Abstract: Methods, devices, and computer readable media are disclosed for automatic management of configuration and reconfiguration procedures of a plurality of systems of an aircraft, for example and without limitation, for aircraft operational and maintenance uses. In some aspects, a centralized device for automatic management of configuration and reconfiguration procedures of a plurality of systems of an aircraft includes a central unit for automatically generation control commands for automatic control of at least one action to be executed for one or both of the configuration or reconfiguration procedure, data links for automatic dispatch of control commands to corresponding systems for automatic execution.

Abstract: A passenger seat has a backrest and a seat which has first and second sections each having a first surface for a seat area and a second opposite surface. The second section pivots relative to the first section between a first position, in which the first surfaces of the first and second sections form a usable total seat area, and a second operational position, in which the second section is folded relative to the first section in the direction towards the backrest. Attached to the second seat section is a holder movable relative to the second surface of the second seat section between a first position, in which the holder extends substantially parallel to the second surface of the second seat section, and a second position, in which the holder extends at from 60° to 120° relative to the second surface of the second seat section.

Abstract: A process for measuring the through stress distribution (12) in a workpiece (10) by taking progressive cuts (14, 16) and measuring the deflection of the workpiece at the cut point.

Abstract: A device for linking a frame and a stringer of an aircraft structure, including a first portion connected to a support surface of a frame, a second portion connected to a support surface of a stringer and a third portion referred to as intermediary portion connecting the first portion to the second portion. The second portion is connected to the intermediary portion by means of an articulation allowing for a relative movement between the two portions along a rotation axis perpendicular to the support surface of the stringer. The first portion is connected to the intermediary portion by means of an articulation allowing for a relative movement between the two portions along a rotation axis parallel to the support surface of the frame and to the support surface of the stringer.

Abstract: A method for detecting piloting conflicts between the crew and the autopilot of an aircraft. According to the method, an automatic trajectory is programmed by checking whether the actual values of navigation parameters converge on said corresponding desired values within a predetermined convergence period; in the case where at least one of the actual values does not converge, within the convergence period, on the corresponding desired value, a predictive calculation is carried out, at consecutive future moments, of the value of at least one particular parameter selected amongst the navigation parameters; and in the case where the predicted value of the particular parameter is higher than a corresponding predefined threshold, an alarm is emitted for the crew of the aircraft to notify them about a piloting conflict being able to jeopardize the flight safety of the aircraft. A device for implementing the method. An aircraft including the device.

Abstract: A method is provided for detecting leaks in the wing of an aircraft prior to the fitting of the wing to the rest of the aircraft. A wing sealing assembly for sealing the wing of an aircraft so that the wing may be leak-tested is also described.

Abstract: A cargo door arrangement for an aircraft includes a fuselage portion, a cargo door and a locking mechanism. The fuselage portion includes a skin portion, at least one fuselage former and an opening. The cargo door includes at least one door former. The locking mechanism includes a first engagement element, a second engagement element and a connecting means. The first engagement element has a tapered portion and is rigidly connected to the door former. The second engagement element includes a tapered cavity having a shape matching the shape of the tapered portion and is rigidly connected the fuselage former. In the closed position the tapered portion is engageable with the cavity. The connecting means is adapted to rigidly connect in the closed position the door former to the first or second engagement element.

Abstract: A method for testing a batch of material used to obtain layers of fibres includes taking a specimen from the batch of material, exerting a tensile force on the specimen, heating the specimen so as to relax the fibres if the specimen contains stresses, after a predetermined period of time, no longer heating and no longer exerting the tensile force on the specimen, measuring a residual extension of the specimen which corresponds to a variation in length of at least a part of the specimen in the direction of the tensile force, before and after the tensile force, and considering the batch of material not to be compliant if the residual extension exceeds a given threshold.

Abstract: A remote data concentrator (RDC) for an avionics network, the RDC comprising an input/output interface (I/O) for connection to one or more input/output devices, and a network interface for connection to a remote processor, wherein the RDC is operable to provide communication between the input/output device(s) and the remote processor, and wherein the RDC further comprises a set of instructions for autonomously driving an output device connected to the I/O. Also, an avionics network including the RDC; an aircraft including the RDC; and a method of operating the RDC.

Abstract: The present invention provides a device for mounting systems, for example an electrical or fluid-conveying line, on a structure, in particular of an aircraft or spacecraft, the device comprising a basic holder which is fastenable to the structure and a system holder for mounting the systems, the system holder being fastenable to a first interface of the basic holder, which system holder is fastenable to a first interface of the basic holder; the basic holder comprising a first part, which comprises the first interface, and a second part, one end of which is attachable to the first part so as to be pivotal about a pivot axis and the other end of which is fastenable to the structure.

Abstract: A repair part enables rapid and efficient repair of damaged metal structures, in particular airframe fuselage skins having internal and external faces, without necessitating any additional thickness compromising the transmission of waves. To this end, the repair part includes a double internal/external plate adapted to be fastened to the internal face and the external face of the metal structure, respectively. The repair part also includes a central hub connecting the internal plate and the external plate and forming a groove between the plates. The part is constituted of a single composite material block, and a glass ply, lining the groove, may be positioned between the plates and the structure. The hub may have passing through it at least one orifice adapted to allow connections to pass through the structure.

Abstract: A wing-fuselage connection of an aircraft, in which a wing (2) that is arranged in the upper region of the fuselage (1) is connected to the fuselage (1) by means of a number of couplings (3, 4, 5, 6), wherein the couplings (3, 4, 5, 6) are provided for taking up forces in various directions and are designed for a maximum load carrying capacity, in particular for a nominal flight- and landing load (10) or a nominal crash load. According to the invention, the load carrying capacity of the individual wing couplings (3, 4, 5, 6) and their direction of force take-up are matched to each other such that in the case of a defect in one of the couplings (3, 4, 5, 6) the maximum load carrying capacity of the remaining couplings (3, 4, 5, 6) is adequate for safe normal flight operation.

Abstract: A process for the production of an acoustic treatment panel that can be connected at a surface of an aircraft, in particular at a leading edge such as an air intake of an aircraft nacelle, whereby the panel includes an acoustically resistive layer (24), at least one alveolar structure (26), and a reflective layer (28), and channels (30) placed between the alveolar structure and the acoustically resistive layer, each channel being bordered by a wall (32), the process including deforming a layer so as to produce furrows at one of its surfaces, flattening and making integral the deformed layer (34) with the acoustically resistive layer so as to border the channels, and removing material in such a way as to eliminate at least a portion of the thickness of the deformed layer (34) in which the furrows are formed between the channels, prior to the assembly of the alveolar structure.

Abstract: Rear fuselage of an aircraft comprising a tail cone end and a rest of the real fuselage whereby the tail cone end is attached to the rest of the rear fuselage by means of an attachment system comprising two upper lugs, two lower lugs and a detachable balancer fitting. The balancer fitting is an adjustable fitting, being locked in a Z and Y directions of a Cartesian axis and being movable along an X direction of the Cartesian axis providing guidance for the tail cone end and the rest of the rear fuselage.

Abstract: A system and method for selecting a datum representative of an air parameter, including a plurality of sources each capable of delivering a datum representative of a measured value of the parameter. The system includes: a mechanism for determining, for at least some sources, a number of other sources from the plurality of sources in agreement with a source in question; and a mechanism for selecting the datum selected from the data delivered by the sources for which the determined agreement number is the maximum. An engine control system, or an aircraft can include such a system or implement such a method.

Abstract: A fluid ejection device for example used as a fire extinguisher in which ejected fluid is an extinguishing agent in liquid or powdery form. The device includes: a cylinder shaped tank, split hermetically, perpendicular to its axis, into two chambers by a piston, slidable axially inside the tank; a first chamber, including a non-gaseous fluid, which communicates with an ejection port closed by a cap, which can open for a pressure greater than or equal to a defined pressure in the first chamber; a second pressurization chamber to be connected to a mechanism increasing pressure in the chamber; and a mechanism to link the piston to the tank in full fixity at a storage position, which mechanism can break and release the piston for axial translation at a pressure higher than or equal to a given pressure in the pressurization chamber, to cause the fluid to be ejected.

Abstract: A method and a device are disclosed for exchanging data between a technical management system of an aircraft and a mission management system of the aircraft, in order to permit one of the systems to determine the consequences of an event detected in the other of the systems. After at least one event has been detected in one of the technical management and mission management systems of the aircraft, at least one information item pertaining to the detected event is transmitted to the other of the technical management and mission management systems of the aircraft. The consequences of the event detected in the other of the technical management and mission management systems of the aircraft are then determined. The adaptation of at least one datum of the other of the technical management and mission management systems of the aircraft is evaluated in response to the determination.

Abstract: A diagnostic system of an aircraft, comprising a plurality of sub-systems at least one of which performs monitoring and notification of at least one detected event, using graphs of feared events. After a message of notification of occurrence of the detected event has been received, a set of feared events linked to this message is created from the graph of feared events, and logic expressions are constructed according to logic links represented in the graph of feared events. A group of feared events then is created according to elements of the logic expressions. The minimal vertexes of the logic expressions associated with the feared events of the group are calculated and form a diagnosis of the system.

Abstract: A fiber laying machine includes a laying head with a roller able to pivot about an axis of rotation and to apply a plurality of preimpregnated fibers to an application surface by rolling over the application surface. The fibers are distributed along a lower generatrix of the roller and in contact with an exterior surface of the roller over an angle of wrap. The roller includes a cylindrical body, pivoting rings around the body, and means for immobilizing the pivoting rings with respect to the body in a direction parallel to the axis of rotation. The pivoting rings are able to pivot independently of one another.

Abstract: A cabin structural segment is provided for an aircraft that includes, but is not limited to a fuselage structure and a floor structure. The fuselage structure defines an interior and separating it from an environment. The fuselage structure includes, but is not limited to an opening for a door. It is possible to provide via the opening a connection between the interior and the environment. The cabin structural segment is designed to be self-supporting. The cabin structural segment is fastenable exclusively to the floor structure. The cabin structural segment is constructed in such a way that the one cabin structural segment frames the opening.