Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Flight Envelope Protection: General Limiting Requirements, 5148-5149 [2013-01379]

Download as PDF 5148 Federal Register / Vol. 78, No. 16 / Thursday, January 24, 2013 / Proposed Rules inoperative could be allowed under an approved minimum equipment list (MEL) that would require flight manual instructions to indicate reduced maximum operating speeds, as described in paragraph (4). In addition, the flightdeck display of the reduced operating speeds, as well as the overspeed warning for exceeding those speeds, must be equivalent to that of the normal airplane with the high-speed protection system operative. Also, it must be shown that no additional hazards are introduced with the highspeed protection system inoperative. Issued in Renton, Washington, on December 10, 2012. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–01457 Filed 1–23–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 25 [Docket No. FAA–2012–1332; Notice No. 25– 12–19–SC] Special Conditions: Embraer S.A., Model EMB–550 Airplanes; Flight Envelope Protection: General Limiting Requirements Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed special conditions. AGENCY: This action proposes special conditions for the Embraer S.A. Model EMB–550 airplane. This airplane will have a novel or unusual design feature(s), specifically new control architecture and a full digital flight control system which provides flight envelope protections. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. 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. DATES: Send your comments on or before March 11, 2013. ADDRESSES: Send comments identified by docket number FAA–2012–1332 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. mstockstill on DSK4VPTVN1PROD with SUMMARY: VerDate Mar<15>2010 18:31 Jan 23, 2013 Jkt 229001 • 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 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://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 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. 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. FOR FURTHER INFORMATION CONTACT: 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 may change these special conditions based on the comments we receive. PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 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. Embraer S.A. has developed comprehensive flight envelope protection features integral to the electronic flight control system design. These flight envelope protection features include limitations on angle-ofattack, normal load factor, bank angle, pitch angle, and speed. To accomplish this flight-envelope-limiting, a significant change (or multiple changes) occurs in the control laws of the electronic flight control system as the limit is approached or exceeded. When failure states occur in the electronic flight control system, flight envelope protection features can likewise either be modified, or in some cases, eliminated. The current regulations were not written with these comprehensive flight-envelope-limiting systems in mind. Type Certification Basis Under the provisions of Title 14, Code of Federal Regulations (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 E:\FR\FM\24JAP1.SGM 24JAP1 Federal Register / Vol. 78, No. 16 / Thursday, January 24, 2013 / Proposed Rules 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 § 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). mstockstill on DSK4VPTVN1PROD with Novel or Unusual Design Features The Model EMB–550 airplane will incorporate the following novel or unusual design features: New control architecture and a full digital flight control system which provides comprehensive flight envelope protections. 18:31 Jan 23, 2013 Jkt 229001 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: 2. Failure States: Electronic flight control system failures (including sensor) must not result in a condition where a parameter is limited to such a reduced value that safe and controllable maneuvering is no longer available. The crew must be alerted by suitable means if any change in envelope limiting or maneuverability is produced by single or multiple failures of the electronic flight control system not shown to be extremely improbable. Issued in Renton, Washington, on December 19, 2012. K.C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–01379 Filed 1–23–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. Discussion The applicable airworthiness regulation in this instance is 14 CFR 25.143. The purpose of § 25.143 is to verify that any operational maneuvers conducted within the operational envelope can be accomplished smoothly with average piloting skill and without exceeding any structural limits. The pilot should be able to predict the airplane response to any control input. During the course of the flight test program, the pilot determines compliance with § 25.143 through primarily qualitative methods. During flight test, the pilot should evaluate all of the following: • The interface between each protection function, • Transitions from one mode to another, • The aircraft response to intentional dynamic maneuvering, whenever applicable, through dedicated maneuvers, • General controllability assessment, • High speed characteristics, and • High angle-of-attack. Section § 25.143, however, does not adequately ensure that the novel or unusual features of the Model EMB–550 airplane will have a level of safety equivalent to that of existing standards. This special condition is therefore required to accommodate the the flightenvelope- limiting systems in the Model EMB–550 airplane. The additional safety standards in this special VerDate Mar<15>2010 condition will ensure a level of safety equivalent to that of existing standards. 5149 14 CFR Part 71 The Proposed Special Conditions Accordingly, the Federal Aviation Administration (FAA) proposes the following special conditions as part of the type certification basis for Embraer S.A. Model EMB–550 airplanes. 1. General Limiting Requirements: a. Onset characteristics of each envelope protection feature must be smooth, appropriate to the phase of flight and type of maneuver, and not in conflict with the ability of the pilot to satisfactorily change airplane flight path, speed, or attitude as needed. b. Limit values of protected flight parameters (and if applicable, associated warning thresholds) must be compatible with the following: i. Airplane structural limits, ii. Required safe and controllable maneuvering of the airplane, and iii. Margins to critical conditions. Unsafe flight characteristics/conditions must not result if dynamic maneuvering, airframe and system tolerances (both manufacturing and inservice), and non-steady atmospheric conditions, in any appropriate combination and phase of flight, can produce a limited flight parameter beyond the nominal design limit value. c. The airplane must be responsive to intentional dynamic maneuvering to within a suitable range of the parameter limit. Dynamic characteristics such as damping and overshoot must also be appropriate for the flight maneuver and limit parameter in question. d. When simultaneous envelope limiting is engaged, adverse coupling or adverse priority must not result. [Docket No. FAA–2012–0609; Airspace Docket No. 12–AEA–10] PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 Proposed Amendment of Class D and Class E Airspace; Caldwell, NJ Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: This action proposes to amend Class D and Class E Airspace at Caldwell, NJ, as the Paterson NonDirectional Radio Beacon (NDB) has been decommissioned and new Standard Instrument Approach Procedures have been developed at Essex County Airport. This action would enhance the safety and airspace management of Instrument Flight Rules (IFR) operations at the airport. DATES: Comments must be received on or before March 11, 2013. ADDRESSES: Send comments on this rule to: U.S. Department of Transportation, Docket Operations, West Building Ground Floor, Room W12–140, 1200 New Jersey SE., Washington, DC 20590– 0001; Telephone: 1–800–647–5527; Fax: 202–493–2251. You must identify the Docket Number FAA–2012–0609; Airspace Docket No. 12–AEA–10, at the beginning of your comments. You may also submit and review received comments through the Internet at http://www.regulations.gov. FOR FURTHER INFORMATION CONTACT: John Fornito, Operations Support Group, Eastern Service Center, Federal Aviation Administration, P.O. Box 20636, SUMMARY: E:\FR\FM\24JAP1.SGM 24JAP1

Agencies

[Federal Register Volume 78, Number 16 (Thursday, January 24, 2013)]
[Proposed Rules]
[Pages 5148-5149]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-01379]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 25

[Docket No. FAA-2012-1332; Notice No. 25-12-19-SC]


Special Conditions: Embraer S.A., Model EMB-550 Airplanes; Flight 
Envelope Protection: General Limiting Requirements

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed special conditions.

-----------------------------------------------------------------------

SUMMARY: This action proposes special conditions for the Embraer S.A. 
Model EMB-550 airplane. This airplane will have a novel or unusual 
design feature(s), specifically new control architecture and a full 
digital flight control system which provides flight envelope 
protections. The applicable airworthiness regulations do not contain 
adequate or appropriate safety standards for this design feature. 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.

DATES: Send your comments on or before March 11, 2013.

ADDRESSES: Send comments identified by docket number FAA-2012-1332 
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 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 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://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 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: 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:

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 may change these special conditions based on the 
comments we receive.

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.
    Embraer S.A. has developed comprehensive flight envelope protection 
features integral to the electronic flight control system design. These 
flight envelope protection features include limitations on angle-of-
attack, normal load factor, bank angle, pitch angle, and speed. To 
accomplish this flight-envelope-limiting, a significant change (or 
multiple changes) occurs in the control laws of the electronic flight 
control system as the limit is approached or exceeded. When failure 
states occur in the electronic flight control system, flight envelope 
protection features can likewise either be modified, or in some cases, 
eliminated. The current regulations were not written with these 
comprehensive flight-envelope-limiting systems in mind.

Type Certification Basis

    Under the provisions of Title 14, Code of Federal Regulations (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

[[Page 5149]]

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 
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 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 Model EMB-550 airplane will incorporate the following novel or 
unusual design features: New control architecture and a full digital 
flight control system which provides comprehensive flight envelope 
protections.

Discussion

    The applicable airworthiness regulation in this instance is 14 CFR 
25.143. The purpose of Sec.  25.143 is to verify that any operational 
maneuvers conducted within the operational envelope can be accomplished 
smoothly with average piloting skill and without exceeding any 
structural limits. The pilot should be able to predict the airplane 
response to any control input. During the course of the flight test 
program, the pilot determines compliance with Sec.  25.143 through 
primarily qualitative methods. During flight test, the pilot should 
evaluate all of the following:
     The interface between each protection function,
     Transitions from one mode to another,
     The aircraft response to intentional dynamic maneuvering, 
whenever applicable, through dedicated maneuvers,
     General controllability assessment,
     High speed characteristics, and
     High angle-of-attack.
    Section Sec.  25.143, however, does not adequately ensure that the 
novel or unusual features of the Model EMB-550 airplane will have a 
level of safety equivalent to that of existing standards. This special 
condition is therefore required to accommodate the the flight-envelope- 
limiting systems in the Model EMB-550 airplane. The additional safety 
standards in this special condition will ensure a level of safety 
equivalent to that of existing standards.

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 Proposed Special Conditions

    Accordingly, the Federal Aviation Administration (FAA) proposes the 
following special conditions as part of the type certification basis 
for Embraer S.A. Model EMB-550 airplanes.
    1. General Limiting Requirements:
    a. Onset characteristics of each envelope protection feature must 
be smooth, appropriate to the phase of flight and type of maneuver, and 
not in conflict with the ability of the pilot to satisfactorily change 
airplane flight path, speed, or attitude as needed.
    b. Limit values of protected flight parameters (and if applicable, 
associated warning thresholds) must be compatible with the following:
    i. Airplane structural limits,
    ii. Required safe and controllable maneuvering of the airplane, and
    iii. Margins to critical conditions. Unsafe flight characteristics/
conditions must not result if dynamic maneuvering, airframe and system 
tolerances (both manufacturing and in-service), and non-steady 
atmospheric conditions, in any appropriate combination and phase of 
flight, can produce a limited flight parameter beyond the nominal 
design limit value.
    c. The airplane must be responsive to intentional dynamic 
maneuvering to within a suitable range of the parameter limit. Dynamic 
characteristics such as damping and overshoot must also be appropriate 
for the flight maneuver and limit parameter in question.
    d. When simultaneous envelope limiting is engaged, adverse coupling 
or adverse priority must not result.
    2. Failure States: Electronic flight control system failures 
(including sensor) must not result in a condition where a parameter is 
limited to such a reduced value that safe and controllable maneuvering 
is no longer available. The crew must be alerted by suitable means if 
any change in envelope limiting or maneuverability is produced by 
single or multiple failures of the electronic flight control system not 
shown to be extremely improbable.

    Issued in Renton, Washington, on December 19, 2012.
K.C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-01379 Filed 1-23-13; 8:45 am]
BILLING CODE 4910-13-P