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'').
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