Abstract: A cap has a body portion forming a central cavity, and an annular flange which extends outwardly from the body portion. The body portion is deformable between a first configuration in which the annular flange is inclined upwardly, and a second configuration in which the annular flange is inclined downwardly. A method includes applying a quantity of sealant to the annular flange in the first configuration; fitting the cap over the end of the fastener so that the fastener is enclosed by the cap; and turning down the annular flange such that the cap assumes the second configuration in which an annular pocket is formed between the flange and the base, and the sealant material fills the annular pocket; and bonding the cap to the structure with the sealant material.

Abstract: An aircraft fuselage frame assembly includes a first lower frame element having a cross member and a curved fuselage tub frame. A second upper frame element of the assembly has a cross member and a curved upper frame segment. A third frame element of the assembly is made of a cross member section, floor strut section and frame section. The third frame element is formed as a single, integral triangle element having a hypotenuse that is curved to adopt a curvature of the aircraft fuselage and joining portions at angle areas of the triangle. A lower frame link is joined to the first upper frame and at a first angle area of the triangle element; an upper frame link is joined to the second upper frame and at a second angle area of the triangle element; and a floor cross member is joined at a third angle area of the triangle element.

Abstract: An aircraft assembly is provided having a first aircraft component and a second aircraft component, at least one of the aircraft components being composed of a fibre-reinforced composite material, a connecting device connecting the first aircraft component to the second aircraft component, the connecting device including a first and a second section having a carrier element connected to the first and second aircraft components respectively, the first section having a first surface facing the first aircraft component and a second surface facing away from the first aircraft components, the second section having a first surface facing the second aircraft component and a second surface facing away from the second aircraft component. The first and second sections include a plurality of hook and loop elements extending from the second surface of the carrier element and cooperate to produce a hook and loop connection between the first and second aircraft components.

Abstract: A separation device is provided for a vacuum toilet system of an aircraft, which makes possible a significantly simpler type of cleaning, which can be done more quickly, of a profile separator. The movably held combination of a wiping device and the profile separator can carry out a relative movement. As a result of mechanical contact between the wiping device and the profile separator the deposits are removed from the profile separator.

Abstract: A pivot joint assembly has a first part with a hole. A pivot pin passes through the hole. A second part is carried by the pivot pin to be rotatable relative to the first part. A bush has an annular sleeve with an inner face engaging the pivot pin and an outer face engaging a bore wall of the first part. A sealing ring between the bush and the first part. The sealing ring has a body attached to the first part, and a sealing member extending away from the body in a radial direction to a sealing lip which engages the bush without being attached thereto. The sealing member is resiliently compressed to urge the sealing lip towards the bush to maintain engagement with the bush in the event that the bush moves away from the body in the radial direction.

Abstract: An aircraft monument for installation in an aircraft cabin comprising a first functional module, a second functional module and a side wall for delimiting the first module from at least one of a region of the aircraft cabin adjacent to the first module and a region of the aircraft monument adjacent to the first module. The side wall is movable between a first and a second operational position and comprises a first side-wall region separating the first and second functional modules and in the second operational position, the side wall is displaced in the direction of the second module relative to its position in the first operational position, so that a movement of the side wall from its first operational position into its second operational position results in an enlargement of a base area of the first module and a corresponding diminution of a base area of the second module.

Abstract: The display device (1) comprises data capture means (2), calculation means (3) and a display screen (4), said calculation means (3) being configured to calculate at least one maximum slope that the aircraft can adopt depending on the data received from the data capture means (2), said device (1) also being configured to display said calculated maximum slope on at least a portion (5) of the display screen (4), which is configured to display a vertical flight plan.

Abstract: An interactive task organizer application may encourage a pilot to be more alert and engaged while operating the aircraft, despite that automation has made the job more passive. The interactive task organizer application may have access to flight data, and may use this data to create a virtual environment that encourages pilots to perform flight related tasks and to make visible explicit mission goals at a global and local level.

Abstract: The description provides a method of forming a seal around an end of a fastener protruding from a structure. The cap includes a cap body with a cavity; a sealing material inlet comprising an opening in the cap body; three or more ridges protruding from the cap body into the cavity; and three or more channels between the ridges. The method includes: installing the cap body over the end of the fastener so that it is enclosed within the cavity and contacted by the ridges; injecting sealing material into the cavity via the sealing material inlet so that the sealing material flows along the channels, fills the cavity, contacts the end of the fastener, and contacts the structure; and curing the sealing material to form the seal.

Abstract: The invention discloses a trailing edge (2) of an aircraft aerodynamic surface, which comprises an upper skin (6) and a lower skin (7), being the upper and lower skins (6, 7) made of composite material. In the trailing edge (2) a lightweight part (1) is assembled at an end section (13) of the upper and lower skins (6, 7). The lightweight part (1) is covered by a metallic sheet (8), and has a “V”-shaped cross section with arms and peak, where the peak of the “V”-shaped cross section has a rounded shape and is located opposite the end section (13) of the upper and lower skins (6, 7).

Abstract: The present disclosure provides an actuation system for a flight control surface of an aircraft, having: a support frame for supporting a flight control surface, the support frame being configured to be mounted to an airframe structure of the aircraft for movement between a first position and a second position to operate and move the control surface; an actuation mechanism configured to effect movement of the support frame between the second position and the first position; and a detection device for detecting a fault in the actuation mechanism, the detection device comprising a deflector configured to deflect or skew the support frame away from or out of the first position in the event of a fault in the actuation mechanism.

Abstract: A method and device for automatically determining an optimised approach and/or descent profile for an aircraft are provided. The device comprises means for optimising an approach and/or descent profile of an aircraft avoiding long and steep geometric segments, the device to this end inserting an idle segment, if it satisfies the restrictions, in the profile relating to the descent phase and/or to the approach phase, wherein said idle segment can be followed by a geometric segment.

Abstract: A computer implemented fuel management method and system for monitoring and minimizing a fuel consumption of an aircraft. The fuel management system and method determines, on the basis of model assumptions, a theoretical value relating to the quantity of fuel that is necessary for travelling along at least one sector of a flight route. Furthermore, the fuel management system and method determine a practical value relating to a quantity of fuel that is necessary for travelling along the same sector of the flight route, taking into account actual measured values. Moreover, the system and method compare the theoretical value with the practical value and to provide at least one measure in order to save fuel during a flight when the practical value differs from the theoretical value by a predeterminable amount.

Abstract: A system for opening and closing a door for a landing gear compartment of an aircraft includes a connection between the landing gear and the door with a first system forming an actuator mounted on the landing gear and a second system forming an actuator mounted on the door. The two systems form actuators connected to each other by at least one fluid communication device such that actuating the first system causes the actuation of the second system.

Abstract: A data processing and display system includes processing and display means adapted for displaying, from a more secured domain and on a same screen of a display processing device, information data from one or more less secured domains and active data from the more secured domain as a superimposition.

Abstract: A conduit harness retention system has a base, a first spacer, a second spacer and a cap which snap-fit together to retain P-clip harnesses in position spaced from an aircraft fuselage.

Abstract: A method for producing a fiber composite component, in particular for aerospace, the method comprising the following steps: forming a mold core from a material comprising cork by a molding tool to establish an outer geometry of said mold core; arranging the so formed mold core adjacent to an at least partly hardened stiffening element on a base element of said composite component to be produced for the shaping of at least one molded portion of said fiber composite component to be produced; and multistage exposure of at least said molded portion to heat and/or pressure to produce said fiber composite component; a corresponding mold core and a corresponding fiber composite component.

Abstract: According to the invention, the shape of each of said chevrons is defined: by two lateral sides (21, 22) having front ends (21A, 22A) that are connected to said nozzle (4, 10) and that, when moving away from the latter, converge towards each other without joining so that the rear ends (21R, 22R) of said lateral walls (21, 22) are spaced from each other; and by a curvilinear transverse line (23.1) connecting the rear ends (21R, 22R) of said lateral walls (21, 22) by forming two rounded side protrusions (24.1, 25.1) separated by an intermediate rounded recess (26.1).

Abstract: The stabilizing device (1) comprises auxiliary stabilizers (6) which are mounted on the horizontal tailplane (2) of the aircraft and which generate a lateral stabilizing effect when brought into a deployed position.

Abstract: A method and device optimize the vertical trajectory of an aircraft in flight along a predetermined approach trajectory. The method and device include the use of a calculator, which is structured to predict a predicted stabilization altitude at which the aircraft will reach a setpoint approach speed as a function of the current aircraft parameter values, a theoretical vertical trajectory, and predetermined models of aerodynamic efficiency of the aircraft. A comparator is structured to determine absolute value differences between the predicted stabilization altitude and the setpoint stabilization altitude and to compare the differences against a predetermined altitude threshold.