Abstract: An internal combustion engine for an aircraft can include a crankshaft configured to drive a propeller; a camshaft coupled to the crankshaft; and an ignition controller coupled to the camshaft and including a visual indicator, the visual indicator configured to produce a visual signal at a predetermined angular position of the engine. An ignition controller for an internal combustion engine can include a housing and a P-lead connection extending from the housing, the ignition controller configured to selectively supply or cut main electrical power from the engine via the P-lead connection, the ignition controller also configured to selectively supply its own power.

Abstract: An internal combustion engine for an aircraft can include a crankshaft configured to drive a propeller; a camshaft coupled to the crankshaft; and an ignition controller coupled to the camshaft and including a visual indicator, the visual indicator configured to produce a visual signal at a predetermined angular position of the engine. An ignition controller for an internal combustion engine can include a housing and a P-lead connection extending from the housing, the ignition controller configured to selectively supply or cut main electrical power from the engine via the P-lead connection, the ignition controller also configured to selectively supply its own power.

Abstract: An internal combustion engine for an aircraft can include a crankshaft configured to drive a propeller; a camshaft coupled to the crankshaft; and an ignition controller coupled to the camshaft and including a visual indicator, the visual indicator configured to produce a visual signal at a predetermined angular position of the engine. An ignition controller for an internal combustion engine can include a housing and a P-lead connection extending from the housing, the ignition controller configured to selectively supply or cut main electrical power from the engine via the P-lead connection, the ignition controller also configured to selectively supply its own power.

Abstract: An internal combustion engine for an aircraft can include a crankshaft configured to drive a propeller; a camshaft coupled to the crankshaft; and an ignition controller coupled to the camshaft and including a visual indicator, the visual indicator configured to produce a visual signal at a predetermined angular position of the engine. An ignition controller for an internal combustion engine can include a housing and a P-lead connection extending from the housing, the ignition controller configured to selectively supply or cut main electrical power from the engine via the P-lead connection, the ignition controller also configured to selectively supply its own power.

Abstract: An internal combustion engine for an aircraft can include a crankshaft configured to drive a propeller; a camshaft coupled to the crankshaft; and an ignition controller coupled to the camshaft and including a visual indicator, the visual indicator configured to produce a visual signal at a predetermined angular position of the engine. An ignition controller for an internal combustion engine can include a housing and a P-lead connection extending from the housing, the ignition controller configured to selectively supply or cut main electrical power from the engine via the P-lead connection, the ignition controller also configured to selectively supply its own power.

Abstract: An internal combustion engine for an aircraft can include a crankshaft configured to drive a propeller; a camshaft coupled to the crankshaft; and an ignition controller coupled to the camshaft and including a visual indicator, the visual indicator configured to produce a visual signal at a predetermined angular position of the engine. An ignition controller for an internal combustion engine can include a housing and a P-lead connection extending from the housing, the ignition controller configured to selectively supply or cut main electrical power from the engine via the P-lead connection, the ignition controller also configured to selectively supply its own power.

Abstract: An internal combustion engine for an aircraft can include a crankshaft configured to drive a propeller; a camshaft coupled to the crankshaft; and an ignition controller coupled to the camshaft and including a visual indicator, the visual indicator configured to produce a visual signal at a predetermined angular position of the engine. An ignition controller for an internal combustion engine can include a housing and a P-lead connection extending from the housing, the ignition controller configured to selectively supply or cut main electrical power from the engine via the P-lead connection, the ignition controller also configured to selectively supply its own power.

Abstract: A heat exchanger for an engine includes: an inlet; an outlet; a radiator spanning the inlet and the outlet and in fluid communication with both the inlet and the outlet; and a bypass element spanning the inlet and the outlet and in fluid communication with both the inlet and the outlet and in parallel fluid communication with the radiator, the bypass element including a control mechanism, the control mechanism including a bypass valve and a control cylinder connected to the bypass valve for operating the bypass valve, the control cylinder including a pneumatic ram cylinder in communication with a turbocharger outlet of the engine.

Abstract: A system, apparatus and method for maintaining power in an internal combustion typically turbocharged aircraft engine is disclosed. During descent, air pressure and temperature in the manifold can fall to dangerous levels. This is because engine power is low and likewise turbocharger output is also low. The system and method provide for a bypass of the heat radiator during low power periods, or with low ambient temperature or both. A parameter is measured, often manifold pressure or temperature and the degree of bypass is adjusted commensurately.

Abstract: A system and method of measuring engine torque by interposing a hub 20 between a power source/engine and a driven device such as a propeller 24. The hub 20 is preferably made unitary of a single material and includes a strain gauge 48/49 to measure twisting forces. The gauge output is transmitted 44 to a receiver not part of any rotating component. A housing 50 shields the gauge but is rigidly connected to only one part of the hub and thus does not impact the strain gauge measurement.