Abstract: A method for monitoring a gearbox in an aircraft. The gearbox comprises at least one gearbox section with at least one measuring area. A first and a second electrical contact are arranged in the measuring area at a spacing from one another. A magnetic field is generated in the gearbox section. The magnetic field is adapted to move at least one ferromagnetic particle arranged in the gearbox section towards the measuring area, so that a bridge produced from one or more of the ferromagnetic particles is formed between the two electrical contacts. A measured value is generated based on an electrical parameter between the two electrical contacts. A measure of the criticality of a flight operation is determined on the basis of the measured value.

Abstract: The present disclosure relates to a gear set, especially for a rotary-wing aircraft, with two intermeshing gear wheels, each mounted on a respective shaft. In particular, in a normal section, the gear wheels of the gear set have different pressure angles on a drive side from the pressure angles on a freewheel side at the beginning of an engagement.

Abstract: The invention relates to an adjustment mechanism that includes a set ring gears which are arranged coaxially towards a central axis and which each include a cylindrical toothing system, two eccentric wheels with beveloid gears which mesh with the cylindrical toothing systems of the ring gears, eccentric axes which are inclined at an angle towards the central axis, and a central shaft that is driven by a drive shaft onto which the eccentric wheels are mounted. The set of ring gears include a center ring gear that is circulating and two outer neighboring ring gears which are solidly fixed.

Abstract: The invention relates to an adjustment mechanism that includes a set ring gears which are arranged coaxially towards a central axis and which each include a cylindrical toothing system, two eccentric wheels with beveloid gears which mesh with the cylindrical toothing systems of the ring gears, eccentric axes which are inclined at an angle towards the central axis, and a central shaft that is driven by a drive shaft onto which the eccentric wheels are mounted. The set of ring gears include a center ring gear that is circulating and two outer neighboring ring gears which are solidly fixed.

Abstract: The present disclosure relates to a gear set, especially for a rotary-wing aircraft, with two intermeshing gear wheels, each mounted on a respective shaft. In particular, in a normal section, the gear wheels of the gear set have different pressure angles on a drive side from the pressure angles on a freewheel side at the beginning of an engagement.