A landing gear door system for a landing gear compartment, comprising: a door and a pivot pin, said door being pivotable about the pivot pin which is configured for disposition in a longitudinal direction on an airframe, the door having an arm and a door panel rigidly connected with the arm such that the door panel and arm generally form a V-shape as viewed in the longitudinal direction; and a mechanism configured to rotate the door about the pivot pin between a closed position, in which an outer surface of the door panel is configured to provide aerodynamic continuity with an outer aircraft skin of the airframe, and an open position, in which the door is rotated into the landing gear compartment and an opening is exposed, wherein the mechanism comprises: a connecting member having opposed first and second connecting member ends (54, 56), wherein the first connecting member end is pivotably connected to the arm; a linkage having opposed first and second linkage ends (62, 64), wherein the first linkage end is pivotably connected to the second connecting member end; a lever having opposed first and second lever ends (72, 74) and a fulcrum point between the first and second lever ends (72, 74), wherein the first lever end is pivotably connected to the second linkage end and the fulcrum point is configured for rotatable connection with a first mounting point within the landing gear compartment; and an actuator rotatably connected to the second lever end and configured for selectively urging the second lever end in a first direction toward the opening and in a second direction away from the opening. a door and a pivot pin, said door being pivotable about the pivot pin which is configured for disposition in a longitudinal direction on an airframe, the door having an arm and a door panel rigidly connected with the arm such that the door panel and arm generally form a V-shape as viewed in the longitudinal direction; and a mechanism configured to rotate the door about the pivot pin between a closed position, in which an outer surface of the door panel is configured to provide aerodynamic continuity with an outer aircraft skin of the airframe, and an open position, in which the door is rotated into the landing gear compartment and an opening is exposed, wherein the mechanism comprises: a connecting member having opposed first and second connecting member ends (54, 56), wherein the first connecting member end is pivotably connected to the arm; a linkage having opposed first and second linkage ends (62, 64), wherein the first linkage end is pivotably connected to the second connecting member end; a lever having opposed first and second lever ends (72, 74) and a fulcrum point between the first and second lever ends (72, 74), wherein the first lever end is pivotably connected to the second linkage end and the fulcrum point is configured for rotatable connection with a first mounting point within the landing gear compartment; and an actuator rotatably connected to the second lever end and configured for selectively urging the second lever end in a first direction toward the opening and in a second direction away from the opening. a connecting member having opposed first and second connecting member ends (54, 56), wherein the first connecting member end is pivotably connected to the arm; a linkage having opposed first and second linkage ends (62, 64), wherein the first linkage end is pivotably connected to the second connecting member end; a lever having opposed first and second lever ends (72, 74) and a fulcrum point between the first and second lever ends (72, 74), wherein the first lever end is pivotably connected to the second linkage end and the fulcrum point is configured for rotatable connection with a first mounting point within the landing gear compartment; and an actuator rotatably connected to the second lever end and configured for selectively urging the second lever end in a first direction toward the opening and in a second direction away from the opening.