an original maturity 

of one year or less. The resulting credit 

equivalent amount is assigned to the risk 

category appropriate to the assets to be 

funded by the liquidity facility based on the 

assets or the obligor, after considering any 

collateral or guarantees. 

* * * * * 

(c) * * * 

(3) Internal ratings-based approach— 

(i) Calculation. Corporate credit unions 

with advanced risk management and 

reporting systems may seek NCUA approval 

to use credit risk models to calculate riskweighted asset amounts for positions 

described in paragraphs II(c)(1) and (2) of this 

section. In determining whether to grant 

approval, NCUA will consider the financial 

condition and risk management 

sophistication of the corporate credit union 

and the adequacy of the corporate’s risk 

models and supporting management 

information systems. 

(ii) Consistent use of internal ratings-based 

approach. A corporate credit union that has 

been granted NCUA approval to use an 

internal ratings-based approach and that has 

determined to use such an approach must do 

so in a consistent manner for all securities so 

rated. 

PART 709—INVOLUNTARY 

LIQUIDATION OF FEDERAL CREDIT 

UNIONS AND ADJUDICATION OF 

CREDITOR CLAIMS INVOLVING 

FEDERALLY INSURED CREDIT 

UNIONS IN LIQUIDATIONS 

11. The authority citation for part 709 

continues to read as follows: 

Authority: 12 U.S.C. 1757, 1766, 1767, 

1786(h), 1787, 1788, 1789, 1789a. 

12. In § 709.10, remove paragraphs 

(a)(5) and (a)(6), and revise the section 

heading and paragraphs (b), (f), and (g) 

to read as follows: 

§ 709.10 Treatment by conservator or 

liquidating agent of financial assets 

transferred in connection with a 

participation. 

* * * * * 

(b) The Board, by exercise of its 

authority to disaffirm or repudiate 

contracts under 12 U.S.C. 1787(c), will 

not reclaim, recover, or recharacterize as 

property of the credit union or the 

liquidation estate any financial assets 

transferred to another party by a 

federally-insured credit union in 

connection with a participation, 

provided that the transfer meets all the 

conditions for sale accounting treatment 

under generally accepted accounting 

principles, other than the ‘‘legal 

isolation’’ condition addressed by this 

section. 

* * * * * 

(f) The Board will not seek to avoid 

an otherwise legally enforceable 

participation agreement executed by a 

federally-insured credit union solely 

because such agreement does not meet 

the ‘‘contemporaneous’’ requirement of 

sections 207(b)(9) and 208(a)(3) of the 

Federal Credit Union Act. 

(g) This section may be repealed by 

the NCUA upon 30 days notice and 

opportunity for comment provided in 

the Federal Register, but any such 

repeal or amendment will not apply to 

any transfers of financial assets made in 

connection with a participation that was 

in effect before such repeal or 

modification. For purposes of this 

paragraph, a participation would be in 

effect on the date that the parties 

executed the participation agreement. 

PART 742—REGULATORY 

FLEXIBILITY PROGRAM 

13. The authority citation for part 742 

continues to read as follows: 

Authority: 12 U.S.C. 1756, 1766. 

14. In § 742.4, revise paragraph 

(a)(6)(i) to read as follows: 

§ 742.4 RegFlex relief. 

(a) * * * 

(6) * * * 

(i) The issuer has at least a very strong 

capacity to meet its financial 

obligations, even under adverse 

economic conditions, for the projected 

life of the security; 

* * * * * 

[FR Doc. 2011–4070 Filed 2–28–11; 8:45 am] 

BILLING CODE 7535–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 33 

[Docket No. NE131; Notice No. 33–10–02– 

SC] 

Special Conditions: Pratt and Whitney 

Canada Model PW210S Turboshaft 

Engine 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed special 

conditions. 

SUMMARY: This action proposes special 

conditions for Pratt and Whitney 

Canada (PWC) model PW210S engines. 

The engine model will have a novel or 

unusual design feature which is a 30– 

Minute All Engines Operating (AEO) 

power rating. This rating is intended to 

be used for hovering at increased power 

for search and rescue missions. The 

applicable airworthiness regulations do 

not contain adequate or appropriate 

safety standards for this design feature. 

These proposed special conditions 

contain the added safety standards that 

the Administrator considers necessary 

to establish a level of safety equivalent 

to that established by the existing 

airworthiness standards. 

DATES: We must receive your comments 

by March 31, 2011. 

ADDRESSES: You must mail two copies 

of your comments to: Federal Aviation 

Administration, Engine and Propeller 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
Federal Register / Vol. 76, No. 40 / Tuesday, March 1, 2011 / Proposed Rules 11173 

Directorate, Attn: Marc Bouthillier, 

Rules Docket (ANE–111), Docket No. 

NE131, 12 New England Executive Park, 

Burlington, Massachusetts 01803–5299. 

You may deliver two copies to the 

Engine and Propeller Directorate at the 

above address. You must mark your 

comments: Docket No. NE131. You can 

inspect comments in the Rules Docket 

weekdays, except Federal holidays, 

between 7:30 a.m. and 4 p.m. 

FOR FURTHER INFORMATION CONTACT: For 

technical questions concerning this 

proposed rule contact Marc Bouthillier, 

ANE–111, Engine and Propeller 

Directorate, Aircraft Certification 

Service, 12 New England Executive 

Park, Burlington, Massachusetts 01803– 

5299; telephone (781) 238–7120; 

facsimile (781) 238–7199; e-mail 

marc.bouthillier@faa.gov. For legal 

questions concerning this proposed rule 

contact Vincent Bennett, ANE–7 Engine 

and Propeller Directorate, Aircraft 

Certification Service, 12 New England 

Executive Park, Burlington, 

Massachusetts 01803–5299; telephone 

(781) 238–7044; facsimile (781) 238– 

7055; e-mail vincent.bennett@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite interested people to take 

part in this rulemaking by sending 

written comments, data, or views. The 

most helpful comments reference a 

specific portion of the special 

conditions, explain the reason for any 

recommended change, and include 

supporting data. We ask that you send 

us two copies of written comments. 

We will file in the docket all 

comments we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

about these special conditions. You can 

inspect the docket before and after the 

comment closing date. If you wish to 

review the docket in person, go to the 

address in the ADDRESSES section of this 

preamble between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. 

We will consider all comments we 

receive by the closing date for 

comments. We will consider comments 

filed late if it is possible to do so 

without incurring expense or delay. We 

may change these special conditions 

based on the comments we receive. 

If you want us to let you know we 

received your comments on this 

proposal, send us a pre-addressed, 

stamped postcard on which the docket 

number appears. We will stamp the date 

on the postcard and mail it back to you. 

Background 

On December 5, 2005, PWC applied 

for type certification for a new model 

PW210S turboshaft engine. This engine 

incorporates a two stage compressor 

driven by a single stage un-cooled 

turbine and a two stage free power 

turbine driving a two stage reduction 

gearbox. The control system includes a 

dual channel full authority digital 

electronic control. The engine will 

incorporate a novel or unusual design 

feature which is a 30–Minute All Engine 

Operating (AEO) power rating. This 

rating was requested by the applicant to 

support rotorcraft search and rescue 

missions that require extensive hover 

operations at high power. 

The applicable airworthiness 

standards do not contain adequate or 

appropriate airworthiness standards to 

address this design feature. Therefore a 

special condition is necessary to apply 

additional requirements for rating 

definition, instructions for continued 

airworthiness (ICA) and endurance 

testing. The 30 minute time limit 

applies to each instance the rating is 

used; however there is no limit to the 

number of times the rating can be used 

during any one flight, and there is no 

cumulative time limitation. The ICA 

requirement is intended to address the 

unknown nature of actual rating usage 

and associated engine deterioration. The 

applicant is expected to make an 

assessment of the expected usage and 

publish ICA’s and ALS limits in 

accordance with those assumptions, 

such that engine deterioration is not 

excessive. The endurance test 

requirement of 25 hours operation at 30 

minutes AEO is similar to several 

special conditions issued over the past 

20 years. Because the PWC model 

PW210S turboshaft engine has a 

continuous OEI rating and limits equal 

or higher than the 30 minute AEO 

rating, the test time performed at the 

continuous OEI rating may be credited 

toward the 25 hour requirement. 

However, test time spent at other rating 

elements of the test, such as takeoff or 

other OEI ratings (that may be equal to 

or higher values), may not be counted 

toward the 25 hours of required 

running. 

These special conditions contain the 

additional airworthiness standards 

necessary to establish a level of safety 

equivalent to the level that would result 

from compliance with the applicable 

standards of airworthiness in effect on 

the date of application. 

Type Certification Basis 

Under the provisions of 14 CFR 21.17, 

PWC must show that the model PW210S 

turboshaft engine meets the provisions 

of the applicable regulations in effect on 

the date of application. The application 

date is December 5, 2005, which 

corresponds to 14 CFR part 33 

Amendment 20. However, PWC has 

elected to demonstrate compliance to 

later amendments of part 33 for this 

model. Therefore, the certification basis 

for the PW210S model turboshaft engine 

will be part 33, effective February 1, 

1965, as amended by Amendments 33– 

1 through 33–24. 

If the Administrator finds that the 

applicable airworthiness regulations in 

part 33, as amended, do not contain 

adequate or appropriate safety standards 

for the PWC model PW210S turboshaft 

engine, because of a novel or unusual 

design feature, special conditions are 

prescribed under the provisions of 

§ 21.16. 

The FAA issues special conditions, as 

defined by 14 CFR 11.19, in accordance 

with 14 CFR 11.38, which become part 

of the type certification basis in 

accordance with § 21.17(b)(2). 

Special conditions are initially 

applicable to the model for which they 

are issued. Should the type certificate 

for that model be amended later to 

include another related model that 

incorporates the same or similar novel 

or unusual design feature, or should any 

other model already included on the 

same type certificate be modified to 

incorporate the same or similar novel or 

unusual design feature, the special 

conditions would also apply to the other 

model. 

Novel or Unusual Design Features 

The Pratt and Whitney Canada (PWC) 

model PW210S turbo shaft engine will 

incorporate a novel or unusual design 

feature which is a 30-Minute All Engine 

Operating (AEO) power rating, for use 

up to 30 minutes at any time between 

the take-off and landing phases of a 

flight. Special conditions for a 30- 

Minute AEO rating are proposed to 

address this novel and unusual design 

feature. The special conditions are 

discussed below. 

Discussion 

The PWC model PW210S turboshaft 

engine is a free turbine turboshaft 

designed for a transport category twinengine helicopter. The helicopter 

manufacturer anticipates that for search 

and rescue, extended hovering 

maneuvers may require more than 

maximum continuous power for periods 

up to 30 minutes. PWC has requested a 

30-Minute All Engine Operating (AEO) 

rating, for use up to 30 minutes at any 

time between the take-off and landing 

phases of a flight. PWC has indicated 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
11174 Federal Register / Vol. 76, No. 40 / Tuesday, March 1, 2011 / Proposed Rules 

that the number of times this rating can 

be used in one flight is not limited. 

Applicability 

As discussed above, these special 

conditions are applicable to PWC model 

PW210S turbo shaft engines. If Pratt and 

Whitney Canada applies later for a 

change to the type certificate to include 

another closely related model 

incorporating the same novel or unusual 

design feature, these special conditions 

would apply to that model as well. 

Conclusion 

This action affects only certain novel 

or unusual design features on one model 

of engine. It is not a rule of general 

applicability, and it affects only the 

applicant who applied to the FAA for 

approval of these features on the engine. 

List of Subjects in 14 CFR Part 33 

Air transportation, Aircraft, Aviation 

safety, Safety. 

The authority citation for these 

special conditions is as follows: 

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

44702, 44704. 

The Proposed Special Conditions 

Accordingly, the Federal Aviation 

Administration (FAA) proposes the 

following special conditions as part of 

the type certification basis for Pratt and 

Whitney Canada (PWC) model PW210S 

turbo shaft engines. 

1. PART 1 DEFINITION. Unless 

otherwise approved by the 

Administrator and documented in the 

appropriate manuals and certification 

documents, the following definition 

applies to this special condition: ‘‘Rated 

30 Minute AEO Power’’, means the 

approved brake horsepower developed 

under static conditions at the specified 

altitude and temperature, and within 

the operating limitations established 

under part 33, and limited in use to 

periods not exceeding 30 minutes each. 

2. PART 33 REQUIREMENTS. 

(a) Sections 33.1 Applicability and 

33.3 General: As applicable, all 

documentation, testing and analysis 

required to comply with the part 33 

certification basis, must account for the 

30 minute AEO rating, limits and usage. 

(b) Section 33.4, Instructions for 

Continued Airworthiness (ICA). In 

addition to the requirements of § 33.4, 

the ICA must: 

(1) Include instructions to ensure that 

in-service engine deterioration due to 

rated 30 minute AEO power usage will 

not be excessive, meaning that all other 

approved ratings, including one engine 

inoperative (OEI), are available (within 

associated limits and assumed usage) for 

each flight; and that deterioration will 

not exceed that assumed for declaring a 

time between overhaul (TBO) period. 

(i) The applicant must validate the 

adequacy of the maintenance actions 

required under paragraph (b)(1) above. 

(2) Include in the airworthiness 

limitations section (ALS), any 

mandatory inspections and 

serviceability limits related to the use of 

the 30-minute AEO rating. 

(c) Section 33.87, Endurance Test. In 

addition to the requirements of 

§§ 33.87(a) and 33.87(d), the overall test 

run must include a minimum of 25 

hours of operation at 30 minute AEO 

power and limits, divided into periods 

of 30 minutes AEO power with alternate 

periods at maximum continuous power. 

(1) Each § 33.87(d) continuous oneengine-inoperative (OEI) rating test 

period of 30 minutes or longer, run at 

power and limits equal to or higher then 

the 30 minute AEO rating, may be 

credited toward this requirement. 

Issued in Burlington, Massachusetts on 

February 1, 2011. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–4570 Filed 2–28–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0099; Directorate 

Identifier 2010–SW–085–AD] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation Model S–76A, S– 

76B, and S–76C Helicopters Modified 

by Supplemental Type Certificate 

SR09211RC 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Sikorsky Aircraft Corporation (Sikorsky) 

S–76 model helicopters with a certain 

life raft deployment system (LRDS) 

installed per Supplemental Type 

Certificate (STC) SR09211RC. This 

proposed AD would require removing 

and replacing the pilot or co-pilot life 

raft deployment handle (handle) located 

on the left side of the ‘‘broom closet’’ of 

the helicopter. This proposed AD is 

prompted by an incident that occurred 

where the handle bent prior to the life 

raft deploying, and this prohibited the 

crew from successfully deploying and 

using the life raft. It was determined 

that the handle in this incident was not 

manufactured to the approved Type 

Design. We are proposing this AD to 

prevent the bending of the handle, 

which could result in failure of the life 

raft to deploy. This failure could lead to 

loss of access to the life raft after an 

emergency ditching on water. 

DATES: We must receive comments on 

this proposed AD by May 2, 2011. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD: 

• 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: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

You may get the service information 

identified in this proposed AD from 

Aero Seats and Systems, Inc., 340 

Thomas Place, Everman, Texas 76140, 

telephone (817) 551–0818, fax (817) 

551–0838, e-mail 

rcrouch@aeroseatsandsystems.com. 

You may examine the comments to 

this proposed AD in the AD docket on 

the Internet at http:// 

www.regulations.gov. 

FOR FURTHER INFORMATION CONTACT: 

Martin Crane, Aviation Safety Engineer, 

FAA, Rotorcraft Directorate, Rotorcraft 

Certification Office, 2601 Meacham 

Blvd., Fort Worth, Texas 76137, 

telephone (817) 222–5170, fax (817) 

222–5783. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2011–0099, Directorate Identifier 

2010–SW–085–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments received by the 

closing date and may amend the 

proposed AD in light of those 

comments. 


jlentini on DSKJ8SOYB1PROD with PROPOSALS