Abstract: An aircraft canopy includes a window pane, a frame from a primary structure of the aircraft, and a flange fastened to the frame with fastening screw, characterized in that: the flange is secured to the peripheral edge of the window pane by engaging of at least one plate of the flange between plies of the window pane, so that flange and window pane form an all in one-piece assembly, at each fastening screw, a load-transferring and distributing member is arranged between an outer surface of the flange and the fasting screw, a cavity being provided in the flange for receiving the load-transferring and distributing member, the member having a recess for receiving the screw head.

Abstract: A method and a system for determining the state of a device in an aircraft, this state being specified by a current version of the device as implemented in the aircraft. The method according to the invention comprises: transmitting a request to a database and receiving in response a list of updates previously performed on the device, each update specifying an earlier version and a later version; and from a directed graph, such that each edge corresponds to an update of a set of updates associated with devices of the type of the device of interest, determining a sub-graph corresponding to the list.

Abstract: An emergency beacon is configured to replace of one or more navigation lamps installed on an aircraft, which has a fuselage with an outer face, on which is fixed a second interface, on which such a navigation lamp is typically disposed; the emergency beacon includes a base, which has a first interface configured to cooperate with the second interface of the aircraft to fix the base onto the outer face of the fuselage; a casing with a control unit, a radio transmitter for transmitting a distress signal, and a detector to detect abnormal aircraft behavior; and a fixing structure to take up a fixation position, ensuring the casing is fixed to the base, or a separation position, in which it does not ensure the casing is fixed to the base; the transition from fixation position to separation position is controlled by the control unit when an abnormal behavior is detected.

Abstract: The disclosure herein relates to a method of controlling the thrust of the jets of a multi-jet aircraft, during the aircraft takeoff phase, which successively comprises a first step of controlling the jets to a first thrust level, until the aircraft reaches a first predetermined speed, and a second step of controlling the jets to a second thrust level, less than the first thrust level, when the aircraft exhibits a speed greater than the first predetermined speed, the first predetermined speed being less than the minimum ground control speed of the aircraft when the jets are at the second thrust level.

Abstract: A method and device for assisting initiation of a flare maneuver of an aircraft during a landing. The device includes an acquisition unit for acquiring current values of flight parameters of the aircraft, including the current height of the aircraft with respect to the ground, a computation unit for computing a first reference height and a second reference height, corresponding to a height starting from which the aircraft attains a current start of flare height while maintaining its current descent conditions over a predetermined first duration and over a predetermined second duration respectively, and an acoustic emission unit for emitting at least two sound signals in the cockpit of the aircraft, namely a first sound signal when the current height of the aircraft attains the first reference height during the descent and a second sound signal when the current height of the aircraft attains the second reference height during descent.

Abstract: A ground-based server is configured for identifying encounters of aircraft with wake turbulences generated by at least one other generating aircraft. The ground-based server is configured for: collecting avionics data for an in-flight aircraft and traffic data for one or more other aircraft in flight at a first flight time of the in-flight aircraft; determining that the in-flight aircraft was near a wake turbulence estimated, using the traffic data, to be generated by another aircraft; determining that the in-flight aircraft experienced at the first flight time a severe impact; determining that the in-flight aircraft experienced at the first flight time at least one of: one or more uncommanded forces and moments, and a wind signature indicative of wake turbulence; and in response, generating a report of a wake turbulence encounter for the in-flight aircraft at the first flight time.

Abstract: A method and device to locate an impact on an outer surface of a body including: locating the impact on the outer surface of a virtual model of the body; selecting a first and a second visual reference element on the virtual model; positioning an acquisition module on the outer surface of the actual body at the impact; measuring, using an acquisition module, measuring distances between the impact and the first visual reference element and between the impact and the second visual reference element; calculating a first arc around the first visual reference element and a second contour around the second visual reference element wherein each arc has a radius equal to one of the measured distances; determining a point of intersection of the first and second contours; and calculating coordinates of the point of intersection on the virtual model to locate the impact on the virtual body.

Abstract: An aircraft fuselage includes at least one space arranged in the aircraft fuselage and at least one wall. The wall resists burnthrough for a period of at least four minutes from outside the aircraft fuselage towards the space, wherein the region of the aircraft fuselage underneath the space does not include burnthrough-resistant insulation. The space may be a cargo compartment of the aircraft or a passenger cabin, while the wall may be designed as a cargo compartment floor, passenger cabin floor or wing/fuselage fairing (belly fairing). The design of the aircraft fuselage results in burnthrough resistance that meets the requirements of FAR §25.856 (b) without any additional burnthrough-resistant insulation in the aircraft fuselage.

Abstract: A method of assistance for troubleshooting is provided. A purpose is to prioritize identifiers each associated with a piece of equipment the failure of which can be the cause of a fault within an aircraft. The method is based on transmitting to an expert system, a list of identifiers, and receiving, for each identifier, a family of pertinent parameters, with each pertinent parameter being associated with at least one sensor of the aircraft and taking measurements of the pertinent parameters. Knowing these measurements, it is possible to deduce therefrom, for each identifier, a priority corresponding to the probability that the associated equipment is effectively defective. A system for implementing this method is also provided.

Abstract: In a communications network including aircraft in flight and at least one ground station, which constitute communication nodes of the network, data are transmitted from a source node to a destination node following a non-predetermined path through the network that includes at least one node which is a so-called intermediate aircraft. Before transmitting data from a transmitting node to at least one receiving node, it envisages a step of selecting the receiving node defining a portion of the path without knowledge of the next portion of the path.

Abstract: The invention relates to a system and a method for preventing inadvertent slide deployment for an aircraft, comprising at least one sensor for sensing the proximity of a person in front of an aircraft door, and at least one optical warning means operable to provide an optical indication in the vicinity of a slide arming lever when the sensor detects the proximity of a person in front of the aircraft door. The system according to the invention provides an effective prevention for inadvertent slide deployment that is capable to guide trained and untrained persons to the information they need in order to disarm the slide in sufficient time before the door handle is gripped and pulled to open the aircraft door in normal operation conditions.

Abstract: According to a first aspect, the subject matter disclosed herein relates to a decision aid method for maintenance operations of aircraft equipment, the aircraft including a maintenance system arranged to make a record of equipment failure messages and of equipment failure warning messages emitted during a flight, the method comprising extracting at least one combination of failure messages corresponding to failure messages recorded by the maintenance system during a flight and a set of previous flights; determining, as a function of the at least one extracted combination, a probability of occurrence of at least one warning message possibly accompanied by one or more failure messages.

Abstract: A device for aiding communication in the aeronautical domain, wherein the device includes a transceiver and data processor assembly that records audio messages corresponding to all the incoming and outgoing audio communications, transcribes the messages, in real time, into textual messages, displays the textual messages, and enables an audio play back of the audio messages.

Abstract: An aircraft according to the invention enables passengers to be received and comprises a first deck for receiving passengers, a second deck for receiving passengers, which is placed over the first deck, as well as at least one access door. The first deck has at least one first zone having a substantially planar floor and situated on the same level as the access door and at least one second zone having a floor offset in height relative to the first zone. The cabin further comprises at least one rectilinear ramp linking the first zone of the first deck to the second zone of the first deck, and at least one rectilinear ramp linking the first zone of the first deck to the second deck.

Abstract: The invention relates to an angle measurement probe on board an aircraft, which comprises a fin, which can move in rotation about an axis, at least one first optical encoder and one second optical encoder, each comprising at least one disk, each disk being fixed at right angles to the central axis and being provided with at least two circular tracks, each track being provided with alternate opaque and transparent zones, means for processing the output signal from each encoder.

Abstract: The invention relates to a method for transmitting data, characterized in that it includes a step of transmitting in-flight data between a first aircraft and at least a second aircraft, the data transmitted being data stored in at least one black box on board the first aircraft.

Abstract: A method and device for aiding the monitoring of a turbine engine of an aircraft, which displays on one and the same indicator of a of a display indication elements illustrating as a percentage the engine start progression or the current sub-idle state of the turbine engine, a margin to a limit temperature of the turbine engine, a margin to a maximum temperature of the turbine engine and a margin to a possible failure of the start that is generated by a too low speed increase of the turbine engine.

Abstract: A module for an aircraft has a fuselage structure and a floor element defining a floor plane. The module includes a frame device adapted for mounting a functional element and the frame device is adapted for attachment to the floor element of the aircraft at a first location in the floor plane.

Abstract: An aircraft is equipped with engines, each engine having at least one pod and one compressor/turbine hitch. The aircraft has at least one data processing unit and at least one system at the engine level. At least one engine is equipped with at least one static pressure probe for measuring the ambient air under the pod. Also, air static pressure probes are arranged at the engine levels, with one pressure probe at the output of the compressor, at least one rotation speed sensor, for example of a blower, and ambient air temperature probes at the air input or in any compression point. The processing unit is able, from measurements performed by such probes at the engine level, to supply to at least one of the systems at the engine level, determination data for the air speed of the aircraft.

Abstract: A module for an aircraft having a fuselage structure and a floor element defining a floor plane. The module includes a frame device adapted for mounting a functional element and the frame device is adapted for attachment to the floor element of the aircraft at a first location in the floor plane. The frame device is adapted for attachment to the fuselage structure of the aircraft at a second location, wherein the second location is not in the floor plane.