Abstract: A differential pressure sensor system for use in an aircraft comprises a differential pressure sensor for determining a differential pressure between a pressurizable aircraft cabin and an aircraft environment, the differential pressure sensor having a first port connectable to the pressurizable aircraft cabin via a first line and a second port connectable to the aircraft environment via a second line. A shut-off device of the differential pressure sensor system is arranged in the second line which is switchable between an open position in which it opens the second line, such that a pressure prevailing in the aircraft environment acts on the second port of the differential pressure sensor, and a shut-off position in which it closes the second line, such that the second port of the differential pressure sensor is shut off from the pressure prevailing in the aircraft environment.

Abstract: A device providing a signal indicating whether a deployed aircraft evacuation slide is ready for use. A tilt sensor measures tilt angle about a predetermined axis and a tilt sensor measurement signal is provided. An inertial sensor detects acceleration and provides an inertial sensor measurement signal. A slide signal input terminal receives a slide signal indicating deployment of an evacuation slide and of a deployment length. A tilt angle signal output terminal at which a tilt angle signal is provided, and a slide status output terminal and a control unit to determine, based on the detected acceleration, a moment when the device is at rest with respect to earth and to set orientation of the reference plane to a predetermined orientation. The control unit stores data depending on position of a door, and can determine a slide length. A slide status signal is provided at the slide status output terminal.

Abstract: A differential pressure sensor system for use in an aircraft comprises a differential pressure sensor for determining a differential pressure between a pressurizable aircraft cabin and an aircraft environment, the differential pressure sensor having a first port connectable to the pressurizable aircraft cabin via a first line and a second port connectable to the aircraft environment via a second line. A shut-off device of the differential pressure sensor system is arranged in the second line which is switchable between an open position in which it opens the second line, such that a pressure prevailing in the aircraft environment acts on the second port of the differential pressure sensor, and a shut-off position in which it closes the second line, such that the second port of the differential pressure sensor is shut off from the pressure prevailing in the aircraft environment.

Abstract: A device for indicating an activation status of an aircraft emergency slide. The indicating device comprises an optical and/or acoustic signal emitting device, a status signal input, with a first input signal for an emergency slide activated state, and a second signal for a deactivated state, and a control, connected to the signal device, and to the status signal input, and configured to operate the signal device as a function of the status signal received, to indicate the status signal state. The indicating device comprises an inclination angle measurement device connected to the control for determining the inclination angle about a predetermined axis and provide an inclination angle signal output. The control determines, based on the determined inclination angle, whether a predetermined inclination angle has been exceeded for a predetermined time period and outputs, via the inclination angle signal output, a predetermined output signal only when this has occurred.

Abstract: An interface unit for use in updating software of an aircraft component on board an aircraft. The interface unit comprises a first interface to connect to a server providing one or more software updates for upload to the aircraft component, and a second interface to connect to the aircraft component. The interface unit further comprises a receiving component configured to receive a software update from the server via the first interface for upload to the aircraft component, and an uploading component configured to upload the received software update to the aircraft component via the second interface.

Abstract: A device providing a signal indicating whether a deployed aircraft evacuation slide is ready for use. A tilt sensor measures tilt angle about a predetermined axis and a tilt sensor measurement signal is provided. An inertial sensor detects acceleration and provides an inertial sensor measurement signal. A slide signal input terminal receives a slide signal indicating deployment of an evacuation slide and of a deployment length. A tilt angle signal output terminal at which a tilt angle signal is provided, and a slide status output terminal and a control unit to determine, based on the detected acceleration, a moment when the device is at rest with respect to earth and to set orientation of the reference plane to a predetermined orientation. The control unit stores data depending on position of a door, and can determine a slide length. A slide status signal is provided at the slide status output terminal.

Abstract: A device for indicating an activation status of an aircraft emergency slide. The indicating device comprises an optical and/or acoustic signal emitting device, a status signal input, with a first input signal for an emergency slide activated state, and a second signal for a deactivated state, and a control, connected to the signal device, and to the status signal input, and configured to operate the signal device as a function of the status signal received, to indicate the status signal state. The indicating device comprises an inclination angle measurement device connected to the control for determining the inclination angle about a predetermined axis and provide an inclination angle signal output. The control determines, based on the determined inclination angle, whether a predetermined inclination angle has been exceeded for a predetermined time period and outputs, via the inclination angle signal output, a predetermined output signal only when this has occurred.

Abstract: A warning light circuitry includes a first logic gate adapted for receiving a first, a second, a third, and a fourth input signal; a second logic gate adapted for receiving a fifth, a sixth, and a seventh input signal; a third logic gate electrically connected to the first and second logic gate; and a warning light electrically connected to the third logic gate. The first logic gate is adapted for providing a first output signal to the third logic gate upon receiving the first, the second, the third, and the fourth input signals. The second logic gate is adapted for providing a second output signal to the third logic gate upon receiving the fifth, the sixth, and the seventh input signals. Therein the third logic gate is adapted for triggering the warning light upon receiving the first or the second output signal.

Abstract: A warning light circuitry includes a first logic gate adapted for receiving a first, a second, a third, and a fourth input signal; a second logic gate adapted for receiving a fifth, a sixth, and a seventh input signal; a third logic gate electrically connected to the first and second logic gate; and a warning light electrically connected to the third logic gate. The first logic gate is adapted for providing a first output signal to the third logic gate upon receiving the first, the second, the third, and the fourth input signals. The second logic gate is adapted for providing a second output signal to the third logic gate upon receiving the fifth, the sixth, and the seventh input signals. Therein the third logic gate is adapted for triggering the warning light upon receiving the first or the second output signal.

Abstract: A system and method are disclosed for equalizing an overpressure in the interior of an aircraft cabin. The system includes a fluid flow path for providing fluid communication between the interior of an aircraft cabin and the exterior of the aircraft and a check valve having an opened state and a closed state. The check valve enables fluid flow through the fluid flow path from the interior of the aircraft cabin to the exterior of the aircraft and blocks fluid flow through the fluid flow path in the reverse direction when the check valve is in the opened state, and blocks fluid flow through the fluid flow path in both flow directions when the check valve is in the closed state. The system also includes a control operatively coupled to the check valve for controlling the check valve to switch between the opened state and the closed state.