List of Lycoming O-360 variants - Engine

avia.wikisort.org - Engine

This is a list of the variants of the Lycoming O-360 aircraft engine. There are 167 different models within the O-360 family of engines, with 12 different prefixes.

Variants

O-360

O-360-A1A: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. The base model. A four-cylinder, horizontally opposed, air-cooled, direct-drive engine which includes provisions for supplying oil through the propeller shaft for installation of a single-acting controllable-pitch propeller. First certified 20 July 1955.[1][2]
O-360-A1AD: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1A except it is equipped with a Bendix D4LN-2021 dual magneto instead of two single magnetos.[1][2]
O-360-A1C: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1A except with a rear-mounted Bendix carburetor and 200 series magnetos.[1][2]
O-360-A1D: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1A except with Bendix 200 series magnetos.[1][2]
O-360-A1F: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1A except with Bendix 1200 impulse coupling, high altitude magnetos.[1][2]
O-360-A1F6: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1F except with counter-weighted crankshaft.[1][2]

O-360-A1F6D: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1F6 except that it is equipped with one Bendix D4LN-2021 impulse coupling dual magneto instead of incorporating two single magneto.[1][2]
O-360-A1G: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1F except with a horizontal carburetor.[1][2]
O-360-A1G6: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1G except has a crankshaft that is equipped with counterweights.[1][2]

The Beechcraft Duchess uses one 180 hp (130 kW) O-360-A1G6D on the left wing and one LO-360-A1G6D on the right wing.

O-360-A1G6D: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1G6 except that it is equipped with a Bendix D4LN-2021 magneto in place of two single magnetos.[1][2]
O-360-A1H: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1G except its crankcase has a propeller governor drive mounted on the left front instead of on the engine accessory housing.[1][2]
O-360-A1H6: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1H except that it has a crankshaft equipped with 6.3 and 8th order pendulum counterweights and it uses Slick magnetos.[1][2]
O-360-A1LD: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1A except that it is equipped with one Bendix D4LN-2021 impulse coupling dual magneto instead of two single magnetos.[1][2]
O-360-A1P: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the C1G except that it has dynafocal engine mounts.[1][2]
O-360-A2A: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1A except that it has no provisions for a controllable-pitch propeller.[1][2]

O-360-A2D: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1D except that it has no provisions for a controllable-pitch propeller.[1][2]
O-360-A2E: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A2D but it is equipped with an AN-type fuel pump drive.[1][2]
O-360-A2F: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1F except has that it has no provisions for a controllable-pitch propeller.[1][2]
O-360-A2G: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1G but it has no provision for a controllable-pitch propeller.[1][2]
O-360-A2H: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1H except does not have propeller governor drive installed.[1][2]

O-360-A3A: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A2A except that it has six special length bushings in propeller flange.[1][2]
O-360-A3AD: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A3A except that it is equipped with a Bendix D4LN-2021 dual magneto instead of Bendix S4LN-21 and S4LN-20 magnetos.[1][2]
O-360-A3D: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A2D except that it has special long propeller attaching bushings for use with Sensenich fixed-pitch propellers.[1][2]

O-360-A4A: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A3A except has stiffer crankshaft.[1][2]
O-360-A4AD: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A4A except is equipped with a Bendix D4LN-2021 impulse coupling dual magneto instead of two single magnetos.[1][2]
O-360-A4D: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A4A except that it has a Bendix S4LN-200 retard breaker and S4LN-204 magnetos.[1][2]
O-360-A4G: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A2G except that it has a stiffer crankshaft and solid main bearing journals.[1][2]
O-360-A4J: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A4G except that it has different magnetos.[1][2]
O-360-A4K: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A4J except that it has Slick 4051 and 4050 magnetos instead of Bendix S4LN-21 and S4LN-204 magnetos.[1][2]
O-360-A4M: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A4A but with Slick 4051 and 4050 magnetos instead of Bendix S4LN-21 and S4LN-204 magnetos.[1][2]
O-360-A4N: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A4M except that it has a non-machined propeller governor pad on left front of crankcase.[1][2]
O-360-A4P: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A4M except that it has short propeller flange bushings.[1][2]
O-360-A5AD: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A4AD except that it has six standard length propeller flange bushings instead of six special length bushings.[1][2]

O-360-B1A: 168 hp (125 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.20:1. Same as the A1A except that it has a lower compression ratio and power rating.[1]
O-360-B1B: 168 hp (125 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.20:1. Same as the B1A except has Bendix 200 series magnetos.[1]
O-360-B2A: 168 hp (125 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.20:1. Same as the B1A except has no provisions for controllable-pitch propeller.[1]
O-360-B2B: 168 hp (125 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.20:1. Same as the B1B except that it has no provisions for controllable-pitch propeller.[1]
O-360-B2C: 168 hp (125 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.20:1. Same as the B2A except that it has heavier IO-360-A crankshaft and rods.[1]

O-360-C1A: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1A except that it has its crankcase machined for conical rubber mount bushings in place of dynafocal mountings.[1][2]
O-360-C1C: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the C1A except with Bendix 200 series magnetos.[1][2]
O-360-C1E: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the C1A except that it is equipped with Slick 4051 and 4050 magnetos instead of Bendix S4LN-21 and S4LN-204 magnetos.[1][2]
O-360-C1F: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1G except that it has Slick 4050 and 4051 magnetos and a rear-type engine mounting instead of dynafocal type mount.[1][2]
O-360-C1G: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the C1A except that the propeller governor drive is located on the left-front of the crankcase, the same as on the O-360-A1H.[1][2]
O-360-C2A: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the C1A except that it has no provision for controllable-pitch propeller.[1][2]
O-360-C2B: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the C2A except that it has a rear-mounted Bendix carburetor.[1][2]
O-360-C2C: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the C2A except that it has Bendix 200 series magnetos.[1][2]
O-360-C2D: 180 hp (134 kW) at 2900 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the C2B except has Bendix 200 series magnetos. First certified.[1][2]
O-360-C2E: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the C2A except that it is equipped with Slick 4051 and 4050 magnetos instead of Bendix S4LN-21 and S4LN-20 magnetos.[1][2]
O-360-C4F: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the C1F except has a solid crankshaft and no provision for a prop governor.[1][2]
O-360-C4P: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A4M except has short propeller flange bushings and conical engine mounts.[1][2]

O-360-D1A: 168 hp (125 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.20:1. Same as the B1A except that it has a crankcase machined for conical rubber mount bushings in place of dynafocal mountings.[1]
O-360-D2A: 168 hp (125 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.20:1. Same as the B2A except that it has a crankcase machined for conical rubber mount bushings in place of dynafocal mountings.[1]
O-360-D2B: 168 hp (125 kW) at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.20:1. Same as the D2A except has Bendix 200 series magnetos.[1]

O-360-E1AD: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 9.00:1. Similar to the A1A except that it has a crankcase with an integral accessory section, front-mounted fuel pump, external mounted oil pump, automatic valve tappets and rocker arms and also a dual magneto.[1]
O-360-E1A6D: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 9.00:1. same as the E1AD except that it is equipped with one 6.3 order and one 8th order counterweight.[1]
O-360-E2AD: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 9.00:1. Similar to the E1AD except without provision for controllable-pitch propeller.[1]
O-360-E1BD: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 9.00:1. Similar to the E1AD except with Bendix D4RN-2200 retard breaker magnetos in place of the Bendix D4RN-2021 impulse coupling magneto.[1]
O-360-E2BD: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 9.00:1. Similar to the E1BD except without provision for controllable-pitch propeller.[1]
O-360-F1A6: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1G6 except that it has two Slick 4191 magnetos, a propeller governor drive on the crankcase left front and oil sump designed for retracted nose wheel clearance.[1][2]
O-360-G1A6: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the F1A6 except that it has a machined pad on the right front of the crankcase for installation equipment.[1][2]

Robinson R22 Beta II with Lycoming O-360-J2A engine.

O-360-J2A: 145 hp (108 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the C1C except has O-320-B2C prop flange bushings, lightweight cylinders and lower power rating for helicopter use.[1][2] This engine is used in the Robinson R22 helicopter.

HO-360

HO-360-A1A: 180 hp (134 kW) at 2900 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1D but with dynafocal mounts and a different series Marvel carburetor.[1][2]
HO-360-B1A: 180 hp (134 kW) at 2900 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as C2D but with a different cam shaft.[1][2]
HO-360-B1B: 180 hp (134 kW) at 2900 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the B1A but with Bendix 200 series retard breaker magnetos.[1][2]
HO-360-C1A: 180 hp (134 kW) at 2900 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the C2D except that it uses an HA-6 carburetor in place of the PSH-5HD carburetor.[1][2]

LO-360

LO-360-A1G6D: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1G6D except that it has counter-clockwise (reverse) rotation.[1][2]
LO-360-A1H6: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1H except that it has counter-clockwise (reverse) rotation.[1][2]
LO-360-E1AD: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 9.00:1. Similar to the E1AD except has counter-clockwise (reverse) rotation.[1]
LO-360-E1A6D: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 9.00:1. Similar to the E1A6D except has counter-clockwise (reverse) rotation.[1]
LO-360-E2AD: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 9.00:1. Similar to the E2AD except has counter-clockwise (reverse) rotation.[1]
LO-360-E1BD: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 9.00:1. Similar to the E1BD except has counter-clockwise (reverse) rotation.[1]
LO-360-E2BD: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 9.00:1. Similar to the E2AD except has counter-clockwise (reverse) rotation.[1]

TO-360

TO-360-A1A6D: 200 hp (149 kW) at 2575 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.00:1. Turbosupercharger: Rajay 301E10-2. Base model, a four-cylinder air-cooled, horizontally opposed, direct drive, carbureted, turbocharged engine with oil jets internal piston cooling.[3]
TO-360-C1A6D: 210 hp (157 kW) at 2575 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 7.30:1. Turbosupercharger: Rajay 301E10-2. Same as the TO-360-A1A6D but with the power output increased, lower compression ratio and carburetor located after the turbocharger instead of before the turbocharger.[3]
TO-360-E1A6D: 180 hp (134 kW) at 2575 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.00:1. Turbosupercharger: AiResearch TA04. Same as the 0-360-E1A6D but with an AiResearch TA402 turbocharger, 8.00:1 compression ratio pistons, piston cooling oil jets and a high pressure fuel pump.[3]
TO-360-F1A6D: 210 hp (157 kW) at 2575 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 7.30:1. Turbosupercharger: Rajay 301E10-2. Same as the TO-360-C1A6D but with rear type mounting (long type 1.12 inch conical mount).[3]

LTO-360

LTO-360-A1A6D: 200 hp (149 kW) at 2575 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.00:1. Turbosupercharger: Rajay 301E10-2. Same as the TO-360-A1A6D But with counter-clockwise (reverse) rotation.[3]
LTO-360-E1A6D: 180 hp (134 kW) at 2575 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.00:1. Turbosupercharger: AiResearch TA04. Same as the TO-360-E1A6D But with counter-clockwise (reverse) rotation.[3]

IO-360

IO-360-A1A: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. The base fuel-injected model, a four-cylinder air-cooled, horizontally opposed, direct-drive, fuel-injected, tuned induction engine with oil jet internal piston cooling. It includes provision for single-action controllable-pitch propeller.[4]

IO-360-A1B: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A1A but with impulse coupling magnetos.[4]
IO-360-A1B6: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A1B but with a crankshaft that has one 6.3 order and one 8th order counterweights.[4]
IO-360-A1B6D: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A1B6 but with Bendix Series impulse coupling dual magnetos instead of two S-1200 Series magnetos.[4]
IO-360-A1C: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A1A but with Bendix S-1200 series high altitude magnetos.[4]
IO-360-A1D: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A1B but with one S-20 series impulse coupling and one S-200 series magnetos in place of the two S-1200 series magnetos.[4]
IO-360-A1D6: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A1B but with a propeller governor drive located on left front of crankcase in place of on the accessory housing. Incorporates crankshaft equipped with one 6.3 order and one 8th order counterweights.[4]
IO-360-A1D6D: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A1D6 but with a Bendix D4LN-3021 dual magneto.[4]

IO-360-A2A: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A1A but with a modified crankshaft to accept a fixed-pitch propeller.[4]
IO-360-A2B: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A2A but with impulse coupling magnetos.[4]
IO-360-A2C: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A2A but with Bendix S-1200 series high altitude magnetos.[4]
IO-360-A3B6: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A1B6D but with the propeller locating bushings rotated 120° clockwise.[4]
IO-360-A3B6D: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A1B6D but with the propeller locating bushings rotated 120° clockwise.[4]
IO-360-A3D6D: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A1D6D but with the propeller locating bushings rotated 120° clockwise.[4]

IO-360-B1A: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1A but with a Simmonds Type 530 fuel injector and without a tuned induction system.[2][4]
IO-360-B1B: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the B1A but with a Bendix RSA-5AD1 injector. Fuel pressure limit at inlet to diaphragm pump.[2][4]
IO-360-B1C: 177 hp (132 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the HIO-360-B1B externally but with a crankcase machined for No. 1 Dynafocal mounts.[2][4]
IO-360-B1D: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the B1B but with an AN fuel pump drive. Fuel pressure to diaphragm pump does not apply.[2][4]
IO-360-B1E: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the B1B except the oil sumps, induction manifolding and alternate magnetos.[2][4]
IO-360-B1F: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the B1B but with Bendix S 1200 series high altitude magnetos.[2][4]
IO-360-B1F6: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the B1F but with a crankshaft that has one 6.3 and one 8th order counterweights.[2][4]
IO-360-B1G6: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the B1E but with a front-mounted governor, provision for bed mounting and a counterweighted crankshaft.[2][4]

IO-360-B2E: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the B1F but without provisions for a controllable-pitch propeller.[2][4]
IO-360-B2F: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the B1F but with different front crankshaft oil plug, for fixed-pitch propeller.[2][4]
IO-360-B2F6: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the B2F but with a crankshaft with one 6.3 and one 8th order counterweights.[2][4]
IO-360-B4A: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the B1B but has different magnetos and a stiffer crankshaft and solid main bearing journals.[2][4]
IO-360-C1A: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A1A but with a rear-mounted injector.[4]

IO-360-C1B: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the C1A but with Bendix 1200 series magnetos.[4]
IO-360-C1C: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the C1B but with a 14-degree fuel injector inlet adapter and an impulse coupling Bendix S4LN-1227 magneto.[4]
IO-360-C1C6: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the C1C but with a crankshaft with one 6.3 order and one 8th order counterweights.[4]
IO-360-C1D6: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the C1B but with an impulse coupled magneto and a crankshaft equipped with one 6.3 order and one 8th order counterweights.[4]
IO-360-C1E6: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the C1C but with different magnetos. This model also has a propeller governor drive on the left front of its crankcase and has a crankshaft equipped with one 6.3 order and one 8th order counterweight.[4]
IO-360-C1E6D: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the C1E6 but with a Bendix D4LN-2021 impulse coupling dual magneto.[4]
IO-360-C1F: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the C1C but with an AN fuel pump and fuel pump drive.[4]
IO-360-C1G6: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the C1D but with two retard magnetos instead of impulse magnetos, a non-machined front governor pad and provision for front bed mounting.[4]

IO-360-D1A: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the C1B but with Dynafocal mounts.[4]
IO-360-E1A: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the B1E but with a retard magneto in place of an impulse coupling type and has Type 2, eighteen degree Dynafocal mounting brackets instead of Type 1, thirty degree brackets.[2][4]
IO-360-F1A: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.50:1. Same as the B2F but with a crankshaft with one 6.3 and one 8th order counterweights.[4]
IO-360-J1AD: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A1B but with Bendix D4LN-2021 dual magneto and provisions for a rear type engine mounting.[4]
IO-360-J1A6D: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the J1AD except crankshaft incorporates one 6.3 order and one 8th order counterweights.[4]
IO-360-K2A: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A2A except equipped with Bendix S4LN-21-20 magnetos and has provisions for straight conical mounts.[4]
IO-360-L2A: 160 hp (119 kW) at 2400 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the B2F but with a lower power rating.[2][4] An asterisk footnote on Page 3 of the TCDS [4] for the L2A variant states that the "engine has an alternate rating of 180 hp (134 kW) @ 2700 RPM". Used in the Cessna 172R and SP.
IO-360-M1A: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the B1E but with a front inlet fuel injector, propeller governor on front of the crankcase and a retard magneto.[2][4]
IO-360-M1B: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the M1A but with a rear-mounted propeller governor and impulse magneto.[2][4]

LIO-360

LIO-360-C1E6: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the IO-360-C1E6 except that it has counter-clockwise (reverse) rotation for use on twin-engined aircraft.[4]

AIO-360

AIO-360-A1A: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the IO-360-A1A but set up for operation in an inverted position. Differences include a front-mounted propeller governor, two dry oil sumps, dual external oil scavenge pumps, an oil tank, three options of position for fuel injector mounting and provisions for a constant speed propeller.[4]
AIO-360-A1B: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A1A except it uses an impulse coupling magneto.[4]
AIO-360-A2A: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A1A but uses a fixed-pitch propeller.[4]
AIO-360-A2B: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A1A but has one impulse coupling magneto and provision for a fixed-pitch propeller.[4]
AIO-360-B1B: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A1B except with a front-mounted fuel injector.[4]

AEIO-360

AEIO-360-A1A: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the IO-360-A1A but it is equipped with an inverted oil system kit for aerobatic flight.[4]
AEIO-360-A1B: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the IO-360-A1B but it is equipped with an inverted oil system kit for aerobatic flight.[4]
AEIO-360-A1B6: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the IO-360-A1B6 but it is equipped with an inverted oil system kit for aerobatic flight.[4]
AEIO-360-A1C: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the IO-360-A1C but it is equipped with an inverted oil system kit for aerobatic flight.[4]
AEIO-360-A1D: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the IO-360-A1D but it is equipped with an inverted oil system kit for aerobatic flight.[4]

AEIO-360-A1E: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the AEIO-360-A1A but with the propeller governor drive on left front of crankcase and Bendix S4LN-21/-20 magnetos.[4]
AEIO-360-A1E6: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as AEIO-360-A1E but the crankshaft has one 6.3 order and one 8th order counterweights[4]
AEIO-360-A2A: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the IO-360-A2A but with an inverted oil system kit for aerobatic flight.[4]
AEIO-360-A2B: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the IO-360-A2B but with an inverted oil system kit for aerobatic flight.[4]
AEIO-360-A2C: 200 hp (149 kW) at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the IO-360-A2C but with an inverted oil system kit for aerobatic flight.[4]
AEIO-360-B1B: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the IO-360-B1B but with an inverted oil system kit for aerobatic flight.[2][4]
AEIO-360-B1D: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the IO-360-B1D but with an inverted oil system kit for aerobatic flight.[2][4]
AEIO-360-B1F: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the IO-360-B1F but with an inverted oil system kit for aerobatic flight.[2][4]
AEIO-360-B1F6: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the IO-360-B1F6 but with an inverted oil system kit for aerobatic flight.[2][4]
AEIO-360-B1G6: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the AEIO-360-B1F6 except equipped with Slick 4051 and 4050 magnetos.[2][4]
AEIO-360-B2F: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the IO-360-B2F but with an inverted oil system kit for aerobatic flight.[2][4]
AEIO-360-B2F6: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the IO-360-B2F6 but with an inverted oil system kit for aerobatic flight.[2][4]
AEIO-360-B1H: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as AEIO-360-H1B except has Dynafocal mounting.[2][4]
AEIO-360-B4A: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the IO-360-B4B but with an inverted oil system kit for aerobatic flight.[2][4]
AEIO-360-H1A: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the AEIO-360-B1G6 but without counterweights and has provision for commercial (straight) engine mount.[2][4]
AEIO-360-H1B: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the AEIO-360-H1A but with the propeller governor drive on left front of crankcase.[2][4]

HIO-360

HIO-360-A1A: 180 hp (134 kW) at 2900 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the IO-360-A1A except that it has a Bendix RSA-5AB1 fuel injector, Bendix S4LN-200 magnetos and lacks provision for propeller governor drive.[4]
HIO-360-A1B: 180 hp (134 kW) at 2900 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the HIO-360-A1A but with conical mounts, no AMC unit on the fuel injector and a 90° fuel injector mount.[4]
HIO-360-B1A: 180 hp (134 kW) at 2900 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the HIO-360-A1A except for the compression ratio and does not have tuned induction.[2][4]
HIO-360-B1B: 180 hp (134 kW) at 2900 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the HIO-360-B1A except has an AN fuel pump drive.[2][4]
HIO-360-C1A: 205 hp (153 kW) at 2900 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the IO-360-A1A except it has a rear-mounted fuel injector.[4]
HIO-360-C1B: 205 hp (153 kW) at 2900 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the HIO-360-C1A except it incorporates Bendix S-1200 series magnetos.[4]
HIO-360-D1A: 190 hp (142 kW) at 3200 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 10:1. Same as the HIO-360-C1A except incorporates narrow crankpin crankshaft and different fuel injector.[4]
HIO-360-E1AD: 190 hp (142 kW) at 2900 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.00:1. Same as the HIO-360-C1A except with a lower compression ratio piston, equipped with dual magneto and incorporates features suitable for turbocharging. When equipped with the Enstrom Helicopter Corporation turbocharger Kit Number SK-28-121000 or equivalent, these engines are capable of delivering 205 hp (153 kW) at 3000 rpm and a manifold pressure of 36.5 inches Hg absolute.[4]
HIO-360-E1BD: 190 hp (142 kW) at 2900 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.00:1. Same as the HIO-360-E1AD but with a Bendix D4LN-2200 (retard breaker) dual magneto. Eligible for turbosupercharging. When equipped with the Enstrom Helicopter Corporation turbocharger Kit Number SK-28-121000 or equivalent, these engines are capable of delivering 205 hp (153 kW) at 3000 rpm and a manifold pressure of 36.5 inches Hg absolute.[4]
HIO-360-F1AD: 190 hp (142 kW) at 3050 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.00:1. Same as the HIO-360-E1AD but with a large crankshaft, high crush thin wall bearings and a large base circle camshaft. Eligible for turbosupercharging. When equipped with modified Enstrom turbocharger Kit No. SK-28-121000, this engine is capable of delivering 225 hp (168 kW) at 3050 rpm at a manifold pressure of 39 inches Hg to a critical altitude of 12,000 ft (3,658 m).[4]
HIO-360-G1A: 180 hp (134 kW) at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.00:1. Same as the HO-360-C1A but with PAC RSA-5AD1 fuel injection system[2][4]

LHIO-360

LHIO-360-C1A: 205 hp (153 kW) at 2900 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the HIO-360-C1A but with counter-clockwise (reverse) rotation.[4]
LHIO-360-C1B: 205 hp (153 kW) at 2900 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the HIO-360-C1B except with counter-clockwise (reverse) rotation.[4]
LHIO-360-F1AD: 190 hp (142 kW) at 3050 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.00:1. Same as the HIO-360-F1AD but with counter-clockwise (reverse) rotation. Eligible for turbosupercharging. When equipped with modified Enstrom turbocharger Kit No. SK-28-121000, this engine is capable of delivering 225 hp (168 kW) at 3050 rpm at a manifold pressure of 39 inches Hg to a critical altitude of 12,000 ft (3,658 m).[4]

TIO-360

TIO-360-A1A: 200 hp (149 kW) at 2575 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 7.30:1. Turbosupercharger: Bendix RSA-5AD1. Base TIO-360 model: a four-cylinder air-cooled, horizontally opposed direct drive, fuel-injected, tuned induction, turbocharged engine with internal piston cooling oil jets.[6]
TIO-360-A1B: 200 hp (149 kW) at 2575 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 7.30:1. Turbosupercharger: AiResearch T04. Same as the A1A except that it has a straight tubular casting in the induction system and no pressure differential door on 14° down fuel injector adapter.[6]
TIO-360-A3B6: 200 hp (149 kW) at 2575 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 7.30:1. Turbosupercharger: AiResearch T04. Same as the A1B but with one 6.3 order and one 8th order counterweights and a pressurized ignition system for high altitude operation.[6]
TIO-360-C1A6D: 210 hp (157 kW) at 2575 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 7.30:1. Turbosupercharger: Rotomaster 3BT1EE10J2. Same as the T0-360-C1A6D except for a Bendix RSA-5AD1 fuel injector instead of Marvel-Schebler HA-6 carburetor.[6]

References

Federal Aviation Administration (December 2003). "TYPE CERTIFICATE DATA SHEET NO. E-286 Revision 19". Retrieved 17 January 2009.
Lycoming (2010). "Lycoming Service Instruction 1070Q" (PDF). Archived from the original (PDF) on 17 November 2011. Retrieved 3 November 2011.
Federal Aviation Administration (March 1986). "TYPE CERTIFICATE DATA SHEET NO. E26EA Revision 4". Retrieved 18 January 2009.
Federal Aviation Administration (24 May 2012). "TYPE CERTIFICATE DATA SHEET NO. 1E10 Revision 24" (PDF). Retrieved 8 February 2015.
Federal Aviation Administration (February 2007). "Docket No. FAA-2006-25948; Directorate Identifier 2006-NE-32-AD; Amendment 39-14951; AD 2007-04-19". Retrieved 9 March 2009.
Federal Aviation Administration (March 1986). "TYPE CERTIFICATE DATA SHEET NO. E16EA Revision 5". Retrieved 18 January 2009.

v t e Lycoming aircraft engines
Opposed piston engines	O-145 O-233 IO-233 O-235 O-290 O-320 O-340 O-360 (O-360 variants) IO-390 O-435 O-480 O-540 TIO-541 GSO-580 IO-580 IO-720 O-1230
Radial engines and H engines	R-680 XR-7755 XH-2470
Aircraft diesel engines	DEL-120
Turbofans	PLF1 ALF 502/YF102 LF 507
Turboprops/Turboshafts	AGT1500 LTS101/LTP101 T53 T55
Aero-derivative marine gas turbines	TF-40
Joint development	Avco (Lycoming)/Pratt & Whitney: T800-APW (Turboshaft)
See also	AlliedSignal Aerospace/Honeywell Aerospace

Variants

O-360

HO-360

LO-360

TO-360

LTO-360

IO-360

LIO-360

AIO-360

AEIO-360

HIO-360

LHIO-360

TIO-360

See also

References

Further reading