|National origin||United States|
|Manufacturer||Teledyne Continental Motors|
|Major applications||Reims Cessna 150
The Continental O-240 engine is a four-cylinder, horizontally opposed, air-cooled aircraft engine that was developed in the late 1960s for use in light aircraft by Continental Motors, Inc. The first O-240 was certified on 7 July 1971.
Design and development
The 130 hp (97 kW) O-240 was a new engine design derived from the six-cylinder Continental O-360 and introduced in 1971. It is generally similar in overall dimensions to the Continental O-200, but with a higher 8.5:1 compression ratio, designed to run on 100/130 avgas. The O-240 delivers 30% more power than the O-200 while it weighs only 12% more. It may be mounted in tractor or pusher configuration.
The O-240 was produced under license in the United Kingdom by Rolls-Royce Limited and was used to power the Reims Aviation-built Cessna 150s constructed in France under license. Rolls-Royce acquired the rights to the O-240, but not the IO-240 in 1977.
The IOF-240 is similar to the IO-240-B except that it employs an Aerosance FADEC system to control the ignition and fuel injection systems. The engine was not selected to power any production North American-manufactured aircraft until the Liberty XL2 entered production in 2006 powered by the IOF-240-B.
- Dual ignition, 130 hp (97 kW) at 2800 rpm, dry weight 246 lb (112 kg) including starter and generator. Uses a Marvel-Schebler MA-3SPA IO 5067 carburetor. Certified 7 July 1971
- Dual ignition, 125 hp (93 kW) at 2800 rpm, dry weight 246 lb (112 kg), uses a TCM 639231A27 fuel injector
- Dual ignition, 125 hp (93 kW) at 2800 rpm, dry weight 246 lb (112 kg), uses a TCM 639231A34 fuel injector
- Aerosance FADEC system controls the ignition and fuel injection systems, 125 hp (93 kW) at 2800 rpm, dry weight 255 lb (116 kg)
- AESL Airtourer T3
- Reims Cessna FRA150 ("A" meaning Aerobat)
- Rutan Voyager (front engine)
- Practavia Sprite (microlight)
- Rollason Condor (D62C)
- St Croix Pietenpol Aerial
- Tri-R KIS TR-1
- Warner Revolution II
Data from TYPE CERTIFICATE DATA SHEET NO. E7SO
- Type: "4-cylinder, air-cooled, naturally aspirated, horizontally opposed, fuel-injected, spark ignition, four-stroke, direct drive. The engine incorporates a full authority digital electronic control (FADEC) system to control the ignition and fuel injection functions."
- Bore: 4.438 in (112.7 mm)
- Stroke: 3.875 in (98.4 mm)
- Displacement: 240 in³ (3.93 L)
- Dry weight: 255 lb (116 kg)
- Valvetrain: One intake and one exhaust valve per cylinder
- Fuel system: Aerosance FADEC system
- Fuel type: 100LL avgas
- Cooling system: Air-cooled
- Power output: 125 hp (93 kW) at 2,800 rpm
- Specific power: 0.52 hp/in³ (23.66 kW/L)
- Compression ratio: 8.5:1
- Power-to-weight ratio: 0.49 hp/lb (0.80 kW/kg)
|Wikimedia Commons has media related to Continental O-240.|
- Federal Aviation Administration (March 2007). "TYPE CERTIFICATE DATA SHEET NO. E7SO Revision 4" (PDF). Retrieved 2008-12-18.
- Federal Aviation Administration (March 2007). "TYPE CERTIFICATE DATA SHEET NO. E11EU Revision 4" (PDF). Retrieved 2008-12-27.
- Christy, Joe: Engines for Homebuilt Aircraft & Ultralights, pages 58-59. TAB Books, 1983. ISBN 0-8306-2347-7
- Shanaberger, Kenneth (2008). "Continental O-240". Retrieved 2008-12-18.
- Gunston 1989, p.42.