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A trailing edge flap arrangement for an aircraft wing, comprising an array of flap elements each discretely moveable between a retracted and an extended position by a respective actuator, wherein the flap elements are arranged to be deployed so as to open up a through slot between an adjacent pair o

A trailing edge flap arrangement for an aircraft wing, comprising an array of flap elements each discretely moveable between a retracted and an extended position by a respective actuator, wherein the flap elements are arranged to be deployed so as to open up a through slot between an adjacent pair of the flap elements only when the aerodynamic leading element of the pair has reached its extended position. Also, a method of operating the trailing edge flap arrangement.

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1. A trailing edge flap arrangement for an aircraft wing, comprising an array of flap elements each discretely moveable between a retracted and an extended position, wherein the flap elements are arranged to be deployed so as to open up a through slot between an adjacent pair of the flap elements on

1. A trailing edge flap arrangement for an aircraft wing, comprising an array of flap elements each discretely moveable between a retracted and an extended position, wherein the flap elements are arranged to be deployed so as to open up a through slot between an adjacent pair of the flap elements only when the aerodynamic leading element of the pair has reached its extended position, and wherein a first hinge point is disposed between the wing and the aerodynamic leading flap element in the array, and a first ram actuator is connected between the wing and the aerodynamic leading flap element across and above the first hinge point for rotating the aerodynamic leading flap element about said first hinge point, andwherein a second hinge point is disposed between the aerodynamic leading flap element and an adjacent aerodynamic trailing flap element aft of the aerodynamic leading flap element, and wherein said aerodynamic leading flap element and aerodynamic trailing flap element are rotatably connected to one another at said second hinge point, and a second ram actuator is connected between said aerodynamic leading flap element and said aerodynamic trailing flap element across and above the second hinge point for rotating the aerodynamic trailing flap element about said second hinge point. 2. A flap arrangement according to claim 1, wherein a through slot is opened up between the wing and the aerodynamic leading flap element in the array when the leading element is in its extended position. 3. A flap arrangement according to claim 1, further comprising a linkage arrangement supporting the array of flap elements from the aircraft wing for movement relative to the wing. 4. A flap arrangement according to claim 3, wherein the linkage arrangement includes a plurality of flap supports each for supporting a respective flap element. 5. A flap arrangement according to claim 1, wherein the array of flap elements includes at least three flap elements, and a respective hinge point is disposed between each adjacent pair of flap elements, and a ram actuator is connected between each said adjacent pair of flap elements across the respective hinge point for rotating the aerodynamic trailing element of said pair of flap elements about said respective hinge point. 6. A flap arrangement according to claim 4, wherein each flap element is rotatable about a respective hinge point, and wherein adjacent flap supports are pivotally connected by one of the hinge points. 7. A flap arrangement according to claim 1, wherein adjacent flap elements are moveable between a first position in which the flap elements are sealed together, and a second position in which a through slot is opened up between the flap elements. 8. A flap arrangement according to claim 1, wherein a through slot is opened up between each adjacent pair of flap elements when all of the elements are in their extended position. 9. A flap arrangement according to claim 1, wherein the array includes three elements. 10. A method of operating a trailing edge flap arrangement on an aircraft wing, the flap arrangement including an array of flap elements each discretely moveable between a retracted and an extended position, wherein a first hinge point is disposed between the wing and the aerodynamic leading flap element in the array, and a first ram actuator is connected between the wing and the aerodynamic leading flap element across and above the first hinge point for rotating the aerodynamic flap element about said first hinge point, and wherein a second hinge point is disposed between the aerodynamic leading flap element and an adjacent aerodynamic trailing flap element aft of the aerodynamic leading flap element, and wherein said aerodynamic leading flap element and aerodynamic trailing flap element are rotatably connected to one another at said second hinge point, and a second ram actuator is connected between said aerodynamic leading flap element and said aerodynamic trailing flap element across and above the second hinge point for rotating the aerodynamic trailing element of said second hinge point, the method comprising deploying the flap elements so as to open up a through slot between said adjacent pair of the flap elements only when the aerodynamic leading element of the pair has reached its extended position. 11. A method according to claim 10, further comprising adjusting the flap arrangement to a first configuration in which the array of flap elements are sealed together and in their retracted position. 12. A method according to claim 10, further comprising adjusting the flap arrangement to a second configuration in which the array of flap elements are sealed together and the aerodynamic leading flap element in the array is in its extended position so as to provide a single slotted flap. 13. A method according to claim 10, further comprising adjusting the flap arrangement to a third configuration in which each of the flap elements are in their extended position so as to provide a multi-slotted flap, with a through slot between each adjacent pair of the elements. 14. A method according to claim 10, wherein the array includes three elements, and the method further comprises adjusting the flap arrangement to a fourth configuration in which each of the elements in the array, except the trailing element, is in its extended position so as to provide a double slotted flap. 15. A method according to claim 10, wherein the array of flap elements includes at least three flap elements, and a respective hinge point is disposed between each adjacent pair of flap elements, and a ram actuator is connected between each said adjacent pair of flap elements across the respective hinge point, and the method includes rotating the aerodynamic trailing element of said pair of flap elements about said respective hinge point.