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: Device (1) for recontouring a gas turbine blade (2), comprising: at least one support (6a, 6b) configured to rest on an edge (3a) of the gas turbine blade (2) during the recontouring, at least one side bearing (5a, 5b) configured to rest on the suction- and/or pressure side (3b, 3c) of the gas turbine blade (2) in a lateral direction (7) during the recontouring, a machining unit (4) via which the gas turbine blade (2) is cutting machined in a machining direction (8) along the edge (3a), wherein the machining unit (4) can be displaced perpendicularly to the machining direction (8).

Abstract: An escape route marking for an airplane with a long luminous strip consisting of a photoluminescent material, a housing in which the luminous strip is arranged and that is designed clear or transparent at least on its top side, and a holding rail for the housing. The holding rail possesses a seating recess for the housing of the luminous strip and cover wings that project laterally on both sides of the holding rail in the longitudinal direction. The top side of the housing inserted in the holding recess is exposed, the cover wings are designed to be elastic, and at least the cover wings of the holding rail consist of a material that is more elastic than the material of the housing.

Abstract: A testing method for an escape path marking which has an installation position and is illuminated by a light source located in a defined position relative to the installation position, in order to charge the escape path marking for achieving afterglow, the following steps: An excitation curve A (?) for the escape path marking is provided; the irradiance E (?) of the light source is recorded for the installation position of the escape path marking; a weighted irradiance B (?) is determined as a product of the irradiance and the excitation curve; a charging irradiance (BiL) is determined as an integral over the weighted irradiance across the wavelength; and a characteristic curve Kt1 (BiL) depending upon the charging time t1 specifies what afterglow time emerges for the escape path marking with the charging time t1 for the charging irradiance (BiL).

Abstract: The invention concerns a securing system for passenger appliances in an aircraft, the securing system comprising a retaining device which can be mounted on or in an aircraft seat. The retaining device comprises a connection device, the connection device being displaceable between a park position and a use position. The securing system has a portable mounting adapter, the mounting adapter having a connection arrangement, and the connection device and the connection arrangement being detachably and mechanically connectable to each other in load-bearing manner. The mounting adapter is arranged to be connected to the passenger appliance in load-bearing manner.

Abstract: The invention relates to a wood substrate rendered flame-retardant. The invention provides that on the substrate there is a coating and/or impregnation system with a flame retardant selected from the group consisting of room-temperature-liquid organic halogen compounds and organic phosphorus compounds and organic boron compounds, and that there is also a layer of coating material applied thereto.

Abstract: A method for recontouring a blade of a gas turbine includes systematically melting a portion of a leading edge of the blade using an energy beam so as to form a new contour of hardened material substantially without incorporating additional material.

Abstract: A device for recontouring a gas turbine blade includes at least one support configured to rest on an edge of the gas turbine blade during the recontouring, at least one side bearing configured to rest on an intake side or an outlet side of the gas turbine blade during the recontouring and a machining unit for machining the gas turbine blade. The machining unit is configured to fuse at least one partial area of the edge of the gas turbine blade using a beam of energy that is targeted such that material of the blade solidifies into a new contour, substantially without the addition of supplementary material.

Abstract: A camera unit (12) in particular for surveillance in a transportation means (10) includes a digital camera (30), an electronic control device (32) for controlling and reading out the camera (30), and an interface (34) for outputting image data to a digital data network (16). The camera unit (12) comprises an active network component (36) for data distribution. The control device (32) is adapted to determine an individual identification from an identification means (40) which is provided at the mounting side at the installation point of the camera unit (12), and to determine at least one network parameter from the identification.

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 invention relates to a backrest for a vehicle seat, wherein the backrest includes a plurality of backrest modules. The backrest modules comprise a central portion, and at least one backrest module is mechanically linked to one or two further backrest modules of similar type at the central portion.

Abstract: A seat for a transport vehicle includes a seat surface, an armrest, and a child armrest. The child armrest is configured to adopt an adult position and a child position. In the adult position the child armrest is arranged in a stowed position in which the child armrest is incorporated in a contour of the armrest. In the child position the child armrest is arranged in a use position in which the child armrest has a reduced spacing from the seat surface in the vertical direction and a reduced spacing from an opposing armrest in the horizontal direction.

Abstract: The subject matter of the invention is a line replaceable unit (LRU) (2) for an aircraft (1). According to the invention, the LRU has: a) a first main memory (7) which contains the software required for certification of the LRU (2), b) a second main memory (8), which is separate from the first main memory (7) and in which a user of the LRU can store individual software which does not adversely affect the certification basis of the LRU. The subject matter of the invention is, furthermore, an arrangement comprising an LRU according to the invention and a database (12) with appropriate individual software, as well as a corresponding method for operation of an LRU.

Abstract: Escape route marking for an aircraft comprising photoluminescent pigments in a carrier material, which luminesce in the dark, the carrier material comprising silicone and the photoluminescent pigments having a mean particle size of less than 150 ?m.

Abstract: A testing method for an escape path marking which has an installation position and is illuminated by a light source located in a defined position relative to the installation position, in order to charge the escape path marking for achieving afterglow, the following steps: An excitation curve A (?) for the escape path marking is provided; the irradiance E (?) of the light source is recorded for the installation position of the escape path marking; a weighted irradiance B (?) is determined as a product of the irradiance and the excitation curve; a charging irradiance (BiL) is determined as an integral over the weighted irradiance across the wavelength; and a characteristic curve Kt1 (BiL) depending upon the charging time t1 specifies what afterglow time emerges for the escape path marking with the charging time t1 for the charging irradiance (BiL).

Abstract: Piece of furniture comprising an electronic switching element (1) for controlling a cabin function (10) for an airliner, wherein the piece of furniture has a structural layer (2) with a cover layer (3) arranged above the structural layer (2), wherein the electronic switching element is configured as a capacitive switching element and is arranged underneath the cover layer (3) inside and/or underneath the structural layer (2).

Abstract: The invention relates to a wood substrate rendered flame-retardant. The invention provides that on the substrate there is a coating and/or impregnation system with a flame retardant selected from the group consisting of room-temperature-liquid organic halogen compounds and organic phosphorus compounds and organic boron compounds, and that there is also a layer of coating material applied thereto.

Abstract: The invention relates to a backrest for a vehicle seat, wherein the backrest includes a plurality of backrest modules. The backrest modules comprise a central portion, and at least one backrest module is mechanically linked to one or two further backrest modules of similar type at the central portion.

Abstract: Method for removing a front seal plate (11) from an aircraft engine (1), the method comprising at least the following steps: a) separating a part engine unit (5) from the aircraft engine (1), the part engine unit (5) comprising the core engine (6) and the low-pressure turbine (7) of the aircraft engine (1), b) removing a front seal plate nut (10) from the part engine unit (5), c) removing the front seal plate (11) from the part engine unit (5).

Abstract: The invention relates to a method and an arrangement for re-creation of an optimized contour of the leading edges of gas-turbine blades, in which a gas-turbine blade (2) is passed by one or more grinding machine or machines (71, 71?) with the aid of a computer-controlled robot (10). The desired contour is achieved by following a movement procedure which is stored in a data memory (21). The stored movement procedure is designed to convert a blade from a previously determined statistical mean wear state to a likewise previously determined or calculated design contour. The contact pressure of the gas-turbine blade on the grinding disk or disks (71, 71?) is measured and is taken into account in the movement procedure of the robot (10) such that the desired design contour is achieved irrespective of the initial contour and wear of the grinding disks.