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Timestamp: 2020-08-09 00:26:18
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Matched Legal Cases: ['art 119', 'art 91', 'art 25', 'art 25', 'art 25', '§ 21', '§ 21', 'art 34', 'art 36', '§ 611', '§ 11', '§ 21', 'art 25', 'art 25', 'art 3', 'art 25']

Special Conditions: Embraer S.A., Model EMB-550 Airplane; Design Roll Maneuver for Electronic Flight Controls, 70384-70385 [2012-28386] :: Federal Aviation Administration :: Department Of Transportation :: Regulation Tracker :: Justia
Justia Regulation Tracker Department Of Transportation Federal Aviation Administration Special Conditions: Embraer S.A., Model EMB-550 Airplane; Design Roll Maneuver for Electronic Flight Controls, 70384-70385 [2012-28386]
Special Conditions: Embraer S.A., Model EMB-550 Airplane; Design Roll Maneuver for Electronic Flight Controls, 70384-70385 [2012-28386]
Download as PDF 70384 Federal Register / Vol. 77, No. 227 / Monday, November 26, 2012 / Proposed Rules (e) Alternative Methods of Compliance (AMOC) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Chinh Vuong, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email chinh. vuong@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (f) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2011–0190, dated September 30, 2011. (g) Subject Joint Aircraft Service Component (JASC) Code: 2810, fuel storage. Issued in Fort Worth, Texas, on November 8, 2012. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2012–28435 Filed 11–23–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 25 [Docket No. FAA–2012–1241; Notice No. 25– 12–15–SC] Special Conditions: Embraer S.A., Model EMB–550 Airplane; Design Roll Maneuver for Electronic Flight Controls 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) 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 proposed special conditions contain the additional safety standards that the Administrator considers necessary to establish a level mstockstill on DSK4VPTVN1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 19:01 Nov 23, 2012 Jkt 229001 of safety equivalent to that established by the existing airworthiness standards. DATES: Send your comments on or before January 10, 2013. ADDRESSES: Send comments identified by docket number [FAA–2012–1241] 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: 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: 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 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 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, 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 E:\FR\FM\26NOP1.SGM 26NOP1 Federal Register / Vol. 77, No. 227 / Monday, November 26, 2012 / Proposed Rules 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 § 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 PROPOSALS Novel or Unusual Design Features The 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 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 VerDate Mar<15>2010 16:40 Nov 23, 2012 Jkt 229001 flight control system. 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. 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. 70385 (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 November 16, 2012. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–28386 Filed 11–23–12; 8:45 am] BILLING CODE 4910–13–P 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. 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. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 DEPARTMENT OF COMMERCE Patent and Trademark Office 37 CFR Part 3 [Docket No. PTO–P–2012–0047] Notice of Roundtable on Proposed Requirements for Recordation of RealParty-in-Interest Information Throughout Application Pendency and Patent Term United States Patent and Trademark Office, Commerce. ACTION: Notice of public meeting; request for comments. AGENCY: The United States Patent and Trademark Office (USPTO) is considering promulgating regulations that would require greater public transparency concerning the ownership of patent applications and patents by requiring the provision of real-party-ininterest information during patent prosecution and at certain times postissuance. As part of this initiative, the USPTO is conducting a roundtable to obtain public input from organizations and individuals on how the USPTO could change its rules of practice to collect and provide such ownership information and make it publicly available. The USPTO plans to invite a number of roundtable participants from among patent user groups, practitioners, industry, independent inventor organizations, academia, and government. The roundtable also is open for any member of the public to provide input. SUMMARY: E:\FR\FM\26NOP1.SGM 26NOP1
[Pages 70384-70385]
[FR Doc No: 2012-28386]
[Docket No. FAA-2012-1241; Notice No. 25-12-15-SC]
Special Conditions: Embraer S.A., Model EMB-550 Airplane; Design
Roll Maneuver for Electronic Flight Controls
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
DATES: Send your comments on or before January 10, 2013.
ADDRESSES: Send comments identified by docket number [FAA-2012-1241]
3356; telephone 425-227-1178; facsimile 425-227-1149.
fly-by-wire elevators, ailerons, and rudder, controlled by the pilot or
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.
appropriate safety standards for the Model EMB-500 airplane because of
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
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.
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 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 proposed special
on one model EMB-550 of airplanes. It is not a rule of general
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).