Lycoming O-290

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O-290
Motore aeronautico - Museo scienza tecnologia Milano D0978.jpg
Type Piston aircraft engine
National origin United States
Manufacturer Lycoming Engines
First run1939
Major applications Taylorcraft Auster IV
Taylorcraft Auster V
Ground Power Unit
Produced1942–1975 out of production
Developed into Lycoming O-435

The Lycoming O-290 is a dual-ignition, four-cylinder, air-cooled, horizontally opposed aircraft engine. It was first run in 1939, and entered production three years later.

Contents

A common variant of the type is the O-290-G, a single-ignition model which was designed to drive a generator as part of a ground power unit.

Variants

Civil models

O-290
Base model engine certified 27 July 1942. 125 hp (93 kW) at 2,450 rpm, 6.25:1 compression ratio, dry weight 244 lb (111 kg) [1]
O-290-A
Certified 27 July 1942. 125 hp (93 kW) at 2,600 rpm continuous, 130 hp (97 kW) at 2,800 rpm for 5 minutes, 6.5:1 compression ratio, dry weight 251 lb (114 kg) with SR4L-8 or N-8 magnetos, 245 lb (111 kg) with N-20 or N-21 magnetos. [1]
O-290-AP
Certified 21 July 1944. 125 hp (93 kW) at 2,600 rpm continuous, 130 hp (97 kW) at 2,800 rpm for 5 minutes, 6.5:1 compression ratio, dry weight 251 lb (114 kg) with SR4L-8 or N-8 magnetos, 245 lb (111 kg) with N-20 or N-21 magnetos. [1]
O-290-B
Certified 22 January 1943. 125 hp (93 kW) at 2,600 rpm continuous, 130 hp (97 kW) at 2,800 rpm for 5 minutes, 6.5:1 compression ratio, dry weight 247 lb (112 kg). [1]
O-290-C
Certified 22 January 1943. 125 hp (93 kW) at 2,600 rpm continuous, 130 hp (97 kW) at 2,800 rpm for 5 minutes, 6.5:1 compression ratio, dry weight 238 lb (108 kg). [1]
O-290-CP
Certified 21 July 1944. 125 hp (93 kW) at 2,600 rpm continuous, 130 hp (97 kW) at 2,800 rpm for 5 minutes, 6.5:1 compression ratio, dry weight 238 lb (108 kg). [1]
O-290-D
Certified 13 December 1949. 125 hp (93 kW) at 2,600 rpm continuous, 130 hp (97 kW) at 2,800 rpm for 5 minutes, 6.5:1 compression ratio, dry weight 230 lb (104 kg). [1]
O-290-D2
Certified 1 May 1952. 135 hp (101 kW) at 2,600 rpm continuous, 140 hp (104 kW) at 2,800 rpm for 5 minutes, 7.5:1 compression ratio, dry weight 233 lb (106 kg). [1]
O-290-D2A
Certified 20 April 1953. 135 hp (101 kW) at 2,600 rpm continuous, 140 hp (104 kW) at 2,800 rpm for 5 minutes, 7.5:1 compression ratio, dry weight 236 lb (107 kg). [1]
O-290-D2B
Certified 30 September 1954. 135 hp (101 kW) at 2,600 rpm continuous, 140 hp (104 kW) at 2,800 rpm for 5 minutes, 7.0:1 compression ratio, dry weight 236 lb (107 kg). [1]
O-290-D2C
Certified 8 May 1961. 135 hp (101 kW) at 2,600 rpm continuous, 140 hp (104 kW) at 2,800 rpm for 5 minutes, 7.0:1 compression ratio, dry weight 235 lb (107 kg). [1]
O-290-G
Non-certified, single ignition model intended for use driving a generator in a ground power unit, 125 hp (93 kW). Has been widely used in homebuilt aircraft, including the prototype Van's Aircraft RV-3. [2]

Military models

O-290-1
Identical to the O-290-B [1]
O-290-3
Identical to the O-290-C [1]
O-290-11
Identical to the O-290-D [1]

Applications

Specifications (O-290-D2A)

Data fromOperator's Manual, Textron Lycoming Aircraft Engines. [3]

General characteristics

Components

Performance

See also

Comparable engines

Related lists

References

  1. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Federal Aviation Administration (June 1963). "Type Certificate Data Sheet NO. E-229" (PDF). Retrieved 7 September 2010.
  2. ↑ EAA AirVenture Museum (2010). "Van Grunsven RV-3 Prototype – Specifications" . Retrieved 7 September 2010.
  3. ↑ Operator's Manual, Textron Lycoming Aircraft Engines, Series O-235 & O-290 60297-9, 4th Edition January 1988, Pages 2-2 & 2-4, Textron Lycoming.
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