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 , wherein the first connecting member end is pivotably connected to the arm ; a linkage having opposed first and second linkage ends , wherein the first linkage end is pivotably connected to the second connecting member end ; a lever having opposed first and second lever ends and a fulcrum point between the first and second lever ends , 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 , wherein the first connecting member end is pivotably connected to the arm ; a linkage having opposed first and second linkage ends , wherein the first linkage end is pivotably connected to the second connecting member end ; a lever having opposed first and second lever ends and a fulcrum point between the first and second lever ends , 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 , wherein the first connecting member end is pivotably connected to the arm ; a linkage having opposed first and second linkage ends , wherein the first linkage end is pivotably connected to the second connecting member end ; a lever having opposed first and second lever ends and a fulcrum point between the first and second lever ends , 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 . <EOS>