Abstract: An electronic control device is provided for an aviation engine. Each cylinder of the engine is equipped with main ignition plugs and back-up ignition plugs. Lane A including a first CPU and lane B including a second CPU are included in an ECU. The ignition control system is multiplexed by the two lanes A, B. The first and second CPU independently calculate ignition timing for each cylinder based on each sensor signal, and then exchange the results of these calculations with each other. At each cylinder, ignition timing is synchronized in such a manner that ignition timing of the main ignition plugs and ignition timing of the back-up ignition plugs match. The electronic control device so configured has a high level of redundancy with a small number of CPU's. Thus, electronic control device can be provided for the aviation engine with few limitations placed in relation to installation location.

Abstract: A shield cover for an engine is provided to shield electric parts, in an engine wherein an engine body includes a crankcase having a plurality of cylinder bores. An intake chamber common to all of the cylinder bores is spaced away from the crankcase. The shield cover is made in one piece, making it possible to reduce the number of parts and also of the cost, and to achieve a generally compact configuration of the engine. A plurality of electric parts 47L, 47R, 62L, 62R, 64 are disposed around an intake plenum 49, and the plural electric parts 47L, 47R, 62L, 62R, 64 are covered with a shield cover 67 attached to the engine body 12 in such a manner as to cover at least part of the intake plenum 49.

Abstract: An electronic control device is provided for an aviation engine. Each cylinder of the engine is equipped with main ignition plugs and back-up ignition plugs. Lane A including a first CPU and lane B including a second CPU are included in an ECU. The ignition control system is multiplexed by the two lanes A, B. The first and second CPU independently calculate ignition timing for each cylinder based on each sensor signal, and then exchange the results of these calculations with each other. At each cylinder, ignition timing is synchronized in such a manner that ignition timing of the main ignition plugs and ignition timing of the back-up ignition plugs match. The electronic control device so configured has a high level of redundancy with a small number of CPU's. Thus, electronic control device can be provided for the aviation engine with few limitations placed in relation to installation location.

Abstract: A shield cover for an engine is provided to shield electric parts, in an engine wherein an engine body includes a crankcase having a plurality of cylinder bores. An intake chamber common to all of the cylinder bores is spaced away from the crankcase. The shield cover is made in one piece, making it possible to reduce the number of parts and also of the cost, and to achieve a generally compact configuration of the engine. A plurality of electric parts 47L, 47R, 62L, 62R, 64 are disposed around an intake plenum 49, and the plural electric parts 47L, 47R, 62L, 62R, 64 are covered with a shield cover 67 attached to the engine body 12 in such a manner as to cover at least part of the intake plenum 49.

Abstract: An oxygen concentration sensor abnormality-detecting system is provided for an internal combustion engine having first and second oxygen concentration sensors arranged in the exhaust system upstream and downstream of a catalytic converter therein. An ECU determines that the first oxygen concentration sensor is functioning abnormally if an output from the first oxygen concentration sensor does not change when an output from the second oxygen concentration sensor changes.