Abstract: A device for non-destructive control of a component analyzes distribution of a leakage magnetic field emitted by the component when it is subjected to an exciting magnetic field, includes means for generating an exciting magnetic field inside the component to be tested, and means for detecting and measuring the distribution of the magnetic field. The set of means is integrated in a flexible housing to form a device in the form of a flexible coating for being fixed on a region of the surface of the component to be tested. The disclosed embodiments are useful for non-destructive testing of aircraft components, but may also be used in all industrial sectors where testing the integrity of components is important, such as the automotive, railway, marine or nuclear industry.

Abstract: A galley including a galley body on a cabin floor for accommodating storage boxes, appliances and at least one service cart; storage boxes for storing goods, and a service cart. The galley body has a plurality of vertical levels that are substantially equidistant from each other, each of the vertical levels divided into a plurality of laterally adjacent compartments whose horizontal and vertical dimensions are equal to an integer multiple of the respective dimensions of a single one of the storage boxes. A transfer table is provided in front of the galley body for access to the compartments. A method includes catering for passengers on an aircraft.

Abstract: A surface seal for sealing a riveted and/or screwed joint between a first and a second component of an aircraft. The surface seal is arranged in the region of joining surfaces of the first and the second component. The surface seal is formed with a pressure-resistant plastic film that is provided with a pressure-sensitive adhesive layer on both sides. The surface seal 1 may furthermore comprise elements for detecting cracks. A method for producing a riveted and/or screwed joint between a first and a second component of an aircraft is also provided, with the joint being sealed with the surface seal.

Abstract: An aerodynamic element attachable to a primary wing to extend in a longitudinal direction at an angle to a spanwise direction of the primary wing. The aerodynamic element includes a downstream end having at least two flow flaps arranged next to each other and oriented in the longitudinal direction of the aerodynamic element.

Abstract: A method for detecting and localizing a fuel leakage in the engine of a multi-engine aircraft consisting in determining a fuel consumption for each aircraft engine, in comparing the consumption of each engine with the other aircraft engines, in determining the engine exhibiting the greater fuel consumption ratio, in determining the excess consumption ratio of the aforementioned engine with respect to the other engines, in checking whether the excessive consumption is caused by a leakage and in triggering an alarm if the step is checked. A system for detecting and localizing a fuel leakage in the engine of a multi-engine aircraft including an airborne computer for carrying out the aforementioned method is also disclosed.

Abstract: A process and a device for detecting aircrafts circulating in an air space surrounding an airplane is disclosed. The device (1A) comprises means (2, 3) for detecting an aircraft circulating in the air space surrounding the airplane and, in case of a detection, for determining a first position and a second position of the aircraft with respect to the airplane, and means (8A) for comparing said first and second positions so as to check whether they match.

Abstract: A method of joining a first component to a second component, the method comprising preparing the first component by forming an array of projections extending from a bond surface of the first component, each projection having a base, a tapered tip and a tapered overhang beneath the tip, wherein the overhang has an undercut surface which is inclined and faces towards the local bond surface; bringing the components together so as to embed the projections in the second component; and hardening the second component after the array of projections has been embedded into it. Also, a joint so formed.

Abstract: A method for starting up an aircraft turbine engine using an electric starter is provided. The aircraft turbine engine is provided with at least one hydraulic fluid circuit for lubricating the aircraft turbine engine, the aircraft turbine engine lubricating circuit is provided with a temperature-regulating section that is able to remove the heat generated by the aircraft turbine engine when the aircraft turbine engine is running, the electric starter is provided with at least one hydraulic fluid circuit for lubricating parts of the electric starter, and the lubricating circuit of the electric starter is provided with the temperature-regulating section that is able to remove the heat emitted by the electric starter when the lubricating circuit of the electric starter is operating.

Abstract: The invention relates to a method for configuring interfaces of computers belonging to an avionic platform. The platform implements a plurality of avionic functions which may exchange functional messages, each functional message comprising one or more parameters. Each avionic function is implemented by means of software modules hosted by computers. For each software module hosted by a computer, signal occurrences are generated for transmitting all the parameters of the functional messages of the function associated with the software module, this on the different communications media. Next all the occurrences are grouped per functional system, parameter and communications medium in order to configure the interfaces of these computers.

Abstract: Method for determination of a rigid value of an aerodynamic coefficient of an aircraft, in which measurements are made in a wind tunnel on a model of the said aircraft and, on the basis of these measurements, at least one value, known as flexible model value, of this aerodynamic coefficient is determined, characterized in that a rigid value of the aerodynamic coefficient is calculated on the basis of the said flexible model value(s) and a correction taking into account the flexibility of the model. A plurality of flexible model values is determined on the basis of measurements made by varying the parameter q/E and maintaining the angle of incidence at a constant value, and the correction consists in an extrapolation operation providing a value of the aerodynamic coefficient corresponding to q/E=0. As a variant, a single flexible model is determined and the correction consists in adjusting the said value with the aid of a correction factor.

Abstract: The invention relates to a device, in particular a connection rod, for bracing a fuselage structure and/or for fastening components on the fuselage structure. In one embodiment, the joints are integrated into fuselage structure for linking on both sides of connection rod to fuselage structure. As a result of the integration of joints, a reduced number of individual parts is produced in comparison to previously known embodiments, which leads to a reduction in weight, a reduced maintenance and servicing outlay and an improved reliability against failure. Moreover, device according to the invention enables the introduction of forces in the region of neutral fibers of fuselage structure. A further configuration of device provides only a one-sided articulated linking of a component to fuselage structure by means of (first) end portion. Second end portion is screwed to fuselage structure. To this end, both end portions are provided with a thread at least in sections.

Abstract: A system box for accommodating aircraft systems, and for load transmission between an aircraft structure and a crew rest compartment. The system box comprises a first, a second and a third region, wherein the three regions differ from each other. The first region is adapted attachment of the system box to the primary structure of the aircraft, wherein the second region is adapted for mechanical contact with a crew rest compartment for the aircrew. The mechanical contact in turn is adapted for load transmission between the aircraft structure and the crew rest compartment. Necessary aircraft systems are accommodated in the third region of the system box.

Abstract: A device for confirming the engine thrust of an aircraft is disclosed. The device, via an operating logic unit (14) of each engine processing different information, including a warning indicator (15) connected to the unit (14) delivers or not thrust confirmation information at the level of the cockpit.

Abstract: A high-lift system on the wing of an aircraft and a method for its operation are described. High-lift flaps (2) which are arranged on the wing (1) are extended from a retracted position in order to increase the lift, and a slot (3) through which flow passes from the lower face to the upper face of the wing (1) is opened (advanced slat/flap-gap control). According to the invention, the slot (3) through which flow passes is opened independently of the position of the high-lift flap (2). This makes it possible to selectively achieve a better maximum coefficient of lift (CL) or a better lift-to-drag ratio with less noise being produced.

Abstract: An engine unit for an aircraft including an engine, a device for hooking the engine, and a nacelle surrounding the engine and provided with fan cowls, the device for hooking including a rigid structure and a front aerodynamic structure whereon the fan cowls are articulated, the front aerodynamic structure including a cradle with a rear mechanism of hooking mounted on the rigid structure. The cradle also includes a front mechanism of hooking mounted on an air inlet of the nacelle.

Abstract: Disclosed is a method and device for assisting guidance of an aircraft. A flight management system is used to determine guidance instructions that include speed instructions having at least one flight time constraint to guide the aircraft to a check-point. An accuracy level for complying with the flight time constraint and at least one error level for at least one flight parameter are generated by an accuracy generating unit. An operating margin for at least one second parameter is determined from the determined accuracy and error levels, with the operating margin being representative of air speed criterion values of the aircraft. A range determining unit is used to determine whether the range of air speed criterion values is within an air speed envelope of the aircraft, and the speed instructions are modified when the range of air speed criterion values is not within the air speed envelope.

Abstract: A method of lifting an aircraft at a lifting location, the method comprising: securing a fitting to the aircraft when the aircraft is at the lifting location; engaging the fitting with a crane hook; transmitting lifting load from the crane hook to the aircraft via the fitting; and removing the fitting from the aircraft. A fitting for transmitting lifting loads from a crane hook to an item, the fitting comprising: an attachment member configured to be secured to the item; and a lifting member which is pivotally coupled to the attachment member and configured to be engaged by the crane hook so as to transmit lifting loads from the crane hook to the item. A crane hook with a ball-and-socket connection is provided.

Abstract: Provided herein are drainage valves for removing water accumulated in the lower part of fuel tanks of an aircraft. The valves can be affixed in correspondence with a lower skin forming part of the tanks. The lower skin includes recesses for the complementary housing of the heads of the valves that, in combination with some axial fastening nuts, immobilize the valves to that skin. The recesses can comprise a conical structure obtained by deformation of the lower skin, and with the deformation an inner elevated seat is further obtained, on which seat the axial fastening nuts press, maintaining the thickness of the skin in the area where the valves are located, thus preventing the area from weakening as it happens conventionally.

Abstract: A method for improving the performance in developing an interprocess digital mockup. Product data elements are compiled from a digital mockup, wherein the product data elements contain geometry data elements and meta data elements. The geometry data elements are addressed and assigned to a geometry structure. The meta data elements are addressed and assigned to a meta structure. The geometry structure and the meta structure are subsequently linked by a communication protocol such that bidirectional interaction between the geometry structure and the meta structure is realized.

Abstract: An aircraft wing assembly, comprising a front spar, a rear spar, and upper and lower wing covers extending between the front and rear spars, wherein the upper and/or lower wing cover overhangs the rear spar and has a non-linear trailing edge profile forming an array of tabs and cut-outs. Also, a method of assembling the aircraft wing.