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Aircraft engine MIKRON IIIA The aircraft engine is certified according to JAR22, sect. H airworthiness requirements. It is a four stroke, air cooled, over-head valve, carbureted, inverted in-line four-cylinder, a version of MIKRON III AE. The engine is designed for powered gliders or for other Light aircraft which can employ its small size. Its cross section enables desirable shaping of the cowling which consequently reduces the frontal drag of the aircraft. The engine is equipped with a carburetter, fuel supply is secured by a dual- diaphragma 2M-50 fuel pump. The air- fuel mixture is preheated in the distribution-manifold by exhaust heat transfer. Dual ignition with two magnetos and two separate sets of plugs. Dry-sump oil system with separate oil tank outside the engine. The electric starter B76, supplied by 12 V DC has 0,5 kW power output. The engine is also equipped with a generator. The AC-generator supplies the systém with 12V / 15A nominal power. Ram air for engine cooling enters through intake opening on the left side (view "shaft forward") of the engine front cowling, is directed around heads and cylinders by sump and baffling and then exhausted through the opening in the right-hand engine cowling. |
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| __ _TECHNICAL DATA |
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| Direction of rotation (as viewed with shaft forward) | : anticlockwise | ||||||||||||||
| Cylinder bore | : 90 mm_____3,54 in | ||||||||||||||
| Pistion stroke | : 90 mm_____3,78 in | ||||||||||||||
| Cubic volume total | : 2,44 lt___148,89 cub. in | ||||||||||||||
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