Abstract: An engine plant for aircraft comprising a multicylinder internal combustion engine (1) whose crankshaft drives an adjustable pitch propeller (5), mechanisms for adjusting the engine speed and a common power stick (4) that controls the operation of the engine and of the adjustment mechanisms, characterized in that said engine is a compression ignition engine (1) that cooperates with an electronic control system (3) controlling the quantity of the fuel injected.

Abstract: The static seal comprises a semi-rigid annular part (11) shaped as a bead and first and second wings (12, 13) extending transversely with respect to the seal axis and laterally connected to the bead portion (11) in a gradual manner by means of concave surfaces with a large curvature radius. The seal has in its axial cross-section the shape of a V lying on its side, the tapered surfaces (16, 17) of the branches (12, 13) of the V being slightly inclined with respect to the planar surfaces (18, 19) of the bead (11) to which they are attached. The branches (12, 13) of the V forming the wings have an elasticity such that by flexure of said tapered surfaces (16, 17) of the V branches and slight flexure of the bead (11), the extremities of said surface may form with the planar surfaces (18, 19) of the bead (11) to which they are attached two sealing regions. Said seal is intended to be used in severe conditions of temperature, pressure, vibrations and chemical attack.