The paper presents a novel scheme to achieve passive satellite attitude maneuver. The proposed control mechanism consists of a small 'pendulum-like' subsatellite mass deployed from the satellite through two identical tethers. A simple steady state and subsequent linearized stability analyses enable predictions of analytical conditions for feasible equilibrium satellite orientations and their stability. These important results facilitate judicious choice of system design parameters. Numerical simulation establishes the feasibility of executing arbitrary satellite slewing maneuver by slowly varying the length of one of the two tethers according to a preprogrammed strategy. The passive nature of the proposed control scheme and the modest auxiliary mass and the tether lengths required make the new concept particularly attractive.