Abstract: A turboshaft engine for a helicopter, comprising a case inside which a gas generator and a turbine are accommodated, the turbine being mounted on a power shaft that extends along a longitudinal direction. The turboshaft engine further comprises means for removably mounting the power shaft into a reduction gearbox inside which at least one gear of a first reduction stage is accommodated. The means for removably mounting the power shaft include a pinion having a central bore, the shape of which is adapted to that of the power shaft in such a way that the pinion can slide over the power shaft; furthermore, the contour of the pinion is adapted to the shape of the gear of the first stage in such a way that the pinion can form a leading input pinion of the gearbox in said gear once the power shaft has been mounted in the reduction gearbox.

Abstract: A turboshaft engine includes a casing in which is arranged a gas generator and a free turbine fitted to a power shaft. The power shaft is configured to be mechanically connected to/disconnected from a reduction gearbox. The turboshaft engine includes at least one centralizer movable between an active position, in which the centralizer forms a bearing for the power shaft and which corresponds to a mechanical disconnection between the power shaft and the reduction gearbox, and a passive position, in which the centralizer is distanced from the power shaft and which corresponds to a mechanical connection between the power shaft the reduction gearbox.

Abstract: A turboshaft engine includes a in which is arranged a gas generator and a free turbine fitted to a power shaft. The power shaft is configured to be mechanically connected to/disconnected from a reduction gearbox. The turboshaft engine includes at least one centraliser movable between an active position, in which the centraliser forms a bearing for the power shaft and which corresponds to a mechanical disconnection between the power shaft and the reduction gearbox, and a passive position, in which the centraliser is distanced from the power shaft and which corresponds to a mechanical connection between the power shaft the reduction gearbox.

Abstract: A turboshaft engine for a helicopter, comprising a case inside which a gas generator and a turbine are accommodated, the turbine being mounted on a power shaft that extends along a longitudinal direction. The turboshaft engine further comprises means for removably mounting the power shaft into a reduction gearbox inside which at least one gear of a first reduction stage is accommodated. The means for removably mounting the power shaft include a pinion having a central bore, the shape of which is adapted to that of the power shaft in such a way that the pinion can slide over the power shaft; furthermore, the contour of the pinion is adapted to the shape of the gear of the first stage in such a way that the pinion can form a leading input pinion of the gearbox in said gear once the power shaft has been mounted in the reduction gearbox.

Abstract: A filler device for a fluid tank, including: a filler duct; a first stopper, for preventing overfilling of the tank, and a second stopper for preventing fluid from leaving the tank in unwanted manner; a first float mechanically connected to the first stopper such that, on being placed in a predetermined position, the first float closes the first stopper; and a holder system for holding the second stopper, which system, when fluid leaves the tank, closes the second stopper, and when fluid enters into the tank, opens the second stopper. In an operating position of the device, and under effect of a heavy element, the holder system acts continuously on the second stopper, tending to maintain the second stopper permanently in its closed position.

Abstract: A filler device for a fluid tank, including: a filler duct; a first stopper, for preventing overfilling of the tank, and a second stopper for preventing fluid from leaving the tank in unwanted manner; a first float mechanically connected to the first stopper such that, on being placed in a predetermined position, the first float closes the first stopper; and a holder system for holding the second stopper, which system, when fluid leaves the tank, closes the second stopper, and when fluid enters into the tank, opens the second stopper. In an operating position of the device, and under effect of a heavy element, the holder system acts continuously on the second stopper, tending to maintain the second stopper permanently in its closed position.