This article is about the 1997 era fuel-injected, six-cylinder aircraft engine series. For the 1959 eight-cylinder, geared, supercharged engine, see Lycoming GSO-580.
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.[4]
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.[1][5]
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.[2]
Variants
IO-580-A1A
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[2]
IO-580-B1A
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[2]
AEIO-580-B1A
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.[2]
^Found Aircraft (n.d.). . Archived from the original on 2009-02-27. Retrieved 2009-01-03.
January 17, 2023
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This article is about the 1997 era fuel injected six cylinder aircraft engine series For the 1959 eight cylinder geared supercharged engine see Lycoming GSO 580 The Lycoming IO 580 engine is a horizontally opposed six cylinder aircraft engine featuring three cylinders per side manufactured by Lycoming Engines 1 IO 580Lycoming AEIO 580 installed in an Extra 330LCType Piston aero engineNational origin United StatesManufacturer Lycoming EnginesFirst run 1996Major applications Extra 330 Expedition E350 XtremeAir Sbach 342Produced 1997 presentDeveloped into Lycoming IO 390There is no carburetted version of the engine which would have been designated O 580 and therefore the base model is the IO 580 2 This engine family competes with the Continental IO 550 series which are also six cylinder engines with similar power output and weight 3 Contents 1 Design and development 2 Variants 3 Applications 4 Specifications IO 580 A1A 4 1 General characteristics 4 2 Components 4 3 Performance 5 See also 6 ReferencesDesign and development EditThe 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 4 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 1 5 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 2 Variants EditIO 580 A1A 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 2 IO 580 B1A 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 2 AEIO 580 B1A 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 2 Applications EditBearhawk 5 Cessna NGP MSW Votec 252T Rockwell Super CommanderIO 580 B1AExpedition E350 factory installation 6 Evektor VUT100 131i SuperCobraAEIO 580 B1AExtra 330 Game Composites GB1 GameBird XtremeAir Sbach 342 XA 42 XtremeAir XA41Specifications IO 580 A1A EditData from Lycoming Specialty Datasheet and Type Certificate Data Sheet No E00004NY Revision 1 2 5 General characteristics 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 dryComponents Fuel system PAC RSA 10ED1 fuel injection Fuel type 100LL avgas Cooling system air cooledPerformance Power output 300 hp 220 kW at 2500 rpm Specific power 0 51 hp in 24 7 kW L Compression ratio 8 90 1 Power to weight ratio 0 68 hp lb 1 12 kW kg See also EditRelated development Lycoming GSO 580Comparable engines Continental IO 550Related lists List of aircraft enginesReferences Edit Wikimedia Commons has media related to Lycoming IO 580 a b Lycoming Engines n d Lycoming IO 580 Retrieved 2009 01 03 a b c d e f 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 a b Lycoming Engines 2004 Specialty datasheet PDF Retrieved 2008 12 20 Found Aircraft n d SPECIFICATIONS FOR THE STANDARD EXPEDITION E350 Archived from the original on 2009 02 27 Retrieved 2009 01 03 Retrieved from https en wikipedia org w index php title Lycoming IO 580 amp oldid 1126141370, wikipedia, wiki, book, books, library,
