11562 Federal Register / Vol. 78, No. 33 / Tuesday, February 19, 2013 / Rules and Regulations 

Æ The pilot should only be able to 

cancel it by achieving a higher energy 

state. 

Æ An adequate hierarchy should exist 

among the warnings so that the pilot is 

not confused and led to take 

inappropriate recovery action if 

multiple warnings occur. 

Simulators and flight test should 

evaluate global energy awareness and 

ensure that low energy cues are not a 

nuisance in all take-off and landing 

altitude ranges for which certification is 

requested. These evaluations should 

include all relevant combinations of 

weight, center of gravity position, 

configuration, airbrakes position, and 

available thrust, including reduced and 

derated take-off thrust operations and 

engine failure cases. A sufficient 

number of tests should be conducted to 

assess the level of energy awareness and 

the effects of energy management errors. 

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. 25–12–11–SC for the Embraer S.A. 

Model EMB–550 airplanes was 

published in the Federal Register on 

November 20, 2012 (77 FR 69573). 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 

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 Model EMB–550 

airplanes. 

1. Electronic Flight Control System: 

Lateral-Directional and Longitudinal 

Stability and Low Energy Awareness. In 

lieu of the requirements of §§ 25.171, 

25.173, 25.175, and 25.177, the 

following special conditions apply: 

a. The airplane must be shown to 

have suitable static lateral, directional, 

and longitudinal stability in any 

condition normally encountered in 

service, including the effects of 

atmospheric disturbance. The showing 

of suitable static lateral, directional, and 

longitudinal stability must be based on 

the airplane handling qualities, 

including pilot workload and pilot 

compensation, for specific test 

procedures during the flight test 

evaluations. 

b. The airplane must provide 

adequate awareness to the pilot of a low 

energy (e.g., low speed, low thrust, or 

low height) state when fitted with flight 

control laws presenting neutral 

longitudinal stability significantly 

below the normal operating speeds. 

‘‘Adequate awareness’’ means warning 

information must be provided to alert 

the crew of unsafe operating conditions 

and to enable them to take appropriate 

corrective action. 

c. The static directional stability (as 

shown by the tendency to recover from 

a skid with the rudder free) must be 

positive for any landing gear and flap 

position and symmetrical power 

condition, at speeds from 1.13 VSR1, up 

to VFE, VLE, or VFC/MFC (as appropriate). 

d. The static lateral stability (as 

shown by the tendency to raise the low 

wing in a sideslip with the aileron 

controls free) for any landing gear and 

wing-flap position and symmetric 

power condition, may not be negative at 

any airspeed (except that speeds higher 

than VFE need not be considered for 

wing-flaps extended configurations nor 

speeds higher than VLE for landing gear 

extended configurations) in the 

following airspeed ranges: 

i. From 1.13 VSR1 to VMO/MMO. 

ii. From VMO/MMO to VFC/MFC, unless 

the divergence is – 

1. Gradual; 

2. Easily recognizable by the pilot; 

and 

3. Easily controllable by the pilot. 

e. In straight, steady sideslips over the 

range of sideslip angles appropriate to 

the operation of the airplane, but not 

less than those obtained with one-half of 

the available rudder control movement 

(but not exceeding a rudder control 

force of 180 pounds), rudder control 

movements and forces must be 

substantially proportional to the angle 

of sideslip in a stable sense; and the 

factor of proportionality must lie 

between limits found necessary for safe 

operation. This requirement must be 

met for the configurations and speeds 

specified in paragraph (c) of this 

section. 

f. For sideslip angles greater than 

those prescribed by paragraph (e) of this 

section, up to the angle at which full 

rudder control is used or a rudder 

control force of 180 pounds is obtained, 

the rudder control forces may not 

reverse, and increased rudder deflection 

must be needed for increased angles of 

sideslip. Compliance with this 

requirement must be shown using 

straight, steady sideslips, unless full 

lateral control input is achieved before 

reaching either full rudder control input 

or a rudder control force of 180 pounds; 

a straight, steady sideslip need not be 

maintained after achieving full lateral 

control input. This requirement must be 

met at all approved landing gear and 

wing-flap positions for the range of 

operating speeds and power conditions 

appropriate to each landing gear and 

wing-flap position with all engines 

operating. 

Issued in Renton, Washington, on February 

12, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–03677 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–2012–1215; Special 

Conditions No. 25–12–482–SC] 

Special Conditions: Embraer S.A., 

Model EMB–550 Airplanes; Flight 

Envelope Protection: High Speed 

Limiting 

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, 

specifically an electronic flight control 

system which contains fly-by-wire 

control laws, including envelope 

protections, for the overspeed protection 

and roll limiting function. The 

applicable airworthiness regulations do 

not contain adequate or appropriate 

safety standards for this design feature. 

These special conditions contain the 


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Federal Register / Vol. 78, No. 33 / Tuesday, February 19, 2013 / Rules and Regulations 11563 

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: Joe 

Jacobsen, FAA, Airplane and Flight 

Crew Interface Branch, ANM–111, 

Transport Airplane Directorate, Aircraft 

Certification Service, 1601 Lind Avenue 

SW., Renton, Washington 98057–3356; 

telephone 425–227–2011; 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 a 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 longitudinal control law design of 

the Embraer S.A. Model EMB–550 

airplane incorporates an overspeed 

protection system in the normal mode. 

This mode prevents the pilot from 

inadvertently or intentionally exceeding 

a speed approximately equivalent to VFC

or attaining VDF. Current Title 14, Code 

of Federal Regulations (14 CFR) part 25 

did not envision a high speed limiter 

that might preclude or modify flying 

qualities assessments in the overspeed 

region. 

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 

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 Model EMB–550 airplane will 

incorporate the following novel or 

unusual design feature: an electronic 

flight control system which contains flyby-wire control laws, including 

envelope protections, for the overspeed 

protection and roll limiting function. 

Current part 25 requirements do not 

contain appropriate standards for high 

speed protection systems. 

Discussion 

As further discussed previously, a 

special condition is necessary in 

addition to the requirements of § 25.143 

for the operation of the high speed 

protection. The general intent is that the 

overspeed protection does not impede 

normal maneuvering and speed control 

and that the overspeed protection does 

not restrict or prevent emergency 

maneuvering. Therefore, 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. 25–12–12–SC for the Embraer S.A. 

Model EMB–550 airplanes was 

published in the Federal Register on 

November 20, 2012 (77 FR 69572). 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 

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. In addition to § 25.143, the 

following requirement applies: 

Operation of the high speed limiter 

during all routine and descent 

procedure flight must not impede 

normal attainment of speeds up to 

overspeed warning. 

Issued in Renton, Washington, on February 

12, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–03676 Filed 2–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1005; Directorate 

Identifier 2012–NE–27–AD; Amendment 39– 

17349; AD 2013–03–14] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Canada Corp Turboshaft 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 


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