The present disclosure provides an aircraft security door as well as methods, systems and apparatus for handling an aircraft security door. In one implementation, a method for installing an aircraft security door onto an aircraft is disclosed. The method includes transferring the aircraft security door to an aircraft service stair, supporting the aircraft security door by a bridge crane coupled to the aircraft service stair, positioning the aircraft service stair in proximity to a fuselage of the aircraft adjacent to an opening in the fuselage, positioning the aircraft security door relative to the opening using the bridge crane, and securing the aircraft security door to the opening.

A nacelle for a bypass turbojet engine includes a cascade thrust reverser provided with reversal cascades arranged around an annular stream of fresh air, beneath front cowls. The cascades move backward with movable rear cowls, opening side passages in the annular stream, which receive the cascades for directing the fresh air flow forward, the bypass turbojet engine. The bypass turbojet engine includes fixing points, and the nacelle includes outer hatches closing openings of the front cowls, which are arranged radially outside the fixing points for access thereto, each hatch opening including a contour with edges of two front cowls.

A dual-interface coupler includes a utilities unit, a number of utility cables configured to provide a number of utilities to the utilities unit, a first coupling unit associated with the utilities unit, and a second coupling unit associated with the utilities unit. The first coupling unit is configured to mechanically couple the utilities unit to a first corresponding coupling unit and comprises a utility interface. The number of utilities are configured to flow from the utilities unit through the utilities interface. The second coupling unit is configured to mechanically couple the second coupling unit to a second corresponding coupling unit.

A dual-interface coupler includes a utilities unit, a number of utility cables configured to provide a number of utilities to the utilities unit, a first coupling unit associated with the utilities unit, and a second coupling unit associated with the utilities unit. The first coupling unit is configured to mechanically couple the utilities unit to a first corresponding coupling unit and comprises a utility interface. The number of utilities are configured to flow from the utilities unit through the utilities interface. The second coupling unit is configured to mechanically couple the second coupling unit to a second corresponding coupling unit.

A method of axially separating an annular system, such as a gas turbine engine (10), comprising first (34) and second (36) annular components. An annular array of fastenings (42) couples the first (34) and second (36) components together axially. The first (34) and second (36) components are supported by support tooling. The fastenings (42) are removed to leave one fastening (42) located on each side of the system. One of the remaining fastenings (42) is removed. The relative height of the first (34) and second (36) components is adjusted so that the apertures (46, 48) for the fastening (42) removed at the previous step are aligned. Then the final fastening (42) is removed.

A method of axially separating an annular system, such as a gas turbine engine (10), comprising first (34) and second (36) annular components. An annular array of fastenings (42) couples the first (34) and second (36) components together axially. The first (34) and second (36) components are supported by support tooling. The fastenings (42) are removed to leave one fastening (42) located on each side of the system. One of the remaining fastenings (42) is removed. The relative height of the first (34) and second (36) components is adjusted so that the apertures (46, 48) for the fastening (42) removed at the previous step are aligned. Then the final fastening (42) is removed.

Aircraft landing gear comprising an axle (100), a wheel (102) borne by the axle, a stack of discs (104) arranged to impose a braking torque on the wheel in response to a pressure imposed on the stack of discs, at least one electromechanical actuator (106) extending facing the stack of discs in order in a controlled manner to apply the imposed pressure to the stack of discs, and an actuator bearer (107) designed to bear the electromechanical actuator, the electromechanical actuator being fixed to the actuator bearer while at the same time being demountable. The actuator bearer is incorporated into the axle in such a way that the axle and the actuator bearer form a single component.

Method of demounting a stack of discs from such a landing gear.

An aircraft tire management system includes a management device capable of communicating with a tire manufacturer, an MRO-providing company, and an airline through a network, and an acquisition device configured to acquire tire individual information on aircraft tires and wheel individual information on wheels. The acquisition device sends the tire individual information acquired in the tire manufacturer to the management device, sends the tire individual information and the wheel individual information on each aircraft tire fitted on the corresponding wheel acquired in the MRO-providing company to the management device, and sends the wheel individual information acquired in the airline to the management device. The management device links the tire individual information with the wheel individual information, and outputs tire management information including at least tire identification information, location information, and date and time information.

An aircraft tire management system includes a management device capable of communicating with a tire manufacturer, an MRO-providing company, and an airline through a network, and an acquisition device configured to acquire tire individual information on aircraft tires and wheel individual information on wheels. The acquisition device sends the tire individual information acquired in the tire manufacturer to the management device, sends the tire individual information and the wheel individual information on each aircraft tire fitted on the corresponding wheel acquired in the MRO-providing company to the management device, and sends the wheel individual information acquired in the airline to the management device. The management device links the tire individual information with the wheel individual information, and outputs tire management information including at least tire identification information, location information, and date and time information.

The embodied invention is a storage frame that supports an aircraft engine with flexible engine mounting and is easily assembled by bolts. It includes feet to anchor the frame to the ground. It has adjustable height legs and is attachable to a variety of engine mount positions. It includes a central lifting tube with lifting connections that allow the frame to be lifted by an overhead crane or forklift. The adjustable legs provide convenience in transferring the engine onto a shipping support stand.