Abstract: The invention relates to a floor attachment assembly for mechanically connecting two aircraft seats to a floor structure of an aircraft, which assembly comprises four attachment points. The floor attachment assembly can be attached to the floor structure by means of one attachment element in each case at the four attachment points. The floor attachment assembly comprises two adapter plates, the two adapter plates being interconnected by means of a connection element. The mechanical connection between at least one of the adapter plates and at least one of the attachment elements is movable along at least one axis. Furthermore, the invention relates to a corresponding aircraft seat.

Abstract: A system for monitoring a nickel-cadmium battery incorporating twenty nickel-cadmium battery cells connected in series in a passenger aircraft includes a plurality of cell sensors for measuring the cell voltage and the cell temperature of individual battery cells and a data processing unit, and is set up to measure the battery current. The data processing unit is set up to determine a state of health value which is indicative of the state of health of the battery from the measurement data of the cell sensors and the measured battery current.

Abstract: Method for providing flight information data for a passenger in an aircraft, wherein the flight information data are transmitted from a cockpit system in the aircraft to at least one passenger information system in the same aircraft, wherein the flight information data are transmitted as a secondary radar signal and/or monitoring signal and received by the at least one passenger information system.

Abstract: A passenger aircraft (10) comprising a pressurized cabin, which comprises a top volume (13) and a passenger deck (12), the passenger deck (12) comprising at least one passenger compartment (14) separated from the rest of the passenger volume (16) by walls (15), is characterized in that a burstable wall (22) that extends below the ceiling (19) of the passenger volume and defines the passenger compartment (14) is arranged so as to be adjacent to the side wall (20), the space (23) between the burstable wall (22) and the side wall (20) being open towards the top volume (13) and forming a common pressure chamber therewith.

Abstract: The invention relates to an endoscopy system and a corresponding method for examining gas turbines, comprising an endoscope and a data processing unit, wherein the endoscope comprises an image recording unit, wherein the endoscope is configured to transmit recorded images of the image recording unit from the inside of the gas turbine to the data processing unit, wherein the endoscopy system is configured to position and align the endoscope comprising the image recording unit introduced into a gas turbine in the gas turbine in a defined manner.

Abstract: The invention relates to a method for repairing an aircraft or gas turbine component, wherein the method comprises the following automated steps: a) checking the component for cracks by means of an optical measurement method, wherein determined geometry and/or damage data are stored with reference to the component, b) generating an adaptive processing strategy on the basis of the determined geometry and/or damage data in a data processing unit, c) machining the component, d) determining the changed geometry data of the component, e) performing repair welding, f) checking the component for cracks by means of an optical measurement method.

Abstract: A method for cleaning a jet engine includes introducing into the engine, via a carrier gas by way of at least one nozzle, a cleaning medium which contains solids. The pressure of the carrier gas is 1 to 5 bar. An exit of the at least one nozzle is disposed at a radial spacing from a rotation axis of the engine which corresponds to 0.6 to 1.2 times the radius of the entry opening of a first compressor stage that is directed upstream. A main exit direction of the nozzle in relation to the rotation axis of the engine encloses an angle of 10 to 30°.

Abstract: An embodiment relates to a data loading device and a corresponding data loading method for loading software into aircraft systems, the data loading device incorporating a portable computer and a data storage device. The data loading device incorporating a switching device, the switching device having an external data connection. The switching device can switch connections between the computer, the data storage device and the data connection, the switching device having a first switching state which includes a connection between the computer and the data storage device. Furthermore, the switching device has a second switching state which includes a connection between the data storage device and the data connection.

Abstract: Method for replacing, inspecting, and/or repairing components in front bearing region of gas turbine, the gas turbine having at least one fan module, housing, low-pressure system, and high-pressure system, the low-pressure system having low-pressure compressor, low-pressure turbine, connecting shaft, stub shaft, and an N1 shaft connected to the low-pressure compressor via the stub shaft and the connecting shaft, the connecting shaft supported in the housing via first bearing unit, and the stub shaft supported in the housing via second bearing unit, the method including dismounting the fan module, fixing the N1 shaft in an axial direction relative to the housing using fixing device, and dismounting the stub shaft using guide device, the orientation of which relative to the gas turbine in at least one spatial direction is determined by a component of the remaining gas turbine, this taking place after fixing the N1 shaft and after dismounting the fan module.

Abstract: The invention relates to an edge material for panels, the edge material being constructed from a plurality of bonded layers. The edge material comprises a first layer, which is non-metallic, and a core layer, which is made of at least one metal layer. The edge material also comprises a second layer, which is non-metallic. Furthermore, the invention relates to a corresponding sandwich panel and to a corresponding cover layer for panels.

Abstract: A method for detecting cracks in an aircraft or gas turbine component includes ascertaining geometric data about the component using an optical measurement method, analyzing the geometric data, using an electronic evaluation device, so as to automatically recognize and/or classify at least one of cracks and other damage and storing a position of the at least one of cracks and other damage.

Abstract: A method for producing an escape route marking in a heatable and malleable support mold is described. The escape route marking has a transparent covering, a supporting element and a photoluminescent material. The method includes procuring the heatable and malleable support mold, inserting a supporting element into the support mold, arranging the photoluminescent material on the supporting element, arranging the transparent covering on the supporting element, heating and deforming the escape route marking in the support mold and solidifying the escape route marking in the support mold in a predetermined position. The resulting escape route marking is also described.

Abstract: A system for monitoring a nickel-cadmium battery comprising twenty nickel-cadmium battery cells connected in series in a passenger aircraft comprises a plurality of cell sensors for measuring the cell voltage and the cell temperature of individual battery cells and a data processing unit, and is set up to measure the battery current. The data processing unit is set up to determine a state of health value which is indicative of the state of health of the battery from the measurement data of the cell sensors and the measured battery current.

Abstract: The invention relates to a filter granulate for binding constituents of a gas flow. The invention furthermore relates to the use of such a filter granulate for filtering the breathing air in means of transport, more particularly aircraft, as well as to an aircraft equipped with a filter comprising a filter granulate according to the invention.

Abstract: Embodiments relate to a gas turbine blade for an aircraft engine, the gas turbine blade having a flow leading edge, a flow trailing edge, a suction side, and a pressure side, where the suction side and pressure side extend from the flow leading edge to the flow trailing edge, wherein the gas turbine blade has a damping layer on the flow leading edge and the damping layer comprising at least one matrix material and particles held in position by this matrix material. Further embodiments relate to a method of coating a gas turbine blade and a gas turbine incorporating a plurality of gas turbine blades in accordance with embodiments of the invention.

Abstract: Method for repairing a gas turbine component, which at least at the spot to be repaired consists of a ceramic composite material, where an energy beam locally heats the gas turbine component in a zone, and where one or more auxiliary materials and optionally fibers and/or particles are fed to this zone, wherein a ceramic is generated in the melting zone through the one or more auxiliary materials, and, optionally, the one or more auxiliary materials together with the fibers and/or particles forms a ceramic composite material.

Abstract: The invention relates to an aircraft seat having a seat assembly, wherein the seat assembly comprises a seat base and a seat surface assembly. The seat surface assembly is translationally movable in one direction relative to the seat base and can be blocked in at least one position. A force-limiting device is provided which, when activated, allows a relative movement between the seat base and the blocked seat surface assembly. Furthermore, the aircraft seat has a rocking ability about a transverse axis between the seat base and at least parts of the seat surface assembly, wherein the rocking ability of the seat surface assembly can be blocked by a blocking element. A force-limiting device is provided, which, when activated, allows a rocking movement of the blocked seat surface assembly.

Abstract: Method for removing a front seal plate from an aircraft engine, the method comprising at least the following steps: a) separating a part engine unit from the aircraft engine, the part engine unit comprising the core engine and the low-pressure turbine of the aircraft engine, b) removing a front seal plate nut from the part engine unit, c) removing the front seal plate from the part engine unit.

Abstract: The invention relates to a floor attachment assembly for mechanically connecting two aircraft seats to a floor structure of an aircraft, which assembly comprises four attachment points. The floor attachment assembly can be attached to the floor structure by means of one attachment element in each case at the four attachment points. The floor attachment assembly comprises two adapter plates, the two adapter plates being interconnected by means of a connection element. The mechanical connection between at least one of the adapter plates and at least one of the attachment elements is movable along at least one axis. Furthermore, the invention relates to a corresponding aircraft seat.

Abstract: The invention relates to a data-loading system and a corresponding method for loading software configurations into the electronic components of aircraft, said data-loading system comprising a databank system and a least one transportable data-loading device. Software configurations for at least one fleet of aircraft are stored in the databank system, and said data-loading device is configured to load, via a port, an allocated software configuration that has been obtained from said databank system into a data bus of an aircraft which corresponds to this software configuration. Said data-loading device is configured to load the latest individual software configurations of all of the aircraft of the fleet, from the databank system, and to store these on said data-loading device, this loading process taking place at a ground-based storing position by means of a data connection.