Abstract: A head protective equipment comprises: —a breathing mask (2) connectable to a breathing-gas source and adapted to be applied, in a use position, around an user's nose and mouth, for supplying said user with breathing gas; —a shield (6) adapted to be applied around the user's eyes; and—first and second lock elements (28, 30, 38, 40), respectively located on said mask and on said shield, and adapted to cooperate with each other in order to secure said shield to said mask when said mask is in said use position around said user's nose and mouth, said first and second elements being adapted to create a snap-together connection, —said shield and said mask being adapted to be locked together by a two-step movement, the first step consisting in approaching the shield to the mask until said shield reaches said mask, and the second step being a substantially linear movement until locking.

Abstract: Embodiments of the present invention provide improved space utilization concepts for aircraft, and particularly to using under floor space created by the envelope designed to house an airstair system. For example, this space may be used to house and integrate one or more fuel cell system(s) and/or components, such as hydrogen tanks and/or the fuel cell body, such that the fuel cell system can deliver useful byproducts to support various aircraft functions. Additionally or alternatively, the space may be used to store other components.

Abstract: Embodiments of the present invention provide double deep, single width ovens for use in aircraft galleys. The ovens are particularly beneficial as they do not change current catering process or equipment, leading to their ease of acceptability and use in the airline galley design and development industry. The ovens may be used with two standard 32-meal carriers, such that the carriers are positioned front to back in the oven. Alternatively, 64-meal carriers may be developed that fit into the double deep oven as well.

Abstract: The invention relates to a method and a configuration and monitoring system for an aircraft cabin element of a plurality of cabin elements in a cabin of an aircraft, the system comprising: a radio frequency identification (RFID) device, wherein the RFID-device is associated with the aircraft cabin element adapted for providing a monitor signal adapted to indicate a status of the aircraft cabin element by a monitor information, a RFID-reader communicatingly connectable to the RFID-device, a controlling unit of a central cabin system.

Abstract: This invention relates to cabin service arrangement assigned to at least one passenger seat in a seat row of an aircraft, comprising: a lighting unit for providing a light projection and at least one man machine interface for operating the lighting unit, wherein the at least one man machine interface is associated with an initiating unit for providing an activation of the lighting unit and a deactivation unit for receiving an indication for deactivation of the light projection, wherein the deactivation is initialisable by an external signal, and wherein the light projection from the lighting unit comprises an illumination, the illumination being adapted to effect a cabin attendant call. According to the invention the illumination is adapted to be projected to a projection spot outside of the seat row, and the deactivation of the illumination is effectable from outside of the seat row.

Abstract: The invention relates to an emergency tubing set, including an oxygen mask adapted to cover a users mouth and nose, a tubing connected at a first end to said tubing set to provide oxygen to said oxygen mask, and a connect or connected to said tubing at a second end opposed to said first end, the connector being adapted to be connected to an oxygen source for supplying oxygen to said tubing. According to the invention the tubing includes an excess tubing section and a connecting tubing section wherein the excess tubing section is stored in a bottom pouch and a first part of an intermediate tubing section is arranged inside the bottom pouch and a second part of said intermediate tubing section is arranged outside said bottom pouch, wherein the intermediate tubing interconnects the excess tubing section and the connecting tubing section.

Abstract: Embodiments of the present invention provide a mounting bracket for use in connection with a rail, for assembling cabin interior components into an aircraft.

Abstract: The valve actuator (1) includes a housing (2), a motor (4) coupled to the valve, wherein rotation of the motor (4) changes the position of the valve from a first position in which fluid flow may occur along at least one path and a second position in which fluid flow is either blocked or may occur along at least one second path, said motor (4) being normally supplied with electrical power from a main source of electrical power, at least one sensor (24,132) configured to detect the position of the valve and/or the valve speed, a switch (16) controlling the delivery of electrical power to the motor (4), and a power circuitry (19) connected to the switch (16).

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: An de-icing system comprising a shield that is configured to deform in a pre-determined way that de-bonds accreted ice. In some embodiments, the shield has a variable (non-uniform) stiffness across its width and/or length such that it undergoes a twist-like or other suitable deformation when subjected to a force. In some embodiments, the system includes a plurality of electro-mechanical actuators configured to generate the force applied to the shield.

Abstract: The invention relates to a respiratory gas supply circuit for an aircraft carrying passengers, comprising a pressurized source of respiratory gas (R1, R2) and a supply line (2, 3), said circuit further comprising on said supply line a regulating device (12, 30) for controlling the supply in respiratory gas to said passengers, wherein said regulating device further comprises an electro-valve (12) controlled by a pulse width modulation signal provided by an electronic unit (20).

Abstract: A breathing assembly for aircraft comprising a storage unit, a breathing mask and a releasable securing device. The storage unit has a guiding surface extending perpendicularly to an elevation direction and a maintaining element. The breathing mask comprises a rigid support having a sliding surface adapted to slide in contact with the guiding surface of the storage unit, along a sliding direction between a storage position and an exit position. The support further has a maintaining element. In the storage position, the sliding surface of the support is prevented from moving away from the guiding surface of the storage unit along the elevation direction at the distal end by engagement of the maintaining element of the support with the maintaining element of the storage unit.

Abstract: According to the invention, the method comprises exposing a surface (3) sensitive to relative wind and monitoring the thermal flow variations between the surface (3) and the aerodynamic flow, said variations resulting from that of the forced-convection thermal exchange coefficient between the surface (3) and the aerodynamic flow depending on the rime or ice build-up, using the temperature sensor (12) under the surface (3), considering that stripping occurs by the flow of an ice layer formed on the surface (3) if it is detected, preferably after heating by at least one heater (4), that there is a brisk rise of the flow at a temperature close to 0° C., and supplying after the detection of ice stripping, a signal indicating the presence of rime or rime conditions. A cooler (5) may cool the surface (3) for anticipating the formation of ice with a heating process. The invention can be used for detecting rime and/or rime conditions on a flying aircraft.

Abstract: Oxygen breathing masks, as well as methods of providing oxygen to persons, are detailed. The devices may include mechanisms for supplying either oxygen or ambient air to a person depending on inspiration pressure applied by the person to a first volume to which the person's mouth and/or nose is connected.

Abstract: A breathing mask (1) for aircraft crewmember or passenger comprises a rigid portion (3) to be fit against the face of an user, said rigid portion comprising elements to bring a breathable gas to the user. The breathing mask further comprises an extensible harness (4) having end portions (5) connected to said rigid portion and including an inflatable element (6) connected to a source (7) of pressurized gas through a manually operable valve which delivers the pressurized gas to the inflatable element for extending the harness when actuated, and which reduces the pressure in said inflatable element to retract the harness and to cause the rigid portion to engage the face of the user when released. The source of pressurized gas is an autonomous container (7) supported by the rigid portion and containing the pressurized gas.

Abstract: The valve actuator (1) includes a housing (2), a motor (4) coupled to the valve, wherein rotation of the motor (4) changes the position of the valve from a first position in which fluid flow may occur along at least one path and a second position in which fluid flow is either blocked or may occur along at least one second path, said motor (4) being normally supplied with electrical power from a main source of electrical power, at least one sensor (24,132) configured to detect the position of the valve and/or the valve speed, a switch (16) controlling the delivery of electrical power to the motor (4), and a power circuitry (19) connected to the switch (16).

Abstract: The aircraft refuelling equipment (20) of an aircraft comprises a pipework (22) in which a fuel supply line (13) is connected to a plurality of tank supply lines, fuel tanks connected to tank supply lines of the pipework, first valves (24, 25,26) allowing each fuel tank to be disconnected from the fuel supply line, and at least one captor (30) that provides a signal indicative of a pressure or a flow rate. For each of said first valves, a first valve flow parameter can be estimated, using said captor. The equipment further comprises:—at least one actuator associated with each of said first valves, the actuator allowing adjustment of the opening of the associated first valve; and an electronic control unit (ECU) connected to the respective actuator-first valve assemblies and adapted to regulate an opening of the first ECU valves, using respective first valve flow parameter data.

Abstract: A liquid sensor system can detect whether liquid is present at a location within a tank or other container, such as an aircraft fuel tank. The system can include a sensor that has a heated negative temperature coefficient (NTC) element and a temperature compensator element. The sensor may be located within the tank. The elements can be polarized by voltages from separate voltage sources. The voltages can be compared to detect a presence or level of liquid within the tank. Only two wires may be needed to connect the sensor with components outside the tank. The system may be able to detect liquid using less than twenty five milliamps and a sensor temperature that is less than two hundred degrees Celsius.

Abstract: A device for oxygen supply of a user in an aircraft comprising a breathing mask (20), a stowage box (1) for the breathing mask and an oxygen supply hose (22) having one end connected to the stowage box and the other end connected to the breathing mask, wherein the device further comprises means (3) to fix the stowage box in a ceiling of the aircraft, an aperture on the bottom side of the stowage box closed by a door (7) and a leash (28) connected to the stowage box by one end and to the breathing mask by the other end so that, when the door is open, the mask falls and is kept hovered by the oxygen supply hose and the leash.

Abstract: The invention relates to a respirator mask with hygienic protection. More specifically, the invention relates to a respirator face mask (2) which provides physiological protection, comprising: an oronasal face piece (10), a semi-flexible lip element (6) which is used to position the oronasal face piece (10) on the user's face (1), and hygienic protection means (4) which are removably-positioned at least partially inside the mask (2). The aforementioned removable protection means (4) comprise (i) a first part (4a) which provides hygienic protection and (ii) a second part (4b) which maintains the hygienic protection means (4) inside the mask (2), said second part (4b) co-operating elastically with the above-mentioned semi-flexible lip element (6) or the face piece (10).