Abstract: An actuator system for an actuatable door, the actuator system comprising a stiff hinge arm, the stiff hinge arm being adapted to pivotally support the actuatable door and to be pivotally mounted to an associated door mounting structure, wherein an actuator with a pneumatically operable actuating rod is provided, the actuating rod comprising a coupling rod joint that is connected to at least one coupling rod, the at least one coupling rod being mounted to at least one torque lever that is pivotally mounted in at least one hinge of the stiff hinge arm by means of at least one torsion bolt, the at least one torsion bolt being drivingly connectable to the actuatable door. The invention is further related to an aircraft having such an actuatable door.

Abstract: An emergency opening system (1) of an aircraft cabin door (3) mounted in an aircraft fuselage structure (4) by means of a hinge arm (2). An actuator (7), designed to assist the opening of the aircraft cabin door (3) against the force of gravity by means of a gas operated actuating rod (8) is mounted with its fix end (9) to said hinge arm (2) and said actuating rod (8) is connected to an actuator joint (10). A fork lever (24) is linked to said actuator joint (10). A bell crank (13) is respectively pivotable mounted to said hinge arm (2) and to said actuator joint (10) for the fork lever (24). At least one coupling lever (12) is pivotable joint to said fork lever (24) at at least one coupling joint (14). Said at least one coupling lever (12) is mounted in at least one hinge (18) of the hinge arm (2) by means of a respective bolt (26), said bolt (26) being drivingly connected to said aircraft cabin door (3) for rotation of said aircraft cabin door (3).

Abstract: An emergency opening system (1) of an aircraft cabin door (3) mounted in an aircraft fuselage structure (4) by means of a hinge arm (2). An actuator (7), designed to assist the opening of the aircraft cabin door (3) against the force of gravity by means of a gas operated actuating rod (8) is mounted with its fix end (9) to said hinge arm (2) and said actuating rod (8) is connected to an actuator joint (10). A fork lever (24) is linked to said actuator joint (10). A bell crank (13) is respectively pivotable mounted to said hinge arm (2) and to said actuator joint (10) for the fork lever (24). At least one coupling lever (12) is pivotable joint to said fork lever (24) at at least one coupling joint (14). Said at least one coupling lever (12) is mounted in at least one hinge (18) of the hinge arm (2) by means of a respective bolt (26), said bolt (26) being drivingly connected to said aircraft cabin door (3) for rotation of said aircraft cabin door (3).