Special Conditions: Extra Flugzeugproduktions and Vertriebs [Extra] GmbH, EA-300/LC; Acrobatic Category Aerodynamic Stability, 26111-26113 [2014-10392]

Download as PDF pmangrum on DSK3VPTVN1PROD with RULES Federal Register / Vol. 79, No. 88 / Wednesday, May 7, 2014 / Rules and Regulations and white types of potatoes monthly. While this rule requires a reporting requirement for shipments of yellow fleshed and white types of potatoes, their exemption from handling regulations also eliminates the more frequent reporting requirements imposed under the order’s special purpose shipment exemptions (§ 946.336(d) and (e)). Under these paragraphs, handlers are required to provide detailed reports whenever they divert regulated potatoes for livestock feed, charity, seed, prepeeling, processing, grading and storing in specified counties in Oregon, and experimentation. Therefore, any additional reporting or recordkeeping requirements on either small or large handlers of yellow fleshed and white types of potatoes are expected to be offset by the elimination of the other reporting requirements currently in effect. In addition, the exemption from handling regulations and inspection requirements for yellow fleshed and white types of potatoes is expected to reduce industry expenses. AMS is committed to complying with the E-government Act, to promote the use of the internet and other information technologies to provide increased opportunities for citizen access to Government information and services, and for other purposes. USDA has not identified any relevant Federal rules that duplicate, overlap or conflict with this rule. The Committee’s meetings were widely publicized throughout the Washington potato industry, and all interested persons were invited to participate in Committee deliberations. Like all Committee meetings, the December 10, 2013, meeting was a public meeting. All entities, both large and small, were able to express views on this issue. Further, interested persons are invited to submit comments on this interim rule, including the regulatory and informational impacts of this action on small businesses. A small business guide on complying with fruit, vegetable, and specialty crop marketing agreements and orders may be viewed at: https://www.ams.usda.gov/ MarketingOrdersSmallBusinessGuide. Any questions about the compliance guide should be sent to Jeffrey Smutny at the previously mentioned address in the FOR FURTHER INFORMATION CONTACT section. This interim rule invites comments on the exemption of yellow fleshed and white types of potatoes from the handling regulations for the 2014–2015 and subsequent fiscal periods. Any comments received will be considered prior to finalization of this rule. VerDate Mar<15>2010 17:31 May 06, 2014 Jkt 232001 After consideration of all relevant material presented, including the Committee’s recommendation, and other information, it is found that this interim rule, as hereinafter set forth, will tend to effectuate the declared policy of the Act. Pursuant to 5 U.S.C. 553, it is also found and determined upon good cause that it is impracticable, unnecessary, and contrary to the public interest to give preliminary notice prior to putting this rule into effect and that good cause exists for not postponing the effective date of this rule until 30 days after publication in the Federal Register because: (1) Any changes resulting from this rule should be effective July 1, 2014, because the temporary exemption for Washington yellow fleshed and white types of potatoes from the handling regulations ends on June 30, 2014; (2) the Committee discussed and unanimously recommended these changes at a public meeting, and all interested parties had an opportunity to provide input; (3) potato handlers are aware of this action and want to take advantage of this handling regulation relaxation; and (4) this rule provides a 60-day comment period, and any comments received will be considered prior to finalization of this rule. List of Subjects in 7 CFR Part 946 Marketing agreements, Potatoes, Reporting and recordkeeping requirements. For the reasons set forth in the preamble, 7 CFR part 946 is amended as follows: PART 946—IRISH POTATOES GROWN IN WASHINGTON 1. The authority citation for 7 CFR part 946 continues to read as follows: ■ Authority: 7 U.S.C. 601–674. 2. The introductory text of § 946.336 is revised to read as follows: ■ § 946.336 Handling regulation. No person shall handle any lot of potatoes unless such potatoes meet the requirements of paragraphs (a), (b), (c), and (g) of this section or unless such potatoes are handled in accordance with paragraphs (d) and (e), or (f) of this section, except that shipments of the blue or purple flesh varieties of potatoes shall be exempt from both this handling regulation and the assessment requirements specified in § 946.41: Provided, That yellow fleshed, white, red, and russet type potatoes shall be exempt from the requirements of PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 26111 paragraphs (a), (b), (c), (e), and (g) of this section. * * * * * Dated: May 1, 2014. Rex A. Barnes, Associate Administrator, Agricultural Marketing Service. [FR Doc. 2014–10369 Filed 5–6–14; 8:45 am] BILLING CODE P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 23 [Docket No. FAA–2014–0155; Notice No. 23– 262–SC] Special Conditions: Extra Flugzeugproduktions and Vertriebs [Extra] GmbH, EA–300/LC; Acrobatic Category Aerodynamic Stability Federal Aviation Administration (FAA), DOT. ACTION: Final special conditions. AGENCY: These special conditions are issued 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 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: These special conditions are May 7, 2014, and are applicable beginning April 25, 2014. 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: SUMMARY: Background On February 3, 2011, Extra GmbH applied for an amendment to Type Certificate No. A67EU to include the model number, EA–300/LC. The EA– E:\FR\FM\07MYR1.SGM 07MYR1 pmangrum on DSK3VPTVN1PROD with RULES 26112 Federal Register / Vol. 79, No. 88 / Wednesday, May 7, 2014 / Rules and Regulations 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. VerDate Mar<15>2010 14:20 May 06, 2014 Jkt 232001 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 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. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 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. Discussion of Comments Notice of proposed special conditions No. 23–14–01–SC for the Extra Flugzeugproduktions and Vertriebs (Extra) GmbH, EA–300/LC airplane was published in the Federal Register on March 18, 2014 (79 FR 15062). No comments were received, and the special conditions are adopted as proposed. 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. Under standard practice, the effective date of final special conditions would be 30 days after the date of publication in the Federal Register; however, as the certification date for the Extra GmbH EA–300/LC is imminent, the FAA finds that good cause exists to make these special conditions effective upon issuance. 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. Citation The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. E:\FR\FM\07MYR1.SGM 07MYR1 Federal Register / Vol. 79, No. 88 / Wednesday, May 7, 2014 / Rules and Regulations pmangrum on DSK3VPTVN1PROD with RULES The Special Conditions Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for Extra GmbH EA– 300/LC airplanes. 1. Acrobatic Category Static Stability Requirements SC23.171 Flight—General: Acrobatic category airplanes 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— VerDate Mar<15>2010 14:20 May 06, 2014 Jkt 232001 (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 April 25, 2014. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–10392 Filed 5–6–14; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 26113 DEPARTMENT OF THE TREASURY Internal Revenue Service 26 CFR Part 1 [TD 9663] RIN 1545–BL42 Information Reporting for Affordable Insurance Exchanges Internal Revenue Service (IRS), Treasury. ACTION: Final regulations. AGENCY: This document contains final regulations relating to requirements for Affordable Insurance Exchanges (Exchanges) to report information relating to the health insurance premium tax credit enacted by the Patient Protection and Affordable Care Act and the Health Care and Education Reconciliation Act of 2010. These final regulations apply to Exchanges that make qualified health plans available to individuals. DATES: Effective date: These regulations are effective on May 7, 2014. Applicability Dates: For dates of applicability, see § 1.36B–1(o). FOR FURTHER INFORMATION CONTACT: Shareen S. Pflanz or Arvind Ravichandran, (202) 317–4718 (not a toll-free call). SUPPLEMENTARY INFORMATION: SUMMARY: Paperwork Reduction Act The collection of information contained in these regulations has been reviewed and approved by the Office of Management and Budget in accordance with the Paperwork Reduction Act of 1995 (44 U.S.C. 3507(d)) under control number 1545–2232. The collection of information in these final regulations is in § 1.36B–5 and will be reported on Form 1095–A. The collection of information is necessary to compute the premium tax credit and to reconcile the amount of the premium tax credit with advance payments of the premium tax credit (advance credit payments) made under section 1412 of the Patient Protection and Affordable Care Act (42 U.S.C. 18082). The collection of information is needed for compliance with the provisions of section 36B(f)(3) of the Internal Revenue Code (Code). The likely respondents are Exchanges established under section 1311 or 1321 of the Patient Protection and Affordable Care Act (42 U.S.C. 13031 or 42 U.S.C. 18041). An agency may not conduct or sponsor, and a person is not required to respond to, a collection of information unless it displays a valid control E:\FR\FM\07MYR1.SGM 07MYR1

Agencies

[Federal Register Volume 79, Number 88 (Wednesday, May 7, 2014)]
[Rules and Regulations]
[Pages 26111-26113]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-10392]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 23

[Docket No. FAA-2014-0155; Notice No. 23-262-SC]


Special Conditions: Extra Flugzeugproduktions and Vertriebs 
[Extra] GmbH, EA-300/LC; Acrobatic Category Aerodynamic Stability

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions.

-----------------------------------------------------------------------

SUMMARY: These special conditions are issued 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 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: These special conditions are May 7, 2014, and are applicable 
beginning April 25, 2014.

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:

Background

    On February 3, 2011, Extra GmbH applied for an amendment to Type 
Certificate No. A67EU to include the model number, EA-300/LC. The EA-

[[Page 26112]]

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 Sec.  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 Sec.  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 
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 Sec.  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 Sec.  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 Sec.  11.38, and they become part of the type-
certification basis under Sec.  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.

Discussion of Comments

    Notice of proposed special conditions No. 23-14-01-SC for the Extra 
Flugzeugproduktions and Vertriebs (Extra) GmbH, EA-300/LC airplane was 
published in the Federal Register on March 18, 2014 (79 FR 15062). No 
comments were received, and the special conditions are adopted as 
proposed.

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.
    Under standard practice, the effective date of final special 
conditions would be 30 days after the date of publication in the 
Federal Register; however, as the certification date for the Extra GmbH 
EA-300/LC is imminent, the FAA finds that good cause exists to make 
these special conditions effective upon issuance.

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.

Citation

    The authority citation for these special conditions is as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701, 44702, 44704.

[[Page 26113]]

The Special Conditions

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the following special conditions are issued as part of 
the type certification basis for Extra GmbH EA-300/LC airplanes.
1. Acrobatic Category Static Stability Requirements
    SC23.171 Flight--General: Acrobatic category airplanes 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 Sec.  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 Sec.  
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 
Sec.  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 Sec.  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 April 25, 2014.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2014-10392 Filed 5-6-14; 8:45 am]
BILLING CODE 4910-13-P

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