Four-engined transport aircraft used by the United States Army Air Forces and U.S Navy in World War II and the Korean War.

General Specifications

• Type: Four-engined medium and long-range troop or cargo transport.
• Wings: Low-wing cantilever monoplane with constant taper from roots to tips. The wing section is NACA 23016/23012, with a 4-degree incidence at the root and a 7-degree dihedral. The wings consist of a three-spar center section with self-sealing fuel tanks integrated into the structure and a single main spar in the outer wings. The structure includes former ribs, spanwise stringers, and a smooth Alclad skin. NACA slotted flaps extend from the fuselage to the ailerons, with controllable tabs in the starboard aileron.
• Fuselage: Semi-monocoque all-metal structure with transverse frames, longitudinal stringers, and a flush-riveted smooth Alclad skin.
• Tail Unit: Cantilever monoplane type with two-spar frames covered with smooth Alclad sheet. The rudder and elevators are statically, aerodynamically, and dynamically balanced, with fabric covering for the rudder and metal leading edges for the elevators.

Landing Gear

• Configuration: Retractable tricycle type, with twin-wheels and single shock-strut on the main gear, and a single steerable nose wheel. Hydraulic retraction system with manual emergency gear extension. The main wheels retract forward into inboard engine nacelles, while the nose wheel retracts backward into the fuselage.

Power Plant

• Engines: Four Pratt & Whitney R-2000-7 or 11 fourteen-cylinder radial air-cooled engines, each with two-speed superchargers, capable of producing 1,350 hp for takeoff and varying power outputs at different altitudes.
• Propellers: Four-bladed Hamilton-Standard Hydromatic constant-speed full-feathering airscrews, 13 ft. 2 in. (4 m) in diameter.
• Fuel and Oil Systems: Fuel tanks are located in both the fuselage and wings, with additional oil tanks in each engine nacelle and an auxiliary oil tank in the fuselage.

Accommodation and Interior

• Crew: Six members including pilot, co-pilot, navigator, radio operator, and two relief crew members. The crew compartment includes facilities such as rest bunks, toilet, water tank, and storage for parachutes and life rafts.
• Passenger/Cargo Configuration:
  • C-54: Equipped with 26 seats, overhead baggage racks, and provisions for life rafts, coatroom, buffet, food storage, and lavatory facilities. The cargo compartment is equipped with tie-down fittings and can carry external loads.
  • C-54A: Designed for troop transport with benches instead of seats, reinforced flooring, and cargo handling equipment, including a built-in twin-boom hoist.
  • C-54B and C-54E: Modified configurations for different missions, including fuel tank rearrangement and additional fittings for passenger or cargo adaptability.

Dimensions and Performance

• Dimensions:
  • Span: 117 ft. 6 in. (35.8 m)
  • Length: 93 ft. 11 in. (28.6 m)
  • Height: 27 ft. 6⅜ in. (8.4 m)
  • Wing Area: 1,462 sq. ft. (135.8 sq. m)
• Weights:
  • C-54: Empty weight 36,400 lbs. (16,526 kg); loaded weight 62,000 lbs. (28,150 kg).
  • C-54A: Empty weight 37,300 lbs. (16,934 kg); maximum loaded weight 65,000 lbs. (29,510 kg).
  • C-54B: Empty weight 38,200 lbs. (17,343 kg); maximum loaded weight 73,000 lbs. (33,142 kg).
• Performance:
  • Maximum Speed: 274 mph (438 km/h) at 14,000 ft. (4,270 m)
  • Cruising Speed: 239 mph (382 km/h) at 15,200 ft. (4,640 m)
  • Stalling Speed: 88 mph (141 km/h) with flaps in landing position
  • Initial Rate of Climb: 1,070 ft./min. (326 m/min.)
  • Service Ceiling: 22,500 ft. (6,860 m); on three engines: 17,300 ft. (5,280 m)
  • Range:
    • Normal: 1,500 miles (2,480 km) with 16,500 lbs. (7,490 kg) cargo at 220 mph (352 km/h) at 10,000 ft. (3,050 m)
    • Maximum: 3,900 miles (6,240 km) with 5,400 lbs. (2,450 kg) cargo at 190 mph (304 km/h) at 10,000 ft. (3,050 m)