Aircraft seat, with at least one a seat component (12a; 12b; 12c; 12d; 12e), in particular a seat component (12a; 12b; 12c; 12d; 12e) realized as a backrest, and with a table device for the aircraft seat, with a table unit (14a; 14b; 14c; 14d; 14e) which is configured for being adjustable at least between a use position and a stowage position, and with at least one locking module (20a; 20b; 20c; 20d; 20e) comprising at least one connection unit (28a; 28b; 28c; 28d; 28e) which is in a mounted state firmly and fixedly connected to the seat component , wherein the table unit (14a; 14b; 14c; 14d; 14e) at least in the stowage position is lockable to the connection unit (28a; 28b; 28c; 28d; 28e), wherein the locking module (20a; 20b; 20c; 20d; 20e) has at least two force-fit and/or form-fit elements (34a, 36a, 38a, 40a; 34b, 36b, 38b, 40b; 34c, 36c, 38c, 40c; 34d, 36d, 38d, 40d; 34e, 36e, 38e, 40e), by means of which the table unit (14a; 14b; 14c; 14d) in a locked state is coupled in a form-fitting and/or force-fitting manner with the connection unit (28a; 28b; 28c; 28d), wherein the locking module (20a; 20c; 20d) comprises an actuation mechanism (42a; 42c; 42d) which is disposed in the connection unit (28a; 28c; 28d) and is configured for an actuation of the force-fit and/or form-fit elements (34a, 36a; 34c, 36c; 34d, 36d), and the locking module (20a; 20b) comprises at least one actuation element (60a; 60b) which is in a coupling with the connection unit configured to actuate the actuation mechanism and is configured to be manually operated by a passenger, characterised in that the actuation element is connected to the table unit (14a; 14b), and has at least one force-fit and/or form-fit element (62a; 62b) by means of which the table unit (14a; 14b) in a locked state is coupled in a form-fitting and/or force-fitting manner to the connection unit (28a; 28b). with at least one a seat component (12a; 12b; 12c; 12d; 12e), in particular a seat component (12a; 12b; 12c; 12d; 12e) realized as a backrest, and with a table device for the aircraft seat, with a table unit (14a; 14b; 14c; 14d; 14e) which is configured for being adjustable at least between a use position and a stowage position, and with at least one locking module (20a; 20b; 20c; 20d; 20e) comprising at least one connection unit (28a; 28b; 28c; 28d; 28e) which is in a mounted state firmly and fixedly connected to the seat component , wherein the table unit (14a; 14b; 14c; 14d; 14e) at least in the stowage position is lockable to the connection unit (28a; 28b; 28c; 28d; 28e), wherein the locking module (20a; 20b; 20c; 20d; 20e) has at least two force-fit and/or form-fit elements (34a, 36a, 38a, 40a; 34b, 36b, 38b, 40b; 34c, 36c, 38c, 40c; 34d, 36d, 38d, 40d; 34e, 36e, 38e, 40e), by means of which the table unit (14a; 14b; 14c; 14d) in a locked state is coupled in a form-fitting and/or force-fitting manner with the connection unit (28a; 28b; 28c; 28d), wherein the locking module (20a; 20c; 20d) comprises an actuation mechanism (42a; 42c; 42d) which is disposed in the connection unit (28a; 28c; 28d) and is configured for an actuation of the force-fit and/or form-fit elements (34a, 36a; 34c, 36c; 34d, 36d), and the locking module (20a; 20b) comprises at least one actuation element (60a; 60b) which is in a coupling with the connection unit configured to actuate the actuation mechanism and is configured to be manually operated by a passenger, characterised in that the actuation element is connected to the table unit (14a; 14b), and has at least one force-fit and/or form-fit element (62a; 62b) by means of which the table unit (14a; 14b) in a locked state is coupled in a form-fitting and/or force-fitting manner to the connection unit (28a; 28b). <EOS>