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: A wing leading edge assembly is disclosed including a leading edge panel and a cover panel located over the structural component. The cover panel has a thermoplastic layer with an inner surface. A thermoplastic fastening member extends through the structural component and is welded to the inner surface so that the structural component is fastened between the inner surface and the fastening member.

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: A leading edge skin panel for an aerodynamic structure of an aircraft. The skin panel includes attachment components for attaching the leading edge skin panel to the structure. A primary attachment component is configured to substantially prevent spanwise relative movement between the leading edge skin panel and the structure. The remaining attachment component are configured to permit a predetermined amount of spanwise relative movement between the leading edge skin panel and the structure.

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: A wing leading edge assembly is disclosed including a leading edge panel and a cover panel located over the structural component. The cover panel has a thermoplastic layer with an inner surface. A thermoplastic fastening member extends through the structural component and is welded to the inner surface so that the structural component is fastened between the inner surface and the fastening member.

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: A leading edge skin panel for an aerodynamic structure of an aircraft. The skin panel includes attachment components for attaching the leading edge skin panel to the structure. A primary attachment component is configured to substantially prevent spanwise relative movement between the leading edge skin panel and the structure. The remaining attachment component are configured to permit a predetermined amount of spanwise relative movement between the leading edge skin panel and the structure.

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.

Abstract: A improved display board including folding portions with multiple regions for attaching and storing stationary and other items, the folding portions being multi-sided overlapping display areas for retaining various articles.