Abstract: An aircraft comprises an outer aerodynamic surface and an exhaust duct having an opening in the outer aerodynamic surface. The duct has a duct wall curved at the opening so as to blend with the aerodynamic surface downstream of the duct. At least one fixed flow diverter is provided for diverting high temperature exhaust gas exiting the duct away from the aerodynamic surface immediately downstream of the duct opening. The curved duct wall provides low aerodynamic drag in cruise. The flow diverter(s) give aircraft designers freedom in terms of where the duct opening can be positioned without compromising the structural integrity of the aircraft through excessive heating of the aerodynamic surface immediately downstream of the duct opening.

Abstract: The disclosed embodiments relate to a fuel line valve for an aircraft, that includes a shell capable of rotation inside the valve body and connected to a driving shaft driven by an electric actuator. The valve further includes a torque generation means and position detection means. The torque generation means are connected to the shell and generate a torque that varies based on the position of said shell in the valve body on the driving shaft. The position detection means provide electric signals characterizing the positions of said driving shaft. The disclosed embodiments also relate to a method for diagnosing the operation of such a valve in order to detect a failure during the operation thereof, and to a device for implementing said method.

Abstract: A locking/unlocking device for electronic boards, the boards being configured to be inserted into an electronic cabinet with at least one slotted plate fit into the rack of the electronic cabinet, the device including a substantially rectangular frame supporting at least one locking slide that locks the electronic board onto the slotted plate through the action of a locking element. The device further includes an extracting lever that rotates between a rest and a locking position around a lateral Y1 axis, the extracting lever fitted so that exerting force is possible along the longitudinal X axis between the electronic board, or the frame and the rack, with the locking unit including an extension to be placed outside, opposite the extracting lever along the longitudinal axis X of the board when the two levers are engaged in the locking position.

Abstract: The vertical profile management device includes a flight management system unit that selects a plurality of successive standard cruise sections, each comprising a level phase and a transition phase. The cruise sections are defined by a plurality of features, including waypoints corresponding to a section starting point and a section ending point, a transition type, a transition mode, a transition speed, a level altitude, and a level speed. The flight management system unit also joins together the successive cruise sections in order to form a vertical profile of a flight plan. The cruise sections are configured to be added, removed, or re-sequenced in the flight plan because each section ending point is configured to be the section starting point of a next cruise section in the series.

Abstract: A system is provided for the detection of deposits in a fluid line that includes, but is not limited to a measuring body, and ultrasonic transducer and an ultrasonic receiver and at least one evaluation unit connected to the ultrasonic transducer and the ultrasonic receiver. The ultrasonic transducer transmits an ultrasonic signal and the ultrasonic receiver receives response signals generated by reflections in the fluid line. From known geometric changes in shape of the fluid line, resulting response signals are finally filtered out of the response signal sequence and from the remaining response signals relating to the deposits, the distances can be calculated between the ultrasonic transducer and the deposits.

Abstract: The invention pertains to a relief valve (10) for being arranged on an opening (10) of a fuselage shell of an aircraft, wherein the opening (10) has a front opening edge (9a) and a rear opening edge (9a), and wherein the relief valve (10) features: a cover (13) that is arranged on the fuselage shell by means of an opening and closing device in order to open and close the opening (10) of the fuselage shell, and a prestressing device for prestressing the cover (13) into an initial position, wherein a guide plate (23) is arranged on the cover (13) by means of a mounting device (20), wherein the guide plate is spaced apart from the cover (13) and extends along the cover (13), and wherein the invention furthermore pertains to a fuselage part with such a relief valve (10) for being installed into an aircraft fuselage with a fuselage shell and a plurality of fuselage frames arranged on the inside of the fuselage shell, as well as to an aircraft fuselage with such a fuselage part.

Abstract: An aircraft area comprises a door, a door aisle and a main aisle. A storage cabinet for emergency equipment objects is disposed adjacent to the door aisle and/or the main aisle, and has an access point that is reachable from the door aisle and/or the main aisle.

Abstract: A method for machining a through-hole in a wall of a component, includes setting in rotation on itself a cutting tool about a rotation axis and setting the rotation axis of the tool in rotation about a first orbital rotation axis parallel to, and eccentric by an eccentricity E with respect to, the rotation axis of the tool. The method further includes setting the first orbital rotation axis in rotation, over at least one revolution, about a second orbital rotation axis parallel to, and eccentric by an amount f with respect to, the first orbital rotation axis, the eccentricity being fixed. This configuration makes it possible to balance the elements located between the rotation axis of the tool and the first orbital rotation axis, so that the rotation axis can thus be set in rotation about the first orbital rotation axis at high rotational speeds that contribute toward increasing productivity.

Abstract: A cabin attendant seat comprising a carrier element which comprises a backrest section and a base section that carries said backrest section. A seat element is fastened to the carrier element. At least one first stowage compartment is integrated into said carrier element. A section of a rear wall of the carrier element is inclined, at least along a section of the stowage compartment integrated into said carrier element, in such a way that a cross-sectional area of said carrier element increases in the direction of the base section of said carrier element.

Abstract: A device for boundary layer suction on the outer skin of an aircraft, on which outer skin a surface where drawing off by suction can take place comprising openings is connected to a suction source by way of at least one suction line, wherein the surface where drawing off by suction can take place is formed by at least one panel-shaped composite component that comprises an extruded profile, made of light metal, as a base body, which extruded profile comprises several suction channels that are open towards the outer skin, onto which base body, for the purpose of forming the outer skin, a micro-perforated metal cover sheet has been applied in the region of the surface where drawing off by suction can take place.

Abstract: A supporting component is provided for reinforcing the skin of an aircraft or spacecraft, for example a stringer or former, this component being configured as a closed profile (hollow profile), such that a system medium (M) can be conducted through the structural component. In this respect, the hollow profile itself serves as a load-bearing component.

Abstract: A flight control system includes at least one actuator for a mobile flight surface of an aircraft, and a flight control module in communication with the actuator. The module includes a first and a second computer. Each computer calculates a control command established according to at least one predetermined law for control of the flight surface. The first computer, known as validating computer, comprises logic means adapted for comparing its control command with that of the second computer, known as master computer, and for transmitting the result of the comparison to the actuator. The actuator comprises logic means adapted for deciding, on the basis of the result, to execute or not to execute the command of the master computer. An aircraft comprising such a system is also disclosed.

Abstract: An aircraft door includes an outer skin configured as a panel structure; and a rear body structure configured as an integral cast structure and operatively connected to the panel structure so as to provide rigidity.

Abstract: The invention concerns a shell segment for the purpose of manufacturing a fuselage cell section for a fuselage cell of an aeroplane, with at least one skin field and with a multiplicity of longitudinal stiffeners arranged thereon, in particular stringers, and also at least one transverse stiffening element running transverse to the longitudinal stiffeners, in particular at least one frame. In that the connection of the at least one transverse stiffening element to the at least one skin field is undertaken with at least one connecting bracket wherein the at least one connecting bracket has at least one corrugation, the supporting brackets for purposes of absorbing tilting moments of the frames, in forms of embodiment of shell segments of prior known art, can be omitted. By this means a considerable weight reduction is possible with, at the same time, a reduced production effort.

Abstract: A hydraulic system for aircraft wherein at least one circuit includes two hydraulic pumps, at least one of which is driven by an engine that may suffer uncontained failure that can damage hydraulic lines close to the pump, is equipped with pressure sensors for the hydraulic fluid in the lines close to the pump and a sensor for the hydraulic fluid level in a hydraulic tank of the circuit supplied by the pump. A control system for a cut-out valve installed on a suction line wherein the fluid arrives at the pump includes logic that determines the occurrence of an uncontained engine failure requiring the isolation of the pumps from line elements that may have been damaged from measurements of the fluid pressures in the lines, from measurement of the level of fluid in the tank and from information supplied late by a uncontained engine failure detection system to command the closure of the cut-out valve.

Abstract: An aerofoil structure (1) comprising at least two spars (2, 4) spaced apart in a fore and aft direction so as to define a fuel carrying volume between the spars, and at least one longitudinal corrugated reinforcing member (6, 7) disposed between the spars, each reinforcing member being corrugated in the longitudinal direction to form a series of forward ridges (9) on a forward side of the reinforcing member and a series of aft ridges (8) on an aft side of the reinforcing member, wherein each reinforcing member is directly attached by its forward ridges to one of the spars or to the aft ridges of an adjacent one of the reinforcing members, and wherein each reinforcing member is directly attached by its aft ridges to one of the spars or to the forward ridges of an adjacent one of the reinforcing members. Also, a method of manufacturing an aerofoil structure.

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: An aircraft engine pylon aft aerodynamic fairing includes upper spars, transverse stiffening ribs, lower spars and a trailing edge where the upper spars and lower spars join together. In this fairing, a profiled structure is formed according to a profile open to the outside of the fairing. In a first end portion, the profiled structure comes to be enclosed between an end portion of the lower spars and the ends of at least one transverse stiffening ribs flush with the lower spars. This structure extends between the lower spars and the upper spars over a straight central portion inclined relative to the first end portion, and comes in a second end portion flush against a portion of the upper spars, parallel to the first end.

Abstract: A fire extinguisher device for aircraft has a hanger structure and a reservoir of extinguishing agent, the aforementioned reservoir being hung beneath the aforementioned hanger structure by metal fittings held by fasteners to the aforementioned hanger structure. The aforementioned extinguisher wherein the reservoir has means of suspension and the hanger structure has carriers complementary to the means of suspension, the aforementioned means of suspension and the aforementioned carriers being such that when the fasteners are withdrawn, the reservoir is in a position called the “intermediate position,” in which the metal fittings are free and the reservoir is suspended by interaction of the means of suspension and the carriers. The disclosed embodiments also relate to a method for fastening such an extinguishing device.

Abstract: A device for mounting an aircraft engine, including a rigid structure, an engine attachment including a connecting plate superposed to an associated connecting plate of said rigid structure, and means for mutually tightening said plates comprising at least one wedge-effect tightening block and corresponding bearing surfaces of said plates which are conformed so that, when each tightening block is applied against said bearing surfaces along a direction parallel to the plane of the contact surface between both of these plates, this block exerts by a wedge-effect a force for tightening these plates against each other along a direction perpendicular to said plane.