Federal Register / Vol. 76, No. 248 / Tuesday, December 27, 2011 / Proposed Rules 80829 

which must include, at a minimum, 

arrangements for pledging collateral to 

secure funding and possible initiatives 

to raise additional capital. 

(3) Require periodic stress testing, 

which analyzes the possible impacts on 

the bank’s cash inflows and outflows, 

liquidity position, profitability and 

solvency under a variety of stress 

scenarios. 

(4) Establish a process for managing 

events that imperil the bank’s liquidity, 

and assign appropriate personnel and 

implement executable action plans that 

carry out the CFP. 

(i) Reservation of Authority. The Farm 

Credit Administration reserves the right 

to require a Farm Credit bank to adjust 

the treatment of assets in its liquidity 

reserve so that it has liquidity that is 

sufficient and commensurate for the 

risks it faces. The Farm Credit 

Administration reserves the right to use 

this authority in response to adverse 

financial, economic, or market 

conditions by requiring any Farm Credit 

bank, on a case-by-case basis, to: 

(1) Apply a greater discount to any 

individual security or any class of 

securities; 

(2) Shift individual or multiple 

securities from one level of the liquidity 

reserve to another, or between one of the 

levels of the liquidity reserve and the 

supplemental liquidity buffer based on 

the performance of such asset(s), or 

based on financial, economic, or market 

conditions affecting the liquidity and 

solvency of the bank; 

(3) Spread out or otherwise change 

concentrations in the allocation of 

securities in any level of the bank’s 

liquidity reserve and its supplemental 

liquidity buffer; 

(4) Perform additional stress tests 

using other or different stress criteria or 

scenarios; 

(5) Hold additional liquid assets to 

cover unfunded commitments and other 

contingent outflows; or 

(6) Take any other action that the 

Farm Credit Administration deems 

necessary to ensure that the bank has 

sufficient liquidity to meet its financial 

obligations as they fall due. 

Dated: December 15, 2011. 

Dale L. Aultman, 

Secretary, Farm Credit Administration Board. 

[FR Doc. 2011–32698 Filed 12–23–11; 8:45 am] 

BILLING CODE 6705–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 23 

[Docket No.FAA–2011–1387; Notice No. 23– 

11–02–SC] 

Special Conditions: XtremeAir GmbH, 

XA42; Acrobatic Category 

Aerodynamic Stability 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed special 

conditions. 

SUMMARY: This action proposes special 

conditions for the XtremeAir GmbH 

XA42 airplane. The XA42 airplane has 

a novel or unusual design feature 

associated with its 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. 

These special conditions are only 

applicable to aircraft certified solely in 

the acrobatic category. 

DATES: Send your comments on or 

before January 26, 2012. 

ADDRESSES: Send comments identified 

by docket number FAA–2011–1387 

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 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: 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 will consider all comments we 

receive 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 May 3, 2011, XtremeAir GmbH 

applied for a type certificate for their 

new XA42. The XA42 is certified under 

EASA authority as a dual category 

(acrobatic/utility) airplane. It has a twoplace tandem canopy cockpit, and a 

single-engine. It also features a 

conventional landing gear, conventional 

low-wing planform and is of composite 

construction. The engine is a Lycoming 

AEIO–580–B1A with a rated power of 

315 Hp at 2,700 rpm. The airplane is 

proposed to be approved for Day-VFR 

operations with no icing approval. 

The maximum takeoff weight is 2,200 

pounds in utility category, 1,874 pounds 

in acrobatic category. VNE is 225 knots, 

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VNO is 185 knots and VA is 174 knots, 

indicated airspeed. Maximum altitude is 

15,000 feet. 

Acrobatic airplanes previously type 

certificated by the FAA did comply with 

the stability provisions of Subpart B of 

14 CFR part 23. However, airplanes like 

the XA42 are considered as ‘‘unlimited’’ 

acrobatic aircraft because they can 

perform at the highest level of aerobatic 

competition and can perform any of the 

maneuvers listed in the Aresti Catalog. 

Generally, 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 stability 

provisions of the regulations. These 

airplanes can still be type-certificated, 

but in the acrobatic category only and 

with an appropriate set of special 

conditions and associated limitations. 

The FAA will only consider certifying 

the XA42 in the acrobatic category. 

XtremeAir GmbH will not be able to 

offer a utility 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 XtremeAir 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 14 CFR, part 23, § 23.337. The 

XA42 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), 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, part 

21, § 21.17, XtremeAir GmbH must 

show that the XA42 meets the 

applicable provisions of part 23, as 

amended by Amendments 23–1 through 

23–59 thereto. 

Part 36 of Title 14 of the Code of 

Federal Regulations, 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 CFR 

23.1415(a)(b) has not been 

demonstrated. 

Approved for VFR-day only. Flight in 

known icing prohibited. 

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 XA42 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 a 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 XA42 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 and the FAA must issue a 

finding of regulatory adequacy under 

§ 611 of Public Law 92–574, the ‘‘Noise 

Control Act of 1972.’’ 

The FAA issues special conditions, as 

defined in 14 CFR, part 11, § 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 XtremeAir GmbH XA42 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 are 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 

part 21 and part 23, special conditions 

are needed to address these static 

stability characteristics. 

Accordingly, these special conditions 

are for the XtremeAir GmbH XA42 static 

stability characteristics to be certified 

solely as an acrobatic category airplane. 

Other conditions may be developed, as 

needed, based on further FAA review 

and discussions with the manufacturer 

and civil aviation authorities. 

Applicability 

As discussed above, these special 

conditions are applicable to the XA42. 

Should XtremeAir 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 and affects only the 

applicant who applied to the FAA for 

approval of these flight characteristics 

on the airplane. 

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, and 

44701; 14 CFR 21.16 and 21.17; and 14 CFR 

11.38 and 11.19. 

The Proposed Special Conditions 

Accordingly, the Federal Aviation 

Administration (FAA) proposes the 

following special conditions as part of 

the type certification basis for 

XtremeAir GmbH XA42 airplanes. 

1. Unlimited Acrobatic-Only Category 

Static Stability Requirements 

For unlimited, acrobatic-only category 

aircraft, the FAA proposes that the 

XtremeAir GmbH XA42 comply with 

the following stability special 

conditions in lieu of the existing 

§§ 23.171, 23.173, 23.175, and 23.177: 

A. In place of 14 CFR part 23, § 23.171 

Flight—General (stability) requirement, 

comply with the following: 

SC23.171 Flight—General: The 

airplane must be neutrally or positively 

stable in the longitudinal, directional, 

and lateral axes under sections 

SC23.173 through SC23.181. In 

addition, 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. 

B. In place of 14 CFR part 23, 

§ 23.173, Static longitudinal stability 

requirement, comply with the following: 

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 and the 

friction within the control system must 

be as follows: 

(a) A pull must be required to obtain 

and maintain speeds below the 

specified trim speed and a push 

required to obtain and maintain speeds 

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Federal Register / Vol. 76, No. 248 / Tuesday, December 27, 2011 / Proposed Rules 80831 

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. 

C. In place of 14 CFR part 23, 

§ 23.175, Demonstration of static 

longitudinal stability requirement, 

comply with the following: 

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 section 

23.69(a). 

(b) Cruise. With the airplane in trim 

with power for level flight at 

representative cruising speeds at high 

and low altitudes, including speeds up 

to VNO, except that 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 that 

the slope need not be stable— 

(i) At speeds less than 1.3 VS1; or 

(ii) For airplanes with VNE established 

under section 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. 

D. In place of 14 CFR part 23, 

§ 23.177, Static directional and lateral 

stability requirement, comply with the 

following: 

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 to the 

type of airplane. At larger angles of 

sideslip, up to that at which full rudder 

is used or a control force limit in section 

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 to the type of 

airplane. 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 section 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 

December 16, 2011. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–33049 Filed 12–23–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 135 

[Docket No. FAA–2011–1397] 

Clarification of Policy Regarding 

Approved Training Programs 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of availability; request 

for comment. 

SUMMARY: This document announces the 

availability of an FAA Notice that 

would require FAA inspectors to review 

14 CFR part 135 approved training 

programs to identify and correct those 

programs which erroneously issued 

credit for previous training or checking. 

The document also provides guidance 

on constructing reduced hour training 

programs based on previous experience. 

Upon review of the comments and any 

necessary revision, this document 

would cancel and replace FAA Order 

8900.1, Volume 3, Chapter 19, 

Paragraph 3–1111. 

DATES: Written comments must be 

received on or before February 27, 2012. 

ADDRESSES: Send comments identified 

by docket number FAA–2011–1397 

using any of the following methods: 

• Federal eRulemaking 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 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://www.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 

dockets, 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 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: 

Robert Burke, Air Carrier Training 

Branch, Air Transportation Division, 

Flight Standards Service, Federal 

Aviation Administration, 800 

Independence Avenue SW., 

Washington, DC 20591; telephone: (202) 

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