Continued From Previous Page The program received approval to enter low rate initial production in 2001. Initial operational and test evaluation by the Air Force Operational Test and Evaluation Center was successfully completed in 2004. Based on maturity of design and other factors the program received approval for full rate production in 2005. Air Education and Training Command, Air Combat Command and Pacific Air Forces are the primary Air Force organizations flying the F-22.  The aircraft designation was the F/A-22 for a short time before being renamed F-22A in December 2005. General Characteristics Primary Function: Air dominance, multi-role fighter Contractor: Lockheed-Martin, Boeing Power Plant: Two Pratt & Whitney F119-PW-100 turbofan engines with afterburners and two-dimensional thrust vectoring nozzles. Thrust: 35,000-pound class (each engine) Wingspan: 44 feet, 6 inches (13.6 meters) Length: 62 feet, 1 inch (18.9 meters) Height: 16 feet, 8 inches (5.1 meters) Weight: 43,340 pounds (19,700 kilograms) Maximum Takeoff Weight: 83,500 pounds (38,000 kilograms) Fuel Capacity: Internal: 18,000 pounds (8,200 kilograms); with 2 external wing fuel tanks: 26,000 pounds (11,900 kilograms) Payload: Same as armament air-to-air or air-to-ground loadouts; with or without 2 external wing fuel tanks. Speed:  Mach 2 class with supercruise capability Range: More than 1,850 miles ferry range with 2 external wing fuel tanks (1,600 nautical miles) Ceiling: Above 50,000 feet (15 kilometers) Armament: One M61A2 20-millimeter cannon with 480 rounds, internal side weapon bays carriage of two AIM-9 infrared (heat seeking) air-to-air missiles and internal main weapon bays carriage of six AIM-120 radar-guided air-to-air missiles (air-to-air loadout) or two 1,000-pound GBU-32 JDAMs and two AIM- 120 radar-guided air-to-air missiles (air-to-ground loadout) Crew: One Unit Cost: $143 million Initial operating capability:  December 2005 Inventory: Total force, 183