Federal Register / Vol. 78, No. 33 / Tuesday, February 19, 2013 / Rules and Regulations 11555 

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. 

■ 1. Limit Pilot Forces for Sidestick 

Control. 

In lieu of the pilot forces specified in 

§ 25.397(c): 

■ (a) The limit pilot forces are: 

Pitch Roll 

Nose up 200 pounds 

force (lbf).

Nose left 100 lbf 

Nose down 200 lbf ....... Nose right 100 lbf 

■ (b) For all other components of the 

sidestick control assembly, excluding 

the internal components of the electrical 

sensor assemblies, to avoid damage as a 

result of an in-flight jam. 

Pitch Roll 

Nose up 125 lbf ............. Nose left 50 lbf 

Nose down 125 lbf ......... Nose right 50 lbf 

Issued in Renton, Washington, on February 

12, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–03657 Filed 2–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 25 

[Docket No. FAA–2012–1241; Special 

Conditions No. 25–480–SC] 

Special Conditions: Embraer S.A., 

Model EMB–550 Airplane; Design Roll 

Maneuver for Electronic Flight 

Controls 

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(s) associated with the design roll 

maneuver for electronic flight controls, 

specifically an electronic flight control 

system that provides control of the 

aircraft through pilot inputs to the flight 

computer. 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: March 21, 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 flight control system for the 

Model EMB–550 airplane does not have 

a direct mechanical link or a linear gain 

between the airplane flight control 

surface and the pilot’s cockpit control 

device, which is not accounted for in 

Title 14, Code of Federal Regulations 

(14 CFR) 25.349(a). Instead, a flight 

control computer commands the 

airplane flight control surfaces, based on 

input received from the cockpit control 

device. The pilot input is modified by 

the flight control computer before the 

command is given to the flight control 

surface. 

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–500 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 

conditions, the 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 

section 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 will incorporate the following 

novel or unusual design features: The 

Model EMB–550 airplane is equipped 

with an electronic flight control system 

that provides control of the aircraft 

through pilot inputs to the flight 

computer. Current part 25 airworthiness 

regulations account for ‘‘control laws’’ 

where aileron deflection is proportional 

to control stick deflection. They do not 

address any nonlinearities, i.e., 

situations where output does not change 

in the same proportion as input, or other 

effects on aileron actuation that may be 

caused by electronic flight controls. 

Discussion 

These special conditions differ from 

current regulatory requirements in that 

they require that the roll maneuver 

result from defined movements of the 

cockpit roll control as opposed to 

defined aileron deflections. Also, these 

special conditions require an additional 


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11556 Federal Register / Vol. 78, No. 33 / Tuesday, February 19, 2013 / Rules and Regulations 

load condition at design maneuvering 

speed (VA), in which the cockpit roll 

control is returned to neutral following 

the initial roll input. 

These special conditions differ from 

similar special conditions previously 

issued on this topic. These special 

conditions are limited to the roll axis 

only, whereas other special conditions 

also included pitch and yaw axes. 

Special conditions are no longer needed 

for the yaw axis because 14 CFR 25.351 

was revised at Amendment 25–91 to 

take into account effects of an electronic 

flight control system. No special 

conditions are needed for the pitch axis 

because the method that Embraer S.A. 

proposed for the pitch maneuver takes 

into account effects of an electronic 

flight control system. 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. 

Discussion of Comments 

Notice of proposed special conditions 

No. 25–12–15–SC for the Embraer S.A. 

EMB–550 airplanes was published in 

the Federal Register on November 26, 

2012 (77 FR 70384). No comments were 

received, and the special conditions are 

adopted as proposed. 

Applicability 

As discussed above, these special 

conditions are applicable to the 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 

EMB–550 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. 

1. Design Roll Maneuver for 

Electronic Flight Controls. 

In lieu of compliance to 14 CFR 

25.349(a), the Embraer S.A. Model 

EMB–550 airplane must comply with 

the following. 

The following conditions, speeds, and 

cockpit roll control motions (except as 

the motions may be limited by pilot 

effort) must be considered in 

combination with an airplane load 

factor of zero and of two-thirds of the 

positive maneuvering factor used in 

design. In determining the resulting 

control surface deflections, the torsional 

flexibility of the wing must be 

considered in accordance with 14 CFR 

25.301(b). 

(a) Conditions corresponding to 

steady rolling velocities must be 

investigated. In addition, conditions 

corresponding to maximum angular 

acceleration must be investigated for 

airplanes with engines or other weight 

concentrations outboard of the fuselage. 

For the angular acceleration conditions, 

zero rolling velocity may be assumed in 

the absence of a rational time history 

investigation of the maneuver. 

(b) At VA, sudden movement of the 

cockpit roll control up to the limit is 

assumed. The position of the cockpit 

roll control must be maintained until a 

steady roll rate is achieved and then 

must be returned suddenly to the 

neutral position. 

(c) At VC, the cockpit roll control 

must be moved suddenly and 

maintained so as to achieve a roll rate 

not less than that obtained in paragraph 

(b). 

(d) At VD, the cockpit roll control 

must be moved suddenly and 

maintained so as to achieve a roll rate 

not less than one third of that obtained 

in paragraph (b). 

Issued in Renton, Washington, on February 

12, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–03658 Filed 2–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 25 

[Docket No. FAA–2012–1246; Special 

Conditions No. 25–481–SC] 

Special Conditions: Embraer S.A., 

Model EMB–550 Airplane; Interaction 

of Systems and Structures 

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(s) associated with the interaction 

of systems and structures. 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: March 21, 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 Embraer EMB–550 

airplane is equipped with systems that, 

directly or as a result of failure or 

malfunction, affect its structural 

performance. Current regulations do not 

take into account loads for the airplane 

due to the effects of systems on 

structural performance including 

normal operation and failure conditions 

with strength levels related to 

probability of occurrence. Special 

conditions are needed to account for 

these features. 

Type Certification Basis 

Under the provisions of Title 14, Code 

of Federal Regulations (14 CFR) 21.17, 


sroberts on DSK5SPTVN1PROD with RULES