Abstract: The present invention relates to a tester, its use and a method for testing signal lines of a flight control system for a trimmable horizontal stabilizer (THS) motor of an aircraft. The tester comprises at least one test-relay (52, 54) to be connected with a relay socket of the flight control system, when the signal lines of the flight control system are to be tested, and at least one indicator (60, 70, 80, 90) being electrically connected with the at least one test-relay (52, 54) for indicating whether a voltage being applied to the test-relay (52, 54) is equal to or larger than a predetermined voltage. The method according to the invention comprises the steps of connecting at least one test-relay (52, 54) of a tester (1), in place of the original relay, with the relay socket of the flight control system, applying a voltage to the at least one test-relay (52, 54) and determining whether a voltage being applied to the at least one test-relay (52, 54) is equal to or larger than a predetermined voltage.

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: A flight management verification apparatus adapted to verify at least one flight management, wherein the flight management in use outputs a warning, disables an aircraft and/or inhibits the activation thereof in response to a power fail condition. The flight management verification apparatus comprises a first connection means adapted to be disposed in a first power indicator line to a first flight management, wherein the first power indicator line provides a signal representative of a condition of a first power supply, and further comprises a first switch connected in use such that the signal of the power indicator line for the first flight management means is switched. Actuating the switch causes the signal on the power indicator line to change indicating a distortion or failure of the power supply of the aircraft and/or a part thereof. The response of the flight management can be verified by the signal output by the flight management, e.g.

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: Disclosed is a flight management means verification apparatus (1) adapted to verify at least one flight management means (36,38), wherein the flight management means in use outputs a warning, disables an aircraft means and/or inhibits the activation thereof in response to a power fail condition. The flight management means verification apparatus comprises a first connection means (2,4) adapted to be disposed in a first power indicator line (74) to a first flight management means, wherein the first power indicator line provides a signal representative of a Condition of a first power supply (30), and further comprises a first switch means (14a) connected in use such that the signal of the power indicator line for the first flight management means (36) is switched. Actuating the switch means causes the signal on the power indicator line to change indicating a distortion or failure of the power supply of the aircraft and/or a part thereof.

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.

Abstract: The present invention relates to a tester, its use and a method for testing signal lines of a flight control system for a trimmable horizontal stabilizer (THS) motor of an aircraft. The tester comprises at least one test-relay (52, 54) to be connected with a relay socket of the flight control system, when the signal lines of the flight control system are to be tested, and at least one indicator (60, 70, 80, 90) being electrically connected with the at least one test-relay (52, 54) for indicating whether a voltage being applied to the test-relay (52, 54) is equal to or larger than a predetermined voltage. The method according to the invention comprises the steps of connecting at least one test-relay (52, 54) of a tester (1), in place of the original relay, with the relay socket of the flight control system, applying a voltage to the at least one test-relay (52, 54) and determining whether a voltage being applied to the at least one test-relay (52, 54) is equal to or larger than a predetermined voltage.