Various components and methods related to a leading edge assembly are disclosed. The leading edge assembly can include an outer strike shell and a foam core. The foam core can be located inside the outer strike shell. The leading edge assembly can include a heating element with a plurality of sensors and wires. A method of manufacturing a leading edge assembly can include forming a composite layer, applying a metallic layer to the composite layer, installing an electronic device, and inserting a foam core into a cavity bounded by the composite layer and/or the electronic device.

The invention concerns a method for generating auxiliary power in an aircraft, comprising the step consisting of: starting up an auxiliary power unit (6) of the aircraft by supplying compressed air to the auxiliary power unit (6) from a supercharger (7), and transferring non-propulsive energy from the auxiliary power unit (6) to the aircraft. The invention also concerns a system (5) for generating auxiliary power in an aircraft and an aircraft implementing such a method.

An aircraft removable equipment fitting device, the aircraft comprising a structure to which the removable equipment is configured to be attached. The aircraft removable equipment fitting device includes a first coupling configured to be joined to the aircraft structure, a second coupling configured to be joined to the removable equipment and to be coupled to the first coupling, and a fastener configured to tighten the removable equipment and the second coupling to the first coupling so that the removable equipment is fastened to the aircraft structure.

The invention relates to an electric power distribution box for an aircraft, comprising a frame (3) containing at least one power connector (7) formed of one or more slide rails (8) that are able to interact with one end (11) of a power circuit board (9), said power circuit board (9) comprising at least one switching element (13) for an electric power distribution plate. The invention also relates to an electric power distribution assembly (1) comprising such a power distribution box.

An engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system in fluid communication with a heat exchanger, an exhaust duct in fluid communication with air passages of the heat exchanger, a fan in fluid communication with the exhaust duct for driving a cooling air flow through the air passages of the heat exchanger and into the exhaust duct, and an intermediate duct in fluid communication with an exhaust of the engine and having an outlet positioned within the exhaust duct downstream of the fan and upstream of the outlet of the exhaust duct. The outlet of the intermediate duct is spaced inwardly from a peripheral wall of the exhaust duct. The engine assembly may be configured as an auxiliary power unit. A method of discharging air and exhaust gases in an auxiliary power unit having an internal combustion engine is also discussed.

A release mechanism comprises a locking body mounted for reciprocating movement in a first axial direction between a locked position and a released position. A force transmitting element is coupled to the locking body for transmitting a force (F) to the locking body for moving the locking body from the locked position to the released position. A biasing element acts on the locking body in a direction for moving the locking body from the released position to the locked position. The locking body comprises a slot having a first slot portion extending in said first direction, and a second slot portion extending transversely from one side of said first slot portion at an end thereof. The slot slidably receives an actuating element therein.

A system and a method for detecting a failure of a heat exchanger provided on an engine of an aircraft. An out-of-range fuel temperature downstream of an outlet of the heat exchanger is detected. A health of a fuel tank temperature signal indicative of a temperature of at least one fuel tank of the aircraft is monitored. A main oil temperature signal indicative of a temperature of oil in the engine is received. The failure is detected based on the main oil temperature and on the health of the fuel tank temperature signal.

Various components and methods related to a leading edge assembly are disclosed. The leading edge assembly can include an outer strike shell and a foam core. The foam core can be located inside the outer strike shell. The leading edge assembly can include a heating element with a plurality of sensors and wires. A method of manufacturing a leading edge assembly can include forming a composite layer, applying a metallic layer to the composite layer, installing an electronic device, and inserting a foam core into a cavity bounded by the composite layer and/or the electronic device.

An aircraft with a system for rearward mounting and dismounting an engine, the engine being placed inside the rear part of the aircraft when mounted. The system for rearward mounting and dismounting the engine comprises a first removable attachment device arranged to attach the engine to the fuselage in the rear part of the aircraft, internal supports fixed in the rear part of the aircraft, at least two longitudinal detachable rails, to be placed on the internal supports and under the engine, and a slider to attach to the engine via a second removable attachment device, to be placed on the longitudinal detachable rails.

A waste-gas line has a first pipe section connectable to a battery and having an inlet end and a first flange, a separate second pipe section having a second outlet end and a second flange, and an inner sleeve and an outer sleeve, both of a non-conductive material. The inner sleeve is positioned on an outer side of the first flange and of the second flange. The outer sleeve surrounds the first flange, the second flange and the inner sleeve. The first and the second flanges are fastened to one another in such a way that at least the second pipe section is electrically insulated by the inner and the outer sleeves and, by the combination of inner and outer sleeves, is heat-resistant up to a temperature of at least 1100 C. and pressure-resistant up to a pressure of at least 8 bar, for a duration of at least 120 seconds.