A tiltwing aircraft (10; 100; 200; 300) convertible between a vertical takeoff and landing flight mode and a forward flight mode comprising: a fuselage (12; 138; 302; 418); a tiltwing rotatably coupled to the fuselage (12; 138; 302; 418), the tiltwing rotatable between a plurality of positions including a substantially vertical position in the vertical takeoff and landing flight mode and a substantially horizontal position in the forward flight mode; and a convertible tailboom and landing gear system (38; 162; 204; 304; 448) rotatably coupled to the fuselage (12; 138; 302; 418), the convertible tailboom and landing gear system (38; 162; 204; 304; 448) rotatable between a plurality of positions including a landing gear position in the vertical takeoff and landing flight mode and a tailboom position in the forward flight mode, the convertible tailboom and landing gear system (38; 162; 204; 304; 448) comprising: a plurality of skids (40, 42; 166; 310; 452); and a plurality of linkages (44, 46, 48, 50; 164; 306, 308; 450) rotatably coupling the skids (40, 42; 166; 310; 452) to the fuselage (12; 138; 302; 418); wherein the skids (40, 42; 166; 310; 452) are positioned below the fuselage (12; 138; 302; 418) in the landing gear position and extend aft of the fuselage (12; 138; 302; 418) in the tailboom position; wherein the convertible tailboom and landing gear system (38; 162; 204; 304; 448) is rotatable through an angular range of motion of at least 90 degrees; and wherein: (i) the angular range of motion between the landing gear position and the tailboom position is approximately 90 degrees; (ii) the linkages (44, 46, 48, 50; 164; 306, 308; 450) remain parallel throughout the angular range of motion; characterised in that (iii) the skids (40, 42; 166; 310; 452) remain horizontal throughout the angular range of motion. a fuselage (12; 138; 302; 418); a tiltwing rotatably coupled to the fuselage (12; 138; 302; 418), the tiltwing rotatable between a plurality of positions including a substantially vertical position in the vertical takeoff and landing flight mode and a substantially horizontal position in the forward flight mode; and a convertible tailboom and landing gear system (38; 162; 204; 304; 448) rotatably coupled to the fuselage (12; 138; 302; 418), the convertible tailboom and landing gear system (38; 162; 204; 304; 448) rotatable between a plurality of positions including a landing gear position in the vertical takeoff and landing flight mode and a tailboom position in the forward flight mode, the convertible tailboom and landing gear system (38; 162; 204; 304; 448) comprising: a plurality of skids (40, 42; 166; 310; 452); and a plurality of linkages (44, 46, 48, 50; 164; 306, 308; 450) rotatably coupling the skids (40, 42; 166; 310; 452) to the fuselage (12; 138; 302; 418); wherein the skids (40, 42; 166; 310; 452) are positioned below the fuselage (12; 138; 302; 418) in the landing gear position and extend aft of the fuselage (12; 138; 302; 418) in the tailboom position; wherein the convertible tailboom and landing gear system (38; 162; 204; 304; 448) is rotatable through an angular range of motion of at least 90 degrees; and wherein: (i) the angular range of motion between the landing gear position and the tailboom position is approximately 90 degrees; (ii) the linkages (44, 46, 48, 50; 164; 306, 308; 450) remain parallel throughout the angular range of motion; characterised in that (iii) the skids (40, 42; 166; 310; 452) remain horizontal throughout the angular range of motion. a plurality of skids (40, 42; 166; 310; 452); and a plurality of linkages (44, 46, 48, 50; 164; 306, 308; 450) rotatably coupling the skids (40, 42; 166; 310; 452) to the fuselage (12; 138; 302; 418); wherein the skids (40, 42; 166; 310; 452) are positioned below the fuselage (12; 138; 302; 418) in the landing gear position and extend aft of the fuselage (12; 138; 302; 418) in the tailboom position; wherein the convertible tailboom and landing gear system (38; 162; 204; 304; 448) is rotatable through an angular range of motion of at least 90 degrees; and wherein: (i) the angular range of motion between the landing gear position and the tailboom position is approximately 90 degrees; (ii) the linkages (44, 46, 48, 50; 164; 306, 308; 450) remain parallel throughout the angular range of motion; characterised in that (iii) the skids (40, 42; 166; 310; 452) remain horizontal throughout the angular range of motion. (i) the angular range of motion between the landing gear position and the tailboom position is approximately 90 degrees; (ii) the linkages (44, 46, 48, 50; 164; 306, 308; 450) remain parallel throughout the angular range of motion; characterised in that (iii) the skids (40, 42; 166; 310; 452) remain horizontal throughout the angular range of motion.