A seal for sealing an aircraft fuel tank, an aircraft wing rib and stringer sealing assembly, an aircraft wing fuel tank, an aircraft structural wing box, an aircraft wing, and a method of sealing an aperture are disclosed. The seal is for sealing a wing rib to a stringer passing through an aperture in the rib at a variable position in the aperture. The seal includes self-adjustment means to absorb any tolerance when forming the seal, upon the stringer being assembled into the aperture in the rib.

Aircraft antenna fairing assemblies include a fairing shell and connection components for positionally fixing the fairing shell to airframe structure of an aircraft. The connection components may comprise a guide assembly having a guide head and a receiver defining a guide channel for receiving the guide head therewithin, and a latch assembly for latching the fairing shell to the airframe structure of the aircraft. The receiver of the guide assembly may define a generally C-shaped or generally U-shaped channel for receiving the guide head therewithin.

Aircraft antenna fairing assemblies include a fairing shell and connection components for positionally fixing the fairing shell to airframe structure of an aircraft. The connection components may comprise a guide assembly having a guide head and a receiver defining a guide channel for receiving the guide head therewithin, and a latch assembly for latching the fairing shell to the airframe structure of the aircraft. The receiver of the guide assembly may define a generally C-shaped or generally U-shaped channel for receiving the guide head therewithin.

Apparatus for improving flow characteristics around aircraft wings by obstructing air flow through an aperture formed in a wing skin for a movable duct or track are disclosed. In one embodiment, the apparatus comprises a substantially rigid panel movable at least partially across the aperture for at least partially occluding the aperture and for accommodating movement of a slat track extending through the aperture. In another embodiment, the apparatus comprises a hinged panel configured to swing outwardly from an outer side of the wing skin toward an open position to accommodate movement of an anti-icing duct extending through the aperture and to swing toward a closed position at least partially occluding the aperture.

Apparatus for improving flow characteristics around aircraft wings by obstructing air flow through an aperture formed in a wing skin for a movable duct or track are disclosed. In one embodiment, the apparatus comprises a substantially rigid panel movable at least partially across the aperture for at least partially occluding the aperture and for accommodating movement of a slat track extending through the aperture. In another embodiment, the apparatus comprises a hinged panel configured to swing outwardly from an outer side of the wing skin toward an open position to accommodate movement of an anti-icing duct extending through the aperture and to swing toward a closed position at least partially occluding the aperture.

A noise abatement system for an aircraft landing gear is provided. The system may have a retention member and a covering member. In this regard, the system may be configured to block the airflow through a structural void to abate noise. Moreover, the system may be shaped to diminish aerodynamic drag.

An aircraft emergency landing stability system includes an aircraft a fuselage and landing gear, and a landing stability apparatus coupled to the fuselage, wherein the landing stability structure mitigates a nose-down pitching moment of the aircraft created in response to contact with a landing surface during an emergency landing.

A strut system for a wing of an aircraft, includes a strut member extending from the wing and a first jury strut assembly associated with the wing. The first jury strut assembly includes a first jury strut, which has a first end connected to the strut member and a second jury strut, which has a first end connected to the strut member, wherein a second end of the first jury strut and a second end of the second jury strut are each connected to the wing spaced apart from one another in a direction of a chord.

A strut system for a wing of an aircraft, includes a strut member extending from the wing and a first jury strut assembly associated with the wing. The first jury strut assembly includes a first jury strut, which has a first end connected to the strut member and a second jury strut, which has a first end connected to the strut member, wherein a second end of the first jury strut and a second end of the second jury strut are each connected to the wing spaced apart from one another in a direction of a chord.

A method may be present for securing a strip in a structure. A first surface of the strip may be masked with a first tape. A surface of the structure may be masked with a second tape, the surface of the structure defining a desired shape. A sealant may be applied in a groove in the structure. The strip may be positioned in the surface such that a second surface of the strip contacts the sealant; and a caul plate may be pressed against the first surface of the strip, the caul plate including a set of ribs that contact the fairing strip, and the plurality of ribs defining a shape that substantially matches the shape of the surface of the structure. Pressing the caul plate against the first surface of the strip may cause sealant to pass between the set of ribs onto the tapes.