A method comprising: adjusting a first flight control device of a rotorcraft to control flight around axes of the rotorcraft in a forward flight mode, the first flight control device exercising flight control authority around a first axis of the rotorcraft, the first flight control device being a ruddervator mounted at an aft end of a fuselage of the rotorcraft; detecting a failure of the first flight control device, wherein detecting the failure of the first flight control device comprises accessing individualized equipment data for the rotorcraft, the individualized equipment data being stored at a computer of the rotorcraft, wherein the individualized equipment data indicates the center of gravity of the rotorcraft and the gross weight of the rotorcraft; transitioning at least a portion of the flight control authority around the first axis of the rotorcraft from the first flight control device to second flight control devices (20a, 20b) of the rotorcraft, the transitioning being performed automatically in response to detecting the failure of the first flight control device, the second flight control devices (20a, 20b) being propulsion assemblies mounted at outboard ends of a wing of the rotorcraft, wherein the propulsion assemblies comprise pylon assemblies (24a, 24b) and proprotor assemblies (26a, 26b); and after the transitioning, adjusting the second flight control devices (20a, 20b) to control flight around the first axis of the rotorcraft, the second flight control devices (20a, 20b)being adjusted by a first control process when the rotorcraft is in a vertical flight mode, the second flight control devices (20a, 20b) being adjusted by a second control process when the rotorcraft is in the forward flight mode, wherein during the first control process the orientations of the pylon assemblies are adjusted differentially such that an amount of difference in the orientations of the pylon assemblies is varied according to the gross weight of the rotorcraft and the center of gravity of the rotorcraft indicated by the individualized equipment data for the rotorcraft, and wherein during the second control process the pitches of the proprotor assemblies are adjusted differentially such that an amount of difference in thrust produced by the proprotor assemblies is varied according to the gross weight of the rotorcraft and the center of gravity of the rotorcraft indicated by the individualized equipment data for the rotorcraft. adjusting a first flight control device of a rotorcraft to control flight around axes of the rotorcraft in a forward flight mode, the first flight control device exercising flight control authority around a first axis of the rotorcraft, the first flight control device being a ruddervator mounted at an aft end of a fuselage of the rotorcraft; detecting a failure of the first flight control device, wherein detecting the failure of the first flight control device comprises accessing individualized equipment data for the rotorcraft, the individualized equipment data being stored at a computer of the rotorcraft, wherein the individualized equipment data indicates the center of gravity of the rotorcraft and the gross weight of the rotorcraft; transitioning at least a portion of the flight control authority around the first axis of the rotorcraft from the first flight control device to second flight control devices (20a, 20b) of the rotorcraft, the transitioning being performed automatically in response to detecting the failure of the first flight control device, the second flight control devices (20a, 20b) being propulsion assemblies mounted at outboard ends of a wing of the rotorcraft, wherein the propulsion assemblies comprise pylon assemblies (24a, 24b) and proprotor assemblies (26a, 26b); and after the transitioning, adjusting the second flight control devices (20a, 20b) to control flight around the first axis of the rotorcraft, the second flight control devices (20a, 20b)being adjusted by a first control process when the rotorcraft is in a vertical flight mode, the second flight control devices (20a, 20b) being adjusted by a second control process when the rotorcraft is in the forward flight mode, wherein during the first control process the orientations of the pylon assemblies are adjusted differentially such that an amount of difference in the orientations of the pylon assemblies is varied according to the gross weight of the rotorcraft and the center of gravity of the rotorcraft indicated by the individualized equipment data for the rotorcraft, and wherein during the second control process the pitches of the proprotor assemblies are adjusted differentially such that an amount of difference in thrust produced by the proprotor assemblies is varied according to the gross weight of the rotorcraft and the center of gravity of the rotorcraft indicated by the individualized equipment data for the rotorcraft.