Federal Aviation Administration (FAA), DOT.
Final special conditions.
These special conditions are issued for the Eclipse Aviation Corporation, Model 500 airplane. This airplane will have a novel or unusual design feature(s) associated with the use of an electronic engine control system instead of a traditional mechanical control 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.
July 8, 2002.Start Further Info
FOR FURTHER INFORMATION CONTACT:
Ervin Dvorak Federal Aviation Administration, Aircraft Certification Service, Small Airplane Directorate, ACE-111, 901 Locust, Room 301, Kansas City, Missouri 64106; 816-329-4123 fax 816-329-4090.End Further Info End Preamble Start Supplemental Information
On July 12, 2001, Eclipse Aviation Corporation applied for a type certificate for their Model 500 airplane.
The Eclipse Model 500 airplane design includes digital electronic engine control systems, which were not envisaged and are not adequately addressed in 14 CFR part 23. The applicable existing regulations do not address electronic control systems since those were not envisioned at the time. Even though the engine control system will be certificated as part of the engine, the installation of an engine with an electronic control system requires evaluation due to the possible effects on or by other airplane systems (e.g., radio interference with other airplane electronic systems, shared engine and airplane power sources). The regulatory requirements were not applicable to systems certificated as part of the engine (ref. § 23.1309(f)(1)). Also, electronic control systems often require inputs from airplane data and power sources and outputs to other airplane systems. Although the parts of the system that are not certificated with the engine could be evaluated using the criteria of § 23.1309, the integral nature of systems such as these makes it unfeasible to evaluate the airplane portion of the system without including the engine portion of the system. However, § 23.1309(f)(1) again prevents complete evaluation of the installed airplane system since evaluation of the engine system's effects is not required.
Type Certification Basis
Under the provisions of 14 CFR 21.17, Eclipse Aviation Corporation must show that the Eclipse Model 500 airplane meets the following:
(1) Applicable provisions of 14 CFR part 23, effective December 18, 1964, as amended by Amendments 23-1 through 23-54 (September 14, 2000).
(2) Part 34 of the Federal Aviation Regulations effective September 10, 1990, plus any amendments in effect on the date of type certification.
(3) Part 36 of the Federal Aviation Regulations effective December 1, 1969, as amended by Amendment 36-1 through the amendment in effect on the date of type certification.
(4) Noise Control Act of 1972.
(5) Special conditions that are not relevant to these proposed special conditions, if any;
(6) Exemptions, if any;
(7) Equivalent level of safety findings, if any; and
(8) Special conditions adopted by this rulemaking action.
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 Model 500 airplane 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 Model 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 pursuant to section 611 of Public Law 92-574, the “Noise Control Act of 1972.”
Special conditions, as appropriate, as defined in 11.19, are issued in accordance with § 11.38, and become part of the type certification basis in accordance with § 21.17(a)(2).
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 Start Printed Page 39262incorporates the same novel or unusual design feature, the special conditions would also apply to the other model under the provisions of § 21.101.
Novel or Unusual Design Features
The Model 500 will incorporate the following novel or unusual design features:
Digital electronic engine control systems. This notice proposes a special condition for a digital electronic engine control system on the Eclipse Model 500 airplane.
Discussion of Comments
Notice of proposed special conditions No. 23-01-05-SC for the Eclipse Model 500 airplanes was published on March 11, 2002 (67 FR 10857). No comments were received, and the special conditions are adopted as proposed.
As discussed above, these special conditions are applicable to the Eclipse Model 500 airplane. Should Eclipse Aviation Corporation 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 under the provisions of § 21.101.
This action affects only certain novel or unusual design features on one model of airplanes. It is not a rule of general applicability, and it affects only the applicant who applied to the FAA for approval of these features on the airplane.Start List of Subjects
List of Subjects in 14 CFR Part 23End List of Subjects
The authority citation for these special conditions is as follows:
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 the Eclipse Aviation Corporation Model 500, airplane.
1. Electronic Engine Control System
The installation of the electronic engine control system must comply with the requirements of § 23.1309(a) through (e) at Amendment 23-49. The intent of this requirement is not to re-evaluate the inherent hardware reliability of the control itself, but rather determine the effects, including environmental effects addressed in § 23.1309(e), on the airplane systems and engine control system when installing the control on the airplane. When appropriate, engine certification data may be used when showing compliance with this requirement.Start Signature
Issued in Kansas City, Missouri, on May 28, 2002.
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 02-14353 Filed 6-6-02; 8:45 am]
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