Special Conditions: Embraer S.A., Model EMB-550 Airplane; Landing Pitchover Condition, 31835-31836 [2013-12534]

Download as PDF Federal Register / Vol. 78, No. 102 / Tuesday, May 28, 2013 / Rules and Regulations 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. 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. [Amended] 15. Section 621.1 is amended by removing the words ‘‘service organizations’’ and adding in their place, the words ‘‘service corporations’’. ■ [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: ■ wreier-aviles on DSK5TPTVN1PROD with RULES 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’’. ■ VerDate Mar<15>2010 15:03 May 24, 2013 Jkt 229001 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. [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’’. ■ ■ § 621.2 21. The authority citation for part 630 continues to read as follows: ■ § 630.20 PART 621—ACCOUNTING AND REPORTING REQUIREMENTS § 621.1 PART 630—DISCLOSURE TO INVESTORS IN SYSTEM-WIDE AND CONSOLIDATED BANK DEBT OBLIGATIONS OF THE FARM CREDIT SYSTEM 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 Federal Aviation Administration (FAA), DOT. ACTION: Final special conditions. AGENCY: 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: PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 31835 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 E:\FR\FM\28MYR1.SGM 28MYR1 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. 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 wreier-aviles on DSK5TPTVN1PROD with RULES Applicability Federal Aviation Administration 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. 14 CFR Part 25 Conclusion AGENCY: This action affects only certain novel or unusual design features on one model VerDate Mar<15>2010 15:03 May 24, 2013 Jkt 229001 [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 Federal Aviation Administration (FAA), DOT. ACTION: Final special conditions. PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 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. E:\FR\FM\28MYR1.SGM 28MYR1

Agencies

[Federal Register Volume 78, Number 102 (Tuesday, May 28, 2013)]
[Rules and Regulations]
[Pages 31835-31836]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-12534]


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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.

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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 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, the special conditions would also 
apply to the other model under Sec.  21.101.
    In addition to the applicable airworthiness regulations and special

[[Page 31836]]

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