Abstract: The present invention relates to a jig for the manufacture, by means of injection and curing processes, of preforms of composite material frames for aircraft fuselages by using the RTM (resin transfer molding) technology. Two preforms are thus manufactured, one with a C shaped section and another with a L shaped section, together with the preforms of the stabilization ribs for stabilizing the web of the frames and the preform of the roving or staple fiber to cover the gap between the C shaped preform and the L shaped preform. Theses preforms are previously manufactured by any known process for manufacturing preforms. According to a second aspect, the present invention relates to a method of manufacturing composite material load frames for aircraft.

Abstract: An aircraft including a cabin, on at least one wall of which are attached first portions of plural multisystem connection devices, each device including a male portion or plug and a female portion or socket capable of fitting into each other. Each male and female portion includes: a first mechanism connecting to a liquid or gas supply of the aircraft; and a second mechanism connecting to a supply of electricity and/or electric signals of the aircraft.

Abstract: A method is provided for mounting a wing of an aircraft to a fuselage of the aircraft, in which a difference between a vertical target position and a vertical actual position of a mounting point is determined. Then, on the basis of the determined difference, a readjustment of the wing is performed.

Abstract: A testing device comprises a transmission path comprising at least one leakage conduction antenna disposed in the cabin of the aircraft, a control device coupled to the transmission path, said control device comprising a generating device for generating a broad-band interference signal and a transfer device for feeding an HF signal to the leakage conduction antenna, wherein the fed HF signal has a pre-defined power level and contains at least the generated broad-band interference signal, at least one measuring device coupled to the transmission path at a pre-defined coupling point, said measuring device measuring the power level of the HF signal at the coupling point and preparing a measurement signal that is proportional to the measured power level, and an evaluation means for preparing a test result by way of a comparison between the prepared measurement signal and a target signal that depends on the power level of the fed HF signal.

Abstract: The invention relates to a device for applying information onto a surface of an aircraft, wherein the information is applicable in variable locations and is modifiable. The device can include a pad unit having at least one pad, at least one hand grip, a press-on mechanism, a hand lever, at least one support, and a housing. By applying varying printing patterns to the pads, any combination of characters can be stamped on. Moreover, the device configured as a hand-held tool can be operated by a user in variable locations. The printing process is effected by operating the hand lever, causing the pads to be brought into contact with the surface, and the information or, as the case may be, the technical coding to be applied onto said surface.

Abstract: An aircraft leading edge panel having an outer aerodynamic surface; and an inner surface carrying the elastomeric impact protection membrane. The membrane comprises a woven or knitted fabric which is impregnated with an elastomeric material. The membrane and the panel may be bonded by an adhesive or co-cured to bond the membrane to the panel. The membrane provides impact protection to the panel by de-bonding from the face of the panel and absorbing at least part of the energy of an object impacting the panel.

Abstract: A wing-fuselage section of an aircraft, which wing-fuselage section comprises a wing root at which the wing of the aircraft is connected to the fuselage, a fuselage region with fuselage frame elements that extent across the longitudinal direction of the aircraft, and a wing region with spars that extend in the direction of the wingspan. According to the invention, the spars of the wing region and the fuselage frame elements of the fuselage region form part of an integral assembly that extends at least over a middle part of the wing and the fuselage region, including the wing roots.

Abstract: An illumination device for an aircraft, comprising a combination of two-dimensional background illumination with a reflection of incident light on a face pointing towards the viewer in order to achieve a particular depth effect, as a result of which the illumination body appears to the viewer in greater visual depth than is actually the case. This is, in particular, of importance in aircraft, in which not only is the available space small, but also the weight aspect that is inevitably associated with large bodies plays an important role.

Abstract: The present invention concerns a system for servicing a plurality of service positions which are assigned to a plurality of installation elements, in particular passenger seats in an aircraft, comprising: a plurality of service units, in particular lighting units, wherein the number of service units exceeds the number of service positions to be serviced, and a control unit, wherein the control unit is adapted to receive a respective item of control information including an identification in respect of an installation element and to control a predetermined service unit on the basis of the identification, and a method of servicing a plurality of service positions which are assigned to a plurality of installation elements, in particular passenger seats in an aircraft, and a corresponding computer program.

Abstract: A fire extinction device includes a reservoir of extinguishing agent and device for generating a pressurized gas such that the gas generated may enter the reservoir when the extinguishing agent is to be ejected onto a fire zone. The extinction device also includes a refractory separating element between the extinguishing agent and the pressurizing gas generated, in order to avoid heat exchanges between the extinguishing agent and the gas and to optimize the ejection of the extinguishing agent.

Abstract: A mounting structure for an aircraft engine including a rigid structure and a mechanism to mount the engine on the rigid structure. The mounting mechanism includes a thrust load device including two side thrust links each including an aft end mounted on an evener bar of the device, via a mechanical connection. Each connection is formed by a lug provided on the evener bar and passing through an orifice made in the aft end, the lug being arranged so as to extend substantially laterally relative to the mounting structure.

Abstract: An aircraft floor including two lengthwise external beams and at least one pair of cross beams extending between the lengthwise beams, an external end of each cross beam being interlocked to the lengthwise beam. The internal ends of the beams of the pair of the cross beams are connected to each other, where the cross beams are inclined in such a way that the internal ends of the cross beams are directed downward when compared to the horizontal plane of the floor. Moreover, the floor includes self-stiffened panels extending between the cross beams.

Abstract: A braking-energy equalization system applied to an aircraft undercarriage, which undercarriage includes at least two sets of landing gear, with each set of landing gear including at least two wheels and with each of wheels being equipped with a brake, wherein the system includes means intended to introduce a delay time to delay the braking of the brakes having a higher braking torque in comparison with the other brakes having a lower braking torque, so as to equalize the braking energies absorbed by the brakes of the landing gear during the landing or during an interrupted takeoff of the aircraft.

Abstract: The present application describes a quick-change fastening system for demountably mounting an element to a fastening structure. The element comprises an engagement element that is designed to engage a bearing element of the fastening structure, wherein the element is hingeably held around the bearing element between a hooked-in position and a fastened position. The element further comprises a fastening element that can be affixed to a locking element of the fastening structure when the element is in its fastened position. The engagement element and the bearing element are designed such that along a hingeing movement of the element a form-fit connection is established when the element is in its hooked-in position, and that a force-fit connection is established when the element is in its fastened position.

Abstract: The object of the invention is in particular a method and a device for aiding in the control of systems installed on board an aircraft comprising at least one display device capable of displaying configuration parameters of the said aircraft and at least one associated acquisition device. After the state of the said aircraft has been determined (900), a plurality of elements to be displayed on the said at least one display device is selected (905), according to the said state of the said aircraft, in a predetermined set of elements comprising at least one parameter for configuration of the avionics, at least one parameter for configuration of support subsystems and at least one activatable representation of least one command of support subsystems of the said aircraft. The said plurality of elements is displayed on the said display device.

Abstract: A galley oven (10) for preparing food on board an aircraft comprises a housing (12) and a rack (18) which is introducable into the housing (12) and removable from the housing (12). The rack (18) comprises a plurality of receiving devices (24) for receiving food containers (26) that are to be heated in the galley oven (10).

Abstract: The invention relates to a mounting (1) for holding an elongate object (13) such as an electric cable in position relative to a structure (12). According to the invention, said mounting comprises: two parts for connecting the mounting to the structure (2, 3, 21, 22) each of which has a bearing surface (2a, 3a, 21a, 22a) suitable for resting each side of the structure against a bearing surface (12a, 12b) of the structure, said two connecting parts being assembled together by a clamping means (7, 8, 10), at least one supporting part (4, 23, 24) suitable for maintaining said elongate object (13) via a holding means (50, 31, 37, 69), characterised in that said mounting part is provided in the form of a substantially cylindrical railing (23, 24), secured to a connecting part.

Abstract: An aircraft having a propeller engine mounted at the rear of the aircraft, on the back thereof, such that the axis of the engine is parallel to the longitudinal axis of the aircraft. The aircraft has a cell, the rear part of which comprises a horizontal empennage and two vertical empennages, positioned one at each end of said horizontal empennage. The propeller is positioned vertically in line with the rear part of the cell, and the rear part of the cell forms a lateral and downward barrier, on each side of a plane of the propeller, that screens an acoustic intensity equal to approximately?5 dB with respect to a maximum acoustic intensity emitted by the engine.

Abstract: A method of lifting an aircraft at a lifting location, the method comprising: securing a fitting (10) to the aircraft when the aircraft is at the lifting location; engaging the fitting with a crane hook (100); transmitting lifting load from the crane hook to the aircraft via the fitting; and removing the fitting from the aircraft. A fitting (10) for transmitting lifting loads from a crane hook (100) to an item, the fitting comprising: an attachment member (11) configured to be secured to the item; and a lifting member (12) which is pivotally coupled to the attachment member and configured to be engaged by the crane hook (100) so as to transmit lifting loads from the crane hook to the item. A crane hook (100) with a ball-and-socket connection is provided.

Abstract: A method for transmitting data via network nodes of a particular network has the following steps: coupling the network nodes to a respective number of coupled end devices via a bus having a transmission line and a receiving line in an interlinked arrangement; providing a first number of first frames which are defined in accordance with the particular network and each comprise safety-related data; providing a second number of second frames which are defined in accordance with the particular network and each comprise non-safety-related data; and transmitting the provided first frames and the provided second frames via the bus in a predetermined sequence, a respective time interval between two respective first frames transmitted via the transmission line and two respective first frames transmitted via the receiving line being set as a function of a determined sampling rate of the audio data by the coupled end devices, and at least one respective second frame being transmitted via the transmission line and via