A device for releasing a panel of an aircraft, the device being configured to be secured to a support, the support having an opening and the device being attached to cover a periphery of the opening, the device comprising a panel configured to be arranged at least opposite the opening. Such a device comprises: at least two ejector members, each of the at least two ejector members comprising at least one link; and at least one control member for applying a pulling force to the at least one link.

An airframe or a part thereof 3, for example a skin assembly or a profile such as a structural profile, comprises: a wall W having an aperture A therethrough, wherein the wall W provides a frame F surrounding, at least in part, the aperture A; a panel P conforming with the aperture A; and wherein the airframe or the part 3 thereof is configurable in: a first configuration, wherein the panel P and the frame F are mutually spaced apart; and a second configuration, wherein the panel P is received in the frame F and wherein the frame F resists movement of the panel P in two or three mutually orthogonal directions.

An aircraft fairing comprising at least one joint connecting a fixed panel to a movable panel, the joint comprising at least one first flange that is connected to the fixed panel, at least one second flange that is connected to the movable panel, and an elastically deformable junction region connecting the first and second flanges, the first and second flanges and the junction region forming a single part.

There is provided a door mechanism comprising a door and a door closure mechanism for moving the door between a first, open, position and second, closed position. The door closure mechanism comprises a drive motor coupled to a drive screw, the drive screw having a first, right handed thread portion and a second, left handed thread portion, a first drive nut threadedly engaged with the first thread portion, a second drive nut threadedly engaged with the second thread portion, a first drive linkage pivotally coupled to the first drive nut at one end and to the door at a second, opposed end, and a second drive linkage pivotally coupled to the second drive nut at one end and to the door at a second, opposed end.

A pressure bulkhead for the pressure-tight axial closure of a pressurized fuselage of an aircraft or spacecraft that can be put under an internal pressure, comprises a pressure dome, which is designed with a concave inner surface and a convex outer surface; inspection hatches, which each form an aperture in the pressure dome from the inner surface to the outer surface; and pressure covers for pressure-tight closure of the inspection hatches, wherein the pressure covers each have a cover and a pressure seal, wherein the cover is designed for the repeatedly releasable fixing of the pressure cover on the concave inner surface over the inspection hatch and wherein the pressure seal is formed at the edge of the cover for the pressure-tight closure of the cover with the pressure dome.

An electronic release system configured to unlock a hold open rod mechanism or latch mechanism includes an actuator interface configured with an input device and an actuator associated with the hold open rod mechanism or the latch mechanism. The input device configured to be actuated by personnel to initiate operation of an unlocking mechanism associated with the hold open rod mechanism or the latch mechanism. The electronic release system also includes a wiring assembly configured to connect the actuator interface to the actuator. The actuator interface configured to determine actuation of the input device and signal the actuator over the wiring assembly. The actuator being configured to operate the unlocking mechanism associated with the hold open rod mechanism or the latch mechanism.

There is provided a method of mounting equipment to an aircraft having an empennage. The method comprises mounting equipment to a mounting structure for mounting to the aircraft; removing an access panel from the outer skin of the empennage of the aircraft to reveal an access panel opening into the empennage; and attaching the mounting structure to or within the access panel opening such that at least a portion of the equipment extends beyond the outer skin of the empennage. The shape of the mounting structure at least partly conforms to the shape of the access panel opening. The method also comprises covering the mounting structure and the equipment mounted thereon with a cover, and attaching the cover to the mounting structure or the empennage. An assembly, structure, tailplane and aircraft are also provided.

A turbofan propulsion assembly includes a thrust reverser with movable flaps. The propulsion assembly further includes an engine and a nacelle surrounding the engine, and the nacelle includes a thrust reverser with sliding cowls and thrust reverser flaps, and an inner structure. The portion of the inner structure positioned perpendicular to the thrust reverser flaps includes two halves that can open toward the exterior of the nacelle cowls.

A fuselage rear end of an aircraft, comprising a structural part comprising a skin and longitudinal and transversal reinforcing members and a fairing. The structural part longitudinally spans over the whole rear end and comprises a first portion in which the transversal reinforcing members occupy the whole perimeter of the corresponding fuselage section and at least a second portion in which the transversal reinforcing members occupy only a portion of the perimeter of the corresponding fuselage section. The fairing is located below the second portion of the structural part.

This application teaches a flush mount, quick inspection portal for aircraft. An object of the invention is to provide a flush inspection portal that will allow quick access into inspection areas. Another object of the invention is to reduce the number of man hours required for periodic inspection of aircraft. Another object of the invention is to reduce the number of man hours required for periodic inspections. Another object of this invention is to provide a flush inspection portal that is durable against extreme temperature changes and vibrations. Another object of the invention is to provide inspection portals that may replace cover plates as an after factory add on or in manufacturing.