Abstract: A tool holds and axially fixes a high-pressure shaft of an aircraft engine in a state where a high-pressure turbine stage is demounted. The tool includes: a shaft end cap having an inner radius, which is adapted to a predetermined shaft diameter, the shaft end cap plugs onto a turbine-side end of the high-pressure shaft; a shaft end cap receptacle receives the shaft end cap in a radially movable manner and in an axially limited manner in a first direction; a connector is fastenable to the shaft end cap receptacle and has a shank, which is insertable into the high-pressure shaft, the connector being configured to axially secure the shaft end cap receptacle; and a spring element, which is positionally fixed with respect to the shaft end cap receptacle, the spring element being configured to apply a predetermined spring force to the shaft end cap in the radial direction.

Abstract: A plug-in connection box for vehicles has a socket and a return apparatus. The socket, is accessible from an access side and has an insertion direction. The socket is arranged in a pivot body, which is mounted in a movable manner in relation to a receptacle in such a way that the insertion direction of the socket is pivotable at an angle in all directions starting from a stationary state of the pivot body. The return apparatus is configured to return the pivot body to the stationary state.

Abstract: An attachment housing is for fastening to an exterior side of an aircraft. The attachment housing has a functional compartment. The functional compartment is divided in two, and has a ventilation compartment and a protective compartment. A surrounding wall is configured to separate the ventilation compartment from an environment. The surrounding wall has at least one ventilation opening for air exchange between the ventilation compartment and the environment. A dividing wall is arranged between the ventilation compartment and the protective compartment. The dividing wall has at least one passage opening for air exchange between the ventilation compartment and the protective compartment. The passage opening is configured to counter act a penetration of water, moisture, or particles into the protective compartment.

Abstract: A functional enhancement module is for vehicles and for enhancing a functional module which is supplied with electric power via a power supply bus. The functional enhancement module is configured to be supplied with the electric power via the power supply bus. The functional enhancement module includes: a controller having a power specification for a maximum power flow of the functional module and being configured to detect a current power flow at a reference point; and a power controller configured to control a power take-up of the functional enhancement module. The controller is configured to control the power controller in accordance with the detected power flow, such that a combined power take-up of the functional module and the functional enhancement module does not exceed the power specification.

Abstract: A method cleans surfaces in an internal volume of an aircraft component through which a medium flows. The method includes: connecting the internal volume to be cleaned to a steam generator; generating a cleaning steam having a predetermined vapour pressure and temperature by the steam generator; applying the cleaning steam to the surfaces to be cleaned in the internal volume; maintaining the vapour pressure and the temperature within the internal volume for the duration of a predetermined condensation time; generating a pressure drop in the internal volume of the aircraft component, in order to vaporise the portion of the cleaning steam that condensed during the condensation time; and removing the cleaning steam from the internal volume via a discharge device.

Abstract: A method for borescope inspection of a component uses a stereo borescope for recording the component. The method includes: generating two stereoscopic partial images by means of the stereo borescope; calculating 3D triangulation data from the two stereoscopic partial images; registering the 3D triangulation data to a 3D CAD reference model of the component captured by the stereo borescope, while determining a projection point; projecting 2D image data determined from the two stereoscopic partial images onto the 3D CAD reference model from the determined projection point; and determining damage by image analysis of the projected 2D image data and by ascertaining deviations of the registered 3D triangulation data vis-à-vis the 3D CAD reference model.

Abstract: A sandwich structure includes two cover layers and a core arranged therebetween, and at least one connecting element for connection to further components. The connecting element has an insert, which is embedded into the sandwich structure at a cover layer of the two cover layers. An embedding depth of the insert is less than a thickness of the core. The connecting element is finished flush with an outer side of the cover layer via which the connecting element is embedded or protrudes from the cover layer.

Abstract: A method for cleaning a jet engine includes introducing a cleaning medium having solid materials into the engine by way of at least one discharging device, wherein the cleaning medium exits from the discharging device at an exit speed of 80 m/s or less.

Abstract: A device for recontouring a gas turbine blade includes: a holding device having at least one cutting tool; and a guide configured to guide the cutting tool along a leading edge of the gas turbine blade. The cutting tool is configured to remove material from the gas turbine blade using a rotational movement about an axis of rotation. The axis of rotation forms an angle together with a chord of the gas turbine blade in a profile section plane, which extends perpendicularly to a radial extent of the gas turbine blade, and the angle is less than 45°.

Abstract: A device that equalizes an aircraft pressure difference has a separating wall, fixable to the aircraft, and a decompression valve. The wall is for fluidically separating first and second spaces, and has a flow opening that fluidically connects the spaces. The valve closes the flow opening. A securing element on the valve or wall enables a release of the valve when a pressure gradient between the spaces is exceeded, such that there is a fluidic connection between the spaces. The receiving element on the wall or valve is connected to the receiving element. The securing element has a rotary element and fixing elements. The rotary element is rotatably mounted about a rotational shaft. The rotary element is receivable in the receiving element. The fixing elements non-rotatably fix the rotary element beneath the predetermined pressure gradient. At least one of the fixing elements is a spring.

Abstract: A radome wall for communication in a frequency band of from 17 to 31 GHz for use on commercial aircraft includes a multilayer structure having an alternating arrangement of force-absorbing solid cover layers and sheer-rigid core layers. The radome wall includes at least four of the cover layers, of which two form outer sides of the radome wall, the cover layers and the core layers being made of a dielectric material.

Abstract: A method determines a thrust force of an aircraft engine that is attached to an aircraft by a force transferring element having a strain gauge for determining its strain state and a temperature sensor for measuring a surface temperature of the force transferring element adjacent to the strain gauge. The method includes: determining the surface temperature; determining a strain of the force transferring element; determining the strain state of the force transferring element based on the determined strain and compensating for temperature effects by taking into account the surface temperature, the compensation of the temperature effects taking into account both static and transient influences; and calculating the thrust force of the aircraft engine from the determined strain state.

Abstract: The invention concerns a communications system and a communications method and software for passengers in an aircraft. The aircraft comprises an aircraft-supported data-processing arrangement and at least one on-board communications interface for communication with a passenger appliance, the communications system being arranged to receive a passenger profile from the passenger appliance by means of the communications interface of the aircraft and transmitting it to the data-processing arrangement.

Abstract: A height-adjustable device has synchronously height-adjustable lifting devices each having a standing and lifting element, which are height-adjustable relative thereto. The height adjustment is configured to be carried out via pulling elements, formed by redirection devices, to raise the lifting element relative to the standing element. Each pulling element is secured in a non-positive or positive locking manner to lifting devices, and each are configured such that a lengthening in the region of the first lifting device brings about a synchronous shortening in the region of the second lifting device. Each pulling element is constructed to raise only the one lifting element relative to the standing element. The height-adjustable device has a locking device that locks the pulling elements by a non-positive or positive locking engagement on the corresponding one of the pulling elements. The locking device is constructed to synchronise the movement of the pulling elements.

Abstract: A data communication system has: a cabin module with a transmission and reception unit; and a furniture module, which is fastened in a furniture item anchored in a cabin, and has a transmission and reception unit. The transmission and reception units each have a controllable light source and a light sensor. The furniture module is disposed relative to the cabin module such that light emanating from the light source of the transmission and reception unit of the cabin module is detectable by the light sensor of the transmission and reception unit of the furniture module and light emanating from the light source of the transmission and reception unit of the furniture module is detectable by the light sensor of the transmission and reception unit the one cabin module.

Abstract: A device for cleaning the core engine of a jet engine includes a supply unit, which provides the cleaning medium, a nozzle unit, which is configured for feeding the cleaning medium into the core engine, and a line connection between the supply unit and the nozzle unit. The nozzle unit includes a means for the rotationally fixed connection to the fan shaft of the jet engine, and that a rotary coupling is provided between the nozzle unit and the line connection. The device may be arranged with a turbo fan jet engine. A method for cleaning, the core engine of a jet engine uses the device.

Abstract: Aircraft seat having a first seat element and a second seat element, the second seat element being mounted so as to be adjustable relative to the first seat element, a spring element that moves the second seat element relative to the first seat element being provided, it being possible for the force acting on the second seat element by the spring element to be released by an actuating element such that the spring element is deactivated in a first switching position of the actuating element, and the spring element is activated in a second switching position of the actuating element, where a force limitation element is provided, by which the force acting on the second seat element by the spring element can be limited to a predetermined value such that intermediate states between the first and the second switching positions can also be set.

Abstract: The invention relates to a floor connection assembly for the mechanical connection of an aircraft seat to a floor structure of an aircraft, comprising at least three fastening points, wherein the floor connection assembly can be fastened on at least three fastening points with in each case one fastening element to the floor structure. The floor connection assembly comprises an adapter plate, wherein the mechanical connection between the adapter plate and the fastening elements is supported about at least one axis in a substantially torque-free manner.

Abstract: The object of the invention is a device for cleaning the core engine of a jet engine, having a supply unit, which provides the cleaning medium, a nozzle unit, which is configured for feeding the cleaning medium into the core engine, and a line connection between the supply unit and the nozzle unit. The invention provides that the nozzle unit has a means for the rotationally fixed connection to the fan shaft of the jet engine, and that a rotary coupling is provided between the nozzle unit and the line connection. The object of the invention is further an arrangement of such a device and a turbo fan jet engine, and a method for cleaning the core engine of a jet engine using the device.

Abstract: A method for a position determination of a turbine blade of a high-pressure turbine stage of a gas turbine that is connected to a high-pressure compressor via a shaft, wherein each turbine blade of the high-pressure turbine is recorded on a record card with a relative position. The method includes: determining a position of a blade lock of a stage of the high-pressure compressor, where the stage is selected such that, when the gas turbine is mounted, the blade lock is brought into view of a boroscope, which is guided through a boroscope opening on the gas turbine by rotating the shaft, and so that the blade lock can be identified; and marking that turbine blade on the record card that is in view of a second boroscope, which is guided through a second boroscope opening on the gas turbine when the blade lock is in view of the boroscope.