Source: https://www.federalregister.gov/articles/2006/08/04/E6-12663/special-conditions-aero-propulsion-inc-piper-model-pa28-236-diesel-cycle-engine-using-turbine-jet
Timestamp: 2015-11-28 09:31:03
Document Index: 335730853

Matched Legal Cases: ['art 23', '§ 23', '§ 21', 'art 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', 'art 23', '§ 21', 'art 36', '§ 11', '§ 21', '§ 21', '§ 21', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', '§ 23', 'art 23', '§ 23']

Federal Register | Special Conditions: Aero Propulsion, Inc., Piper Model PA28-236; Diesel Cycle Engine Using Turbine (Jet) Fuel
-44185 (4 pages)
Document Number: E6-12663
Shorter URL: https://federalregister.gov/a/E6-12663 Related Topics
These special conditions are issued to Aero Propulsion, Inc., for the Piper Model PA28-236 airplanes with a Societe de Motorisation Aeronautiques (SMA) Model SR305-230 Aircraft Diesel Engine (ADE). This airplane will have a novel or unusual design feature(s) associated with the installation of a diesel cycle engine utilizing turbine (jet) fuel. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for installation of this new technology engine. 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.
On August 20, 2003, Aero Propulsion, Inc., applied for a supplemental type certificate for the installation of an SMA Model SR305-230 ADE (type certificated in the United States, type certificate number E00067EN) in Piper Model PA28-236 airplanes. Piper Model PA28-236 airplanes, approved under Type Certificate No. 2A13, are four place, single engine airplanes.
In anticipation of the reintroduction of diesel engine technology into the small airplane fleet, the FAA issued Policy Statement PS-ACE100-2002-004 on May 15, 2004, which identified areas of technological concern involving introduction of new technology diesel engines into small airplanes. For a more detailed summary of the FAA's development of diesel engine requirements, refer to this policy.
The general areas of concern involved the power characteristics of the diesel engines, the use of turbine fuel in an airplane class that has typically been powered by gasoline fueled engines, and the vibration characteristics and failure modes of diesel engines. These concerns were identified after review of the historical record of diesel engine used in aircraft and a review of the 14 CFR part 23 regulations, which identified specific regulatory areas that needed to be evaluated for applicability to diesel engine installations. These concerns are not considered universally applicable to all types of possible diesel engines and diesel engine installations. However, after review of the Aero Propulsion installation, and after applying the provisions of the diesel policy, the FAA proposed these fuel system and engine related special conditions. Other special conditions issued in a separate notice include special conditions for HIRF and application of § 23.1309 provisions to the Full Authority Digital Engine Control (FADEC).
Under the provisions of § 21.101, Aero Propulsion, Inc., must show that the Piper Model PA28-236 airplanes, with the installation of an SMA Model SR305-230 ADE, continue to meet the applicable provisions of 14 CFR part 23 and CAR 3 thereto. In addition, the certification basis includes special conditions and equivalent levels of safety for the following:
Engine torque (Provisions similar to § 23.361, paragraphs (b)(1) and (c)(3))
Flutter (Compliance with § 23.629, paragraphs (e)(1) and (2))
Powerplant—Installation (Provisions similar to § 23.901(d)(1) for turbine engines)
Powerplant—Fuel System—Fuel system with water saturated fuel (Compliance with § 23.951 requirements)
Powerplant—Fuel System—Fuel system hot weather operation (Compliance with § 23.961 requirements)
Powerplant—Fuel system—Fuel tank filler connection (Compliance with § 23.973(f) requirements)
Powerplant—Fuel system—Fuel tank outlet (Compliance with § 23.977 requirements)
Equipment—General—Powerplant Instruments (Compliance with § 23.1305 requirements)
Operating Limitations and Information—Powerplant limitations—Fuel grade or designation (Compliance with § 23.1521(d) requirements)
Markings and Placards—Miscellaneous markings and placards—Fuel, oil, and coolant filler openings (Compliance with § 23.1557(c)(1) requirements)
Powerplant—Fuel system—Fuel Freezing
If the Administrator finds that the applicable airworthiness regulations (i.e., part 23) do not contain adequate or appropriate safety standards for the Piper Model PA28-236 airplanes with the installation of an SMA Model SR305-230 ADE 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 Piper Model PA28-236 airplanes, with the installation of an SMA Model SR305-230 ADE, must comply with 14 CFR 21.115 noise certification requirements of 14 CFR part 36.
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 § 21.101.
Special conditions are initially applicable to the model for which they are issued. Should the applicant apply for a supplemental type certificate to modify any other model included on the same type certificate to incorporate the same novel or unusual design feature, the special conditions would also apply to the other model under the provisions of § 21.101.
The Piper Model PA28-236 airplanes, with the installation of an SMA Model SR305-230 ADE, will incorporate the following novel or unusual design features: The Piper Model PA28-236 airplanes, with the installation of an SMA Model SR305-230, will incorporate an aircraft diesel engine utilizing turbine (jet) fuel.
A notice of proposed special conditions No. 23-06-03-SC for Aero Propulsion, Inc., for the Piper Model PA28-236 airplanes, with the installation of an SMA Model SR305-230 ADE, was published on June 14, 2006 (71FR 34292). No comments were received, and the special conditions are adopted as proposed.
As discussed above, these special conditions are applicable to the Piper Model PA28-236 airplanes, with the installation of an SMA Model SR305-230 ADE. 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 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 the Piper Model PA28-236 airplanes, with the installation of an SMA Model SR305-230 ADE. 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.
Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued to Aero Propulsion, Inc., as part of the type certification basis for the Piper Model PA28-236 airplanes, with the installation of an SMA Model SR305-230 ADE.
1. Engine torque (Provisions similar to § 23.361, paragraphs (b)(1) and (c)(3)):
2. Flutter—(Compliance with the requirements of § 23.629 (e)(1) and (e)(2) requirements): The flutter evaluation of the airplane done in accordance with 14 CFR 23.629 must include—
(b) Propeller, engine, engine mount and airplane structure stiffness and damping variations appropriate to the particular configuration, and (c) The flutter investigation will include showing the airplane is free from flutter with one cylinder inoperative.
3. Powerplant—Installation (Provisions similar to § 23.901(d)(1) for turbine engines): Considering the vibration characteristics of diesel engines, the applicant must comply with the following:
4. Powerplant—Fuel System—Fuel system with water saturated fuel (Compliance with § 23.951 requirements): Considering the fuel types used by diesel engines, the applicant must comply with the following:
Methods of compliance that are acceptable for turbine engine fuel systems requirements of § 23.951(c) are also considered acceptable for this requirement.
5. Powerplant—Fuel System—Fuel flow (Compliance with § 23.955(c) requirements): In lieu of 14 CFR 23.955(c), engine fuel system must provide at least 100 percent of the fuel flow required by the engine, or the fuel flow required to prevent engine damage, if that flow is greater than 100 percent. The fuel flow rate must be available to the engine under each intended operating condition and maneuver. The conditions may be simulated in a suitable mockup. This flow must be shown in the most adverse fuel feed condition with respect to altitudes, attitudes, and any other condition that is expected in operation.
6. Powerplant—Fuel System—Fuel system hot weather operation (Compliance with § 23.961 requirements): In place of compliance with § 23.961, the applicant must comply with the following:
7. Powerplant—Fuel system—Fuel tank filler connection (Compliance with § 23.973(f) requirements): In place of compliance with § 23.973(e) and (f), the applicant must comply with the following:
8. Powerplant—Fuel system—Fuel tank outlet (Compliance with § 23.977 requirements): In place of compliance with § 23.977(a)(1) and (a)(2), the applicant will comply with the following:
9. Equipment—General—Powerplant Instruments (Compliance with § 23.1305): In addition to compliance with § 23.1305, the applicant will comply with the following:
The following are required in addition to the powerplant instruments required in § 23.1305:
(a) A fuel temperature indicator.
(c) An indicating means for the fuel strainer or filter required by § 23.997 to indicate the occurrence of contamination of the strainer or filter before it reaches the capacity established in accordance with § 23.997(d).
10. Operating Limitations and Information—Powerplant limitations—Fuel grade or designation (Compliance with § 23.1521 requirements): All engine parameters that have limits specified by the engine manufacturer for takeoff or continuous operation must be investigated to ensure they remain within those limits throughout the expected flight and ground envelopes (e.g., maximum and minimum fuel temperatures, ambient temperatures, as applicable, etc.). This is in addition to the existing requirements specified by 14 CFR 23.1521 (b) and (c). If any of those limits can be exceeded, there must be continuous indication to the flight crew of the status of that parameter with appropriate limitation markings.
Instead of compliance with § 23.1521(d), the applicant must comply with the following:
The minimum fuel designation (for diesel engines) must be established so that it is not less than that required for the operation of the engines within the limitations in paragraphs (b) and (c) of § 23.1521.
11. Markings and Placards—Miscellaneous markings and placards—Fuel, oil, and coolant filler openings (Compliance with § 23.1557(c)(1) requirements): Instead of compliance with § 23.1557(c)(1), the applicant must comply with the following:
12. Powerplant—Fuel system—Fuel-Freezing: If the fuel in the tanks cannot be shown to flow suitably under all possible temperature conditions, then fuel temperature limitations are required. These will be considered as part of the essential operating parameters for the aircraft and must be limitations.
13. Powerplant Installation—Vibration levels: Vibration levels throughout the engine operating range must be evaluated and:
14 CFR part 23, §§ 23.251; 23.613; 23.627; 23.629 (or CAR 3.159, as applicable to various models); 23.572; 23.573; 23.574 and 23.901.
14. Powerplant Installation—One cylinder inoperative: It must be shown by test or analysis, or by a combination of methods, that the airframe can withstand the shaking or vibratory forces imposed by the engine if a cylinder becomes inoperative. Diesel engines of conventional design typically have extremely high levels of vibration when a cylinder becomes inoperative.
15. Powerplant Installation—High Energy Engine Fragments: It may be possible for diesel engine cylinders (or portions thereof) to fail and physically separate from the engine at high velocity (due to the high internal pressures). This failure mode will be considered possible in engine designs with removable cylinders or other non-integral block designs. The following is required:
[FR Doc. E6-12663 Filed 8-3-06; 8:45 am]