Abstract: An adjustable fixed structure attachment system 200 for an aircraft wing, the attachment system 200 including a bracket 210 having: a wall 212 for connection to a wing box, a protrusion 214 protruding from the wall 212, and a slot 216 extending through the protrusion 214, wherein the slot 216 has a height and a width, and a bush 220 having a bore 222 extending therethrough for receipt of a pin, wherein the bush 222 is insertable into the slot 216 and dimensioned relative to the slot 216 so that the bush 220 is substantially immovable in a width-wise direction of the slot 216, and is moveable in a height-wise direction of the slot 216 to thereby vary a position of the bush 220 within the slot 216.

Abstract: Apparatus for laminar flow control for a skin panel for an aircraft including a body for receipt into a recess of the skin panel. The body defines a chamber. The body includes an outer portion defining one or more micro apertures through the outer portion, each of the one or more micro apertures being in fluid communication with the chamber. The body includes a support portion supporting the outer portion, the support portion defining at least one outlet for allowing air to be drawn from the chamber in use by a suction means in fluid communication with the outlet in use. The apparatus is arranged such that, in use, air is drawn through the one or more micro apertures into the chamber and out of the outlet, thereby to promote laminar airflow over the outer portion in use.

Abstract: An aircraft joint between overlapping first and second components includes a fastener assembly. The fastener assembly includes a threaded fastener and a boss having an outer diameter and a threaded internal bore. The boss is fixedly attached to the second component at the overlap region. The first component has a through hole having a diameter sized to receive the outer diameter of the boss. The boss is received in the through hole from a first side of the first component. The fastener extends through the through hole from a second side of the first component opposite the first side. The fastener is threadably received in the internal bore of the boss and reacts against the second side of the first component to fasten the first component to the second component.

Abstract: An adjustable fixed structure attachment system 200 for an aircraft wing, the attachment system 200 including a bracket 210 having: a wall 212 for connection to a wing box, a protrusion 214 protruding from the wall 212, and a slot 216 extending through the protrusion 214, wherein the slot 216 has a height and a width, and a bush 220 having a bore 222 extending therethrough for receipt of a pin, wherein the bush 222 is insertable into the slot 216 and dimensioned relative to the slot 216 so that the bush 220 is substantially immovable in a width-wise direction of the slot 216, and is moveable in a height-wise direction of the slot 216 to thereby vary a position of the bush 220 within the slot 216.

Abstract: An aircraft joint between overlapping first and second components includes a fastener having a head and a shank, and a fastener retainer fixedly attached to the second component at the overlap region. The fastener retainer has a recess and a through hole. The fastener head is situated in the recess and between the fastener retainer and the second component. The fastener shank extends through the hole in the fastener retainer and into the first component to fasten the first component to the second component. The joint may be between an aircraft wing cover and a wing panel.

Abstract: Apparatus for laminar flow control for a skin panel for an aircraft including a body for receipt into a recess of the skin panel. The body defines a chamber. The body includes an outer portion defining one or more micro apertures through the outer portion, each of the one or more micro apertures being in fluid communication with the chamber. The body includes a support portion supporting the outer portion, the support portion defining at least one outlet for allowing air to be drawn from the chamber in use by a suction means in fluid communication with the outlet in use. The apparatus is arranged such that, in use, air is drawn through the one or more micro apertures into the chamber and out of the outlet, thereby to promote laminar airflow over the outer portion in use.

Abstract: An aerodynamic structure including a structural torsion box; a leading edge part fixed to a front side of the torsion box; an air inlet provided on a surface of the leading edge part; and a spanwise extending duct. The air inlet is provided at a first spanwise location, and is for enabling air to flow into an interior of the aerodynamic structure. The duct fluidly connects the air inlet to an air outlet which is spaced apart from the air inlet along a spanwise direction. The duct is within the torsion box.

Abstract: An aircraft joint between overlapping first and second components includes a fastener having a head and a shank, and a fastener retainer fixedly attached to the second component at the overlap region. The fastener retainer has a recess and a through hole. The fastener head is situated in the recess and between the fastener retainer and the second component. The fastener shank extends through the hole in the fastener retainer and into the first component to fasten the first component to the second component. The joint may be between an aircraft wing cover and a wing panel.

Abstract: An aircraft joint between overlapping first and second components includes a fastener assembly. The fastener assembly includes a threaded fastener and a boss having an outer diameter and a threaded internal bore. The boss is fixedly attached to the second component at the overlap region. The first component has a through hole having a diameter sized to receive the outer diameter of the boss. The boss is received in the through hole from a first side of the first component. The fastener extends through the through hole from a second side of the first component opposite the first side. The fastener is threadably received in the internal bore of the boss and reacts against the second side of the first component to fasten the first component to the second component.