Abstract: A monitoring device for differential transformer sensors in an aircraft includes a first sensor interface which can be coupled with a first differential transformer sensor, a second sensor interface which can be coupled with a second differential transformer sensor, a calculation apparatus which is coupled with the first sensor interface and the second sensor interface and is designed to detect and output first measurement values from a first differential transformer sensor which is coupled with the first sensor interface and second measurement values from a second differential transformer sensor which is coupled with the second sensor interface, and having a display device which is designed to display the detected first measurement values and the detected second measurement values separately or together.

Abstract: A method, and corresponding apparatus, for testing an aircraft control system is disclosed. The method includes simultaneously coupling a test device to a plurality of separate test points in an aircraft control system, selecting each test point individually such that the test device is enabled for electrical connection with the selected test point, conducting a test on the control system at each selected test point using the test device, detecting a signal or voltage at the selected test point, and indicating a result of the test at the selected test point to an operator.

Abstract: An apparatus (10) for testing an aircraft pedal system (12) comprises a pedal actuation device (14) for actuating an aircraft pedal (12?, 12?), a force sensor (26) for sensing an actuation force applied to the aircraft pedal (12?, 12?) upon actuation of the aircraft pedal (12?, 12?) and for providing a signal indicative of the actuation force, a deflection sensing device (28, 30) for sensing an angular deflection of a device (12?, 12?; 13) deflected in response to the actuation of the aircraft pedal (12?, 12?), and a control unit (32) adapted to process the signals of the force sensor (26) and the deflection sensing device (28, 30) so as to generate an output indicating the angular deflection of the device (12?, 12?; 13) deflected in response to the actuation of the aircraft pedal (12?, 12?) in dependence on the actuation force applied to the aircraft pedal (12?, 12?).

Abstract: An apparatus (10) for testing an aircraft pedal system (12) comprises a pedal actuation device (14) for actuating an aircraft pedal (12?, 12?), a force sensor (26) for sensing an actuation force applied to the aircraft pedal (12?, 12?) upon actuation of the aircraft pedal (12?, 12?) and for providing a signal indicative of the actuation force, a deflection sensing device (28, 30) for sensing an angular deflection of a device (12?, 12?; 13) deflected in response to the actuation of the aircraft pedal (12?, 12?), and a control unit (32) adapted to process the signals of the force sensor (26) and the deflection sensing device (28, 30) so as to generate an output indicating the angular deflection of the device (12?, 12?; 13) deflected in response to the actuation of the aircraft pedal (12?, 12?) in dependence on the actuation force applied to the aircraft pedal (12?, 12?).

Abstract: The present invention provides a method and apparatus for testing an aircraft control system. The method comprises the steps of: coupling a test device (1) to a plurality of separate test points in an aircraft control system simultaneously; selecting each of the plurality of test points individually, such that the test device is enabled for electrical connection with the selected one of the plurality of test points; conducting a test on the control system at each of the plurality of test points selected with the selector means (20,22) using the test device, including detecting a signal or voltage at the test point selected with the selector means; indicating a result of the test at the selected test point to an operator.