|Lycoming AEIO-580 installed in an Extra 330LC|
|Type||Piston aero engine|
|National origin||United States|
|Major applications||Extra 330 |
XtremeAir Sbach 342
|Developed into||Lycoming IO-390|
Design and development
The IO-580 had originally been developed at the behest of Cessna, who were looking for a modern engine to power their Cessna 206 Stationair. Development was slow, and the aircraft was delayed to wait for the engine. When production began, Cessna found problems with the cylinders, and instead of further delaying the introduction, they moved the 206 to the older and less powerful 260 hp Lycoming IO-540. Lycoming eventually addressed all of the problems, and the engine found some use in various aerobatic aircraft, but no serious production was undertaken.
The IO-580 family of engines covers a range from 300 to 315 hp (224 to 235 kW). The engine has a fuel injection system which meters fuel in proportion to the induction airflow through air-bled nozzles at the individual cylinder intake ports. The engine has a displacement of 583 cubic inches (9.554 litres) and produces a maximum of 315 hp (235 kW) in its B1A version. The cylinders have air-cooled heads cast from aluminum-alloy with a fully machined combustion chamber.
The first IO-580 was type certified on 12 August 1997 on the regulatory basis of FAR 33 effective February 1, 1965 as amended to 33-1 through 33-18. The engine is certified for use in either tractor or pusher configuration installations.
- Six-cylinder, horizontally opposed, air-cooled direct drive, 583 cubic inches (9.55 litres), 300 hp (224 kW) at 2500 rpm, dry weight 444 lb (201 kg), PAC-RSA-10ED1 fuel-injection system, certified 12 August 1997
- Six-cylinder, horizontally opposed, air-cooled direct drive, 583 cubic inches (9.55 litres), 315 hp (235 kW) at 2700 rpm, dry weight 434 lb (197 kg), PAC-RSA-10ED1 fuel-injection system, certified 23 March 2001
- Six-cylinder, horizontally opposed, air-cooled direct drive, 583 cubic inches (9.55 litres), 315 hp (235 kW) at 2700 rpm, dry weight 446 lb (202 kg), certified 13 August 2007. This model has an aerobatic fuel and oil system. It may be equipped with either the PAC-RSA-10ED1 fuel-injection system or a Lycoming FM-250 system.
- Type: 6-cylinder fuel-injected horizontally opposed aircraft engine
- Bore: 5.319 in (135.1 mm)
- Stroke: 4.375 in (111.1 mm)
- Displacement: 583 in3 (9.55 L)
- Length: 39.34 in (999 mm)
- Width: 34.25 in (870 mm)
- Height: 21.04 in (534 mm)
- Dry weight: 444 lb (201 kg) dry
- Fuel system: PAC-RSA-10ED1 fuel-injection
- Fuel type: 100LL avgas
- Cooling system: air-cooled
- Power output: 300 hp (220 kW) at 2500 rpm
- Specific power: 0.51 hp/in³ (24.7 kW/L)
- Compression ratio: 8.90:1
- Power-to-weight ratio: 0.68 hp/lb (1.12 kW/kg)
|Wikimedia Commons has media related to Lycoming IO-580.|
- Lycoming Engines (n.d.). "Lycoming IO-580". Retrieved 2009-01-03.
- Federal Aviation Administration (August 2007). "TYPE CERTIFICATE DATA SHEET NO. E00004NY, Revision 1". Retrieved 2009-01-03.
- Federal Aviation Administration (March 2007). "TYPE CERTIFICATE DATA SHEET NO. E3SO Revision 10". Retrieved 2008-12-28.
- Goyer, Robert (12 April 2007). "New Power to the Commander". AOPA.
- Lycoming Engines (2004). "Specialty datasheet" (PDF). Retrieved 2008-12-20.
- Found Aircraft (n.d.). "SPECIFICATIONS FOR THE STANDARD EXPEDITION E350". Retrieved 2009-01-03.