A rotary actuator mounting system configured to attach a rotary actuator to and between two relatively moveable parts, the rotary actuator being attached to a first of the two relatively moveable parts and to a second of the relatively moveable parts such that operation of the actuator causes one of the first and second relatively movable parts to rotate relative to the other of the first and second relatively movable parts about an axis of the rotary actuator. The system includes a compliant attachment component connecting the actuator to the first relatively moveable part, the compliant attachment component having a first end attached to the first movable part and a second end attached to the actuator, and wherein at least one of the first and the second end is in the form of a ball bearing arranged to be received in a complementary socket on the actuator and/or the first movable part.

An air-redirection formation for a tip portion of an aerofoil such as an aircraft wing includes: a first portion, which includes a first surface which forms a continuation of the aerodynamic lifting surface of the wing, and which is for directing vortices away from the aerofoil; and a second portion, which is spaced from the first portion and which is positioned to generate uplift due to the directed vortices.

A joint for coupling a wing tip to a wing base includes a linking member that extends from a first end to a second end. The linking member first end is coupleable to the wing base, and the linking member second end is coupleable to the wing tip. The linking member defines first second hinge lines that are substantially parallel. The joint also includes at least one actuator. A first end of each at least one actuator is coupled to the linking member, and a second end of each at least one actuator is coupleable to one of the wing base and the wing tip. The at least one actuator is operable to rotate the wing tip about the first and second hinge lines between a first orientation and a second orientation relative to the wing base.

A wing arrangement for an aircraft is described including a wing (5) having a base section (5) and a tip section (13), the base section (7) having a first end portion (9) and a second end portion (11), the tip section (13) having a third end portion (15) and a fourth end portion (17), wherein the second end portion (11) and the third end portion (15) are coupled with each other by a coupling arrangement so that the tip section (13) is pivotable with respect to the base section (7) about a pivot axis (19, 19′).

A wing (1) having a fixed wing (3) and a wing tip device (4) rotatable between a flight configuration and a ground configuration, a rotational joint (10) rotatably couples the wing tip device (4) to the fixed wing (3) and a locking mechanism (46) locks the wing tip device (4) in the flight and ground configurations. The locking mechanism (11) includes first and second locking members (51, 52) and first and second receiving members (53, 54), the locking mechanism (11) being configured to lock the wing tip device (4) in one of the flight configuration and ground configuration by receiving the first and second locking members (51, 52) in the first and second receiving members (53, 54) respectively, and to lock the wing tip device (4) in the other of the flight configuration and ground configuration by receiving the first locking member (51) in the second receiving member (54).

An aircraft (2) including a wing (1), the wing (1) comprising a fixed wing (3) and a wing tip device (4) that is rotatable between a flight configuration and a ground configuration, the wing having a rotational joint (101) that rotatably couples the wing tip device (4) to the fixed wing (3), the rotational joint having an outer race (8) and an inner race (9), one of which is rotationally fixed relative to the wing tip device (4), to rotate about a rotational axis (B), and the other of which is rotationally fixed relative to the fixed wing (3), a rotational drive member (70) and the race that is rotationally fixed relative to the wing tip device (4) each being provided with a coupling section (110, 111, 114), the coupling sections being coupled to each other by a coupling member (119), that is received in a bore (112, 113) in one of the coupling sections, such that rotation of the drive member (70) rotates the race that is rotationally fixed relative to the wing tip device, to rotate the wing tip device (4) from one configuration to the other, wherein the coupling member (119) is mounted in the bore such that it is movable radially within the bore.

An aircraft (102) including a wing (101), having a fixed wing (105) with a wing tip device (103) moveably mounted at the outer end thereof. The wing tip device (103) is moveable between: a flight configuration; and a ground configuration. The wing tip device (103) and the fixed wing (105) are separated along an oblique primary cut plane (113). The wing tip device (103) and the fixed wing (105) meet along an interfacing cut line (135). The interfacing cut line (135) comprises a first length (137) offset from the primary cut plane (113) in a first direction; a second length (141) offset from the primary cut plane (113) in a second direction, opposite to the first direction; and a transition section (139) over which the interfacing cut line (135) transitions from the first length to the second length.

A wing assembly for an aircraft has a wing, a moveable wing tip device and an actuation assembly to move the wing tip device. The actuation assembly is disposed externally of the wing assembly. In a further aspect, the actuation assembly has a first connector member connected externally of the wing assembly at the actuator and pivotably connected at a lower portion of the wing or wing tip. This can facilitate the provision of effective internal supporting structure for transferring flight loads across the interface of the wing and wing tip device, especially in wing assemblies having a high aspect ratio. In a still further aspect, the wing assembly has a seal extending chordwise within the wing assembly, for resisting passage of air through an interface region between the wing and the wing tip device.

A manual brake override system includes a gear system, an electric motor in operative communication with the input of the gear system, a holding brake in operative communication with the input of the gear system. The holding brake is configured to prevent movement within the gear system when engaged. A manual handwind is provided in operative communication with the input of the gear system and the manual handwind and holding brake are configured such that the input of the gear system can be driven, with the manual handwind, whilst the holding brake is engaged.

A rotatable locking member for locking an aircraft wing with a movable wing tip device. The rotatable locking member including a U-shaped receiving portion arranged such that in an unlocked position the locking pin may be moved into and out of the U-shaped receiving portion, and in a locked position the locking pin is not able to be moved out of the U-shaped receiving portion, and the rotatable locking member is configured to be moved between the unlocked and locked position by rotational movement around the longitudinal central axis of the locking pin.