Abstract: Disclosed is a reinforcing material for the local reinforcement of a component formed with a composite material, in particular in areas of force introduction and/or connecting areas. The reinforcing material is formed by a metallic sheet-like formation, the metallic sheet-like formation having a surface with increased roughness to improve adhesion and a coating applied to the surface to provide a seal and improve the bond with the composite material. As a result of the presence of a coating on the metallic sheet-like formation, once it has been rolled up on supply rolls, said sheet-like formation can be drawn off from the supply rolls and at the same time processed in an automated manner by means of known computer-controlled laying devices with CRP prepreg materials in web form by laying layer by layer to produce components, in particular of large format, for aircraft.

Abstract: A holder assembly for a line installation in an opening of a support structure of an aircraft, includes at least one holder element to mount a line that is guided through the opening, with the line featuring a clamping section, arranged radially on the outside, to be attached to the opening as well as at least one central receiving section to fix the line, wherein the receiving section of a first holder element encompasses the line hook-like, and the receiving section of at least a second, oppositely positioned holder element also encompasses the line hook-like such that both hook-like receiving sections encompass the line.

Abstract: A repair process for a composite material panel that forms part of a fuselage, wings, or stabilizers of an aircraft, with the panel having large dimensions and including irregular contours in some areas and edges prone to damages occurring from handling and assembly of the panel. The process a) locates the damage in the element of the composite material panel; b) sands the area that includes the damage in an area larger than the damage, makes a cut in the panel, having the cut of a same form as a piece that will serve to repair panel; c) places the piece in the cut, so that it is perfectly flush with the panel to be repaired; and d) attaches the piece to the composite material panel.

Abstract: The invention relates to a method of assisting piloting an aircraft. The method is performed when the real position of a symbol for display lies outside the display limit of the screen. The symbol is representative of a parameter associated with the dynamic behavior of the aircraft (FPV, . . . ) or liable to influence said behavior (FD, . . . ). The symbol possesses two components, and the first component is to be given precedence on display over the second component. In the method, the display of the symbol depends firstly on the orthogonal projection (FPV-lock) of the real position (FPV) of the symbol onto the axis of the first component, and secondly on the position of said projection relative to the display limit of the screen. Such a display makes it possible to give reliable information to the pilot.

Abstract: The invention relates to a method of assembling composite material parts (10, 12). The method makes provision for: mounting (S6) the parts for assembly under stress on a stand (14), which parts have been partially polymerized; heating (S7) these parts so as to polymerize them completely, thereby enabling the stresses in the parts to be relaxed and enabling them to match the shape of the sand; cooling (S8) the parts; and assembling (S9) in conventional manner the parts as cooled in this way.

Abstract: The invention has as its object in particular a method and a device for aiding in the diagnosis and in the decision on operation of an aircraft comprising means for detection of failures relating to the pieces of equipment thereof. After having received (400) at least one alert linked to the detection of at least one failure relating to at least one piece of equipment of the said aircraft, the said at least one alert comprising at least one indication relating to the said at least one failure, and at least one information item relating to the next mission of the said aircraft, a database comprising a minimum equipment list and operating conditions and/or limitations associated with the operation thereof is accessed.

Abstract: This disclosure relates to a cooler for an aircraft cooling system. The cooler includes a matrix body in which a plurality of coolant channels are designed and extend from a first surface of the matrix body to a second surface of the matrix body, allowing a coolant to flow through the matrix body. The matrix body of the cooler is designed to form a section of the outer skin of the aircraft.

Abstract: A motorization mechanism for a wheel of a landing gear assembly, including an input gear driven by a motor-reducer unit; a pendulum element, carrying two intermediate gear wheels driven in rotation by this element, with the intermediate gear wheels having synchronized rotation blocking mechanisms such that the two intermediate gear wheels can be simultaneously engaged or simultaneously released. The angular displacement of the pendulum element around its rotation axis is limited by a first and a second adjustable stop. These adjustable stops are set so that when the pendulum element comes into contact with an adjustable stop, the blocking mechanism of the intermediate gear wheels is freed, whereas it is engaged when the pendulum element is in the neutral position. This pendulum assembly faces a cog wheel that is capable of driving the hub of the said wheel.

Abstract: An air intake of an aircraft nacelle includes: on the one hand, a lip (42) that is defined by a wall (52) whose surface that is in contact with the aerodynamic flows is extended on the inside of the nacelle by an inside wall (44) that borders a pipe that empties out at a power plant and on the outside of the nacelle by an outside wall (46), and, on the other hand, a surface-type Joule-effect defrosting system (58); at least a first alveolar structure (60.1) that is made of a material that conducts the heat and that is flattened against the inside surface of the wall (52) and inserted between the wall (52) and the defrosting system (58), and at least one second alveolar structure (60.2) that is made of composite material that is adjacent to the first structure (60.1).

Abstract: An aircraft assembly comprising a wing and an engine attachment pylon fixed to the wing by an attachment comprising a first and a second front wing system cleat connecting a rigid structure of the attachment pylon and a front longeron of the wing. The first front wing system cleat comprises a first shearing pin oriented in the transversal direction to ensure take-up of forces exerted in the longitudinal and vertical directions of the pylon, and the second front wing system cleat comprises a second shearing pin oriented in the longitudinal direction to ensure take-up of forces exerted in the transversal and vertical directions of the pylon.

Abstract: A system for preventing icing in a conduit, as can occur in an aircraft's air conditioning system, includes at least one sensor for acquiring mechanical oscillations of the conduits, an electronic evaluation unit and an electronic control unit. The sensor is connected to the electronic evaluation unit, which knows characteristics relating to the oscillation behavior of the conduit and is equipped to compare the measured conduit oscillations with these characteristics, and through correlation to interpret them as conduit icing, and in the case of conduit icing to emit a signal to the control unit. If the operation-associated oscillations are inadequate, oscillations can be generated or amplified through an actuator. With this system an icing state within the conduit can be detected without the use of sensors located in the interior cross section of the conduit, which itself serves as a sensitive element.

Abstract: A device (10) for protection of an external probe (12) of an aircraft that projects through an opening (14) that is made in the outside surface (16) of the aircraft. The protective device (10) includes a rigid flange (22) for attachment to the outside surface (16) of the aircraft and a flexible envelope (24) for protection of the probe. The flange is attached by rapid attachment elements to the outside surface of the aircraft.

Abstract: A method for laying a floor covering onto a floor in a cabin of a vehicle comprises the steps of applying a connection means to an element of a group comprising the floor covering and a floor, compacting the floor covering into a compact unit having an open end, bringing the floor covering into the cabin, pulling the open end of the floor covering along a length of the cabin beneath seats disposed in the cabin on the cabin floor and connecting the floor covering to the cabin floor using the connection means. The connection is made by way of one or more adhesive layers, for example. In this way, a carpet floor can be laid or replaced in a cabin of a vehicle without having to remove the seats located in the cabin.

Abstract: An energy protecting device for three and four-engined aircraft includes a detecting unit configured to detect failure of each engine. A control unit is configured to provide a protective function by controlling maximum thrust of each engine. A triggering unit is configured to monitor a plurality of parameters and trigger the control unit to provide maximum thrust at predetermined conditions of the monitored parameters. An inhibiting unit is linked to the triggering unit and is configured to inhibit the protective function, when at least one of the engine on the wings of the aircraft has failed. The control unit is also configured to control the engines that have not failed to minimize thrust imbalance.

Abstract: The device includes, but is not limited to a calculating unite for automatically applying, if conditions for turning of the aircraft are met, a symmetrical braking value at a brake assembly, then in the course of the turn automatically distributing this symmetrical braking value in differential braking between braking device of the left main landing gear and braking device of the right main landing gear of the aircraft, as a function of current directional command orders, in such a way as to maintain a constant overall braking level, at least for directional command orders below a predetermined threshold.

Abstract: A device for mixing at least two separate streams of components which, when mixed, form a combined fluid stream. The device comprises a conduit with at least two separate passageways leading to exit openings at an end face of the conduit. Each passageway communicates with a separate component stream and is arranged to direct the separate component stream in a downstream direction. The exit openings each have a predetermined cross-sectional flow area. A separate channel is located at a downstream end of each passageway exit opening. The channels are arranged to redirect the flow from each passageway to an axial direction. A single mixing chamber communicates with all of the separate channels, the mixing chamber being arranged to receive each of the component streams at an upstream end thereof and to permit a mixing of the component streams. An outlet is arranged downstream of the mixing chamber through which the combined fluid stream is dispensed.

Abstract: The present invention provides a fireproof bulkhead, having a highly porous structure with an intumescent coating, the highly porous structure being formed as a reticulated foam or as a highly porous pimple or nub structure.

Abstract: The present invention concerns a device for use in an aircraft fuel pressure sensor line. More particularly, but not exclusively, this invention concerns a fuel pressure sensor line connecting an aircraft fuel pump to a pressure sensor. The invention also concerns a fuel pressure sensor line reservoir for use with a sensor line connecting an aircraft fuel pump to a pressure sensor. An aircraft fuel pump system comprises an aircraft fuel pump and a pressure sensor connected the aircraft fuel pump via a sensor line. The sensor line includes a reservoir located between the aircraft fuel pump and the pressure sensor. The reservoir acts to prevent liquid contacting the pressure switch when the fuel pump is not active.

Abstract: A holding arrangement for a mobile device in a cabin of a vehicle has a cabin equipment component, a support device arranged on the cabin equipment component, a holding device for holding a mobile device and a covering pane. The support device is designed to receive the holding device and further has an access opening arranged on a side opposite the cabin equipment component. Furthermore, the support device is designed to slidably hold the covering pane for opening and closing the access opening arranged on the side opposite the cabin equipment component in such a manner that the covering pane is movable to a closed position and to an open position, wherein in its open position the covering pane extends beyond the support device. Hereby, an improved holding function and temporary theft prevention may be accomplished.

Abstract: An electrical cabinet of an aircraft is provided. The electrical cabinet includes at least one motherboard including on a first face sockets into which are plugged PCB boards ensuring one or more electrical functions, the said electrical cabinet being linked to the electrical circuit of the aircraft organized as various electrical harnesses by way of an electrical connection system, characterized in that the electrical connection system comprises at the level of the second face of the motherboard at least one additional layer, the free face of the last additional layer comprising sockets each ensuring electrical connection with an electrical harness of the aircraft, the additional layer or layers comprising tracks which make it possible to reorganize the electrical circuits emanating from the sockets intended for the PCB boards so as to render them compliant with the sockets intended for the harnesses of the aircraft.