Abstract: The disclosed embodiments offer a solution for controlling the thickness of a finished structural composite part when precise tolerances must be complied with for the quality of the assembly and in order to ease the assembly operations of this part. In order to implement the method according to the disclosed embodiments, an additional layer of plies made out of a non-structural composite material, called calibrating plies, is applied onto the structural plies of the structural part, at least in an area where the thickness must be maintained within close tolerances and, after the composite material has been cured, the calibrating plies are machined in order to obtain the thickness required for the finished part. The thickness of the calibrating plies applied is determined according to the possible thicknesses of structural plies, taking into account the manufacturing spreads so that the machining operation for the calibrating plies does not affect the structural plies.

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: 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: 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: 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: 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: 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 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: 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: 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: 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: An aircraft tail surface, such as a horizontal tail plane or a vertical tail plane, including a leading edge having, in at least a section along the tail span, an undulated shape formed by a continuous series of smooth protrusions and recesses so that, in icing conditions, the ice accretion is produced only on the peaks of the protrusions and on the bottoms of the recesses, thereby creating a channeled airflow and an arrangement of air vortices which impart energy to the airflow in the aerofoil boundary layer which delay the airflow separation that causes the stall, thus reducing the detrimental effects of ice accretion in its aerodynamic performance.

Abstract: A locking mechanism for an aircraft door includes a plurality of frame-side fittings and a plurality of door-side fittings. Each frame-side fitting includes a pin with an eccentric rotary cylinder mounted on each pin. Each door-side fitting includes an eccentric rotary latch configured to encompass at least a section of a corresponding rotary cylinder. Also a method of locking a door using the locking mechanism.

Abstract: An exhaust silencer for the air conditioning system of an aircraft is disclosed.

Abstract: An aircraft engine attachment pylon including a box formed by an assembly of a first spar, a second spar, two lateral panels, and an aft engine attachment fitted with an aft attachment body. The engine attachment may be provided with two lateral fittings associated with the two lateral panels to which they are fixed to and project from laterally outside the box, each of the fittings forming a plane attachment interface with the attachment body through which bolts pass. Each attachment interface may be in the shape of a straight segment inclined at 45° from a vertical direction of the pylon.

Abstract: During the cooking of a composite component including layers of fibers embedded into a matrix, a superficial pressure is exerted. This superficial pressure generates a deformation that causes local contacts of fibers of at least two layers without damaging these fibers. As a result, when an electrical current is applied on a side of the composite component, such as during a lightning strike or a short circuit, the added local contacts enable the electric current to flow along multiple fibers in the composite component, thereby avoiding significant spikes in temperature.

Abstract: A drilling system is formed as a support structure to be mounted on a surface to be drilled, a beam supported by the support structure, a tool holder supported by the beam and having a locking orifice, and a drilling tool mounted on the tool holder by sliding connection in the direction parallel to the drilling axis. The drilling tool includes a bearing mandrel and an expandable ring closely fitting the bearing mandrel along a tapered contact surface for expanding the ring to ensure its locking in the locking orifice. Relative movement between the ring locked in the locking orifice and the bearing mandrel procures, by movement of the drilling tool relative to the tool holder via the slide connection, a movement of the bearing mandrel towards the surface to be drilled, through the locking orifice.

Abstract: A de-icing device includes a hot air circuit including an inlet for hot air bled from an engine, and a duct connecting the inlet to an outlet of the circuit which opens towards the leading edge. The device also includes electrical heating means associated with the duct, and control means for controlling the heating means connected to detection means that detect the temperature of the hot air downstream of the heating means and are able to activate these if the detected temperature of the bled air is below a value corresponding to a minimum temperature required for de-icing, increased by a predetermined margin. The range of temperatures of the hot air supplied to the leading edge is lowered overall, whereas the minimum de-icing temperature is assured. Composite materials can be used near the leading edge without being damaged.

Abstract: The invention relates to a method according to which an aircraft (10) is moved along the ground by means of at least two separate appliances (12) connected to the aircraft independently from each other or other appliances. A control element is provided for moving an aircraft, said element sending instructions to at least two separate appliances in order to move the aircraft along the ground by means of the appliances. The invention also relates to an appliance (12) for implementing the method according to the invention, which can communicate with an identical appliance in order to transmit and/or receive at least one datum relating to a position and/or a movement of one of the appliances.