Abstract: The invention relates to a servo valve, in particular a two-stage or multistage electrohydraulic servo valve, having a first stage which works as a pilot stage, and a second stage which works as a power stage, wherein the second stage has a valve block and a control slide valve sleeve arranged therein and having a jacket surface (18), wherein the jacket surface and/or another region of the control slide valve sleeve is preferably provided with at least one flow passage for transferring control flow and/or volume flow, and wherein a control slide valve is movably arranged in the control slide valve sleeve, wherein at least one of the flow passages is formed by a groove which is arranged in the surface of the control slide valve sleeve and which does not extend sectionally or overall in the peripheral direction of the control slide valve sleeve.

Abstract: The present invention relates to an emergency power system for an aircraft having at least one fuel cell unit for producing electric power, wherein the fuel cell unit is cooled via at least one cooling circuit which includes at least one heat exchanger, and wherein the heat exchanger is connected to at least one air distribution system of the aircraft cabin so that exhaust air heated by the heat exchanger in the operation of the emergency power system can be distributed via the air distribution system in the aircraft cabin.

Abstract: The invention relates to a flap actuator, in particular to a servo/spoiler actuator, comprising at least one electrohydraulic servo valve and at least one actuator which are hydraulically connected to one another, wherein the actuator comprises at least one actuator housing in and/or at which the at least one channel is arranged by means of which one or more components, preferably likewise arranged in and/or at the actuator housing, are hydraulically connected and wherein no valve block is arranged between the actuator and the servo valve.

Abstract: The invention relates to a flap actuator, in particular to a servo/spoiler actuator, comprising at least one electrohydraulic servo valve and at least one actuator which are hydraulically connected to one another, wherein the actuator comprises at least one actuator housing in and/or at which the at least one channel is arranged by means of which one or more components, preferably likewise arranged in and/or at the actuator housing, are hydraulically connected and wherein no valve block is arranged between the actuator and the servo valve.

Abstract: The present invention relates to an emergency power system for an aircraft having at least one fuel cell unit for producing electric power, wherein the fuel cell unit is cooled via at least one cooling circuit which includes at least one heat exchanger, and wherein the heat exchanger is connected to at least one air distribution system of the aircraft cabin so that exhaust air heated by the heat exchanger in the operation of the emergency power system can be distributed via the air distribution system in the aircraft cabin.