A rotorcraft, comprising: a control element (231, 233); a trim motor (209, 213) connected to the control element (231, 233) and operable to selectively attempt to drive the control element (231, 233) to a trim position; a control sensor (235, 211, 237, 215) connected to the control element (231, 233), wherein the control sensor (235, 211, 237, 215) is operable to generate trim data indicating a displacement of the control element (231, 233) in relation to a trim position of the control element (231, 233); and a flight control computer in signal communication with the control sensor (235, 211, 237, 215) and operable to monitor the trim data and determine an active detent state of the control element (231, 233) according to the trim data, wherein the active detent state is one of an in-detent state, an out-of-detent state, and an in-transition state, wherein the in-detent state is a state where a pilot has released manual control of the control element (231, 233), wherein the out-of-detent state is a state where the pilot has taken manual control of the control element (231, 233), wherein the FCC is operable to control the trim motor (209, 213) to drive the control element (231, 233) to the trim position, wherein the trim position is a default position of the control element (231, 233) when the trim motor (209, 213) is not driving the control element (231, 233) and is the position to which the trim motor (209, 213) is attempting to drive the control element (231, 233) when the trim motor (209, 213) is driving the control element (231, 233), wherein the FCC is further operable to buffer a transition of the active detent state from the in-detent state to the out-of-detent state using the in-transition state, wherein the FCC is further operable to provide a first flight management function when the active detent state is the in-detent state or the in-transition state, and wherein the FCC is further operable to provide a second flight management function when the active detent state is the out-of-detent state. a control element (231, 233); a trim motor (209, 213) connected to the control element (231, 233) and operable to selectively attempt to drive the control element (231, 233) to a trim position; a control sensor (235, 211, 237, 215) connected to the control element (231, 233), wherein the control sensor (235, 211, 237, 215) is operable to generate trim data indicating a displacement of the control element (231, 233) in relation to a trim position of the control element (231, 233); and a flight control computer in signal communication with the control sensor (235, 211, 237, 215) and operable to monitor the trim data and determine an active detent state of the control element (231, 233) according to the trim data, wherein the active detent state is one of an in-detent state, an out-of-detent state, and an in-transition state, wherein the in-detent state is a state where a pilot has released manual control of the control element (231, 233), wherein the out-of-detent state is a state where the pilot has taken manual control of the control element (231, 233), wherein the FCC is operable to control the trim motor (209, 213) to drive the control element (231, 233) to the trim position, wherein the trim position is a default position of the control element (231, 233) when the trim motor (209, 213) is not driving the control element (231, 233) and is the position to which the trim motor (209, 213) is attempting to drive the control element (231, 233) when the trim motor (209, 213) is driving the control element (231, 233), wherein the FCC is further operable to buffer a transition of the active detent state from the in-detent state to the out-of-detent state using the in-transition state, wherein the FCC is further operable to provide a first flight management function when the active detent state is the in-detent state or the in-transition state, and wherein the FCC is further operable to provide a second flight management function when the active detent state is the out-of-detent state.