An aircraft hubcap/wheel cover which uses ambient airflow (120 mph-175 mph) to rotate wheels on the landing gear of an aircraft accomplished by using slightly protruding slats, blades, scoops or other air capturing shapes, (once the landing gear has been lowered). These air capturing shapes are integrated as part of the hubcap/wheel cover during manufacture and are directly determined by ground speed applicable to that aircraft with the ultimate purpose being tire longevity. The wheel cover hubcap is a single piece design and has no moving parts.

A method, apparatus and system are disclosed in which an indication given by at least one tyre monitoring device is confirmed by input received from another source is disclosed. The method includes causing, by the control device, at least one tyre monitoring device mounted on a wheel to measure a tyre pressure and to indicate a status using an indicator provided on the tyre monitoring device; receiving, from the at least one tyre monitoring device, data representative of the status of the at least one tyre monitoring device; receiving input representative of the status indicated on the indicator of the at least one tyre monitoring device; comparing the received data representative of the status with the received input representative of the status; and taking action based on the result of the comparing.

A method, apparatus and system are disclosed in which an indication given by at least one tyre monitoring device is confirmed by input received from another source is disclosed. The method includes causing, by the control device, at least one tyre monitoring device mounted on a wheel to measure a tyre pressure and to indicate a status using an indicator provided on the tyre monitoring device; receiving, from the at least one tyre monitoring device, data representative of the status of the at least one tyre monitoring device; receiving input representative of the status indicated on the indicator of the at least one tyre monitoring device; comparing the received data representative of the status with the received input representative of the status; and taking action based on the result of the comparing.

An aircraft wheel (1) comprising a hub connected to a rim (3) provided with a tire (100), the hub having an outer surface that extends facing an inner surface (4) of the rim (3) and that co-operates therewith to define an annular space for receiving a stack of brake disks including rotor disks having axial peripheral notches, each notch receiving a segment of an axial bar (10) extending projecting from the inner surface (4) of the rim (3), and respective heat shields (20), each in the form of an annular segment, being mounted between the two bars (10) of respective pairs of adjacent bars. Each heat shield (20) includes at least one holder portion bearing against at least one first abutment (19, 119) secured to the rim (3) in order to hold the heat shield (20) in position on the rim (3) elastically.

An aircraft wheel (1) comprising a hub connected to a rim (3) provided with a tire (100), the hub having an outer surface that extends facing an inner surface (4) of the rim (3) and that co-operates therewith to define an annular space for receiving a stack of brake disks including rotor disks having axial peripheral notches, each notch receiving a segment of an axial bar (10) extending projecting from the inner surface (4) of the rim (3), and respective heat shields (20), each in the form of an annular segment, being mounted between the two bars (10) of respective pairs of adjacent bars. Each heat shield (20) includes at least one holder portion bearing against at least one first abutment (19, 119) secured to the rim (3) in order to hold the heat shield (20) in position on the rim (3) elastically.

A deployable aircraft flotation system. The deployable aircraft flotation system includes a pair of flotation members. The pair of flotation members are positioned on opposing sides of a bottom surface of an aircraft body. Each flotation member of the pair of flotation members has an inner layer that is made of a first buoyant material, an outer layer that is made of a second buoyant material, and a middle layer between the inner layer and the outer layer that is made of a rigid material. The flotation members can be moved from a stowed position, where they are stored in housings, to a deployed position, where they emerge and are positioned on the bottom of the plane.

A deployable aircraft flotation system. The deployable aircraft flotation system includes a pair of flotation members. The pair of flotation members are positioned on opposing sides of a bottom surface of an aircraft body. Each flotation member of the pair of flotation members has an inner layer that is made of a first buoyant material, an outer layer that is made of a second buoyant material, and a middle layer between the inner layer and the outer layer that is made of a rigid material. The flotation members can be moved from a stowed position, where they are stored in housings, to a deployed position, where they emerge and are positioned on the bottom of the plane.

An aircraft landing gear assembly including structural members coupled via a coupling including a bearing. The bearing has a body defining a first bearing surface arranged to contact a first counter-face of the coupling. The first bearing surface is defined by a first tubular layer of fibre reinforced polymer of a first type having an axis and containing synthetic fibres of a first type wound around and along the axis of the bearing. The bearing body further has a second tubular layer of fibre reinforced polymer of a second type containing synthetic fibres of a second type wound around and along the axis of the bearing.

Systems and methods for a heat-insulated wheel are disclosed herein. A wheel may comprise a wheel body comprising an outer diameter surface, an inner rim on an inboard side of the wheel body, an outer rim on an outboard side of the wheel body opposite the inner rim, and a heat insulator coupled to the outer diameter surface between the inner rim and the outer rim.

Systems and methods for a heat-insulated wheel are disclosed herein. A wheel may comprise a wheel body comprising an outer diameter surface, an inner rim on an inboard side of the wheel body, an outer rim on an outboard side of the wheel body opposite the inner rim, and a heat insulator coupled to the outer diameter surface between the inner rim and the outer rim.