An instrument for displaying pitch-and-roll attitude of an aircraft. A two-degree-of-freedom vertical gyroscope is suspended within a frame or housing, and is connected to an attitude indicator which moves in the same manner with respect to the frame and aircraft instrument panel as the aircraft moves in pitch and roll with respect to the earth. A novel linkage between the gyroscope and indicator transmits both pitch-and-roll position information over a single path to minimize the number of moving parts in the instrument, thereby reducing friction and other errors which affect accuracy and reliability of the attitude display.