The MH-60L can be adapted to the attack mission by attaching dual weapons pylons to both sides of the fuselage. The MH-60L is powered by 2 General Electric T700-GE-701C 1,843 shaft-horsepower turboshaft engines. Survivability equipment includes radar and missile warning systems and IR jammers. The MH-60L features various modifications to include updated cockpit, additional avionics, precision navigation system, forward looking infrared (FLIR), aircraft survivability equipment, external tank system. The MH-60 is capable of operating from fixed base facilities, remote sites, or ocean going vessels. Secondary missions of the MH-60L include external load, CSAR and MEDEVAC operations. The primary mission of the MH-60L is to conduct overt or covert infiltration, exfiltration, and resupply of special operations forces across a wide range of environmental conditions. The aircraft provides medium and utility helicopter support to special operations forces unique misions. The MH-60L Black Hawk is the Army special operations aircraft variant of the UH-60L. The UH-60L also incorporated the automatic flight control system (AFCS) from the SH-60 for better flight control due to handling issues with the more powerful engines. Its external lift capacity increased by 1,000 lb (450 kg) up to 9,000 lb (4,100 kg). The UH-60L also featured more power and lifting capability with upgraded T700-GE-701C engines and a stronger gearbox, both developed for the SH-60B Seahawk. The new model incorporated all of the modifications made to the UH-60A fleet as standard design features. Deliveries of the UH-60A to the Army began in October 1978 and the helicopter formally entered service in June 1979.ĭue to weight increases from the addition of mission equipment and other changes, the Army ordered the improved UH-60L in 1987. The Army selected the UH-60 for production in December 1976. Three of the prototypes were delivered to the Army in March 1976, for evaluation against the rival Boeing-Vertol design, the YUH-61A, and one was kept by Sikorsky for internal research. Prior to delivery of the prototypes to the US Army, a preliminary evaluation was conducted in November 1975 to ensure the aircraft could be operated safely during all testing. The conflict saw the first use of the UH-60 in combat.įour prototypes were constructed, with the first YUH-60A flying on 17 October 1974. UH-60A Black Hawks over Port Salinas during the invasion of Grenada, 1983. The UTTAS requirements for improved reliability, survivability and lower life-cycle costs resulted in features such as dual-engines with improved hot and high altitude performance, and a modular design (reduced maintenance footprint) run-dry gearboxes ballistically tolerant, redundant subsystems (hydraulic, electrical and flight controls) crashworthy crew (armored) and troop seats dual-stage oleo main landing gear ballistically tolerant, crashworthy main structure quieter, more robust main and tail rotor systems and a ballistically tolerant, crashworthy fuel system. Transport aboard the C-130 limited the UTTAS cabin height and length. The RFP also included air transport requirements. The Army released its UTTAS request for proposals (RFP) in January 1972. Based on experience in Vietnam, the Army required significant performance, survivability and reliability improvements from both UTTAS and the new powerplant. The Army also initiated the development of a new, common turbine engine for its helicopters that would become the General Electric T700. In the late 1960s, the United States Army began forming requirements for a helicopter to replace the UH-1 Iroquois and designated the program as the Utility Tactical Transport Aircraft System (UTTAS). Missiles: AGM-114 Hellfire laser guided missiles, AIM-92 Stinger air-to-air missiles Hardpoints: 4, 2 per ESSS stub wings and provisions to carry combinations of: Rotational speed: Engine 20,900 RPM, main rotor 258 RPM (gear ratio 81:1) Crew: 2 pilots (flight crew) with 2 crew chiefs/gunnersĬapacity: 2,640 lb (1,200 kg) of cargo internally, including 11 troops or 6 stretchers, or 9,000 lb (4,100 kg) (UH-60L) of cargo externally
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