Federal Register / Vol. 78, No. 102 / Tuesday, May 28, 2013 / Rules and Regulations 31835 

association does not have an equity 

interest, but manages the operations of 

a UBE that is controlled by a System 

institution, describe this business 

relationship and any fees received. 

(ii) If the UBE is organized for the 

purpose of acquiring and managing 

unusual or complex collateral 

associated with loans, the bank or 

association need only disclose the name 

of the UBE, the type of business entity, 

and the purpose for which the UBE was 

organized. 

PART 621—ACCOUNTING AND 

REPORTING REQUIREMENTS 

■ 14. The authority citation for part 621 

continues to read as follows: 

Authority: Secs. 5.17, 8.11 of the Farm 

Credit Act (12 U.S.C. 2252, 2279aa–11); sec. 

514 of Pub. L. 102–552. 

§ 621.1 [Amended] 

■ 15. Section 621.1 is amended by 

removing the words ‘‘service 

organizations’’ and adding in their 

place, the words ‘‘service corporations’’. 

§ 621.2 [Amended] 

■ 16. Section 621.2(e) is amended by 

removing the words ‘‘service 

organization’’ and adding in their place, 

the words ‘‘service corporation’’. 

PART 622—RULES OF PRACTICE AND 

PROCEDURE 

■ 17. The authority citation for part 622 

continues to read as follows: 

Authority: Secs. 5.9, 5.10, 5.17, 5.25–5.37 

of the Farm Credit Act (12 U.S.C. 2243, 2244, 

2252, 2261–2273); 28 U.S.C. 2461 note; and 

42 U.S.C. 4012a(f). 

§ 622.2 [Amended] 

■ 18. Section 622.2(d) is amended by 

removing the words ‘‘service 

organization chartered under part E of 

title IV of the Act’’ and adding in their 

place, the words ‘‘service corporation 

chartered under the Act’’. 

PART 623—PRACTICE BEFORE THE 

FARM CREDIT ADMINISTRATION 

■ 19. The authority citation for part 623 

is revised to read as follows: 

Authority: Secs. 5.9, 5.10, 5.17, 5.25–5.37 

of the Farm Credit Act (12 U.S.C. 2243, 2244, 

2252, 2261–2273). 

§ 623.2 [Amended] 

■ 20. Section 623.2(d) is amended by 

removing the words ‘‘service 

organization chartered under part E of 

title IV of the Act’’ and adding in their 

place, the words ‘‘service corporation 

chartered under the Act’’. 

PART 630—DISCLOSURE TO 

INVESTORS IN SYSTEM-WIDE AND 

CONSOLIDATED BANK DEBT 

OBLIGATIONS OF THE FARM CREDIT 

SYSTEM 

■ 21. The authority citation for part 630 

continues to read as follows: 

Authority: Secs. 4.2, 4.9, 5.9, 5.17, 5.19 of 

the Farm Credit Act (12 U.S.C. 2153, 2160, 

2243, 2252, 2254); sec. 424 of Pub. L. 100– 

233, 101 Stat. 1568, 1656; sec. 514 of Pub. L. 

102–552, 106 Stat. 4102. 

§ 630.20 [Amended] 

■ 22. Section 630.20 is amended by 

removing the words ‘‘service 

organization’’ in paragraph (a)(2) and 

adding in their place, the words 

‘‘service corporation’’. 

Dated: May 21, 2013. 

Dale L. Aultman, 

Secretary, Farm Credit Administration Board. 

[FR Doc. 2013–12594 Filed 5–24–13; 8:45 am] 

BILLING CODE 6705–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 25 

[Docket No. FAA–2013–0148; Special 

Conditions No. 25–490–SC] 

Special Conditions: Embraer S.A., 

Model EMB–550 Airplane; Landing 

Pitchover Condition 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final special conditions. 

SUMMARY: These special conditions are 

issued for the Embraer S.A. Model 

EMB–550 airplane. This airplane will 

have a novel or unusual design feature 

associated with landing loads due to the 

automatic braking system. The 

applicable airworthiness regulations do 

not contain adequate or appropriate 

safety standards for this design feature. 

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. 

DATES: Effective Date: June 27, 2013. 

FOR FURTHER INFORMATION CONTACT: 

Todd Martin, FAA, Airframe and Cabin 

Safety Branch, ANM–115, Transport 

Airplane Directorate, Aircraft 

Certification Service, 1601 Lind Avenue 

SW., Renton, Washington, 98057–3356; 

telephone 425–227–1178; facsimile 

425–227–1232. 

SUPPLEMENTARY INFORMATION: 

Background 

On May 14, 2009, Embraer S.A. 

applied for a type certificate for their 

new Model EMB–550 airplane. The 

Model EMB–550 airplane is the first of 

a new family of jet airplanes designed 

for corporate flight, fractional, charter, 

and private owner operations. The 

aircraft has a conventional configuration 

with low wing and T-tail empennage. 

The primary structure is metal with 

composite empennage and control 

surfaces. The Model EMB–550 airplane 

is designed for 8 passengers, with a 

maximum of 12 passengers. It is 

equipped with two Honeywell 

HTF7500–E medium bypass ratio 

turbofan engines mounted on aft 

fuselage pylons. Each engine produces 

approximately 6,540 pounds of thrust 

for normal takeoff. The primary flight 

controls consist of hydraulically 

powered fly-by-wire elevators, aileron 

and rudder, controlled by the pilot or 

copilot sidestick. 

The Model EMB–550 airplane is 

equipped with an automatic braking 

system. This feature is a pilot-selectable 

function that allows earlier braking at 

landing without pilot pedal input. 

When the autobrake system is armed 

before landing, it automatically 

commands a pre-defined braking action 

after the main wheels touch down. This 

might cause a high nose gear sink rate, 

and potentially higher gear and airframe 

loads than would occur with a 

traditional braking system. Therefore, 

the FAA has determined special 

conditions are necessary. 

Type Certification Basis 

Under the provisions of 14 CFR 21.17, 

Embraer S.A. must show that the Model 

EMB–550 airplane meets the applicable 

provisions of part 25, as amended by 

Amendments 25–1 through 25–127 

thereto. 

If the Administrator finds that the 

applicable airworthiness regulations 

(i.e., 14 CFR part 25) do not contain 

adequate or appropriate safety standards 

for the Model EMB–550 airplane 

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, the special 

conditions would also apply to the other 

model under § 21.101. 

In addition to the applicable 

airworthiness regulations and special 


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31836 Federal Register / Vol. 78, No. 102 / Tuesday, May 28, 2013 / Rules and Regulations 

conditions, the Embraer S.A. Model 

EMB–550 airplane 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 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 Embraer S.A. Model EMB–550 

airplane is equipped with an automatic 

braking system, which is a pilotselectable function that allows earlier 

maximum braking at landing without 

pilot pedal input. When the autobrake 

system is armed before landing, it 

automatically commands maximum 

braking at main wheels touchdown. 

This will cause a high nose gear sink 

rate, and potentially higher gear and 

airframe loads than would occur with a 

traditional braking system. 

Discussion 

These special conditions define a 

landing pitchover condition that 

accounts for the effects of the automatic 

braking system. The special conditions 

define the airplane configuration, 

speeds, and other parameters necessary 

to develop airframe and nose gear loads 

for this condition. The special 

conditions require that the airplane be 

designed to support the resulting limit 

and ultimate loads as defined in 

§ 25.305. 

Discussion of Comments 

Notice of proposed special conditions 

No. 25–13–01–SC for the Embraer S.A. 

Model EMB–550 airplanes was 

published in the Federal Register on 

February 19, 2013 (78 FR 11609). No 

comments were received, and the 

special conditions are adopted as 

proposed. 

Applicability 

As discussed above, these special 

conditions are applicable to the Embraer 

S.A. Model EMB–550 airplane. Should 

Embraer S.A. 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 25 

Aircraft, Aviation safety, Reporting 

and recordkeeping requirements. 

The authority citation for these 

special conditions is as follows: 

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

44702, 44704. 

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 Embraer S.A. 

Model EMB–550 airplanes. 

Landing Pitchover Condition 

A landing pitchover condition must 

be addressed that takes into account the 

effect of the autobrake system. The 

airplane is assumed to be at the design 

maximum landing weight, or at the 

maximum weight allowed with the 

autobrake system on. The airplane is 

assumed to land in a tail-down attitude 

and at the speeds defined in § 25.481. 

Following main gear contact, the 

airplane is assumed to rotate about the 

main gear wheels at the highest pitch 

rate allowed by the autobrake system. 

This is considered a limit load 

condition from which ultimate loads 

must also be determined. Loads must be 

determined for critical fuel and payload 

distributions and centers of gravity. 

Nose gear loads, as well as airframe 

loads, must be determined. The airplane 

must support these loads as described in 

§ 25.305. 

Issued in Renton, Washington, on May 21, 

2013. 

Jeff Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–12534 Filed 5–24–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 25 

[Docket No. FAA–2012–1301; Special 

Conditions No. 25–491–SC] 

Special Conditions: Embraer S.A., 

Model EMB–550 Airplane, Dive Speed 

Definition With Speed Protection 

System 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final special conditions. 

SUMMARY: These special conditions are 

issued for the Embraer S.A. Model 

EMB–550 airplane. This airplane will 

have a novel or unusual design feature 

when compared to the state of 

technology envisioned in the 

airworthiness standards for transport 

category airplanes. These design 

features include a high-speed protection 

system. The applicable airworthiness 

regulations do not contain adequate or 

appropriate safety standards for this 

design feature. 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. 

DATES: Effective Date: June 27, 2013. 

FOR FURTHER INFORMATION CONTACT: 

Todd Martin, FAA, Airframe and Cabin 

Safety Branch, ANM–115, Transport 

Airplane Directorate, Aircraft 

Certification Service, 1601 Lind Avenue 

SW., Renton, Washington, 98057–3356; 

telephone 425–227–1178; facsimile 

425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Background 

On May 14, 2009, Embraer S.A. 

applied for a type certificate for their 

new Model EMB–550 airplane. The 

Model EMB–550 airplane is the first of 

a new family of jet airplanes designed 

for corporate flight, fractional, charter, 

and private owner operations. The 

aircraft has a conventional configuration 

with low wing and T-tail empennage. 

The primary structure is metal with 

composite empennage and control 

surfaces. The Model EMB–550 airplane 

is designed for 8 passengers, with a 

maximum of 12 passengers. It is 

equipped with two Honeywell 

HTF7500–E medium bypass ratio 

turbofan engines mounted on aft 

fuselage pylons. Each engine produces 

approximately 6,540 pounds of thrust 

for normal takeoff. The primary flight 

controls consist of hydraulically 

powered fly-by-wire elevators, ailerons 

and rudder, controlled by the pilot or 

copilot sidestick. 

The Model EMB–550 airplane 

incorporates a high-speed protection 

system in the airplane’s flight control 

laws. The airplane’s high-speed 

protection system limits nose-down 

pilot authority by adding automatic 

control inputs at threshold speeds above 

VMO/MMO, which influence the results 

of the traditional recovery maneuvers 

required in Title 14, Code of Federal 

Regulations (14 CFR) 25.335(b)(1). This 

speed protection system was not 

envisioned when § 25.335 was 

promulgated. 


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