Abstract: An inerting system of a fuel tank of an aircraft includes an air separation module supplied at the inlet with air at a certain pressure to generate at the outlet an inert gas to be injected into the fuel tank comprising a certain flow rate and a certain oxygen concentration. A control method includes, at a given instant and at a constant air temperature and atmospheric pressure, (1) reducing the inert gas flow rate to a determined value, and (2) reducing the air pressure in order to cause an increase in the oxygen concentration from an initial value to a determined value. Decreasing the inert gas flow rate is performed by compensating for a loss of inert gas flow caused by the air pressure reduction, and decreasing the air pressure is performed by compensating for a reduction in the oxygen concentration caused by the inert gas flow rate reduction.

Abstract: A method for manufacturing a strainer, such as a strainer of an ejector used to transfer fuel between two tanks of an aircraft or to supply fuel to an engine is provided. The strainer includes a conduit whereof a first end is intended to be connected to an inlet of the ejector, and whereof a second end is located within a housing including an open face for the passage of fuel, the open face being closed off by a grate acting as a filter. The method includes the step of manufacturing the conduit, the housing and the grate of the strainer as a single monobloc part.

Abstract: A fluid gauging system includes a set of fuel level probes and two computation modules adapted for inferring fluid level information based on measurement signals which originate from the probes. In a refuelling operation mode, the probes are distributed into two dynamically configurable subsets, which are separate and assigned respectively to the computation modules for deriving two results for the fluid level independently from each other. Such system has special interests for fuel tank equipment designed for aircraft. A major advantage is a reduction in the total number of fuel level probes which are necessary to obtain reliable results whatever the fuel level and the aircraft attitude and acceleration.

Abstract: A capacitor fuel probe comprises a plurality of capacitor segments which are superposed on one another along a probe axis. The capacitor segments are distributed into three sets and connected electrically in parallel within each set separately. A capacity measurement which is performed for all the sets allows determining a fuel level while taking into account a possible variation of a dielectric constant of the fuel parallel to the probe axis. Top height values hn of the capacitor segments are selected so that hn?1<hn·(Kmin?1)/(Kmax?1), for any integer n-value from 2 to N, N being the number of capacitor segments, n varying according a superposition order of the capacitor segments, and Kmin and Kmax being minimum and maximum values for a fuel dielectric constant which are prescribed for the capacitor fuel probe.

Abstract: A breathing system for an aircraft crew member or passenger may include a face-fitting device, a storage area added to a seat headrest for retaining the face-fitting device in a storage position apart from the head, and a back portion for retaining the face-fitting device on the user's head when the breathing system is used. The back portion is retained on the headrest by a removable fixing mechanism when the face-fitting device is in the storage position, and the removable fixing mechanism is released upon the tightening the face-fitting device on the user's head.

Abstract: Described are inerting systems that may be used on board an aircraft or other passenger transportation vehicle to reduce a risk of fire due to electronic components or to other elements in a compartment and to assist in preventing or extinguishing any fire or hazardous condition that may occur. The systems include a source of inert gas such as oxygen depleted air generated from a fuel cell on board the aircraft. The oxygen depleted air or other inert gas is conveyed through ducts to compartments that house the electronics, thus changing the conditions in the compartment to be less conducive to fire.

Abstract: An electronic circuit includes: a motherboard; an input/output connector including at least one group containing N input/output contacts; a set containing expansion slots having expansion contacts electrically connected to input/output contacts; each input/output contact being identified by an identifier T, each expansion slot being identified by an identifier S, each connected expansion contact being identified by an identifier R, for: each expansion slot of identifier S; and each connected expansion contact of identifier R. Each input/output contact of identifier T is electrically connected to a single expansion contact of identifier R of the expansion slot of identifier S, and the identifier T is calculated according to the following relation: T?[(R+D×S) modulo (N)], where D is fixed in each group and is an integer sub-multiple of the natural number N.

Abstract: A method for controlling an inerting system designed to inject a flow of inert gas into a fuel tank of an aircraft during a mission. The method includes: determining a value of a parameter of the mission of the aircraft at a given moment; determining the ratio between the determined value of the mission parameter and a value at the given moment of an equivalent parameter of a standard mission profile, and deducing a weight coefficient therefrom; using the weight coefficient to weight a value of the inert gas flow rate recommended by the standard mission profile for the value of the equivalent parameter at the given moment so that an appropriate inert gas flow rate to be injected is determined for the needs of the mission at the given moment; and commanding the inerting system to inject the inert gas flow rate determined at the given moment.

Abstract: An emergency oxygen system for aircraft comprising: a breathing gas supply circuit to be connected upstream to a source of breathing gas and downstream to at least one mask, a flow control valve configured to adjust the flow of breathing gas supplied to the mask, an electronics board configured to control the flow control valve, a power source, a switching device interposed between the power source and the electronics board, the switching device comprising a switch configured to have a first state in which power from the power source is supplied to the electronics board and a second state in which the electronics board is not supplied with power from the power source.

Abstract: Oxygen-delivery systems are described. The systems may supply emergency respiratory gas on demand to aircraft passengers. To reduce risk of blockage of tubes delivering anti-blocking gas to the face masks worn by the passengers, the systems may be designed to provide a continuous trickle flow of respiratory gas, or one or more anti-blocking pulses of gas, into a delivery tube.

Abstract: Regulator assemblies for breathing masks of aircraft crewmembers are described, with such an assembly including a mode selection knob mounted on a support. The knob is movable between at least two positions, allowing an associated regulator to operate in at least two modes of supplying breathing gas to a crewmember. One or more protrusions of the knob, when contacted by fingers of the crewmember, may bias the knob toward a particular one of the at least two positions.

Abstract: The invention relates to a tank for receiving fuel, said tank comprising a venting system comprising a flap for closing an opening made in the tank, said flap being subjected to a float and mounted in a hinged manner in the tank so as to adopt a closed position, pushed by the float when the level of fuel in the tank reaches a certain threshold, and an open, venting position, driven by the float when the level of fuel is below said threshold. According to the invention, the flap comprises a valve controlled by means that can open the valve when the flap is in a closed position and the level of fuel is below said threshold.

Abstract: An electronic circuit includes: a motherboard; an input/output connector including at least one group containing N input/output contacts; a set containing expansion slots having expansion contacts electrically connected to input/output contacts; each input/output contact being identified by an identifier T, each expansion slot being identified by an identifier S, each connected expansion contact being identified by an identifier R, for: each expansion slot of identifier S; and each connected expansion contact of identifier R. Each input/output contact of identifier T is electrically connected to a single expansion contact of identifier R of the expansion slot of identifier S, and the identifier T is calculated according to the following relation: T?[(R+D×S) modulo (N)], where D is fixed in each group and is an integer sub-multiple of the natural number N.

Abstract: An emergency equipment for an aircraft comprising: —a respiratory mask (5) comprising a harness (6), the respiratory mask (5) being adapted to be applied in a use position around the nose and the mouth of a user, —a stowage box (1) comprising a housing, the housing having side walls (2), a back wall (3) and an opening (4) opposite to the back wall (3), the side walls (2) and the back wall (3) defining an internal space (32) adapted to stow the respiratory mask (5) in a stowage position. The emergency equipment further comprises a support (10) supporting the respiratory mask (5) in the stowage position. The support (10) comprises a main plate (11) which is rigid and which is movable with respect to the stowage box (1) between a backward position and a frontward position along a longitudinal direction. The support (10) is in the backward position in the stowage position of the respiratory mask (5).

Abstract: A fuel manifold adapted to communicate with at least one fuel tank of an aircraft is presented. The manifold defines an enclosure adapted to be filled with fuel and to have an internal pressure P1 higher than the internal pressure P2 of the fuel tank. The enclosure includes at least one ceiling and at least one side wall provided with overflow holes adapted to communicate with the fuel tank. The manifold includes a mechanism for discharging an air pocket, trapped between the ceiling and the level of the overflow holes, to the fuel tank.

Abstract: Assembly intended in particular to be arranged in a cockpit of an aircraft, said assembly comprising a respiratory mask and a stowage device, wherein: the respiratory mask has a face cover and a harness, the stowage device comprises a base and a platform, the platform is adapted to receive the respiratory mask in a stowage position where the harness forms a loop extending around the platform, the platform comprises a main element movable relative to the base between a retracted position and a protruding position, and the platform further comprises auxiliary elements, the auxiliary elements movable with respect to the main element between a flattened configuration and an expanded configuration of the platform.

Abstract: A demand regulator (1) for aircraft breathing device (100) comprising: —a respiratory chamber (9) supplied with respiratory gas comprising breathable gas and dilution gas, —a breathable gas supply line (12, 13), —a dilution gas supply line (14, 15), —a first adjusting device (50, 60) of non-electrical type adjusting the pressure in the respiratory chamber (9), and —a second adjusting device (22, 24, 40, 41-49) adjusting the rate of dilution gas in the respiratory gas supplied to the respiratory chamber (9), the second adjusting device comprising a dilution valve (24) disposed in the dilution gas supply line (14, 15), a sensor (41-49) and an electrical control unit (40) adjusting the rate of dilution gas in the respiratory gas by controlling the dilution valve (24).

Abstract: There is provided a breathing assembly for an aircraft that includes a breathing mask to be connected to a source of breathing gas. The assembly also includes a stowage box forming a receptacle for receiving the breathing mask in a stowage position, and a valve assembly comprising a valve having an open position in which the valve allows the feed of breathing gas to the breathing mask and a closed position in which the valve prevents the feed of breathing gas to the breathing mask, the valve assembly being supported by the breathing mask. There may also be provided a retaining element connected to the stowage box and cooperating with the valve assembly to maintain the valve in the closed position when the breathing mask is in the stowage position.

Abstract: A protective system for aircraft pilot comprises a breathing mask, an eye protection and a safety device. The breathing mask is designed to supply the pilot with a respiratory gas and the breathing mask comprises an oxygen supply duct intended to be connected to an aircraft cockpit. The eye protection comprises a screen intended to extend between the pilot's eyes and an external space. The safety device comprises a display device and a support. The display device is able to display, notably in front of a pilot's eye, information intended to assist in the piloting of the aircraft. The support carries the display device so as to keep the display of information in front of the pilot's eye.

Abstract: An inert gas generation system from a flow of air, notably for an inerting system for at least one aircraft fuel tank. The generation system includes an air circuit having an air inlet, an inert gas outlet, and a first and a second air separation module arranged in series on the air circuit to deplete oxygen within the air and to generate a nitrogen-enriched inert gas.