Abstract: The invention relates to a load introduction structure for an aircraft, comprising two lateral frames which are arranged opposite one another in the two lateral regions of a fuselage airframe structure of the aircraft and adjoin a continuous floor surface which rests on a floor frame. The two lateral frames are connected via the top thereof by a ceiling frame, the ceiling frame being suspended from a ceiling region of the fuselage airframe structure. Each lateral frame is divided into at least two lateral frame segments. At least three track portions which extend parallel to a longitudinal axis of the aircraft are arranged on each lateral frame segment. The lateral frames are connected to the fuselage airframe structure, the ring frames in particular, by a plurality of x-rods, y-rods and y-cardan rods.

Abstract: The invention relates to a testing device (12) for checking the operability of a bow steer control unit (10) in an aircraft. The bow steer control unit has a plurality of input ports and a plurality of output ports, wherein at least one of the input ports of the bow steer control unit is connectable to a speed sensor, which provides a signal representing the actual speed of the bow wheel of the aircraft. The bow steer control unit outputs a blocking signal to be transmitted to a steering mechanism as soon as the detected actual speed of the bow wheel exceeds a predetermined bow wheel speed value.

Abstract: The disclosed embodiments concerns a traction pad to be bonded for coating adhesion or surface cohesion tests by tearing including a counterbore designed to control the thickness of the adhesive film. Support elements such as wedges or a border maintain the base of the counterbore at the required distance from the tested surface and openings are provided for evacuating the adhesive prior to its controlled hardening when the traction pad is applied on the tested surface.

Abstract: A system for stockkeeping in an aircraft galley includes a plurality of receiving devices which are provided for reception in a base body of the aircraft galley and are each provided with a transponder which is configured to emit an identification signal characteristic of the content of the corresponding receiving devices. Furthermore, the stockkeeping system includes at least one transmitting/receiving unit which is provided on the aircraft galley and is configured to read in identification signals emitted by the transponders of the receiving devices and transmit these signals to a data processing unit, the data processing unit being configured to determine, on the basis of the identification signals transmitted by the transmitting/receiving unit, the inventory of the aircraft galley. An output unit of the system is configured to output the inventory of the aircraft galley determined by the data processing unit.

Abstract: A method for verifying coherence of takeoff parameters of an aircraft from an airport with an available runway length at a moment of takeoff comprises a step of identifying a takeoff runway and a step of validating takeoff parameters with a view to authorizing takeoff of the aircraft if the takeoff distance is shorter than the remaining runway length associated with the identified takeoff runway.

Abstract: A method of braked pivot turning an aircraft, the aircraft comprising a fuselage and a landing gear assembly located to one side thereof. The landing gear comprises a bogie with wheels mounted thereon, at least one wheel being located on a first side of the bogie and at least one wheel being located on a second side of the bogie. The method includes the steps of applying thrust (7?) for moving or turning the aircraft, and via the braking of at least one wheel, applying a greater braking force to the first side of the bogie than to the second side. The first side is located closer to the center of turning of the aircraft than the second side. The method thereby generates relatively low torque loads in the landing gear leg, reducing fatigue damage. A brake control system is also provided for selectively braking wheels during a turn.

Abstract: The invention relates to a conveying device for a trolley, in particular to a refreshments trolley, in an aircraft passenger cabin and consists in the fact that the conveying device comprises an electric drive with two drive wheels 12, 13 for moving the trolley 7 inside the aircraft passenger cabin, a further electric drive for raising and lowering the trolley 7 and a current collector 20 for supplying current to the installed electric motors 36, 37. The service crew is as a result relieved of physically tiring work and the trolley 7 is secured against uncontrolled movements during the service phase.

Abstract: An aircraft landing gear (10) includes a torque link set (12) comprising a first fairing (12a) rotatably connected at a first end (18) to a first end (19) of a second fairing (12b). The fairings (12a), (12b) may be arranged to act as first and second torque links. The fairings may be in the form of noise reduction fairings.

Abstract: A method for assembling a cabin window to a bay in a side wall of an aircraft fuselage, where the cabin window including an outer transparent element and at least one inner transparent element, includes making a non-through hole in a portion of the side wall. The outer transparent element includes a first part having a diameter greater than that of the bay and which is shaped to co-operate with the portion of the side wall to block the outer transparent element in the bay both laterally and longitudinally. A second part of the outer transparent element has a groove that projects into the fuselage. The outer transparent element and the at least one inner transparent element are welded to the fuselage using a strap which presses a seal against at least the fuselage and the inner wall of the groove.

Abstract: A device for cooling hot gas to be discharged from an aircraft includes a duct for leading the hot gas from a hot gas source which is connectable to the device to an outlet point, and a frame which surrounds the duct and serves for mounting the duct. The duct is formed from one or more pipe sections and has one or more cooling air inlet points which is connectable to one or more cooling air sources in order to mix the hot gas with cooling air. An outlet pipe section of the duct extends outwards beyond the aircraft outer skin to lead hot gas through and out of a flow boundary layer on the outer skin.

Abstract: A method of joining a wing to an aircraft fuselage by forming a series of pinned lug joints between a fuselage side and a wing side of a wing box structure. The joint forming process includes providing a single row of lugs on one side of the joint to be formed, and providing a respective double row of lugs on the other side of the joint to be formed. A gap between opposing lugs of the double row varies along the row. The wing side and the fuselage side of the wing box structure are brought together such that the lugs of the single row are located within the respective gaps between opposing lugs of the double row, and the lugs are pinned to form the series of pinned lug joints. Also, a joint formed by the method.

Abstract: In the method of controlling an aircraft, a device implements the steps consisting in determining a first global value on the basis of only some amongst first individual values calculated by respective applications, modifying at least one parameter to take account of how the determination step took place and determining a second global value on the basis of second individual values calculated by the respective applications and on the basis of the parameter(s).

Abstract: An aircraft structure comprising; a rear spar, an upper cover which is attached to the rear spar and overhangs to its rear; a lower cover which is attached to the rear spar and overhangs to its rear, a hinge rib assembly comprising: a first hinge rib arm attached to a first one of the covers; and a second hinge rib arm connected to the first hinge rib arm and attached to a second one of the covers; and an aerodynamic control element pivotally mounted to the hinge rib assembly. The first and second hinge rib arms are separate parts. This provides the ability to disassemble the hinge rib in-situ for repair or maintenance purposes; the ability to install or remove the hinge rib without having to move it inboard along the structure; reduced material wastage during manufacture; and the ability to install one or more elongate lines which extend in a span-wise direction along the aircraft structure.

Abstract: The invention relates to an aircraft with a protection shield for the rear composite material, fuselage 25) for conducting tail impact tests, in addition to a tail absorber, the shield (11) being formed by a plurality of pieces (21) joined to supports (23) fixed to the rear fuselage (25) behind the tail absorber (1), said pieces (21) having a laminar structure with an outer steel sheet (13), an inner composite sheet (17) and an intermediate high resistance silicon sheet (15).

Abstract: A device for control of a plurality of support subsystems in an aircraft includes a filtering unit that determines at least one command associated with at least one support subsystem of the plurality of support subsystems according to at least one context parameter. The device also includes a display unit that displays at least one representation of the at least one determined command. The at least one representation of the at least one determined command includes an indication relating to a state of the at least one support subsystem controlled by the at least one determined command. The device further includes a selection unit that selects the at least one representation. In addition, the device includes an activation unit that transmits the at least one determined command to the at least one support subsystem in response to an activation of the at least one selected representation.

Abstract: An assembly for an aircraft including a first structure mounted to a second structure, and a power transfer assembly electrically connecting the first and second structures. The first structure is movable relative to the second structure between a retracted and an extended position. The power transfer assembly includes a housing, a spool mounted for rotation relative to the housing and biased to rotate in a first direction, and an electrical cable adapted to be wound around the spool when the spool rotates, such that movement of the first structure from its retracted to its extended position causes the cable to be unwound from the spool by rotation of the spool in a second direction opposite the first. Also, a method of electrically connecting the first and second structures. The invention may be applied to an aircraft wing to electrically connect a leading edge slat to a fixed aerofoil portion.

Abstract: A data viewing system for an aircraft includes a concentration unit including a first element for acquiring all of the compound images generated by a plurality of image sources, a second element for processing the acquired compound images, and a third element for managing the display of the processed compound images implemented on a plurality of viewing screens.

Abstract: A method and device for reducing actual loads generated on airplane by an aerodynamic disturbance is provided, the device including means for determining a load exceeding envelope and means for determining deflection orders of airplane control surfaces to reduce loads applied on the latter, when the airplane flies inside the load exceeding envelope. More specifically, a flight envelope of the airplane is determined and used with theoretical loads applied to the aircraft to produce the load exceeding envelope based on couples of the flight envelope with theoretical loads that equal or exceed a load threshold.

Abstract: An equipment holder is provided with an optional grid function for positioning a first cabin component of an aircraft relative to a second cabin component of the aircraft and for attaching the two cabin components to each other. The equipment holder includes, but is not limited to an attachment element, a fixing element, and a position determination device. In this arrangement the attachment element is designed to attach the equipment holder to the first cabin component. The fixing element is designed to fix a position of the equipment holder relative to the second cabin component. Furthermore, the position determination device is designed to discontinuously indicate the position of the equipment holder relative to the second cabin component with a position signal.

Abstract: One or more main aircraft fuel tanks are provided with one or more fuel gauges arranged to provide a measure of the amount of fuel in said one or more main fuel tanks. One or more auxiliary fuel tanks are also provided. The aircraft uses fuel during a first phase of fuel consumption, upon commencement of which phase the auxiliary fuel tanks hold fuel. After the first phase said one or more auxiliary fuel tanks are empty and a second phase commences. During the first phase, an indication of the amount of fuel carried by the aircraft is provided by means of summing (i) the amount of fuel in the main fuel tanks as measured by said one or more fuel gauges and (ii) the amount of fuel remaining in said one or more auxiliary fuel tanks as calculated using a measure relating to the fuel consumption rate. During the second phase of fuel consumption, an indication of the amount of fuel carried by the aircraft is provided on the basis of the amount of fuel measured by said one or more fuel gauges.