Abstract: The invention relates to an aeronautic engine (1), comprising: a housing (10), made of electrically insulating material, said housing (10) comprising at least one metallic piece (16a, 16b, 17, 18), a structural piece (2) of the engine (1), comprising metallic material (2, 3) and connected to the housing (10), and an equipment (30), fixed to the housing (10), the aeronautic engine (1) being characterized in that the equipment is connected to the structural piece (2) by means of the metallic piece (16a, 16b, 17, 18) by means of an electrically conductive connecting path (20, 22).

Abstract: The invention proposes an arrangement of a tank of lubrication liquid for an aircraft turbomachine (12), under a nacelle cowling (10) covering said turbomachine (12), with the tank being arranged in the volume located between the turbomachine (12) and the nacelle cowling (10), with the nacelle cowling (10) comprising an opening (22) for access to said volume, characterised in that the tank (18) is fastened to an internal face (20a) of a panel (20) closing off said opening (22), with the unit formed by the panel (20) and the tank being added onto the nacelle cowling (10) and able to be mounted and dismounted from the nacelle cowling (10).