Abstract: A flight sensor for controlling electronic components in an aircraft includes a vibration sensor for converting structure-borne sound to electric vibration signals. A filtering device receives the vibration signals and determines the fraction thereof which is attributable to the aircraft engine, relative to the overall sound in the vibration signals. A comparator compares the engine sound with the overall sound and generates a flight condition signal based on the result of the comparison, which flight condition signal indicates a defined flight status of the aircraft, such as “flight” or “no flight”. Electronic components on board an aircraft are controlled such that the emission of interfering electromagnetic waves is prevented when the flight status signal indicates that the aircraft is in flight.

Abstract: In a method of measuring stress/strain by detecting Barkhausen noise, an exciting/sensing device is arranged at least adjacent to a magnetic or magnetizable element, and passing an increasing magnetizing current through the exciting device. The start of the Barkhausen noise in the element, as a function of the magnetizing current is detected by the sensing device, and the magnetizing current at that time represents a measurement of the stress/strain condition of the element.

Abstract: A flight sensor for controlling electronic components in an aircraft includes a vibration sensor for converting structure-borne sound to electric vibration signals. A filtering device receives the vibration signals and determines the fraction thereof which is attributable to the aircraft engine, relative to the overall sound in the vibration signals. A comparator compares the engine sound with the overall sound and generates a flight condition signal is based on the result of the comparison, which flight condition signal indicates a defined flight status of the aircraft, such as “flight” or “no flight”. Electronic components on board an aircraft are controlled such that the emission of interfering electromagnetic waves is prevented when the flight status signal indicates that the aircraft is in flight.

Abstract: Aircraft maintenance and repair work is facilitated, especially for a commercial aircraft, by a diagnostic system and method, wherein an aircraft component or assembly of components is monitored by at least one sensor which produces and preferably also stores component status information. Respective status information signals are transmitted, preferably in a wireless manner, from a transmitter of the sensor to a receiver of a signal processing unit which provides status information on a display screen. The status information signals are preferably processed and evaluated with reference to rated maintenance and repair reference information to provide instructions as to what needs to be done where and when for a maintenance or repair. The sensor or sensors may operate during flight and the respective stored information is then processed and used on the ground.

Abstract: In a method of measuring stress/strain by detecting Barkhausen noise, an exciting/sensing device is arranged at least adjacent to a magnetic or magnetizable element, and passing an increasing magnetizing current through the exciting device. The start of the Barkhausen noise in the element, as a function of the magnetizing current is detected by the sensing device, and the magnetizing current at that time represents a measurement of the stress/strain condition of the element.

Abstract: Aircraft maintenance and repair work is facilitated, especially for a commercial aircraft, by a diagnostic system and method, wherein an aircraft component or assembly of components is monitored by at least one sensor which produces and preferably also stores component status information. Respective status information signals are transmitted, preferably in a wireless manner, from a transmitter of the sensor to a receiver of a signal processing unit which provides status information on a display screen. The status information signals are preferably processed and evaluated with reference to rated maintenance and repair reference information to provide instructions as to what needs to be done where and when for a maintenance or repair. The sensor or sensors may operate during flight and the respective stored information is then processed and used on the ground.

Abstract: Aircraft maintenance and repair work is facilitated, especially for a commercial aircraft, by a diagnostic system and method, wherein an aircraft component or assembly of components is monitored by at least one sensor which produces and preferably also stores component status information. Respective status information signals are transmitted, preferably in a wireless manner, from a transmitter of the sensor to a receiver of a signal processing unit which provides status information on a display screen. The status information signals are preferably processed and evaluated with reference to rated maintenance and repair reference information to provide instructions as to what needs to be done where and when for a maintenance or repair. The sensor or sensors may operate during flight and the respective stored information is then processed and used on the ground.

Abstract: Aircraft maintenance and repair work is facilitated, especially for a commercial aircraft, by a diagnostic system and method, wherein an aircraft component or assembly of components is monitored by at least one sensor which produces and preferably also stores component status information. Respective status information signals are transmitted, preferably in a wireless manner, from a transmitter of the sensor to a receiver of a signal processing unit which provides status information on a display screen. The status information signals are preferably processed and evaluated with reference to rated maintenance and repair reference information to provide instructions as to what needs to be done where and when for a maintenance or repair. The sensor or sensors may operate during flight and the respective stored information is then processed and used on the ground.

Abstract: An apparatus for cleaning hydraulic fluid includes a centrifugal fluid-spinning disk arranged in a housing, of which an upper portion forms a vapor chamber and a lower portion forms a fluid collecting basin. A vacuum pump is connected to the housing through an oil mist separator, such that water vapor is vacuumed away and hydraulic fluid collects in the oil mist separator to then be pumped away. The apparatus further includes preferably a single container that contains both the contaminated hydraulic fluid that is to be cleaned and the cleaned hydraulic fluid. A flexible inlet line and a flexible outlet line with respective hydraulic quick connectors are provided to connect the apparatus and particularly the oil container to a hydraulic system of an aircraft, for example. A high pressure pump connected to the outlet line pumps the cleaned hydraulic fluid into the aircraft hydraulic system and a pressure maintaining valve in the inlet line maintains the system pressure.