Source: https://www.federalregister.gov/documents/2006/06/16/E6-9410/special-conditions-aero-propulsion-inc-piper-model-pa28-236-installation-of-societe-de-motorisation
Timestamp: 2018-02-19 14:32:50
Document Index: 154560292

Matched Legal Cases: ['art 21', '§\u200921', 'art 3', 'art 23', '§\u200921', '§\u200923', '§\u200921', '§\u200921']

Federal Register :: Special Conditions: Aero Propulsion, Inc., Piper Model PA28-236; Installation of Societe de Motorisation Aeronautiques (SMA) Model SR305-230 Aircraft Diesel Engine (ADE) for Full Authority Digital Engine Control (FADEC) System and the Protection of the System From the Effects of High Intensity Radiated Fields (HIRF)
Special Conditions: Aero Propulsion, Inc., Piper Model PA28-236; Installation of Societe de Motorisation Aeronautiques (SMA) Model SR305-230 Aircraft Diesel Engine (ADE) for Full Authority Digital Engine Control (FADEC) System and the Protection of the System From the Effects of High Intensity Radiated Fields (HIRF)
Docket No. CE250
Special Conditions No. 23-190-SC
https://www.federalregister.gov/d/E6-9410 https://www.federalregister.gov/d/E6-9410
These final special conditions are issued to Aero Propulsion, Inc., for Piper Model PA28-236 airplanes with a Societe de Motorisation Aeronautiques (SMA) Model SR305-230 ADE. The supplemental type certificate for these airplanes will have a novel or unusual design feature associated with the installation of an aircraft diesel engine that uses an electronic engine control system instead of a 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.
Comments on these special conditions may be mailed in duplicate to: Federal Aviation Administration (FAA), Regional Counsel, ACE-7, Attention: Rules Docket, Docket No. CE250, 901 Locust Street, Room 506, Kansas City, Missouri 64106, or delivered in duplicate to the Regional Counsel at the above address. Comments must be marked: Docket No. CE250. Comments may be inspected in the Rules Docket weekdays, except Federal holidays, between 7:30 a.m. and 4 p.m.
Peter L. Rouse, Federal Aviation Administration, Aircraft Certification Service, Small Airplane Directorate, ACE-111, 901 Locust Street, Room 301, Kansas City, Missouri 64106; telephone: 816-329-4135, fax: 816-329-4090.
Interested persons are invited to submit such written data, views, or arguments as they may desire. Communications should identify the regulatory docket or special condition number and be submitted 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 special conditions 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. Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this notice must include a self-addressed, stamped postcard on which the following statement is made: “Comments to Docket No. CE250.” The postcard will be date stamped and returned to the commenter.
On August 20, 2003, Aero Propulsion, Inc., applied for a Supplemental Type Certification of Piper Model PA28-236 airplanes with the installation of an SMA Model SR305-230 engine. The airplane is powered by an SMA Model SR305-230 engine that is equipped with an electronic engine control system with full authority capability in these airplanes.
Under the provisions of 14 CFR part 21, § 21.101, Aero Propulsion, Inc., must show that the Piper Model PA28-236 airplanes, as changed, continue to meet the applicable provisions of the regulations incorporated by reference in the original type certification basis of the Piper Model PA28-236 airplanes, as listed on Type Certificate No. 2A13 or the applicable regulations in effect on the date of application for the change; exemptions, if any; and the special conditions adopted by this rulemaking action. The regulations incorporated by reference in the type certificate are commonly referred to as the “original type certification basis.” The Model PA28-236 airplanes were originally certified under Part 3 of the Civil Air Regulations.
If the Administrator finds that the applicable airworthiness regulations (i.e., CAR 3; 14 CFR part 23) do not contain adequate or appropriate safety standards for the Model PA28-236 airplanes because of a novel or unusual design feature, special conditions are prescribed under the provisions of § 21.16.
The Aero Propulsion, Inc., modified Piper Model PA28-236 airplanes will incorporate a novel or unusual design Start Printed Page 34788feature, an engine that includes an electronic control system with FADEC capability.
Many advanced electronic systems are prone to either upsets or damage, or both, at energy levels lower than analog systems. The increasing use of high power radio frequency emitters mandates requirements for improved HIRF protection for electrical and electronic equipment. Since the electronic engine control system used on the Aero Propulsion, Inc., modified Piper Model PA28-236 airplanes will perform critical functions, provisions for protection from the effects of HIRF should be considered and, if necessary, incorporated into the airplane design data. The FAA policy contained in Notice 8110.71, dated April 2, 1998, establishes the HIRF energy levels that airplanes will be exposed to in service. The guidelines set forth in this notice are the result of an Aircraft Certification Service review of existing policy on HIRF, in light of the ongoing work of the Aviation Rulemaking Advisory Committee (ARAC) Electromagnetic Effects Harmonization Working Group (EEHWG). The EEHWG adopted a set of HIRF environment levels in November 1997 that were agreed upon by the FAA, the Joint Aviation Authorities (JAA), and industry participants. As a result, the HIRF environments in this notice reflect the environment levels recommended by this working group. This notice states that a FADEC is an example of a system that should address the HIRF environments.
Therefore, special conditions are proposed for the Aero Propulsion, Inc., modified Piper Model PA28-236 airplanes to provide HIRF protection and to evaluate the installation of the electronic engine control system for compliance with the requirements of § 23.1309(a) through (e) at Amendment 23-49.
As discussed above, these special conditions are applicable to the Aero Propulsion, Inc., modified Piper Model PA28-236 airplanes. Should Aero Propulsion, Inc., apply at a later date for a supplemental type certificate to modify any other model included on Type Certificate No. 2A13 to incorporate the same novel or unusual design features, 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 Aero Propulsion, Inc., modified Piper Model PA28-236 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.
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 Piper Model PA28-236 is imminent, the FAA finds that good cause exists to make these special conditions effective upon issuance.
Authority: 49 U.S.C. 106(g), 40113 and 44701; 14 CFR §§ 21.16 and 21.101; and 14 CFR 11.38 and 11.19.
Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the supplemental type certification basis for Aero Propulsion, Inc., modified Piper Model PA28-236 airplanes.
(2) The applicant may demonstrate by a system test and analysis that the electrical and electronic systems that perform critical functions can withstand a minimum threat of 100 volts per meter peak electrical strength, without the benefit of airplane structural shielding, in the frequency range of 10 KHz to 18 GHz. When using this test to show Start Printed Page 34789compliance with the HIRF requirements, no credit is given for signal attenuation due to installation. Data used for engine certification may be used, when appropriate, for airplane certification.
[FR Doc. E6-9410 Filed 6-15-06; 8:45 am]