Abstract: An annular cover for a lubrication chamber of a rotary bearing of a turbomachine. The cover includes a wall that is generally circular and flared with an orifice that is designed to receive a transmission shaft opposite an assembly surface for the cover, and at least one duct communicating with the inside of the wall and extending along the wall as far as the assembly surface. The duct is formed in the thickness of the body of the wall which is made from the same material, and which includes a composite material with a thermoplastic matrix and carbon fibers.

Abstract: The present application relates to an annular cover for a lubrication chamber of a rotary bearing of a turbomachine. The cover includes a wall that is generally circular and flared with an orifice that is designed to receive a transmission shaft opposite an assembly surface for the cover, and at least one duct communicating with the inside of the wall and extending along the wall as far as the assembly surface. The duct is formed in the thickness of the body of the wall which is made from the same material, and which includes a composite material with a thermoplastic matrix and carbon fibres. The present application also relates to a turbomachine including a compressor linked to a turbine via a transmission shaft, an intermediate fan casing, and a bearing joining the transmission shaft to the intermediate casing. The casing is placed in a lubrication chamber delimited by an annular chamber cover, a chamber casing carrying the bearing and the cover.

Abstract: The invention relates to servicing an aircraft. For this purpose said aircraft is provided with a permanently monitoring device comprising piezo-electric sensors. The inventive method consists in continuously recording signals transmitted by said sensors and in subsequently calculating a fatigue to which the aircraft critical parts are exposed, thereby making it possible to better monitoring said critical parts. Said invention makes it possible to reduce the aircraft servicing costs.