Lycoming O-290

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O-290
Type Piston aircraft engine
Manufacturer Lycoming Engines
First run 1939
Major applications Aero Commander 100
Taylorcraft Auster V
Piper PA-20 Pacer
Seibel S-4
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.

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[edit]

Civil models[edit]

O-290
Base model engine certified 27 July 1942. 125 hp (93 kW) at 2450 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 2600 rpm continuous, 130 hp (97 kW) at 2800 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 2600 rpm continuous, 130 hp (97 kW) at 2800 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 2600 rpm continuous, 130 hp (97 kW) at 2800 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 2600 rpm continuous, 130 hp (97 kW) at 2800 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 2600 rpm continuous, 130 hp (97 kW) at 2800 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 2600 rpm continuous, 130 hp (97 kW) at 2800 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 2600 rpm continuous, 140 hp (104 kW) at 2800 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 2600 rpm continuous, 140 hp (104 kW) at 2800 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 2600 rpm continuous, 140 hp (104 kW) at 2800 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 2600 rpm continuous, 140 hp (104 kW) at 2800 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[edit]

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[edit]

Specifications (O-290-D2A)[edit]

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

General characteristics

  • Type: 4-cylinder air-cooled horizontally opposed piston aircraft engine
  • Bore: 4.875 in (124 mm)
  • Stroke: 3.875 in (98 mm)
  • Displacement: 289 cu in (4.74 L)
  • Dry weight: 264 lbs (119.7 kg)

Components

Performance

See also[edit]

Related lists

References[edit]

  1. ^ a b c d e f g h i j k l m n Federal Aviation Administration (June 1963). "Type Certificate Data Sheet NO. E-229". 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.
  • Gunston, Bill (1986). World Encyclopedia of Aero Engines. Wellingborough: Patrick Stephens.