Lycoming IO-390
| IO-390 | |
|---|---|
| 300px | |
| Type | Piston aero-engine |
| Manufacturer | Lycoming Engines |
| First run | 2002 |
| Major applications | Amateur-built aircraft |
The Lycoming IO-390 engine is a horizontally opposed, four-cylinder aircraft engine, manufactured by Lycoming Engines.[1][2]
There is no carburetted version of the engine, which would have been designated O-390 and therefore the base model is the IO-390.[1][2]
Contents
Design and development
The engine was originally conceived in the 1970s as the IO-400-X, but the project was never pursued.[3]
The IO-390 family of engines, which Lycoming refers to as the IO-390-X, produce 200 hp (149 kW) to 210 hp (157 kW). The IO-390 was developed from the similar IO-360 engine, by using cylinders from the IO-580 to increase the O-360's cylinder bore. It features a tuned induction system, roller tappets and Slick Start ignition. The engine has a fuel injection system which meters fuel in proportion to the induction airflow with fuel vaporization taking place at the intake ports. The engine has a displacement of 390 cubic inches (6.39 litres). The cylinders have air-cooled heads.[1][2][3]
The IO-390 was first introduced at AirVenture 2002. It has a factory recommended TBO of 2000 hours and requires a dynafocal engine mount.[2][3]
The IO-390 was initially marketed through Lycoming's custom engine subsidiary, Thunderbolt Engines, prior to the engine's certification and was at that time only available for installation on non-certified aircraft. The IO-390 was certified on 30 March 2009 to FAR 33 effective February 1, 1965, as amended by 33-1 through 33-24.[1][2][3][4]
In January 2009 the base price of the IO-390-EXP version was USD$32,650.00.[5]
In November 2009 Lycoming announced that it had obtained an FAA Supplemental Type Certificate to replace the originally fitted Lycoming O-360 engines in the Mooney M20E, M20F and M20J with a new or remanufactured IO-390-A3A6 engine.[6] Also on November 12, 2009 Commander Aircraft received an STC for its model 112B using the MTV-12-B/188-59b propeller.[7]
Variants
- IO-390-X
- Four-cylinder, fuel-injected, horizontally opposed, air-cooled direct drive, 390 cubic inches (6.39 litres), 210 hp (157 kW) at 2700 rpm, dry weight 308 lb (140 kg), The "X" designation is a generic indicator for all engines in the family.[1][2]
- IO-390-EXP
- Four-cylinder, fuel-injected, horizontally opposed, air-cooled direct drive, 390 cubic inches (6.39 litres), 210 hp (157 kW) at 2700 rpm, dry weight 308 lb (140 kg), non-certified engine for experimental aircraft assembled by Lycoming's Thunderbolt division.[5]
- IO-390-A1A6
- The initial certified version: four-cylinder, fuel-injected, horizontally opposed, air-cooled direct drive, 390 cubic inches (6.39 litres), 210 hp (157 kW) at 2700 rpm. This model includes provisions for a single-action controllable-pitch propeller. Certified 30 March 2009.[3][4]
- IO-390-A3A6
- Certified version: four-cylinder, fuel-injected, horizontally opposed, air-cooled direct drive, 390 cubic inches (6.39 litres), 210 hp (157 kW) at 2700 rpm. This model includes provisions for a single-action controllable-pitch propeller. This model is similar to the A1A6 but has its propeller flange bushings reindexed. Certified 27 August 2009.[8]
- HIO-390
- Developed for use on helicopters such as the Enstrom TH180.[citation needed]
Applications
- Amateur-built aircraft
- Glasair Sportsman[3]
- Ibis GS-750 Grand Magic
- Lancair ES[3]
- MSW Votec 221
- Pipistrel Panthera
- Van's Aircraft RV-7[3]
- Van's Aircraft RV-8[3]
- Van's Aircraft RV-14
- Certified aircraft
- Cessna 177RG - available in July 2009 under an STC[3][9][10]
- Mooney M20 E, F & J - available in November 2009 under an STC[3][6][10]
- Piper PA-28R Arrow - proposed under STC[3]
- Symphony SA-160 - proposed as a factory installed 200 hp (149 kW) version, but aircraft no longer in production[11]
- Military Aircraft
Specifications (IO-390-X)
Data from Lycoming Specialty Datasheet[2] & Type Certificate Data Sheet[4]
General characteristics
- Type: 4-cylinder fuel-injected horizontally opposed aircraft engine
- Bore: 5.319 in (135.1 mm)
- Stroke: 4.375 in (111.1 mm)
- Displacement: 389 cu in (6.37 L)
- Length: 30.70 in (780 mm)
- Width: 34.25 in (870 mm)
- Height: 19.35 in (491 mm)
- Dry weight: 308 lb (139.71 kg) dry
Components
- Fuel system: fuel-injection
- Fuel type: 100LL avgas
- Cooling system: air-cooled
Performance
- Power output: 210 hp (160 kW) at 2700 rpm
- Specific power: 0.54 hp/in³ (26.0 kW/L)
- Compression ratio: 8.70:1
- Fuel consumption: 11.1 gallons per hour (42 liters per hour; 9.2 imperial gallons per hour) at 65 percent power
- Power-to-weight ratio: 0.68 hp/lb (1.12 kW/kg)
See also
References
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