Foldable wing and actuator arrangement

A wing arrangement for an aircraft comprising:

• a wing having:
• a base section having a first end portion and an opposite second end portion, wherein the first end portion is adapted to be secured to a fuselage of the aircraft, and
• a tip section having a third end portion and an opposite fourth end portion, wherein the third end portion is pivotably connected to the second end portion such that the tip section is pivotable about a pivot axis between a deployed position and a stowed position in which the spanwise length of the wing is smaller than in the deployed position, and
• an actuating arrangement including:
• a linear hydraulic actuator, which comprises a cylinder defining a cylinder chamber and a piston movably arranged in the cylinder chamber and sealingly dividing the cylinder chamber into a first chamber section and a second chamber section, wherein the linear hydraulic actuator is coupled between the base section and the tip section such that the linear hydraulic actuator is operable to selectively move the tip section between the deployed position and the stowed position,
• a first hydraulic connection portion connected to the linear hydraulic actuator such that the first hydraulic connection portion is in fluid communication with the first chamber section,
• a second hydraulic connection portion connected to the linear hydraulic actuator such that the second hydraulic connection portion is in fluid communication with the second chamber section, and
• a first hydraulic subsystem and a second hydraulic subsystem, each connected to and branching off the first and second hydraulic connection portions, and each operable to supply pressurized hydraulic fluid to the first and second hydraulic connection portions, wherein
• a first shut-off valve is located between the first hydraulic subsystem and the first and second hydraulic connection portions, and is operable to selectively separate the first hydraulic subsystem from the first and second hydraulic connection portions,
• the first hydraulic subsystem comprises a first hydraulic supply including a first connector assembly adapted to be connected to a first hydraulic system of an aircraft which first hydraulic system is operable to supply a plurality of consumers of the aircraft with pressurized hydraulic fluid, and
• the second hydraulic subsystem comprises a motor and a pump, wherein the motor is coupled via a motor shaft to the pump such that motor is operable to drive the pump to pump hydraulic fluid contained in the second hydraulic subsystem to the first and second hydraulic connection portions.