An exposed main landing gear cavity in a bottom wall of an aircraft fuselage may include a main landing gear cavity outer ring recessed within the fuselage and having an inner surface encircling the main landing gear cavity, first baffle extending inward from the outer ring inner surface at an aft and inboard position on the inner surface, and a second baffle extending inward from the outer ring inner surface at an aft and outboard position on the outer ring inner surface. The main landing gear cavity may further include an aft fairing disposed proximate the outer ring bottom edge of the outer ring and connected to the fuselage at an aft side of the main landing gear cavity. An aft fairing top surface may have curvature causing the top surface to extend downward away from the outer ring as the top surface extends inward away from the outer ring.

An aircraft landing gear assembly has a longitudinally elongated frame coupled to a lower portion of a fuselage of an aircraft, the frame being capable of supporting at least a portion of the weight of the aircraft. A fairing encloses substantially all of the frame. An optional integrated step can be carried by the frame, and a longitudinally elongated aperture would be formed in the fairing adjacent the step. The step allows a user to place a foot into the aperture and onto the step. An optional door can cover the aperture, and an optional secondary step can be carried by the door.

An aircraft controller configured to determine a period and/or distance over which deployment of a landing gear can be initiated for landing including a determined first portion during which landing gear deployment can be safely initiated and a determined second portion, closer to aircraft landing than the first portion, during which the landing gear deployment can be safely initiated in an efficient landing mode; issue a first pilot feedback when the first portion is entered by the aircraft; issue a second pilot feedback when the second portion of the determined; and initiate landing gear deployment when the aircraft is in the determined period and/or distance in response to receiving a deployment signal from the pilot.

The invention relates to a body (2), a cavity (3) located on the body (2), enabling to place ammunition and similar payloads therein, a rear wall (4) which is the surface on which an airflow (AF) occurring with the movement of the body (2) leaves the cavity (3), and a floor (5) over which the airflow (AF) moves along the cavity (3).

There is provided an acoustically treated landing gear door for reducing noise from a landing gear of an aircraft. The acoustically treated landing gear door includes a landing gear door for attachment to the aircraft. The landing gear door includes an acoustic treatment assembly integrated on an inner mold line of an interior side, and extending within an interior cavity of the landing gear door. The acoustic treatment assembly includes a core structure having a first side and a second side, a plurality of core cells extending between the first side and the second side, and a drainage system. The acoustic treatment assembly further includes an acoustic facesheet and a nonporous backsheet. The acoustically treated landing gear door reduces the noise from the landing gear, when the landing gear is in a deployed position, by attenuating acoustic waves emanating from the landing gear and reflected off the acoustic treatment assembly.

An aircraft landing gear assembly including a plurality of noise-inducing elements, at least one of the noise-inducing elements comprising a brake assembly or electric drive assembly, and a noise reduction fairing arranged to shield only at least a portion of the brake assembly from incident airflow.

An aircraft landing gear assembly comprising: a structural pin defining a first bore having a longitudinal insertion axis; a cap for covering the bore, the cap comprising: a base portion; a head portion; a body portion positioned between the base portion and the head portion; and a bolt which extends between the head portion and the base portion and comprises a threaded portion so that engagement of either the head portion or the base portion with the threaded portion moves either the head portion or the base portion relative to the other, the body being formed of an elastically deformable material such that upon tightening of the bolt, the base portion moves towards the head portion and the elastically deformable material moves radially outwards such that a contact surface of the elastically deformable material engages with an inner surface of the first bore in order to retain the cap.

A landing gear assembly is also provided. The landing gear assembly may include a thin-skin support member defining a cavity and a cylindrical cavity. A cylinder may extend from the cylindrical cavity with an axle extending from the cylinder. A torsion link may be coupled to the axle and a torsion interface of the thin-skin support member.

A landing gear assembly is also provided. The landing gear assembly may include a thin-skin support member defining a cavity and a cylindrical cavity. A cylinder may extend from the cylindrical cavity with an axle extending from the cylinder. A torsion link may be coupled to the axle and a torsion interface of the thin-skin support member.

An aircraft landing gear which includes a noise-inducing region and a cover. The cover comprises a cover portion arranged to enclose the noise-inducing region to inhibit an airflow negotiating the noise-inducing region when the landing gear is in use.