A rotorcraft comprising: a control element (231; 233); a first control sensor connected to the control element, the first control sensor operable to generate position data indicating an actual position of the control element; and a flight control computer (FCC) in signal communication with the first control sensor, wherein the FCC is operable to: determine a suggested position for the control element, wherein the FCC comprises an error monitor , the error monitor operable to compare the suggested position of the control element with the actual position of the control element and determine whether a second control sensor is functional or defective, wherein the second control sensor is operable to sense a detent state associated with the control element, the detent state indicating whether a pilot has manual control of the control element, and comprising an in-detent state and an out-of-detent state, characterized in that the error monitor is operable to compare the suggested position of the control element with the actual position of the control element only when the control element is in the in-detent state, and wherein the FCC is further operable to: provide a first flight management function when the second control sensor is determined to be functional, and provide a second flight management function when the second control sensor is determined to be defective, and wherein flight modes that depend on signals from the second control sensor are turned off in the second flight management function. a control element (231; 233); a first control sensor connected to the control element, the first control sensor operable to generate position data indicating an actual position of the control element; and a flight control computer (FCC) in signal communication with the first control sensor, wherein the FCC is operable to: determine a suggested position for the control element, wherein the FCC comprises an error monitor , the error monitor operable to compare the suggested position of the control element with the actual position of the control element and determine whether a second control sensor is functional or defective, wherein the second control sensor is operable to sense a detent state associated with the control element, the detent state indicating whether a pilot has manual control of the control element, and comprising an in-detent state and an out-of-detent state, characterized in that the error monitor is operable to compare the suggested position of the control element with the actual position of the control element only when the control element is in the in-detent state, and wherein the FCC is further operable to: provide a first flight management function when the second control sensor is determined to be functional, and provide a second flight management function when the second control sensor is determined to be defective, and provide a first flight management function when the second control sensor is determined to be functional, and provide a second flight management function when the second control sensor is determined to be defective, and wherein flight modes that depend on signals from the second control sensor are turned off in the second flight management function. <EOS>