Abstract: A method for the manufacture of a light-weight panel, e.g. for aircraft, comprising preparing a panel preform having a pair of surface members or skins (29, 30) separated and supported by an internal core (26-28) in which spaces or interconnected pores provide vents to an edge of the panel, the wall surface members and the core comprising fibrous material, which may be carbon fibre, and using a pyrolysis process such as CVD to form a pyrolyric matrix around the fibres within the fibrous material, there being a flow of gas through the vents during the pyrolysis process.

Abstract: A multi-disc brake suitable for an aircraft has a stack of rotor and stator discs in which the discs of a set at one end of the stack each have a greater allowance for wear than the discs of a set at the other end of the stack whereby the group of discs are removed together from one end of the stack as a fully worn group at a brake servicing operation. An unworn group of discs is added to the other end of the stack.

Abstract: A method for the manufacture of a light-weight panel, e.g. for aircraft, comprising preparing a panel preform having a pair of surface members or skins separated and supported by an internal core in which spaces or interconnected pores provide vents to an edge of the panel, the wall surface members and the core comprising fibrous material, which may be carbon fiber, and using a pyrolysis process such as CVD to form a pyrolytic matrix around the fibers within the fibrous material, there being a flow of gas through the vents during the pyrolysis process.

Abstract: A multi-disc brake suitable for an aircraft has a stack of rotor and stator discs in which the discs of a set at one end of the stack each have a greater allowance for wear than the discs of a set at the other end of the stack whereby the group of discs are removed together from one end of the stack as a fully worn group at a brake servicing operation. An unworn group of discs is added to the other end of the stack.

Abstract: To monitor for the formation of a crack in a metal wheel such as that of an aircraft tire and wheel assembly the wheel is provided with an optical fiber arranged to extend no-rectilinearly in a position of the wheel surface selected to be preferential for the development of a crack; preferably the preferential region for crack development is the tire bead seat region and the optical fiber is arranged to extend non-rectilinearly around the circumference of the tire bead seat region thereby to lie interposed between the wheel and tire.

Abstract: A multi-disc brake suitable for an aircraft has a stack of rotor and stator discs in which the discs of a set at one end of the stack each have a greater allowance for wear than the discs of a set at the other end of the stack whereby the group of discs are removed together from one end of the stack as a fully worn group at a brake servicing operation. An unworn group of discs is added to the other end of the stack.