Abstract: A method for testing a portable electronic device. The method comprises the following steps: acquiring at least one set of parameters; storing the at least one set of parameters in a first area of a storage unit of the portable electronic device; storing the at least one set of parameters in a second area of the storage unit; generating at least a first image by means of a first processing operation; in a first displaying step, displaying the at least one first image for a predetermined time period; in a first erasing step, erasing first intermediate results corresponding to calculation steps carried out during the first processing operation; generating at least one second image by means of a second processing operation; and in a second displaying step, displaying the at least one second image for a predetermined time period.

Abstract: A method for testing a portable electronic device. The method comprises the following steps: acquiring at least one set of parameters; storing the at least one set of parameters in a first area of a storage unit of the portable electronic device; storing the at least one set of parameters in a second area of the storage unit; generating at least a first image by means of a first processing operation; in a first displaying step, displaying the at least one first image for a predetermined time period; in a first erasing step, erasing first intermediate results corresponding to calculation steps carried out during the first processing operation; generating at least one second image by means of a second processing operation; and in a second displaying step, displaying the at least one second image for a predetermined time period.

Abstract: An adjustment device for adjusting the position of the center of gravity of an aircraft, the aircraft having at least two thrust production units that contribute at least to providing the aircraft with lift, the adjustment device comprising at least one heavy member that is movable relative to an airframe of the aircraft and also at least one actuator for causing the heavy member to move. The adjustment device includes an avionics system configured to detect a failure of any one of the thrust production units and, in the presence of such a failure, to control the at least one actuator to cause the heavy member to move.

Abstract: An undercarriage having an undercarriage leg carrying at least one stub, the stub being provided with a hollow element. An onboard device comprises a bar and at least one measurement unit. The measurement unit comprises two pieces of equipment, one of the pieces of equipment comprising a measurement member and one of the pieces of equipment comprising a wall. One of the two pieces of equipment is secured to the bar and one of the two pieces of equipment is secured to the hollow element, the onboard device including a test system. The test system has movement means for imparting, on request, relative movement between the pieces of equipment in order to detect a potential malfunction and in order to generate an alert if a malfunction is detected.

Abstract: An adjustment device for adjusting the position of the center of gravity of an aircraft, the aircraft having at least two thrust production units that contribute at least to providing the aircraft with lift, the adjustment device comprising at least one heavy member that is movable relative to an airframe of the aircraft and also at least one actuator for causing the heavy member to move. The adjustment device includes an avionics system configured to detect a failure of any one of the thrust production units and, in the presence of such a failure, to control the at least one actuator to cause the heavy member to move.

Abstract: An undercarriage having an undercarriage leg carrying at least one stub, the stub being provided with a hollow element. An onboard device comprises a bar and at least one measurement unit. The measurement unit comprises two pieces of equipment, one of the pieces of equipment comprising a measurement member and one of the pieces of equipment comprising a wall. One of the two pieces of equipment is secured to the bar and one of the two pieces of equipment is secured to the hollow element, the onboard device including a test system. The test system has movement means for imparting, on request, relative movement between the pieces of equipment in order to detect a potential malfunction and in order to generate an alert if a malfunction is detected.

Abstract: A monitor system for monitoring the reliability of at least one piece of electronic equipment installed in an aircraft. In order to monitor each piece of electronic equipment, such a monitor system comprises: monitor means for measuring variations of at least one state parameter P as a function of time t; concatenation means for generating data groups (ti, Pi, Sj); transmission means for transmitting the data groups (ti, Pi, Sj) to a centralized unit; first computation means for determining an observed reliability Robs of the or each piece of electronic equipment; second computation means for determining an expected reliability Rexp of the or each piece of electronic equipment; comparator means for comparing the observed reliability Robs with the expected reliability Rexp of the or each piece of electronic equipment; and warning means.

Abstract: A lighting module for automobile vehicles, including at least one optical module adapted to produce a first cut-off beam; a support plate for a heatsink; the heatsink adapted to receive the optical module; wherein the support plate includes a first surface; the heatsink includes rotational adjustment means adapted to enter into contact with the first surface of the support plate; and to pivot about a particular rotation axis so as to position the first cut-off beam produced by the optical module at a reference position.

Abstract: A monitor system for monitoring the reliability of at least one piece of electronic equipment installed in an aircraft. In order to monitor each piece of electronic equipment, such a monitor system comprises: monitor means for measuring variations of at least one state parameter P as a function of time t; concatenation means for generating data groups (ti, Pi, Sj); transmission means for transmitting the data groups (ti, Pi, Sj) to a centralized unit; first computation means for determining an observed reliability Robs of the or each piece of electronic equipment; second computation means for determining an expected reliability Rexp of the or each piece of electronic equipment; comparator means for comparing the observed reliability Robs with the expected reliability Rexp of the or each piece of electronic equipment; and warning means.

Abstract: A method of stopping an overspeeding engine (4) of a rotorcraft (1). A protection device stops the overspeeding engine (4) on condition of a comparison between a mechanical power requirement (19) of the rotorcraft (1) and a predefined power threshold (22). Stopping of the overspeeding engine (4) is authorized by the protection device (8) on condition that said mechanical power requirement (19) is identified as being less than or equal to the predefined power threshold (22). The mechanical power requirement (19) of the rotorcraft (1) is calculated on the basis of at least one current or anticipated value for the opposing torque (15) of a main rotor (5) of the rotorcraft.

Abstract: A lighting module for automobile vehicles, including at least one optical module adapted to produce a first cut-off beam; a support plate for a heatsink; the heatsink adapted to receive the optical module; wherein the support plate includes a first surface; the heatsink includes rotational adjustment means adapted to enter into contact with the first surface of the support plate; and to pivot about a particular rotation axis so as to position the first cut-off beam produced by the optical module at a reference position.

Abstract: A method of stopping an overspeeding engine (4) of a rotorcraft (1). A protection device stops the overspeeding engine (4) on condition of a comparison between a mechanical power requirement (19) of the rotorcraft (1) and a predefined power threshold (22). Stopping of the overspeeding engine (4) is authorized by the protection device (8) on condition that said mechanical power requirement (19) is identified as being less than or equal to the predefined power threshold (22). The mechanical power requirement (19) of the rotorcraft (1) is calculated on the basis of at least one current or anticipated value for the opposing torque (15) of a main rotor (5) of the rotorcraft.

Abstract: A standby instrument (10) for an aircraft, the instrument comprising at least one inertial sensor (1), at least one pressure sensor (2), calculation means (3) connected to said inertial and pressure sensors (1, 2), a display unit (4). Said calculation means (3) are suitable for determining critical flight information for said aircraft, and for displaying said critical flight information on the display unit (4) in the event of a main information system of said aircraft failing. In addition, said standby instrument (10) also incorporates stabilization relationships enabling said calculation means (3) to determine control relationships in order to control the actuators (15) of an autopilot of said aircraft in the event of said autopilot failing. Finally, said calculation means (3) are connected to at least one engine operation computer (5) enabling said instrument (10) to display information about a first limit of the engine on said display unit (4).

Abstract: A standby instrument (10) for an aircraft, the instrument comprising at least one inertial sensor (1), at least one pressure sensor (2), calculation means (3) connected to said inertial and pressure sensors (1, 2), a display unit (4). Said calculation means (3) are suitable for determining critical flight information for said aircraft, and for displaying said critical flight information on the display unit (4) in the event of a main information system of said aircraft failing. In addition, said standby instrument (10) also incorporates stabilization relationships enabling said calculation means (3) to determine control relationships in order to control the actuators (15) of an autopilot of said aircraft in the event of said autopilot failing. Finally, said calculation means (3) are connected to at least one engine operation computer (5) enabling said instrument (10) to display information about a first limit of the engine on said display unit (4).