15062 Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Proposed Rules 

(202) 586–2945. If possible, please 

submit all items on a CD, in which case 

it is not necessary to include printed 

copies. 

Instructions: All submissions received 

must include the agency name and 

docket number and/or RIN for this 

rulemaking. No telefacsimilies (faxes) 

will be accepted. 

Docket: The docket is available for 

review at http://www.regulations.gov, 

and will include Federal Register 

notices, framework document, public 

meeting attendee lists and transcripts, 

comments, and other supporting 

documents/materials throughout the 

rulemaking process. The regulations.gov 

Web page contains simple instructions 

on how to access all documents, 

including public comments, in the 

docket. The docket can be accessed by 

searching for docket number EERE– 

2013–BT–STD–0040 on the 

regulations.gov Web site. All documents 

in the docket are listed in the 

www.regulations.gov index. However, 

not all documents listed in the index 

may be publicly available, such as 

information that is exempt from public 

disclosure. 

For information on how to submit a 

comment, review other public 

comments and the docket, or participate 

in the public meeting, contact Ms. 

Brenda Edwards at (202) 586–2945 or by 

email: Brenda.Edwards@ee.doe.gov. 

FOR FURTHER INFORMATION CONTACT: 

James Raba, U.S. Department of Energy, 

Office of Energy Efficiency and 

Renewable Energy, Building 

Technologies Office, EE–5B, 1000 

Independence Avenue SW., 

Washington, DC 20585–0121. 

Telephone: (202) 586–8654. Email: 

jim.raba@ee.doe.gov. 

Michael Kido, U.S. Department of 

Energy, Office of the General Counsel, 

GC–71, 1000 Independence Avenue 

SW., Washington, DC 20585–0121. 

Telephone: (202) 586–8145. Email: 

michael.kido@hq.doe.gov. 

For information on how to submit or 

review public comments and on how to 

participate in the public meeting, 

contact Ms. Brenda Edwards, U.S. 

Department of Energy, Office of Energy 

Efficiency and Renewable Energy, 

Building Technologies Office, EE–5B, 

1000 Independence Avenue SW., 

Washington, DC 20585–0121. 

Telephone (202) 586–2945. Email: 

Brenda.Edwards@ee.doe.gov. 

SUPPLEMENTARY INFORMATION: On 

February 5, 2014, DOE published a 

notice announcing the availability of a 

Framework Document and a public 

meeting to discuss that document. See 

79 FR 6839. That notice announced that 

the public meeting would be held on 

March 3, 2014 and that written 

comments to DOE regarding the 

Framework Document would need to be 

submitted by no later than March 24, 

2014. In light of the inclement weather 

that forced the cancellation of the March 

3rd meeting, DOE is rescheduling the 

meeting to be held on April 1, 2014 and 

is providing commenters until April 22, 

2014 to provide any written comments 

regarding the Framework Document. 

Accordingly, DOE will consider any 

comments received by April 22, 2014, to 

be timely submitted. 

Issued in Washington, DC, on March 12, 

2014. 

Kathleen B. Hogan, 

Deputy Assistant Secretary for Energy 

Efficiency, Energy Efficiency and Renewable 

Energy. 

[FR Doc. 2014–05933 Filed 3–17–14; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 23 

[Docket No. FAA–2014–0155; Notice No. 23– 

14–01–SC] 

Special Conditions: Extra 

Flugzeugproduktions and Vertriebs 

[Extra] GmbH, EA–300/LC; Acrobatic 

Category Aerodynamic Stability 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed special 

conditions. 

SUMMARY: This action proposes special 

conditions for the Extra EA–300/LC 

airplane. This airplane will have a novel 

or unusual design feature(s) associated 

with static stability. This airplane can 

perform at the highest level of aerobatic 

competition. To be competitive, the 

aircraft was designed with positive and, 

at some points, neutral stability within 

its flight envelope. Its lateral and 

directional axes are also decoupled from 

each other providing more precise 

maneuvering. The applicable 

airworthiness regulations do not contain 

adequate or appropriate safety standards 

for these design features. 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 to EA–300/LC 

airplanes certified solely in the 

acrobatic category. 

DATES: Send your comments on or 

before April 17, 2014. 

ADDRESSES: Send comments identified 

by docket number [FAA–2014–0155] 

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 of 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 9 

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: Mr. 

Ross Schaller, Federal Aviation 

Administration, Small Airplane 

Directorate, Aircraft Certification 

Service, 901 Locust, Room 301, Kansas 

City, Missouri 64106; telephone (816) 

329–4162; facsimile (816) 329–4090. 

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 consider all comments we 

receive on or before the closing date for 

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Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Proposed Rules 15063 

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 3, 2011, Extra GmbH 

applied for an amendment to Type 

Certificate No. A67EU to include the 

derivative model number, EA–300/LC. 

The EA–300/LC, which is a derivative of 

the EA–300/L, currently approved 

under Type Certificate No. A67EU, is a 

single engine, two-place tandem canopy 

cockpit, low wing aerobatic monoplane 

with conventional landing gear. 

Its maximum takeoff weight is 2095 

pounds (950 kilograms). VNE is 219 

knots, VNO is 138 knots, and VA is 154 

knots, indicated airspeed. Maximum 

altitude is 10,000 feet. The engine is a 

Lycoming AEIO–580–B1A with a rated 

power of 315 Horsepower (Hp) at 2,700 

revolutions per minute (rpm). The 

airplane is proposed to be approved for 

Day-VFR operations with no icing 

approval. The EA–300/LC is certified 

under European Aviation Safety Agency 

(EASA) authority (Type Certificate Data 

Sheet EASA.A.362) as a dual category 

(normal/acrobatic) airplane. 

Acrobatic airplanes previously type 

certificated by the FAA did comply with 

the stability provisions of part 23, 

subpart B. However, airplanes like the 

EA–300/LC are considered as 

‘‘unlimited’’ acrobatic aircraft because 

they can perform at the highest level of 

aerobatic competition and can perform 

any maneuvers listed in the Aresti 

Catalog. The evolution of the 

‘‘unlimited’’ types of acrobatic airplanes 

with very low mass, exceptional roll 

rates, and very high G capabilities, in 

addition to power to mass ratios that are 

unique to this type of airplane, have led 

to airplanes that cannot comply with the 

regulatory stability requirements. These 

airplanes can still be type-certificated, 

but in the acrobatic category only and 

with special conditions and limitations. 

The FAA will only consider certifying 

the EA–300/LC in the acrobatic 

category. Extra GmbH will not be able 

to offer a normal category-operating 

envelope to accommodate the increased 

fuel load designed for cross-country 

operations. The FAA does recognize 

that fuel exhaustion is one of the top 

accident causes associated with this 

class of aircraft. For this reason, the 

FAA proposes to allow Extra to seek 

certification of a limited acrobatic 

envelope at a higher weight that will 

still meet the minimum load 

requirements of +6/-3 g associated with 

§ 23.337. The EA–300/LC airplane 

would be approved for unlimited 

maneuvers at or below its designed 

unlimited acrobatic weight. The 

airplane would also be approved, at 

some higher weight (for fuel/passenger), 

that would still meet the requirements 

of § 23.337 for acrobatic category and 

may have restrictions on the maneuvers 

allowed. 

Type Certification Basis 

Under the provisions of 14 CFR 

21.101, Extra GmbH must show that the 

EA–300/LC meets the applicable 

provisions of part 23, as amended by 

Amendment 23–34 effective September 

14, 1987 and Special Condition 23– 

ACE–65, published in the Federal 

Register (57 FR 175), September 9, 1992. 

These regulations will be incorporated 

into Type Certificate No. A67EU after 

type certification approval of the EA– 

300/LC. 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 A67EU are 

as follows: 

14 CFR part 36, effective December 1, 

1969, as amended by Amendments 36– 

1 through 36–28. 

Not approved for ditching; 

compliance with provisions for ditching 

equipment in accordance with 14 FR 

23.1415(a)(b) has not been 

demonstrated. 

Approved for VFR-day only. Flight in 

known icing prohibited. 

In addition, the certification basis 

includes other regulations, special 

conditions and exemptions that are not 

relevant to these proposed special 

conditions. Type Certificate No. A67EU 

will be updated to include a complete 

description of the certification basis for 

this model airplane. 

If the Administrator finds that the 

applicable airworthiness regulations 

(i.e., 14 CFR part 23) do not contain 

adequate or appropriate safety standards 

for the EA–300/LC 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. 

In addition to the applicable 

airworthiness regulations and special 

conditions, the EA–300/LC must 

comply with the fuel vent and exhaust 

emission requirements of 14 CFR part 

34 and the noise certification 

requirements of 14 CFR part 36. 

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 

§ 21.101. 

Novel or Unusual Design Features 

The Extra GmbH EA–300/LC will 

incorporate the following novel or 

unusual design features: 

For acrobatic category airplanes with 

unlimited acrobatic capability: 

Neutral longitudinal and lateral static 

stability characteristics 

Discussion 

The Code of Federal Regulations 

states static stability criteria for 

longitudinal, lateral, and directional 

axes of an airplane. However, none of 

these criteria is adequate to address the 

specific issues raised in the flight 

characteristics of an unlimited aerobatic 

airplane. Therefore, the FAA has 

determined after a flight-test evaluation 

that, in addition to the requirements of 

parts 21 and 23, special conditions are 

needed to address these static stability 

characteristics. 

Applicability 

As discussed above, these special 

conditions are applicable to the EA– 

300/LC. Should Extra GmbH 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. 

Conclusion 

This action affects only certain novel 

or unusual design features on one model 

of airplanes. It is not a rule of general 

applicability. 

List of Subjects in 14 CFR Part 23 

Aircraft, Aviation safety, Signs and 

symbols. 

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 Extra 

GmbH EA–300/LC airplanes. 

1. Unlimited Acrobatic-Only Category 

Static Stability Requirements 

SC23.171 Flight—General: Acrobatic 

category airplanes with unlimited 

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15064 Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Proposed Rules 

acrobatic capability must be neutrally or 

positively stable in the longitudinal, 

directional, and lateral axes under Secs. 

SC23.173 through SC23.177. 

Additionally, the airplane must show 

suitable stability and control ‘‘feel’’ 

(static stability) in any condition 

normally encountered in service, if 

flight tests show it is necessary for safe 

operation. 

SC23.173 Static longitudinal stability: 

Under the conditions specified in 

SC23.175 and with the airplane 

trimmed as indicated, the characteristics 

of the elevator control forces, positions, 

and the friction within the control 

system must be as follows: 

(a) A pull on the yoke must be 

required to obtain and maintain speeds 

below the specified trim speed and a 

push on the yoke required to obtain and 

maintain speeds above the specified 

trim speed. This must be shown at any 

speed that can be obtained, except that 

speeds requiring a control force in 

excess of 40 pounds or speeds above the 

maximum allowable speed or below the 

minimum speed for steady unstalled 

flight need not be considered. 

(b) The stick force or position must 

vary with speed so that any substantial 

speed change results in a stick force or 

position clearly perceptible to the pilot. 

SC23.175 Demonstration of static 

longitudinal stability: 

(a) Climb. The stick force curve must 

have, at a minimum, a neutrally stable 

to stable slope at speeds between 85 and 

115 percent of the trim speed, with— 

(1) Maximum continuous power; and 

(2) The airplane trimmed at the speed 

used in determining the climb 

performance required by § 23.69(a). 

(b) Cruise. With the airplane power 

and trim set for level flight at 

representative cruising speeds at high 

and low altitudes, including speeds up 

to VNO, except the speed need not 

exceed VH— 

(1) The stick force curve must, at a 

minimum, have a neutrally stable to 

stable slope at all speeds within a range 

that is the greater of 15 percent of the 

trim speed plus the resulting free return 

speed range, or 40 knots plus the 

resulting free return speed range above 

and below the trim speed, except the 

slope need not be stable— 

(i) At speeds less than 1.3 VS1; or 

(ii) For airplanes with VNE established 

under § 23.1505(a), at speeds greater 

than VNE. 

(c) Landing. The stick force curve 

must, at a minimum, have a neutrally 

stable to stable slope at speeds between 

1.1 VS1 and 1.8 VS1 with— 

(1) Landing gear extended; and 

(2) The airplane trimmed at— 

(i) VREF, or the minimum trim speed 

if higher, with power off; and 

(ii) VREF with enough power to 

maintain a 3-degree angle of descent. 

SC23.177 Static directional and lateral 

stability: 

(a) The static directional stability, as 

shown by the tendency to recover from 

a wings level sideslip with the rudder 

free, must be positive for any landing 

gear and flap position appropriate to the 

takeoff, climb, cruise, approach, and 

landing configurations. This must be 

shown with symmetrical power up to 

maximum continuous power, and at 

speeds from 1.2 VS1 up to the maximum 

allowable speed for the condition being 

investigated. The angle of sideslip for 

these tests must be appropriate for the 

airplane type. At larger angles of 

sideslip, up to where full rudder is used 

or a control force limit in § 23.143 is 

reached, whichever occurs first, and at 

speeds from 1.2 VS1 to VO, the rudder 

pedal force must not reverse. 

(b) In straight, steady slips at 1.2 VS1

for any landing gear and flap positions, 

and for any symmetrical power 

conditions up to 50 percent of 

maximum continuous power, the rudder 

control movements and forces must 

increase steadily, but not necessarily in 

constant proportion, as the angle of 

sideslip is increased up to the maximum 

appropriate to the type of airplane. The 

aileron control movements and forces 

may increase steadily, but not 

necessarily in constant proportion, as 

the angle of sideslip is increased up to 

the maximum appropriate for the 

airplane type. At larger slip angles, up 

to the angle at which the full rudder or 

aileron control is used or a control force 

limit contained in § 23.143 is reached, 

the aileron and rudder control 

movements and forces must not reverse 

as the angle of sideslip is increased. 

Rapid entry into, and recovery from, a 

maximum sideslip considered 

appropriate for the airplane must not 

result in uncontrollable flight 

characteristics. 

Issued in Kansas City, Missouri on March 

11, 2014. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2014–05951 Filed 3–17–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2014–0076; Airspace 

Docket No. 14–ANE–4] 

Proposed Amendment of Class E 

Airspace; Bridgeport, CT 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

amend Class E Airspace at Bridgeport, 

CT, as the Bridgeport VOR has been 

decommissioned, requiring airspace 

redesign at Igor I. Sikorsky Memorial 

Airport. This action would enhance the 

safety and airspace management of 

Instrument Flight Rules (IFR) operations 

at the airport. This action also would 

update the geographic coordinates of 

Sikorsky Heliport. 

DATES: Comments must be received on 

or before May 2, 2014. 

ADDRESSES: Send comments on this rule 

to: U.S. Department of Transportation, 

Docket Operations, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001; Telephone: 1–800– 

647–5527; Fax: 202–493–2251. You 

must identify the Docket Number FAA– 

2014–0076; Airspace Docket No. 14– 

ANE–4, at the beginning of your 

comments. You may also submit and 

review received comments through the 

Internet at http://www.regulations.gov. 

FOR FURTHER INFORMATION CONTACT: John 

Fornito, Operations Support Group, 

Eastern Service Center, Federal Aviation 

Administration, P.O. Box 20636, 

Atlanta, Georgia 30320; telephone (404) 

305–6364. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested persons are invited to 

comment on this rule by submitting 

such written data, views, or arguments, 

as they may desire. Comments that 

provide the factual basis supporting the 

views and suggestions presented are 

particularly helpful in developing 

reasoned regulatory decisions on the 

proposal. Comments are specifically 

invited on the overall regulatory, 

aeronautical, economic, environmental, 

and energy-related aspects of the 

proposal. 

Communications should identify both 

docket numbers (FAA Docket No. FAA– 

2014–0076; Airspace Docket No. 14– 

ANE–4) and be submitted in triplicate to 

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