Lycoming O-340

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O-340
Type Piston aero-engine
Manufacturer Lycoming Engines
First run 1954
Major applications TEMCO-Riley D-16A Twin Navion[1]
Brantly B-2[1]

The Lycoming O-340 is a family of four-cylinder horizontally opposed, carburetor-equipped aircraft engines, that was manufactured by Lycoming Engines in the mid-1950s.[2]

Design and development[edit]

The O-340 was designed by Lycoming specifically for the TEMCO-Riley D-16A Twin Navion project. Jack Riley, the designer of that aircraft was interested in an upgraded version of the Lycoming O-320 that would produce more power to give the Twin Navion a better single-engine service ceiling. The Lycoming O-360 was still years away in development and so a modification of the O-320 was undertaken by Lycoming. The O-320 received longer cylinder barrels and a crankshaft with a longer stroke to increase displacement and different piston connecting rods. This increased the compression to 8.5:1 and boosted power output to 170 hp (127 kW) over the O-320's 150 hp (112 kW). The engine was later used in a number of airplanes and helicopters and also in amateur-built aircraft designs.[1]

The O-340 family of engines covers a range from 160 hp (119 kW) to 170 hp (127 kW). All have a displacement of 340.4 cubic inches (5.58 litres) and the cylinders have air-cooled heads.[2]

The O-340 series was certified under Type Certificate E-277 and first approved on 20 July 1954. The engines are approved for both tractor and pusher applications.[2]

Variants[edit]

O-340-A1A
Four-cylinder, horizontally opposed, 340.4 cubic inches (5.58 litres), 170 hp (127 kW) at 2700, dry weight 250 lb (113 kg), Marvel-Schebler MA-4-5 carburetor, Scintilla S4LN-20 and S4LN-21 magneto. Minimum fuel grade 91/96 avgas. Certified on 13 January 1955.[2]
O-340-A2A
Four-cylinder, horizontally opposed, 340.4 cubic inches (5.58 litres), 170 hp (127 kW) at 2700, dry weight 250 lb (113 kg), Marvel-Schebler MA-4-5 carburetor, Scintilla S4LN-20 and S4LN-21 magneto. Minimum fuel grade 91/96 avgas. Identical to the A1A but with no provision for a hydraulic propeller control. Certified on 16 November 1956.[2]
O-340-B1A
Four-cylinder, horizontally opposed, 340.4 cubic inches (5.58 litres), 160 hp (119 kW) at 2700, dry weight 247 lb (112 kg), Marvel-Schebler MA-4-5 carburetor, Scintilla S4LN-20 and S4LN-21 magneto. Minimum fuel grade 80/87 avgas. Identical to the A1A except with a reduced 7.15:1 compression ratio and 160 hp to run on 80/87 fuel. Certified on 20 July 1954. The O-340-B1A was originally certified as just the "O-340", but the designation was changed to "O-340-B1A" on 27 September 1956.[2]

Applications[edit]

Specifications (O-340-A1A)[edit]

Data from TYPE CERTIFICATE DATA SHEET NO. E-277, Revision 5[2]

General characteristics

  • Type: 4-cylinder horizontally opposed, aircraft engine
  • Bore: 5.125 in (130 mm)
  • Stroke: 4.125 (105 mm)
  • Displacement: 340.4 in³ (5.58 litres)
  • Dry weight: 250 lb (113 kg) dry

Components

  • Fuel type: 91/96 avgas minimum
  • Cooling system: air-cooled

Performance

See also[edit]

Related lists

References[edit]

  1. ^ a b c d e f g h twinnavion.com (n.d.). "An O-340? What's that?". Retrieved 2009-04-19. 
  2. ^ a b c d e f g Federal Aviation Administration (April 1963). "TYPE CERTIFICATE DATA SHEET NO. E-277, Revision 5". Retrieved 2009-04-19.