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An aircraft slat assembly comprises a first slat and a second slat positioned adjacent thereto. The first and second slats are moveable between extended and retracted positions. The slats are connected by a joint, the joint being arranged to transfer a shear load from one slat to the other slat when

An aircraft slat assembly comprises a first slat and a second slat positioned adjacent thereto. The first and second slats are moveable between extended and retracted positions. The slats are connected by a joint, the joint being arranged to transfer a shear load from one slat to the other slat when the slats are urged into a configurations in which there would be differential extension/retraction of the slats, such as a skewed position.

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1. An aircraft slat assembly comprising a first slat and a second slat positioned adjacent thereto and aligned therewith, the first and second slats being moveable between extended and retracted positions in which the first and second slats remain aligned, wherein the slats are connected by a joint,

1. An aircraft slat assembly comprising a first slat and a second slat positioned adjacent thereto and aligned therewith, the first and second slats being moveable between extended and retracted positions in which the first and second slats remain aligned, wherein the slats are connected by a joint, the joint prevents the slats becoming misaligned and the joint being arranged to transfer the shear load generated as the slats are being urged into a misaligned configuration, from one slat to the other slat, such that the shear load may be detected or otherwise used to identify the existence of a condition which could have lead to excess misalignment, before such misalignment actually occurs. 2. An assembly according to claim 1, wherein the slat assembly comprises an actuator system arranged to drive the slats between the extended and retracted positions. 3. An assembly according to claim 2, wherein the actuator system comprises a common drive means arranged to drive both the slats between the extended and retracted positions. 4. An assembly according to claim 2 further comprising a protector system, wherein the protector system is arranged to trip at least part of the actuator system in the event of an excessive load occurring in the actuator system. 5. An assembly according to claim 4 wherein the protector system is arranged to trip the actuator system when the magnitude of the shear load transferred from one slat to the other slat exceeds a threshold magnitude. 6. An assembly according to claim 1 wherein the joint comprises a rigid coupling between the slats, which substantially resists deformation under the shear load. 7. An assembly according to claim 1, wherein the joint is arranged to allow relative movement between the slats in a direction along the longitudinal axis of the slats. 8. An assembly according to claim 1, wherein the joint is arranged to allow relative rotation between the slats. 9. An assembly according to claim 1, wherein each slat comprises a first region proximal to the joint, and a second region distal from the joint, the first region being stiffer than the second region such that deformation of the slat in the first region, under the influence of the shear load, is inhibited. 10. An aircraft slat assembly comprising a first slat and a second slat positioned adjacent thereto and aligned therewith, the first and second slats being moveable between extended and retracted positions in which the first and second slats remain aligned, wherein the slats are connected by a joint, the joint permitting relative movement between the slats in at least some directions, but the joint prevents relative movement between the slats in the direction of extension/retraction of the slats, the joint thereby prevents the slats becoming misaligned.