Lycoming O 340

Design and development

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.

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.

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.

Variants

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.

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.

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.

Applications

Brantly B-2 and B-2A helicopter

Cessna 170 (modified under STC)

Oakland Super V

Piper Apache (modified under STC)

TEMCO-Riley D-16A Twin Navion

Specifications (O-340-A1A)

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

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

Power output: 170 hp (127 kW) at 2700 rpm

Specific power: 0.50 hp/in³ (22.7 kW/L)

Compression ratio: 8.5:1

Power-to-weight ratio: 0.68hp/lb (1.11 kW/kg)