Continental O-240-A
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Continental O-240-A
Teledyne Continental Motors IO-240-B Diamond DA20-C1 C-GEQA.jpg
Continental IO-240B
Type Piston aero-engine
United States
Manufacturer Teledyne Continental Motors
First run 1971
Issoire APM 40 Simba
Diamond DA20-C1
AESL Airtourer
Liberty XL2
Produced 1971-Today,
1993-Today (IO)
Continental O-360

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.[1][2]

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.[3][4]

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.[5] Rolls-Royce acquired the rights to the O-240, but not the IO-240 in 1977.[2]

The fuel-injected IO-240-A and -B were introduced in 1993. The A and B versions differ only in the type of fuel injector used.[1][4]

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.[1] 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[2][3]
Dual ignition, 125 hp (93 kW) at 2800 rpm, dry weight 246 lb (112 kg), uses a TCM 639231A27 fuel injector[1]
Dual ignition, 125 hp (93 kW) at 2800 rpm, dry weight 246 lb (112 kg), uses a TCM 639231A34 fuel injector[1]
Aerosance FADEC system controls the ignition and fuel injection systems, 125 hp (93 kW) at 2800 rpm, dry weight 255 lb (116 kg)[1]


The Liberty XL2 is equipped with a Continental IOF-240-B engine.

Specifications (IOF-240-B)


General characteristics

  • 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


See also



  1. ^ a b c d e f g Federal Aviation Administration (March 2007). "TYPE CERTIFICATE DATA SHEET NO. E7SO Revision 4" (PDF). Retrieved .
  2. ^ a b c Federal Aviation Administration (March 2007). "TYPE CERTIFICATE DATA SHEET NO. E11EU Revision 4" (PDF). Retrieved .
  3. ^ a b Christy, Joe: Engines for Homebuilt Aircraft & Ultralights, pages 58-59. TAB Books, 1983. ISBN 0-8306-2347-7
  4. ^ a b Shanaberger, Kenneth (2008). "Continental O-240". Archived from the original on 2008-10-10. Retrieved .
  5. ^ Gunston 1989, p.42.


  • Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9

  This article uses material from the Wikipedia page available here. It is released under the Creative Commons Attribution-Share-Alike License 3.0.



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