Airbus Operations

Disclosed is an aircraft refuelling system, the aircraft refuelling system comprising: a fuel tank; a refuel connector; and a conduit extending between the refuel connector and the fuel tank configured to carry a fluid; wherein the aircraft refuelling system further comprises a flame arrester removably mounted to the refuel connector.

Disclosed is a rib for an aircraft aerodynamic structure. The rib comprises a monolithic frame (30) that forms at least a majority of a perimeter of a space, and comprises first and second frame connectors. The space is between the first and second frame connectors. The rib comprises a replaceable strut (121, 122, 123, 124, 125, 126) having first (401, 403, 406, 408, 409, 412) and second (402, 404, 405, 407, 410, 411) ends that are releasably connected to the first and second frame connectors, respectively, so that the replaceable strut extends across the space.

A trolley arrangement (10, 10'), in particular for use in an aircraft cabin, comprises a trolley body (12) defining an interior space, a plurality of carriers (26) removably accommodated in the interior space of the trolley body (12), a plurality of heating devices (32, 32'), each heating device (32, 32') being associated with at least one of the plurality of carriers (26) and being configured to heat an item (28) arranged in at least a partial region (34a-c) of the carrier (26), a power distribution network (38) connectable to each of the heating devices (32, 32'), and a control unit (54) configured to receive an individual heating command for each of the heating devices (32, 32') and to control the power distribution network (38) so as to individually provide power to a selected one of the plurality of heating devices (32, 32') in response to a respective individual heating command.

A system for servicing a vacuum space in a hydrogen storage and distribution system of an aircraft is provided, the vacuum space being an interspace between a vessel and an insulated jacket, and having a vacuum valve communicating with the space. The system controls a vacuum pump arrangement using a sensor such as a microphone for sensing the pressure in the interspace, to equalise the pressure on the pump side of the valve with the vacuum space before opening the valve. This mitigates any damage to internal equipment which can result from high flow rates in the interspace.

A pipe assembly (100) comprising: a first rigid pipe section (110) having a first longitudinal axis (A1); a second rigid pipe section (120) having a second longitudinal axis (A2); and a flexible pipe section (130) attached to the first and second rigid pipe sections and configured to allow relative movement between the first rigid pipe section and the second rigid pipe section. The pipe assembly comprises a first sliding support (140) comprising a first joint section (142) fixed with respect to the first rigid pipe section and a second joint section (144) fixed with respect to the second rigid pipe section. The first joint section is configured to be in sliding contact with the second joint section during relative movement between the first rigid pipe section and the second rigid pipe section so as to limit axial misalignment between the first and second longitudinal axes. The pipe assembly comprises a second sliding support (150) comprising a third joint section (152) fixed with respect to the first rigid pipe section and a fourth joint section (154) fixed with respect to the second rigid pipe section. The third joint section is spaced apart from the fourth joint section in a first state. The third joint section is in sliding contact with the fourth joint section and maintains said sliding contact during relative movement between the first rigid pipe section and the second rigid pipe section so as to limit axial misalignment between the first and second longitudinal axes in a second state in which the first sliding support has failed.

The present invention relates to a computer system (100) and a computer-implemented method (300) for providing assistance data for at least one passenger-owned device (200) in an aircraft (10). The method (300) comprises providing (310), via an in-aircraft first data interface (112), real-time data indicative for at least one of an aircraft context and a cabin context of the aircraft (10). Alternatively or additionally, the method (300) comprises providing (320), via the first data interface (112) or via a ground-bound second data interface (120), static data descriptive for at least one of cabin characteristics of the aircraft (10) and in-flight service offerings. Further, the method (300) comprises processing (330), by at least one accessibility application (202) running on the at least one passenger-owned device (200), at least one of the real-time data and the static data to generate the assistance data.

This cavity filling device (26) for a track (24) of a high lift system (16) is configured for being installed in a cavity (33, 36, 40) of the track (24) for obstructing said cavity (33, 36, 40), the cavity filling device (26) comprising an obstructing portion defining an obstruction face, the obstruction face being configured to be flush with a border (B) of the cavity (33, 36, 40) when the cavity filling device (26) is installed in said cavity (33, 36, 40).

Set (1) for a modular antenna arrangement (2) for an aircraft (50), comprising a base module (10) for connecting at least one plate shaped antenna element (20a, 20b) with a fuselage (51) of the aircraft (50), wherein the base module (10) has a bottom surface (11) mechanically connectable with the fuselage (51) of the aircraft (50) and a top surface (12) comprising at least one accommodation recess (13a, 13b) for accommodating, at least partially, the at least one plate shaped antenna element (20a, 20b); at least one interchangeable antenna adapter module (30a, 30b) connectable to the base module (10) and the at least one plate shaped antenna element (20a, 20b), wherein the interchangeable antenna adapter module (30a, 30b) is configured to be arranged in the accommodation recess (13a, 13b) between a bottom (14a, 14b) of the accommodation recess (13a, 13b) and the plate shaped antenna element (20a, 20b); and a cover module (40) configured for at least partially covering the base module (10), wherein the cover module (40) comprises at least one opening (41a, 41b), wherein an opening cross-section of the at least one opening (41a, 41b) is adapted to a cross-section of the at least one plate shaped antenna element (20a, 20b).

The present invention provides an actuation unit (1) in an aircraft wing (201a, b) comprising two actuators (2a, b) driving a hinged lever (3) rotatably mounted in an attachment structure (4) with the attachment structure (2) having a base plate (16) and a first and a second flange (12a, b) each including a through hole (11a, b) and extend-ing vertically with respect to the base plate (16), with a receiving space (15) for receiving an end portion of the lever (3) formed between the flanges (12a, b) , wherein a tube (5) rotatably supported in the through holes (11a, b) extends through the flanges (12a, b) and the lever end and projects on both sides of the flanges (12a, b), wherein the tube (5) comprises on its outer circumferential surface (18) an outer structure (8a) engaged with the lever end for transmitting torque and on its inner circumferential surface an inner spline structure (7) engaged with an outer spline structure (14) of output shafts (6a, b) of the actuators (2a, b) attached on the outer surfaces (17, 19) of the flanges (12a, b), a method of assembling an actuation unit (1), an aircraft wing and an aircraft having such wing.

The present invention provides an actuation and latching system (100) in an aircraft wing (201a, b) having a fixed wing part (12) and a wing tip (11) part foldable relative to the fixed wing part (12) about a hinge axis (30) aligned perpendicular to an aircraft wing (201a, b) longitudinal axis, comprising at least one tip actuation unit (9) providing an interface between the fixed wing part (12) and the foldable wing tip (11) having hinge levers (5); at least one latching unit (7) arranged in the fixed wing part (12), wherein the at least one latching unit (7) comprises two latching bolts (8a, b) displaceable in opposite directions parallel to the hinge axis (30), wherein said latching bolts (8a, b) can be brought into engagement with the hinge levers (5) extending into the latching unit (7); a drive unit (101) arranged in the fixed wing part (12) and axially down-stream of the latching unit (7) with the drive unit (101) having at least a first drive shaft (3) coupled to the latching unit (7) and a second drive shaft (4) passing through the latching unit (7) and coupled to the tip actuation unit (9); and a control unit (13) for controlling the drive unit (101), a method for extending the foldable wing tip (11) part of an aircraft wing (201a, b), an aircraft wing (201a, b) and an aircraft (200) having such wing (201a, b) .