Federal Register / Vol. 80, No. 102 / Thursday, May 28, 2015 / Proposed Rules 30389 

transaction (other than a collateralized 

deposit), secured lending transaction, 

asset exchange, or collateralized 

derivatives transaction that matures 

within 30 calendar days of the 

calculation date where the [BANK] will 

provide an asset that is eligible HQLA 

and the counterparty will provide an 

asset that will be eligible HQLA. 

(h) * * * 

(3) The adjusted public sector entity 

security cap excess amount. 

* * * * * 

(k) Calculation of the adjusted public 

sector entity security cap excess 

amount. As of the calculation date, the 

adjusted public sector entity security 

cap excess amount equals the greater of: 

(1) The adjusted public sector entity 

security liquid asset amount minus the 

adjusted level 2 cap excess amount 

minus the adjusted level 2B cap excess 

amount minus 0.0526 times the sum of: 

(i) The adjusted level 1 liquid asset 

amount; 

(ii) The adjusted level 2A liquid asset 

amount: and 

(iii) The adjusted level 2B liquid asset 

amount minus the adjusted public 

sector entity security liquid asset 

amount; or 

(2) 0. 

■ 4. Amend § 249.22, by redesignating 

paragraph (c) as paragraph (d) and 

adding new paragraph (c) to read as 

follows: 

§ 249.22 Requirements for eligible highquality liquid assets. 

* * * * * 

(c) Securities of public sector entities 

as eligible HQLA. A Board-regulated 

institution may include as eligible 

HQLA a general obligation security 

issued by, or guaranteed as to the timely 

payment of principal and interest by, a 

public sector entity if each of the 

following is satisfied: 

(1) The fair value of a single issuance 

of securities that are included as eligible 

HQLA by the Board-regulated 

institution is no greater than 25 percent 

of the total amount of outstanding 

securities with the same CUSIP number 

at the calculation date; and 

(2) The fair value of the aggregate 

amount of securities of a single public 

sector entity issuer that are included as 

eligible HQLA by the Board-regulated 

institution is no greater than two times 

the average daily trading volume during 

the previous four quarters of all general 

obligation securities issued by that 

public sector entity. 

* * * * * 

By order of the Board of Governors of the 

Federal Reserve System, May 18, 2015. 

Robert deV. Frierson, 

Secretary of the Board. 

[FR Doc. 2015–12850 Filed 5–27–15; 8:45 am] 

BILLING CODE P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 33 

[Docket No. FAA–2015–1771; Notice No. 33– 

15–01–SC] 

Special Conditions: Pratt and Whitney 

Canada, PW210A; Flat 30-Second and 

2-Minute One Engine Inoperative 

Rating 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed special 

conditions. 

SUMMARY: This action proposes special 

conditions for the Pratt and Whitney 

Canada PW210A engine model. This 

engine will have a novel or unusual 

design feature—an additional one 

engine inoperative (OEI) rating that 

combines the 30-second and 2-minute 

OEI ratings into a single rating. The 

applicable airworthiness regulations do 

not contain adequate or appropriate 

safety standards for this design feature. 

These proposed special conditions 

contain the additional safety standards 

that the Administrator considers 

necessary to establish a level of safety 

equivalent to that established by the 

existing airworthiness standards. 

DATES: Send your comments on or 

before June 8, 2015. 

ADDRESSES: Send comments identified 

by docket number FAA–2015–1771 

using any of the following methods: 

• Federal eRegulations Portal: Go to 

http://www.regulations.gov and follow 

the online instructions for sending your 

comments electronically. 

• Mail: Send comments to Docket 

Operations, M–30, U.S. Department of 

Transportation (DOT), 1200 New Jersey 

Avenue SE., Room W12–140, West 

Building Ground Floor, Washington, DC 

20590–0001. 

• Hand Delivery or Courier: Take 

comments to Docket Operations in 

Room W12–140 of the West Building 

Ground Floor at 1200 New Jersey 

Avenue SE., Washington, DC, between 8 

a.m., and 5 p.m., Monday through 

Friday, except Federal holidays. 

• Fax: Fax comments to Docket 

Operations at 202–493–2251. 

Privacy: The FAA will post all 

comments it receives, without change, 

to http://regulations.gov, including any 

personal information the commenter 

provides. Using the search function of 

the docket Web site, anyone can find 

and read the electronic form of all 

comments received into any FAA 

docket, including the name of the 

individual sending the comment (or 

signing the comment for an association, 

business, labor union, etc.). DOT’s 

complete Privacy Act Statement can be 

found in the Federal Register published 

on April 11, 2000 (65 FR 19477–19478), 

as well as at http://DocketsInfo.dot.gov. 

Docket: Background documents or 

comments received may be read at 

http://www.regulations.gov at any time. 

Follow the online instructions for 

accessing the docket or go to the Docket 

Operations in Room W12–140 of the 

West Building Ground Floor at 1200 

New Jersey Avenue SE., Washington, 

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

through Friday, except Federal holidays. 

FOR FURTHER INFORMATION CONTACT: For 

technical questions concerning this 

proposed rule, contact Tara Fitzgerald, 

ANE–111, Engine and Propeller 

Directorate, Aircraft Certification 

Service, 12 New England Executive 

Park, Burlington, Massachusetts 01803– 

5213; telephone (781) 238–7130; 

facsimile (781) 238–7199. 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; email 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 will consider all comments 

received in the docket on or before 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. 

Background 

On February 14, 2013, Pratt and 

Whitney Canada applied for an 

amendment to Type Certificate No. 

E00083EN–E to include the new 

PW210A engine model. The PW210A, 

which is a derivative of the PW210S 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
30390 Federal Register / Vol. 80, No. 102 / Thursday, May 28, 2015 / Proposed Rules 

currently approved under E00083EN–E, 

is intended for rotorcraft use. For their 

PW210A engine model, Pratt and 

Whitney Canada requests an additional 

OEI rating that combines the 30-second 

and 2-minute OEI rating into a single 

rating to satisfy the rotorcraft 

requirements for increased power in OEI 

scenarios. This additional OEI rating is 

named ‘‘Flat 30-second and 2-minute 

OEI.’’ 

These special conditions are 

necessary because the applicable 

airworthiness regulations do not contain 

adequate or appropriate safety standards 

for combining the requirements of the 

flat 30-second and 2-minute OEI rating. 

Type Certification Basis 

Under the provisions of § 21.101, Pratt 

and Whitney Canada must show that the 

PW210A meets the applicable 

provisions of 14 CFR part 33, as 

amended by Amendments 33–1 through 

33–30. These regulations will be 

incorporated into Type Certificate No. 

E00083EN after type certification 

approval of the PW210A. The 

regulations incorporated by reference in 

the type certificate are commonly 

referred to as the ‘‘original type 

certification basis.’’ The regulations 

incorporated by reference in Type 

Certificate No. E00083NE are as follows: 

Title 14 of the Code of Federal 

Regulations (14 CFR part 33), effective 

February 1, 1965, Amendments 33–1 

through 33–24 and two special 

conditions: 33–008–SC: For on ground 

engine operation in auxiliary power unit 

(APU) mode, and 33–009–SC: For 30- 

minutes all engines operating (AEO) 

hovering power engine rating. 

For the PW210A the certification 

basis is: 

1. Airworthiness Standards: 14 CFR 

part 33, effective February 1, 1965, 

Amendments 33–1 through 33–30, 

inclusive. 

2. Environmental Standards: 14 CFR 

part 34, effective September 10, 1990, as 

amended by 34–1 through 34–4 and 40 

CFR part 87, effective (ICAO Annex 16, 

Volume II—Aircraft Engine Emissions, 

as amended up to and including 

Amendment 6). 

In addition, the certification basis 

includes other regulations, special 

conditions and exemptions that are not 

relevant to these proposed special 

conditions. Type Certificate No. 

E00083EN will be updated to include a 

complete description of the certification 

basis for this model engine. 

If the Administrator finds that the 

applicable airworthiness regulations 

(i.e., 14 CFR part 33) do not contain 

adequate or appropriate safety standards 

for the PW210A because of a novel or 

unusual design feature, special 

conditions are prescribed under the 

provisions of § 21.16. 

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 any other 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 under § 21.101. 

Accordingly, should type certificate 

E00083EN be amended to include 

another model that incorporates the 

‘‘Flat 30-second and 2-minute OEI,’’ the 

special conditions as defined would 

apply to models whose certification 

basis is amendment 33–25 or later. 

The FAA issues special conditions, as 

defined in 14 CFR 11.19, in accordance 

with § 11.38, and they become part of 

the type-certification basis under 

§ 21.17(a)(2). 

Novel or Unusual Design Features 

The PW210A will incorporate the 

following novel or unusual design 

features: The design feature is a ‘‘Flat 

30-second and 2-minute’’ one engine 

inoperative (OEI) rating. The Flat 30- 

second and 2-minute OEI rating 

represents a case where the power levels 

and associated operating limitations for 

the 30-second OEI and 2-minute OEI 

ratings (defined in Part 33) are the same. 

Discussion 

These proposed special conditions are 

necessary because current part 33 

regulations do not contain airworthiness 

standards for extending the 2-minute 

OEI rating for 30-seconds. These special 

conditions extend the time dependent 

requirements applicable to the 30- 

second OEI or 2-minute OEI to the 2.5 

minutes time duration of the ‘‘Flat 30- 

second and 2-minute OEI’’ Power. 

The 2.5 minutes time duration for the 

rating may affect the engine’s structural 

and operational characteristics that are 

time dependent, such as the values for 

transients, time duration for 

stabilization to steady state, and part 

growth due to deformation. To address 

these aspects, we propose special 

conditions based on revised 

requirements of §§ 33.27, 33.87(a)(7), 

and 33.88(b). 

The 2.5 minutes time duration for the 

rating affects the test conducted for the 

endurance test. For the 30-second OEI 

and 2-minute OEI the test schedule of 

§ 33.87(f) is divided among the two 

ratings. We propose special conditions 

based on revised requirements of 

§ 33.87(f) to ensure the test will be run 

for 2.5 minutes duration with no 

interruption. 

The 2.5 minutes time duration for the 

rating necessitates extending the time 

duration requirement of § 33.28(k) 

applicable to the 30-second OEI rating 

from 30 seconds to 2.5 minutes. This 

proposed requirement is for automatic 

availability and control of the engine for 

the entire duration of the rating’s usage. 

The 2.5 minutes time duration for the 

rating necessitates extending the 

requirements of § 33.29(c) that are 

applicable to 30-second OEI and 2- 

minute OEI ratings to the single Flat 30- 

second and 2-minute OEI Power rating. 

We propose special conditions to ensure 

that the instrumentation requirements 

normally reserved for 30-second OEI 

and 2-minute OEI ratings are applied to 

the Flat 30-second and 2-minute OEI 

Power rating over its whole duration. 

The pilot does not have to be alerted at 

the end of 30 seconds use of the Flat 30- 

second and 2-minute OEI Power rating, 

only after the entire 2 minutes 30 

seconds has expired. 

Paragraph 2.(e)(3) of these special 

conditions states that the engine must 

provide means or provision of means to 

alert maintenance of use of the Flat 30- 

second and 2-minute OEI Power rating, 

‘alert’ means after the aircraft lands, so 

any required maintenance actions can 

be completed before next flight. 

Applicability 

As discussed above, these special 

conditions are applicable to the 

PW210A. Should Pratt and Whitney 

Canada apply at a later date for a change 

to the type certificate to include another 

model incorporating the same novel or 

unusual design feature, the special 

conditions would apply to that model as 

well. 

Certification of the PW210A is 

currently scheduled for May 1, 2015. 

The substance of these special 

conditions has been subject to the notice 

and public-comment procedure in a 

prior instance. Therefore, because a 

delay would significantly affect the 

applicant’s both installation of the 

system and certification of the airplane, 

we are shortening the public-comment 

period to 10 days. 

Conclusion 

This action affects only the Flat 30- 

second and 2-minute OEI design 

features on the PW210A engine model. 

It is not a rule of general applicability 

and applies only to Pratt and Whitney 

Canada, who requested FAA approval of 

this engine feature. 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 102 / Thursday, May 28, 2015 / Proposed Rules 30391 

List of Subjects in 14 CFR Part 33 

Air Transportation, Aircraft, Aviation, 

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 PW210A engine 

model. 

Flat 30-Second and 2-Minute OEI 

1. Part 1.1 Definitions 

‘‘Rated Flat 30-second and 2-minute 

One Engine Inoperative (OEI) Power,’’ 

with respect to rotorcraft turbine 

engines, means (1) a single rating for 

which the shaft horsepower and 

associated operating limitations of the 

30-second OEI and 2-minute OEI ratings 

are equal, and (2) the shaft horsepower 

is that developed under static 

conditions at the altitude and 

temperature for the hot day, and within 

the operating limitations established 

under Part 33. The rating is for 

continuation of flight operation after the 

failure or shutdown of one engine in 

multiengine rotorcraft, for up to three 

periods of use no longer than 2.5 

minutes each in any one flight, and 

followed by mandatory inspection and 

prescribed maintenance action. 

2. Part 33 Requirements 

(a) The airworthiness standards in 

Part 33 Amendment 30 for the 30- 

second OEI and 2-minute OEI ratings 

are applicable to the Flat 30-second and 

2-minute OEI Power rating. In addition 

the following special conditions apply; 

(b) Section 33.7 Engine ratings and 

operating limitations. Flat 30-second 

and 2-minute OEI Power rating and 

operating limitations are established for 

power, torque, rotational speed, gas 

temperature, and time duration. 

(c) Section 33.27 Turbine, 

compressor, fan, and turbosupercharger 

rotor overspeed. The requirements of 

§ 33.27, except that following the test, 

the rotor may not exhibit conditions 

such as cracking or distortion which 

preclude continued safe operation. 

(d) Section 33.28 Engine controls 

systems. Must incorporate a means, or a 

provision for a means, for automatic 

availability and automatic control of the 

Flat 30-second and 2-minute OEI Power 

within the declared operating 

limitations. 

(e) Section 33.29 Instrument 

Connection. In lieu of the requirements 

of 33.29(c) the PW210A must 

incorporate a means or a provision for 

a means to: 

(1) Alert the pilot when the engine is 

at the Flat 30-second and 2-minute OEI 

Power level, when the event begins, and 

when the time interval expires; 

(2) Automatically record each usage 

and duration of power at the Flat 30- 

second and 2-minute OEI Power rating; 

(3) Following each flight when the 

Flat 30-second and 2-minute OEI Power 

rating is used, alert maintenance 

personnel in a positive manner that the 

engine has been operated at the Flat 30- 

second and 2-minute OEI Power level, 

and permit retrieval of the recorded 

data; and 

(4) Enable routine verification of the 

proper operation of the above means. 

(f) Section 33.87 Endurance test. The 

requirements applicable to 30-second 

and 2-minute OEI ratings, except for: 

(1) The test of § 33.87(a)(7) for the 

purposes of temperature stabilization, 

must be run with a test period time of 

2.5 minutes. 

(2) The tests in § 33.87(f)(2) and (3) 

must be run continuously for the 

duration of 2.5 minutes, and 

(3) The tests in § 33.87(f)(6) and (7) 

must be run continuously for the 

duration of 2.5 minutes. 

(g) Section 33.88 Engine 

overtemperature test. The requirements 

of § 33.88(b) except that the test time is 

5 minutes instead of 4 minutes. 

Issued in Burlington, Massachusetts, on 

May 18, 2015. 

Carlos Pestana, 

Acting Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–12986 Filed 5–27–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1425; Directorate 

Identifier 2014–NM–185–AD] 

RIN 2120–AA64 

Airworthiness Directives; Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Lockheed Martin Corporation/Lockheed 

Martin Aeronautics Company Model 

188 series airplanes. This proposed AD 

was prompted by an evaluation by the 

design approval holder (DAH) 

indicating that a certain circumferential 

fuselage splice is subject to widespread 

fatigue damage (WFD). This proposed 

AD would require an inspection for 

corrosion and previous repairs, severed 

stringers, cracking, and loose or 

distressed fasteners of the forward and 

aft ends of the stringer splices of certain 

stringers, inspection for cracking and 

modification of certain fastener holes 

common to the stringer and splice 

member at the forward and aft ends of 

the splice, and related investigative and 

corrective actions if necessary. We are 

proposing this AD to prevent loss of 

residual strength of a certain 

circumferential fuselage splice, which 

could lead to rapid decompression of 

the cabin and potential loss of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by July 13, 2015. 

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 Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company, Airworthiness 

Office, Dept. 6A0M, Zone 0252, Column 

P–58, 86 S. Cobb Drive, Marietta, GA 

30063; phone: 770–494–5444; fax: 770– 

494–5445; email: ams.portal@lmco.com; 

Internet http://

www.lockheedmartin.com/ams/tools/

TechPubs.html. You may view this 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

1425; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS