Abstract: A rear suspension (10) for an aircraft engine assembly comprises a structure comprising two three-point shackles (12, 12?) and one two-point shackle (14). One of the hinge pins in waiting on the two-point shackle (14), preferably the hinge pin (26) fixed to the engine yoke joint, is mounted with clearance and with a damping ring acting as a spring to prevent vibrations of the engines as long as the hinge pin (26) is not engaged. Each of the suspension connecting pins (10) is a ball joint connection, the beam (16) of the suspension (10) being provided with five aligned orifices (24, 24a, 28, 24?, 24a?).

Abstract: The disclosed embodiments relate to an airplane fuselage produced by assembling, at a circumferential joint, at least two sections including a skin and at least one stringer split into two elements and which are assembled at the joint between the two sections by at least one splicing plate. The splicing plate includes a web having a bearing surface including two surfaces bearing on lateral faces of the elements of the stringer, the two surfaces being offset by an amount ? substantially equal to an error of alignment between the lateral faces of the elements of the stringer.

Abstract: The invention relates to a power supply system for several user systems onboard an aircraft. This system comprises at least two power supply electronics (10, 11) and means of connecting these at least two power supply electronics to at least two user systems (12, 13, 14, 15), characterised in that these connecting means comprise a network of connecting contactors (16, 17; 32, 33) from each power supply electronics with at least two user systems not performing similar functions but technologically compatible such that these power supply electronics supply these user systems at different times.

Abstract: A method for updating a content of a given warning message emitted in an aircraft by a monitoring system in case of detection of a particular state of at least one monitored system of the aircraft, the method including a step of delivery of a plurality of modification information items to a selection tool, each modification information item defining a modification of a content of a warning message capable of being emitted by the monitoring system, the selection tool being capable of selecting at least one information item among the plurality of modification information items in such a way as to permit modification of the content of the given warning message.

Abstract: A method for inspecting a part by a non-destructive ultrasound inspection, the part is immersed in an acoustic wave conducting medium and an incident ultrasound wave having a wide beam of section ? is emitted into the ultrasound-conducting medium towards the part. The characteristics of the waves reflected by faces of the part to be inspected are measured on at least a small section ?, the characteristic dimensions of which are substantially less than those of the section ?. The location of the section or sections ? is determined such that, despite the possible variations of the position of the part and the relative slopes of its faces, the section ? is always located in the volumes passed through by the reflected waves, for example substantially in an area close to the axis of the incident beam when the incident beam is controlled to be oriented substantially in a direction perpendicular to a face of the part.

Abstract: A system and a method for distribution of electric power inside an aircraft. The system includes at least two systems distributing electric power from at least one power source to electric loads of the aircraft via electric and/or electronic protection/switching components, the components being configurable and commandable by dedicated electronics. Each electric distribution system includes command electronics in which a configuration file is downloaded allocating an installation status to each of the protection/switching components.

Abstract: The invention relates to a method to display page by page a roll-down message in a display zone of a viewer in an aircraft's cockpit, comprising, for each message, the following operations: selection of a full length for the message to be displayed, selection of a visible length for the message to be displayed in the display zone, selection of a repeated length for the message, this repeated length being the length displayed in a current page and copied again into the next page, determination of a total number of pages to be displayed in order for the total length of the message to be displayed with the selected repeated lengths, such total number of pages being determined in the following manner: Np = lower_full ? _part ? ( Lm - Lv + 2 ? Lc - 1 Lc ) ?with Lc=Lv?Lr, ?where Np is the total number of pages, Lm is the total length of the message, Lv is the visible length of the message in the display zone, Lr is the repeated length of the message and Lc is the non-repeated length of th

Abstract: A method for the automatic sequencing of the specifications of a computer comprises an analysis of the specifications constituted by nodes with a simplification and distribution of these nodes into at least two types of nodes, and an assigning of these nodes in repetitive sub-cycles of processing tasks in order to obtain a substantially uniform distribution of the tasks.

Abstract: A device includes a current position unit for determining a current position of a aircraft, a mapping database, a navigation system, a current heading unit for determining the current heading of the aircraft, and a display system for displaying on a viewing screen, at least a partial map of the airport and, thereon, an aircraft symbol which is positioned at the current position and which is oriented in accordance with the current heading.

Abstract: A rigid structure of a suspension pylon for an aircraft engine, which is in a shape of a box closed by first and second box side panels. The structure includes inter-rib spaces, each space delimited by two directly consecutive box transverse ribs. For each inter-rib space forming part of a group including at least three arbitrary and directly consecutive inter-rib spaces, a single access opening is provided on the side panels, the openings arranged alternately on the first and second side panels.

Abstract: The invention concerns a system for deicing the leading edge of a nose inlet cowl for a turbine engine. The invention is characterized in that one of the two elements formed by the pressurized hot air supply duct (6) and by the protective casing (15) is longitudinally rigid, while the other of said elements comprises at least two mutually nested parts adapted to slide sealingly relative to each other; and said two elements (6, 15) are, on one side, rigidly fixed to one of said partitions (5) of the structure box (10), while, on the other side, said two elements are rigidly linked to each other (in 18) and are adapted to slide jointly relative to a sliding bearing (17) provided in the other partition (16).

Abstract: An aircraft with reduced environmental impact includes a turboprop, having two contra-rotating propellers, disposed on the rear portion on the back of the aircraft's fuselage so that the interaction noise of the propellers is masked, in the forward direction, by the wings and, in the rearward direction, by the aircraft's horizontal stabilizer.

Abstract: The invention is a turbofan provided with a pre-cooler. In order to evacuate the heated cool air stream, at least one discharge pipe is arranged in a chamber and connects the pre-cooler to at least one discharge orifice provided in the inner fairing, in output of an exhaust nozzle and at least more or less opposite the wing.

Abstract: A device for protection against icing for aircraft engines including at least one sensor, sensitive to an amount of accumulated ice, arranged in the air intake of an aircraft engine, a system for measuring the amount and comparing the amount to be predetermined threshold and a triggering system for launching a response to the detection of the crossing of the predetermined threshold, the response may be an alarm, an increase in the engine power delayed by the engine control system or the return of hot air upstream of the engine.

Abstract: A production unit for which a schedule of tasks is to be accomplished is prepared and stored in a central management device. The unit includes individual electronic devices, control stations, and a network linking the individual electronic devices and the control stations to the central management device. Each individual electronic device includes a device to input the tasks accomplished and problems encountered and further includes a transmission device for information input. The central management device compares data received with the schedule of tasks, generates a warning signal when the comparison detects a gap or discrepancy between the data received and the schedule of tasks, and transmits the warning signal to the individual electronic devices and control stations. The individual electronic devices and the control stations include a device to display the warning signal.

Abstract: The invention relates to a system and a method for supplying power to an aircraft comprising several generators supplying alternating current to several different primary electrical master boxes (10, 11, 12 and 13), the various aircraft loads being connected to each of these master boxes. This system comprises conventional master boxes (10, 11, 12 and 13) which supply power loads and at least one master box (40, 41) devoted to actuator loads, this at least one devoted master box being connected to conventional master boxes.

Abstract: A method and device for predicting the stopping position of an aircraft while landing. The stopping position is predicted from the variation of total energy of the aircraft before the beginning of its flare out.

Abstract: A device for controlling an electromechanical actuator includes an electric motor and an actuator operated by the electric motor. It also includes a digital signal processor (DSP) providing data of reference voltages (Ud—ffw, Uq—ffw) on the basis of an decoupled electrical model of the motor. The processor has at least one Park transformation module receiving measurement data for the currents of at least two supply phases of the motor (i_mot—2, i_mot—3) and a datum for the estimated angle of the motor (?estimated) and transforming them into data regarding the component of current with stator current axis (id) and the component of current in quadrature with the stator current (iq).

Abstract: An aft attachment for an aircraft engine assembly. The attachment has a double boomerang structure including two three-point shackles that are duplicated: only four attachment points are present at the engine mount and two at the engine, the failsafe function being ensured by the dual structure. This attachment design does not sacrifice safety criteria, while providing a more lightweight structure.

Abstract: A super-transporter aircraft for transporting at least one element of a secondary aircraft, wherein the structural rigidity of a fuselage of the super-transporter is at least partly imparted by the transported element. The super-transported aircraft can be equipped with a securing device for securing the transported element to the fuselage of the super-transporter aircraft, the securing device adapted to pick up the loads to which the super-transporter aircraft is subjected.