Abstract: An aircraft wing high lift assembly comprising a movable element and a load receiving element including a body portion having a first load receiving region arranged to receive loads from the movable element in a first direction during normal operation of the high lift assembly and including at least one restraining arm projecting from the body portion, the or each restraining arm having a second load receiving region arranged to receive loads from the movable element in a second direction in the event of a failure within the high lift assembly.

Abstract: An aircraft wing high lift assembly comprising a movable element and a load receiving element including a body portion having a first load receiving region arranged to receive loads from the movable element in a first direction during normal operation of the high lift assembly and including at least one restraining arm projecting from the body portion, the or each restraining arm having a second load receiving region arranged to receive loads from the movable element in a second direction in the event of a failure within the high lift assembly.

Abstract: A deployment mechanism for moving an aircraft wing leading edge slat (2) or trailing edge flap (4) relative to a main airfoil (1) is provided. The mechanism includes an I-section support beam (6) extending between the main airfoil (1) and the slat (2) or flap (4). The support beam (6) is driven into and out of the main airfoil (1) by a rack and pinion mechanism (22, 23), the rack (22) being disposed along a lower boom (20) of the beam (6) and the beam (6) being supported for rolling contact with the main airfoil (1) by upper and lower straddle rollers (8, 9, 10, 11) positioned between wing leading edge ribs (12, 13). Roller tracks (16, 17, 18) extend along upper and lower booms (19, 20) of the beam with at least one roller track (17, 18) co-extending with the rack (22) adjacent thereto along the beam.