Abstract: Apparatus for preventing fluid spray at a leakage area of a fluid pipe comprises at least one first enveloping element and at least one second enveloping element which encloses the fluid pipe so as to be flush with it, and which are circumferentially interrupted, wherein the circumferential interruptions of the enveloping elements are arranged so as to be offset relative to each other. In this way, fluid spray formation may be prevented in an economical way. The simple design ensures easy installation and economical production.

Abstract: An aircraft spherical bearing assembly comprises a first part which is in sliding contact with an intermediate part for sliding therebetween to form a spherical joint. A second slip path is provided between the intermediate component and an outer component which can be selectively actuated when the force through the first slip path exceeds a predetermined level.

Abstract: An aircraft cooling system evaporator arrangement has at least two mutually independent coolant circuits, at least two evaporation devices arranged to be hydraulically parallel for enabling an exchange of heat between the coolant and a refrigerant, at least two supply lines for supplying refrigerant to the evaporation devices, and at least two discharge lines for discharging refrigerant from the evaporation devices. A different one of the evaporation devices, a different one of the supply lines and a different one of the discharge lines are assigned to each of the coolant circuits, and the supply lines are hydraulically separate from each other as are the discharge lines. At least one refrigerant sensor monitors a refrigerant state of each of the discharge lines and an expansion valve is driven in accordance with the refrigerant sensors to control streams of refrigerant through the supply lines.

Abstract: A wing, having an adjustable flap that can be moved between a retracted and an extended setting is provided, as well as a gap-covering device, with an adjustment lever and a gap-covering flap arranged on the latter with a flow surface. The adjustment lever with the gap-covering flap is pre-loaded by means of a pre-loading device into a first setting, in which the gap-covering flap is located in the interior of the wing. The adjustable flap and the adjustment lever with the gap-covering flap are mechanically coupled such that as the adjustable flap moves into its retracted setting, a movement of the adjustment lever takes place against the pre-load effected by the pre-loading device, into a second setting. The flow surface of the gap-covering flap in the second setting of the adjustment lever runs between the upper side of the retracted adjustable flap and the wing flow surface.

Abstract: An adjustment mechanism of a device for coupling a flap to a wing of an aerofoil and for adjusting the flap. The adjustment mechanism includes: a first lever, hinged to the wing via a first rotational joint to form a first axis of rotation; a second lever; a third lever, hingedly coupled to the second lever via a second rotational joint to form a second axis of rotation and hingedly coupled to the flap via a fourth rotational joint; and a push-pull rod, which is connected via a first ball joint to the second lever and via a second ball joint to the flap. The first lever and the second lever are hingedly coupled to one another via a middle joint to form a third axis of rotation. The first, second and third axes of rotation in each position of the flap run through a common pole.

Abstract: A method for repairing the skin of the fuselage of an airplane from the inside to be used when the skin of the fuselage has been damaged between a first stringer and a second stringer adjacent to the first one is provided. The method includes filling the damage, placing a first doubler over the filling, placing a second doubler over the first doubler and bending this second doubler at least over a flange of one of the stringers, and securing the second doubler.

Abstract: An aircraft cooling system evaporator arrangement has an evaporation device including four evaporators that are hydraulically separate from each other with respect to coolant flow. Refrigerant flows from a feed line into first and second evaporators, from the first evaporator into and through a third evaporator, and from the second evaporator into and through a fourth evaporator. The first and third evaporators define a first pair of evaporators arranged parallel to a second pair of evaporators defined by the second and fourth evaporators. First and second coolant supply lines of a first coolant circuit supply coolant to one of the evaporators in each of the first and second pair of evaporators respectively, and first and second coolant supply lines of a second, independent coolant circuit supply coolant to the other of the evaporators in each of the first and second pair of evaporators respectively.

Abstract: According to the invention, an alert may be generated when a sudden inversion of the rudder occurs. To this end, the pilot having beforehand moved a commanding system in such a manner that the movement of the commanding system overcomes the position of the commanding system corresponding to the maximum rotation breakpoint in one of the rotating directions of the rudder. The alert is launched if, during a first time interval having a predetermined duration, the pilot moves the commanding system in such a manner that the movement of the commanding system overcomes the position of the commanding system corresponding to the maximum rotation breakpoint in the other rotating direction of the rudder, thereby indicating a sudden rudder inversion and a potential unsafe condition to be corrected by the pilot.

Abstract: A keel beam connected to a central wing box of an aircraft and ensuring the connection between a front structure and a rear structure of an aircraft is characterized in that it includes, on the one hand, a U-shaped body with a horizontal base and two solid lateral walls, and on the other hand, a cover which has a U shape oriented in the same manner as the body, with a base in the lower portion and curved edges, the ends of which are oriented upward so that each curved edge includes an outer surface flattened against and fixed to the inner surface of the lateral walls in order to define, with the body, a closed section, the cover including openings for accessing the inside of the keel beam.

Abstract: A method for controlling the piloting of an aircraft comprising the steps of receiving at least one first instruction for modification of a current velocity vector of the aircraft, determining a target velocity vector of the aircraft, on the basis of said at least one first instruction received, and determining, on the basis at least of said target velocity vector, at least one actuation command intended for at least one actuator of the aircraft in order to modify the movement of the aircraft according to said at least one first instruction received.

Abstract: A method for updating a software application stored in an equipment item on board an aircraft. The method comprises downloading update files to an on-board dataloader, checking the integrity and authenticity of the new software application version, transmitting this new software application version to the equipment item concerned, storing the new software application version in question into a standby memory zone of said equipment item, while this equipment item is still controlled by a previous version of said software application stored in an active memory zone, distinct from said standby memory zone, and finally, switching said standby and active memory zones, said equipment item being then controlled by the new software application version stored in the active memory zone after the memory zones have been switched.

Abstract: An optical measuring device for measuring a surface contour of an object, includes a tripod on which a camera platform is mounted, wherein on the camera platform at least two photo cameras are arranged for imaging the object comprising marking elements, and the at least two photo cameras are arranged on the camera platform in such a manner that imaging the object can be carried out from two different perspectives, wherein between the camera platform and the tripod a displacement device for the linear displacement of the camera platform in three directions that are independent of each other is arranged.

Abstract: A system for detecting misalignment of an aero surface relative to other aero surfaces during simultaneous deployment of said aero surfaces is disclosed. It comprises a generator configured to shine a laser through aligned apertures in a series of aero surfaces towards a reflector during deployment of said aero surfaces, a receptor to detect reflection of said laser from said reflector back through said apertures to the generator and, a controller operable to terminate further deployment of said aero surfaces in the event that no reflection is detected by said receptor, or if an actual time taken for the reflected beam of light to be detected by the receptor differs from a predetermined time. In a preferred embodiment the aero sufaces are slats extending from the leading edge of an aircraft wing.

Abstract: A manufacturing procedure of a composite material part (11), with an edge region (13) destined to be joined to another part by rivets, making a change in the geometry of said edge region (13) with respect to an initial surface (41) on the part's external face, comprising the following steps: a) providing a laying-up tool incorporating a modified surface (43) according to said change in the edge region (13) geometry; b) providing the composite material plies needed for the laying-up of the part, with the plies (51, 51?, . . . , 51n) destined for the edge region (13) of the part affected by the geometric modification being already cut so that they finish as they reach said modified surface (43); c) laying-up said plies over said tool and curing the resultant laminate. The invention also refers to a lower skin of an aircraft wing (11) manufactured according to said procedure.

Abstract: An aircraft slat assembly comprising a pair of slats separated by a gap. A weather seal seals the gap between the slats and forms part of an outer aerodynamic surface of the slat assembly. An anti-icing system is provided with a pair of piccolo tubes, each tube being housed within a respective one of the slats and having spray holes for delivering hot gas to a leading edge of the slat in which it is housed. A flexible duct delivers hot gas between the piccolo tubes, the flexible duct passing across the gap between the slats. A vent in the weather seal can open to permit hot gas from the anti-icing system to exit the gap between the slats.

Abstract: A blind fixation device for attaching an assembly of a pre-drilled member set that includes a rod defining a traction mandrel, a first bushing, and a second deformation brushing. The second deformation bushing is capable of deformation on an inaccessible side of the set of pre-drilled members between the head of the mandrel rod and the end portion of the first bushing. The first bushing is capable of bearing on the accessible side surface of the set of pre-drilled members to be assembled, and is capable of radial deformation so as to come in close contact with the drilling profile of at least one pre-drilled member when, upon assembly, the portion of the mandrel rod initially in the second bushing enters the first bushing.

Abstract: An aircraft engine assembly including a turboshaft engine with a propeller and an attachment pylon intended to be laterally attached on a rear portion of the structure of the aircraft is disclosed. The pylon has an outer surface forming an aerodynamic profile incorporating a trailing edge which is arranged upstream of the propeller of the turboshaft engine. The pylon includes a mobile rear flap at least partially defining the trailing edge and a controller which steers the incidence of the flap according to a law depending on the incidence of the aircraft.

Abstract: An aircraft includes a part defining an aerodynamic surface against which flows an air stream, with at least one hood able to block an opening made at the aerodynamic surface, kept in the closed position by at least one locking mechanism, and an access flap for the locking mechanism, pivoting relative to the hood around an axis substantially parallel to the flow direction of the air stream and including elements for keeping it flattened against the hood, characterized in that it includes a device for protection of the access flap that includes a coverage plate that pivots around an axis of rotation, and which is able to occupy a first position in which it projects relative to the aerodynamic surface and another position in which after pivoting around the axis of rotation, it is flattened against the outside surface of the access flap such that the protective device limits the appearance of a scoop phenomenon.

Abstract: A system for setting a span load distribution of a wing of an aircraft with a base flap system comprises at least one inboard flap element and one outboard flap element, which elements in the direction of the span are arranged on the trailing edge of the wing, and can be positioned relative to the span direction of the wing. The flap elements are not mechanically coupled with each other and are controlled independently of each other for the purpose of setting the span load distribution.

Abstract: An ultrasound scanner (100) which has a plurality of ultrasound transducers (104) directed normal to a scanning surface (106) to scan a workpiece (114), the scanner (100) comprising a couplant filled latex rubber sheath (106) shaped to the surface of a workpiece (114).