Source: https://www.federalregister.gov/articles/2008/01/23/E8-1077/special-conditions-embraer-sa-model-emb-500-brakes-designation-of-applicable-regulations
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Federal Register | Special Conditions: Embraer S.A.; Model EMB-500; Brakes-Designation of Applicable Regulations
Special Conditions: Embraer S.A.; Model EMB-500; Brakes-Designation of Applicable Regulations
Publication Date: Wednesday, January 23, 2008
Dates: Comments must be received on or before February 22, 2008.
Comments Close: 02/22/2008
73 FR 3884
-3885 (2 pages)
Docket No. CE283
Notice No. 23-08-01-SC
Document Number: E8-1077
Shorter URL: https://federalregister.gov/a/E8-1077 Related Topics
This notice proposes special conditions for the Embraer S.A.; Model EMB-500 airplane. This airplane has a novel or unusual design feature associated with the braking system. 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 harmonize with Brazil's Agencia Nacional de Aviacao Civil (ANAC) and to maintain the same level of safety between the ANAC Type Certificate and the U.S. Type Certificate.
Mail comments on this proposal in duplicate to: Federal Aviation Administration, Regional Counsel, ACE-7, Attention: Rules Docket, Docket No. CE283, 901 Locust, Room 506, Kansas City, Missouri 64106, or delivered in duplicate to the Regional Counsel at the above address. Comments must be marked: CE283. Comments may be inspected in the Rules Docket weekdays, except Federal holidays, between 7:30 a.m. and 4 p.m.
Leslie B. Taylor, Federal Aviation Administration, Aircraft Certification Service, Small Airplane Directorate, ACE-111, 901 Locust, Room 301, Kansas City, Missouri, 816-329-4134, fax 816-329-4090, e-mail at leslie.b.taylor@faa.gov.
Interested persons are invited to participate in the making of these proposed special conditions by submitting such written data, views, or arguments as they may desire. Identify the regulatory docket or notice number and submit them in duplicate to the address specified above. All communications received on or before the closing date for comments will be considered by the Administrator. The proposals described in this notice may be changed in light of the comments received. All comments received will be available in the Rules Docket for examination by interested persons, both before and after the closing date for comments. A report summarizing each substantive public contact with FAA personnel concerning this rulemaking will be filed in the docket. If you wish the FAA to acknowledge receipt of the comments submitted in response to this notice, include with those comments a self-addressed, stamped postcard on which the following statement is made: “Comments to Docket No. CE283.” The postcard will be date stamped and returned to the commenter.
On October 5, 2005, Embraer S.A. applied for a type certificate for their new Model EMB-500. The EMB-500 is a twin engine jet of a type popularly referred to as a very light jet. The airplane is proposed to be type certificated in the normal category of 14 CFR part 23 (and comparable Brazilian requirements RBHA 23). The EMB-500 is predominantly of metallic construction and is a conventionally configured low-wing monoplane with a T-tail and tricycle landing gear. The two Pratt and Whitney of Canada 1,600 pound thrust PWC 617F/1 turbofan engines are aft fuselage mounted in typical business jet fashion. The engines are full authority digital engine control (FADEC) equipped.
The airplane's maximum takeoff weight is 9,965 pounds. The VMO/MMO is 275 KIAS/M .70, with a maximum operating altitude of 41,000 feet. Requested operations are day/night VFR/IFR, and icing operations approval is requested.
The FAA considers it necessary to add an additional airworthiness standard to adopt the commuter category requirement in 14 CFR 23.735(e), which the Administrator considers necessary to harmonize with ANAC and to maintain the same level of safety between the ANAC Type Certificate and the U.S. Type Certificate.
Under the provisions of 14 CFR part 21, § 21.17, Embraer S.A. must show that the EMB-500 meets the applicable provisions of 14 CFR part 23, as amended by Amendment 23-1 through Amendment 23-55 thereto.
If the Administrator finds that the applicable airworthiness regulations (i.e., 14 CFR part 23) do not contain adequate or appropriate safety standards for the EMB-500 because of a novel or unusual design feature, special conditions are prescribed under the provisions of § 21.16.
In addition to the applicable airworthiness regulations and special conditions, the EMB-500 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 92, the “Noise Control Act of 1972.”
Special conditions, as appropriate, as defined in § 11.19, are issued under § 11.38 and become part of the type certification basis under § 21.17(a)(2).
The EMB-500 will incorporate the following novel or unusual design features: The takeoff speed and takeoff distance for this jet airplane make it necessary to adopt rejected takeoff requirements.
As discussed above, these special conditions are applicable to the EMB-500. If Embraer S.A. applies 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 under § 21.101(a)(1).
Accordingly, the Federal Aviation Administration (FAA) proposes the following special conditions as part of the type certification basis for the Embraer S.A. Model EMB-500 airplanes. Brakes-Designation of Applicable Regulations.
SC 23.735(e): Delete “In addition, for commuter category airplanes.”
The rejected takeoff brake kinetic energy capacity rating of each main wheel brake assembly must not be less than the kinetic energy absorption requirements determined under either of the following methods.
(e)(1) The brake kinetic energy absorption requirements must be based on a conservative rational analysis of the sequence of events expected during a rejected takeoff at the design takeoff weight.
(e)(2) Instead of rational analysis, the kinetic energy absorption requirements for each main wheel brake assembly may be derived from the following formula—
KE = 0.0443WV
KE =Kinetic energy per wheel (ft.-lbs.);
W = Design takeoff weight (lbs.);
V = Ground speed, in knots, associated with the maximum value of V 1 selected in accordance with § 23.51(c)(1);
N = Number of main wheels with brakes.
[FR Doc. E8-1077 Filed 1-22-08; 8:45 am]