An assembly comprising an aircraft engine, a propeller, and a blade angle feedback ring assembly, wherein the aircraft engine comprises a reduction gearbox; wherein the propeller is rotatable by a propeller shaft about a longitudinal axis, the propeller having blades with adjustable blade angle; and wherein the blade angle feedback ring assembly comprises: a feedback ring having one or more position markers disposed thereon; at least one sensor positioned proximate the feedback ring, one of the at least one sensor and the feedback ring coupled to the propeller to rotate therewith and to move axially with adjustment of the blade angle of the blades of the propeller, and the other of the at least one sensor and the feedback ring fixedly mounted to a static portion of the engine, the at least one sensor configured to detect, as one of the at least one sensor and the feedback ring rotates, relative passage of the one or more position markers, characterised in that: a first electrically-conductive path is defined between the propeller and the engine via the feedback ring, the feedback ring assembly further comprises an electric current conduction element (502;602;702) comprising an annular slip ring (502;602;702) disposed between the propeller and the reduction gearbox, the electric current conduction element (502;602;702) electrically conductively coupled to the engine to define a second electrically-conductive path between the propeller and the engine in parallel to the first electrically-conductive path, the second electrically-conductive path configured with a lower electrical resistance to electrical conduction between the propeller and the engine than the first electrically-conductive path. wherein the aircraft engine comprises a reduction gearbox; wherein the propeller is rotatable by a propeller shaft about a longitudinal axis, the propeller having blades with adjustable blade angle; and wherein the blade angle feedback ring assembly comprises: a feedback ring having one or more position markers disposed thereon; at least one sensor positioned proximate the feedback ring, one of the at least one sensor and the feedback ring coupled to the propeller to rotate therewith and to move axially with adjustment of the blade angle of the blades of the propeller, and the other of the at least one sensor and the feedback ring fixedly mounted to a static portion of the engine, the at least one sensor configured to detect, as one of the at least one sensor and the feedback ring rotates, relative passage of the one or more position markers, a feedback ring having one or more position markers disposed thereon; at least one sensor positioned proximate the feedback ring, one of the at least one sensor and the feedback ring coupled to the propeller to rotate therewith and to move axially with adjustment of the blade angle of the blades of the propeller, and the other of the at least one sensor and the feedback ring fixedly mounted to a static portion of the engine, the at least one sensor configured to detect, as one of the at least one sensor and the feedback ring rotates, relative passage of the one or more position markers, characterised in that: a first electrically-conductive path is defined between the propeller and the engine via the feedback ring, the feedback ring assembly further comprises an electric current conduction element (502;602;702) comprising an annular slip ring (502;602;702) disposed between the propeller and the reduction gearbox, the electric current conduction element (502;602;702) electrically conductively coupled to the engine to define a second electrically-conductive path between the propeller and the engine in parallel to the first electrically-conductive path, the second electrically-conductive path configured with a lower electrical resistance to electrical conduction between the propeller and the engine than the first electrically-conductive path. a first electrically-conductive path is defined between the propeller and the engine via the feedback ring, the feedback ring assembly further comprises an electric current conduction element (502;602;702) comprising an annular slip ring (502;602;702) disposed between the propeller and the reduction gearbox, the electric current conduction element (502;602;702) electrically conductively coupled to the engine to define a second electrically-conductive path between the propeller and the engine in parallel to the first electrically-conductive path, the second electrically-conductive path configured with a lower electrical resistance to electrical conduction between the propeller and the engine than the first electrically-conductive path.