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

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 high quality 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


### 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.


### 30391 Federal Register / Vol. 80, No. 102 / Thursday, May 28, 2015 / Proposed Rules

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,