List of Lycoming O-360 variants explained

See main article: Lycoming O-360. 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
  • 1800NaN0 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
  • 1800NaN0 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.
    O-360-A1C
  • 1800NaN0 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.
    O-360-A1D
  • 1800NaN0 at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1A except with Bendix 200 series magnetos.
    O-360-A1F
  • 1800NaN0 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.
    O-360-A1F6
  • 1800NaN0 at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1F except with counter-weighted crankshaft.
    O-360-A1F6D
  • 1800NaN0 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.
    O-360-A1G
  • 1800NaN0 at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A1F except with a horizontal carburetor.
    O-360-A1G6
  • 1800NaN0 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.
    O-360-A1G6D
  • 1800NaN0 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.
    O-360-A1H
  • 1800NaN0 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.
    O-360-A1H6
  • 1800NaN0 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.
    O-360-A1LD
  • 1800NaN0 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.
    O-360-A1P
  • 1800NaN0 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.
    O-360-A2A
  • 1800NaN0 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.
    O-360-A2D
  • 1800NaN0 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.
    O-360-A2E
  • 1800NaN0 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.
    O-360-A2F
  • 1800NaN0 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.
    O-360-A2G
  • 1800NaN0 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.
    O-360-A2H
  • 1800NaN0 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.
    O-360-A3A
  • 1800NaN0 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.
    O-360-A3AD
  • 1800NaN0 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.
    O-360-A3D
  • 1800NaN0 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.
    O-360-A4A
  • 1800NaN0 at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A3A except has stiffer crankshaft.
    O-360-A4AD
  • 1800NaN0 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.
    O-360-A4D
  • 1800NaN0 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.
    O-360-A4G
  • 1800NaN0 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.
    O-360-A4J
  • 1800NaN0 at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the A4G except that it has different magnetos.
    O-360-A4K
  • 1800NaN0 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.
    O-360-A4M
  • 1800NaN0 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.
    O-360-A4N
  • 1800NaN0 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.
    O-360-A4P
  • 1800NaN0 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.
    O-360-A5AD
  • 1800NaN0 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.
    O-360-B1A
  • 1680NaN0 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.
    O-360-B1B
  • 1680NaN0 at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.20:1. Same as the B1A except has Bendix 200 series magnetos.
    O-360-B2A
  • 1680NaN0 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.
    O-360-B2B
  • 1680NaN0 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.
    O-360-B2C
  • 1680NaN0 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.
    O-360-C1A
  • 1800NaN0 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.
    O-360-C1C
  • 1800NaN0 at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the C1A except with Bendix 200 series magnetos.
    O-360-C1E
  • 1800NaN0 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.
    O-360-C1F
  • 1800NaN0 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.
    O-360-C1G
  • 1800NaN0 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.
    O-360-C2A
  • 1800NaN0 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.
    O-360-C2B
  • 1800NaN0 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.
    O-360-C2C
  • 1800NaN0 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.
    O-360-C2D
  • 1800NaN0 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.
    O-360-C2E
  • 1800NaN0 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.
    O-360-C4F
  • 1800NaN0 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.
    O-360-C4P
  • 1800NaN0 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.
    O-360-D1A
  • 1680NaN0 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.
    O-360-D2A
  • 1680NaN0 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.
    O-360-D2B
  • 1680NaN0 at 2700 rpm, Minimum fuel grade 80/87 avgas, compression ratio 7.20:1. Same as the D2A except has Bendix 200 series magnetos.
    O-360-E1AD
  • 1800NaN0 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.
    O-360-E1A6D
  • 1800NaN0 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.
    O-360-E2AD
  • 1800NaN0 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.
    O-360-E1BD
  • 1800NaN0 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.
    O-360-E2BD
  • 1800NaN0 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.
    O-360-F1A6
  • 1800NaN0 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.
    O-360-G1A6
  • 1800NaN0 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.
    O-360-J2A
  • 1450NaN0 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. This engine is used in the Robinson R22 helicopter.

    HO-360

    HO-360-A1A
  • 1800NaN0 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.
    HO-360-B1A
  • 1800NaN0 at 2900 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as C2D but with a different cam shaft.
    HO-360-B1B
  • 1800NaN0 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.
    HO-360-C1A
  • 1800NaN0 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.

    LO-360

    LO-360-A1G6D
  • 1800NaN0 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.
    LO-360-A1H6
  • 1800NaN0 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.
    LO-360-E1AD
  • 1800NaN0 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.
    LO-360-E1A6D
  • 1800NaN0 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.
    LO-360-E2AD
  • 1800NaN0 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.
    LO-360-E1BD
  • 1800NaN0 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.
    LO-360-E2BD
  • 1800NaN0 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.

    TO-360

    TO-360-A1A6D
  • 2000NaN0 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
  • 2100NaN0 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.
    TO-360-E1A6D
  • 1800NaN0 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.
    TO-360-F1A6D
  • 2100NaN0 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).

    LTO-360

    LTO-360-A1A6D
  • 2000NaN0 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.
    LTO-360-E1A6D
  • 1800NaN0 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.

    IO-360

    IO-360-A1A
  • 2000NaN0 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
  • 2000NaN0 at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A1A but with impulse coupling magnetos.
    IO-360-A1B6
  • 2000NaN0 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.
    IO-360-A1B6D
  • 2000NaN0 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.
    IO-360-A1C
  • 2000NaN0 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.
    IO-360-A1D
  • 2000NaN0 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.
    IO-360-A1D6
  • 2000NaN0 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.
    IO-360-A1D6D
  • 2000NaN0 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.
    IO-360-A2A
  • 2000NaN0 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.
    IO-360-A2B
  • 2000NaN0 at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the A2A but with impulse coupling magnetos.
    IO-360-A2C
  • 2000NaN0 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.
    IO-360-A3B6
  • 2000NaN0 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.
    IO-360-A3B6D
  • 2000NaN0 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.
    IO-360-A3D6D
  • 2000NaN0 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.
    IO-360-B1A
  • 1800NaN0 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.
    IO-360-B1B
  • 1800NaN0 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.
    IO-360-B1C
  • 1770NaN0 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.
    IO-360-B1D
  • 1800NaN0 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.
    IO-360-B1E
  • 1800NaN0 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.
    IO-360-B1F
  • 1800NaN0 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.
    IO-360-B1F6
  • 1800NaN0 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.
    IO-360-B1G6
  • 1800NaN0 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.
    IO-360-B2E
  • 1800NaN0 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.
    IO-360-B2F
  • 1800NaN0 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.
    IO-360-B2F6
  • 1800NaN0 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.
    IO-360-B4A
  • 1800NaN0 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.
    IO-360-C1A
  • 2000NaN0 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.
    IO-360-C1B
  • 2000NaN0 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.
    IO-360-C1C
  • 2000NaN0 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.
    IO-360-C1C6
  • 2000NaN0 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.
    IO-360-C1D6
  • 2000NaN0 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.
    IO-360-C1E6
  • 2000NaN0 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.
    IO-360-C1E6D
  • 2000NaN0 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.
    IO-360-C1F
  • 2000NaN0 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.
    IO-360-C1G6
  • 2000NaN0 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.
    IO-360-D1A
  • 2000NaN0 at 2700 rpm, Minimum fuel grade 100 or 100LL avgas, compression ratio 8.70:1. Same as the C1B but with Dynafocal mounts.
    IO-360-E1A
  • 1800NaN0 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.
    IO-360-F1A
  • 1800NaN0 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.
    IO-360-J1AD
  • 2000NaN0 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.
    IO-360-J1A6D
  • 2000NaN0 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.
    IO-360-K2A
  • 2000NaN0 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.
    IO-360-L2A
  • 1600NaN0 at 2400 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as the B2F but with a lower power rating. An asterisk footnote on Page 3 of the TCDS for the L2A variant states that the "engine has an alternate rating of 1800NaN0 @ 2700 RPM". Used in the Cessna 172R and SP.
    IO-360-M1A
  • 1800NaN0 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.
    IO-360-M1B
  • 1800NaN0 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.

    LIO-360

    LIO-360-C1E6
  • 2000NaN0 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.

    AIO-360

    AIO-360-A1A
  • 2000NaN0 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.
    AIO-360-A1B
  • 2000NaN0 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.
    AIO-360-A2A
  • 2000NaN0 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.
    AIO-360-A2B
  • 2000NaN0 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.
    AIO-360-B1B
  • 2000NaN0 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.

    AEIO-360

    AEIO-360-A1A
  • 2000NaN0 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.
    AEIO-360-A1B
  • 2000NaN0 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.
    AEIO-360-A1B6
  • 2000NaN0 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.
    AEIO-360-A1C
  • 2000NaN0 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.
    AEIO-360-A1D
  • 2000NaN0 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.
    AEIO-360-A1E
  • 2000NaN0 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.
    AEIO-360-A1E6
  • 2000NaN0 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
    AEIO-360-A2A
  • 2000NaN0 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.
    AEIO-360-A2B
  • 2000NaN0 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.
    AEIO-360-A2C
  • 2000NaN0 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.
    AEIO-360-B1B
  • 1800NaN0 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.
    AEIO-360-B1D
  • 1800NaN0 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.
    AEIO-360-B1F
  • 1800NaN0 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.
    AEIO-360-B1F6
  • 1800NaN0 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.
    AEIO-360-B1G6
  • 1800NaN0 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.
    AEIO-360-B2F
  • 1800NaN0 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.
    AEIO-360-B2F6
  • 1800NaN0 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.
    AEIO-360-B1H
  • 1800NaN0 at 2700 rpm, Minimum fuel grade 91/96 avgas, compression ratio 8.50:1. Same as AEIO-360-H1B except has Dynafocal mounting.
    AEIO-360-B4A
  • 1800NaN0 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.
    AEIO-360-H1A
  • 1800NaN0 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.
    AEIO-360-H1B
  • 1800NaN0 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.

    HIO-360

    HIO-360-A1A
  • 1800NaN0 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.
    HIO-360-A1B
  • 1800NaN0 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.
    HIO-360-B1A
  • 1800NaN0 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.
    HIO-360-B1B
  • 1800NaN0 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.
    HIO-360-C1A
  • 2050NaN0 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.
    HIO-360-C1B
  • 2050NaN0 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.
    HIO-360-D1A
  • 1900NaN0 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.
    HIO-360-E1AD
  • 1900NaN0 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 2050NaN0 at 3000 rpm and a manifold pressure of 36.5 inches Hg absolute.
    HIO-360-E1BD
  • 1900NaN0 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 2050NaN0 at 3000 rpm and a manifold pressure of 36.5 inches Hg absolute.
    HIO-360-F1AD
  • 1900NaN0 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 2250NaN0 at 3050 rpm at a manifold pressure of 39 inches Hg to a critical altitude of 120000NaN0.
    HIO-360-G1A
  • 1800NaN0 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

    LHIO-360

    LHIO-360-C1A
  • 2050NaN0 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.
    LHIO-360-C1B
  • 2050NaN0 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.
    LHIO-360-F1AD
  • 1900NaN0 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 2250NaN0 at 3050 rpm at a manifold pressure of 39 inches Hg to a critical altitude of 120000NaN0.

    TIO-360

    TIO-360-A1A
  • 2000NaN0 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.[5]
    TIO-360-A1B
  • 2000NaN0 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.
    TIO-360-A3B6
  • 2000NaN0 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.
    TIO-360-C1A6D
  • 2100NaN0 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.

    See also

    Further reading

    Notes and References

    1. Web site: TYPE CERTIFICATE DATA SHEET NO. E-286 Revision 19. 2009-01-17. Federal Aviation Administration. December 2003.
    2. Web site: Lycoming Service Instruction 1070Q . 3 November 2011 . Lycoming . 2010 . dead . https://web.archive.org/web/20111117095958/http://www.lycoming.com/support/publications/service-instructions/pdfs/SI1070Q.pdf . 17 November 2011 .
    3. Web site: TYPE CERTIFICATE DATA SHEET NO. E26EA Revision 4. 2009-01-18. Federal Aviation Administration. March 1986.
    4. Web site: TYPE CERTIFICATE DATA SHEET NO. 1E10 Revision 24. 8 February 2015. Federal Aviation Administration. 24 May 2012.
    5. Web site: TYPE CERTIFICATE DATA SHEET NO. E16EA Revision 5. 2009-01-18. Federal Aviation Administration. March 1986.

    This article is licensed under the GNU Free Documentation License. It uses material from the Wikipedia article "List of Lycoming O-360 variants".

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