An aircraft having a high lift system, comprising: • a flight control computer, • at least one high lift body (13a, 13b; 14a, 14b; A, B; C, D), disposed on each respective wing of the aircraft so as to be adjustable relative to the latter, • a drive device (110, 210), coupled with the high lift bodies (13a, 13b; 14a, 14b; A, B; C, D), which is configured such that it adjusts the high lift bodies (13a, 13b; 14a, 14b; A, B; C, D) between a retracted position and an extended position on the basis of activation commands, • a multiply redundant activation device (120, 220) connected to the drive device via an analog data connection and including an activation function that generates activation commands for setting an adjustment state of the high lift bodies and that generates monitoring and locking commands for locking the high lift bodies (13a, 13b; 14a, 14b; A, B; C, D) in the event of a system failure, wherein the activation device (120, 220) is connected via a digital data connection to the flight control computer for receiving flight state-related data, • an input device arranged in the cockpit of the aircraft, the input device receiving input of target commands for adjusting the high lift bodies (13a, 13b; 14a, 14b; A, B; C, D), • sensors configured to detect an adjustment state of the high lift bodies (13a, 13b; 14a, 14b; A, B; C, D) which are connected via analog signal lines to the activation device (120, 220), • and wherein the input device is connected via a digital data connection to the activation device (120, 220) for the transmission of target commands for adjusting the high lift bodies (13a, 13b; 14a, 14b; A, B; C, D), characterized in that • the activation device (120, 220) of the high lift system is installed in a cargo compartment of the aircraft's fuselage and in an area extending, when viewed in a longitudinal direction of the aircraft's fuselage, from a location which is spaced apart from a front side (F4-1) of a wingbox by a distance ( /3) of one third of a fuselage length extending from there to a tip of the aircraft, as far as a location which is spaced apart from a rear side (F4-2) of the wingbox by a distance ( /3) of one third of a fuselage length extending from there to a fuselage end at a tail end of the aircraft. • a flight control computer, • at least one high lift body (13a, 13b; 14a, 14b; A, B; C, D), disposed on each respective wing of the aircraft so as to be adjustable relative to the latter, • a drive device (110, 210), coupled with the high lift bodies (13a, 13b; 14a, 14b; A, B; C, D), which is configured such that it adjusts the high lift bodies (13a, 13b; 14a, 14b; A, B; C, D) between a retracted position and an extended position on the basis of activation commands, • a multiply redundant activation device (120, 220) connected to the drive device via an analog data connection and including an activation function that generates activation commands for setting an adjustment state of the high lift bodies and that generates monitoring and locking commands for locking the high lift bodies (13a, 13b; 14a, 14b; A, B; C, D) in the event of a system failure, wherein the activation device (120, 220) is connected via a digital data connection to the flight control computer for receiving flight state-related data, • an input device arranged in the cockpit of the aircraft, the input device receiving input of target commands for adjusting the high lift bodies (13a, 13b; 14a, 14b; A, B; C, D), • sensors configured to detect an adjustment state of the high lift bodies (13a, 13b; 14a, 14b; A, B; C, D) which are connected via analog signal lines to the activation device (120, 220), • and wherein the input device is connected via a digital data connection to the activation device (120, 220) for the transmission of target commands for adjusting the high lift bodies (13a, 13b; 14a, 14b; A, B; C, D), characterized in that • the activation device (120, 220) of the high lift system is installed in a cargo compartment of the aircraft's fuselage and in an area extending, when viewed in a longitudinal direction of the aircraft's fuselage, from a location which is spaced apart from a front side (F4-1) of a wingbox by a distance ( /3) of one third of a fuselage length extending from there to a tip of the aircraft, as far as a location which is spaced apart from a rear side (F4-2) of the wingbox by a distance ( /3) of one third of a fuselage length extending from there to a fuselage end at a tail end of the aircraft.