Source: https://www.federalregister.gov/documents/2009/05/28/E9-12417/special-conditions-embraer-sa-model-emb-505-full-authority-digital-engine-control-fadec-system
Timestamp: 2017-09-25 23:22:20
Document Index: 398150609

Matched Legal Cases: ['art 23', 'art 23', '§\u200923', '§\u200923', '§\u200923', '§\u200923', '§\u200923', '§\u200921', 'art 23', 'art 23', '§\u200921', '§\u200911', '§\u200921', '§\u200923', '§\u200923']

Federal Register :: Special Conditions: Embraer S.A. Model EMB-505; Full Authority Digital Engine Control (FADEC) System
Special Conditions: Embraer S.A. Model EMB-505; Full Authority Digital Engine Control (FADEC) System
The effective date of these special conditions is May 20, 2009. We must receive your comments by June 29, 2009.
74 FR 25388
25388-25390 (3 pages)
Docket No. CE295
Special Conditions No. 23-235-SC
E9-12417
https://www.federalregister.gov/d/E9-12417 https://www.federalregister.gov/d/E9-12417
These special conditions are issued for the Embraer S.A. Model EMB-505 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.
Mail two copies of your comments to: Federal Aviation Administration, Small Airplane Directorate, Attn: Rules Docket (ACE-7), Docket No. CE295, 901 Locust, Room 301, Kansas City, Missouri 64106. You may deliver two copies to the Small Airplane Directorate at the above address. Mark your comments: Docket No. CE295. You may inspect comments in the Rules Docket weekdays, except Federal holidays, between 7:30 a.m. and 4 p.m.
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 Start Printed Page 25389supporting data. We ask that you send us two copies of written comments.
On October 9, 2006, Embraer S.A. applied for a type certificate for their new Model EMB-505. The EMB-505 is a twin engine jet which has applied for type certification in the commuter category. As such, the airplane is proposed to be type certificated in the commuter category of 14 CFR part 23 (and comparable Brazilian requirements RBHA 23) by exemption from 14 CFR 23.3(d). The EMB-505 is predominantly of metallic construction and is a conventionally configured low-wing monoplane with a T-tail and tricycle landing gear. The airplane's maximum takeoff weight is 17490 pounds. The VMO/MMO is 320 KCAS/M .78, with a maximum operating altitude of 45,000 feet. Requested operations are day/night VFR/IFR and icing operations.
The Embraer S.A. Model EMB-505 airplane is equipped with two Pratt and Whitney of Canada 3360 pound thrust PW535E turbofan engines, each using an electronic engine control system (FADEC) instead of a traditional mechanical control system. 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 critical environmental effects and possible effects on or by other airplane systems. For example, indirect effects of lightning, radio interference with other airplane electronic systems, shared engine and airplane data and power sources.
The regulatory requirements in 14 CFR part 23 for evaluating the installation of complex systems, including electronic systems and critical environmental effects, are contained in § 23.1309. However, when § 23.1309 was developed, the use of electronic control systems for engines was not envisioned. Therefore, the § 23.1309 requirements were not applicable to systems certificated as part of the engine (reference § 23.1309(f)(1)). 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.
Under the provisions of 14 CFR § 21.17, Embraer S.A. must show that the Model EMB-505 meets the applicable provisions of 14 CFR part 23, as amended by Amendments 23-1 through 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 Model EMB-505 because of a novel or unusual design feature, special conditions are prescribed under the provisions of § 21.16.
The FAA issues special conditions, as appropriate, as defined in 11.19, under § 11.38, and they become part of the type certification basis under § 21.17(a)(2).
The Embraer S.A. Model EMB-505 will incorporate the following novel or unusual design features:
As discussed above, these special conditions are applicable to the Model EMB-505. 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.
This action affects only certain novel or unusual design features on one model, Model EMB-505, of airplane. It is not a rule of general applicability and affects only the applicant who applied to the FAA for approval of these features on the airplane.
Under standard practice, the effective date of final special conditions would be 30 days after the date of publication in the Federal Register; however, as the certification date for the Embraer S.A. Model EMB-505 is imminent, the FAA finds that good cause exists to make these special conditions effective upon issuance.
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 Embraer S.A. Model EMB-505 airplanes.
The installation of the electronic engine control system must comply with the requirements of § 23.1309(a) through (e) at Amendment 23-55. The intent of this requirement is not to reevaluate the inherent hardware Start Printed Page 25390reliability 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; however, the effects of the installation on this data must be addressed.
Issued in Kansas City, Missouri on May 20, 2009.
[FR Doc. E9-12417 Filed 5-27-09; 8:45 am]