Abstract: A method for actuating at least one positioning flap on each wing of an aircraft, which positioning flap is actuated by at least two flap coupling devices each including a flap actuator device, where at least on one flap actuator device for each positioning flap a brake mechanism is arranged by means of whose actuation an adjustment state of the respective flap actuator device can be locked, including the steps of: actuating each brake mechanism of a positioning flap individually, subsequently actuating the flap actuator device by means of the drive motor, in the case of a change in the adjustment state of the positioning flap by a predetermined extent, terminating actuation of the positioning flap concerned, and a system for implementing the method.

Abstract: A method and a device for fault detection in the load path of a spindle actuator which is provided for actuating an aerodynamically active surface, in particular a high-lift flap of an aircraft, wherein the spindle actuator has a redundant load path which is formed by a spindle and a secondary connection which are connected rotationally fixedly to one another on the driven side and are coupled to the surface to be actuated and which are assigned separate load paths on the drive side, whereof the primary load path contains a primary spindle which is driven by a motor and can be fixed in its rotational movement by a primary brake, and the secondary load path contains the secondary inner connection, which is in particular arranged concentrically in the primary spindle, which can be fixed in its rotational movement by a secondary brake, in which output signals representing the turning position of the spindle, which are generated by means of at least one turning position sensor which is coupled to the primary spin

Abstract: A lift-augmenting leading edge flap for a carrying wing of an aircraft, wherein the flap comprises an essentially rigid main body which makes a transition from the first side to the second side of the wing the flap being adjustable by a retention- and actuation mechanism coupled between the flap and wing box, between a first, retracted, position and a second, extended, position, wherein the first transition region of the flap is slidable to rest in each position essentially free of any gap, against the first skin of the wing box or against the wing end cover, in relation to the wing end cover.

Abstract: An actuator having two or more interconnected movement components, wherein the movement components are designed as linear actuators with substantially coaxial longitudinal axes or longitudinal axes that are parallel to each other and that are interconnected in longitudinal direction such that their linear movements are superimposed on one another, and such that at least one of the linear actuators can be stopped at one or several predetermined positions.