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The Sikorsky SH-60/MH-60 Seahawk (or Sea Hawk) is a twin turboshaft engine, multi-mission United States Navy helicopter based on the United States Army UH-60 Black Hawk and a member of the Sikorsky S-70 family. The most significant airframe modification is a hinged tail to reduce its footprint aboard ships.

The U.S. Navy uses the H-60 airframe under the model designations SH-60B, SH-60F, HH-60H, MH-60R, and MH-60S. Able to deploy aboard any air-capable frigate, destroyer, cruiser, fast combat support ship, amphibious assault ship, or aircraft carrier, the Seahawk can handle anti-submarine warfare (ASW), anti-surface warfare (ASUW), naval special warfare (NSW) insertion, search and rescue (SAR), combat search and rescue (CSAR), vertical replenishment (VERTREP), and medical evacuation (MEDEVAC). All Navy H-60s carry a rescue hoist for SAR/CSAR missions.


Design and development

During the 1970s the U.S. Navy began looking for new helicopter to replace the Kaman SH-2 Seasprite. The SH-2 Seasprite was used by the Navy as its platform for the Light Airborne Multi-Purpose System (LAMPS) Mark I avionics suite for the maritime warfare and a secondary search and rescue capability. Advances in sensor and avionic technology lead to LAMPS Mk II suite, but the SH-2 was not large enough to carry the Navy's required equipment. In the mid-1970s the Army was evaluating of the Sikorsky YUH-60 and Boeing-Vertol YUH-61 for its Utility Tactical Transport Aircraft System (UTTAS) competition.

The Navy based its requirements on the Army's UTTAS specification to decrease costs from commonality. Sikorsky and Boeing-Vertol submitted proposals for Navy versions of their Army UTTAS helicopters in April 1977 for review. The Navy also looked at helicopters being produced by Bell, Kaman, Westland and MBB, but these were too small for the mission. In early 1978 the Navy selected Sikorsky's S-70B design, which was designated "SH-60B Seahawk".


General characteristics

Crew: 3-4

Capacity: 5 passengers in cabin, slung load of 6,000 lb (2,700 kg) or internal load of 4,100 lb (1,900 kg) for B, F and H models; and 11 passengers or slung load of 9,000 lb (4,100 kg) for S-model

Length: 64 ft 8 in (19.75 m)

Rotor diameter: 53 ft 8 in (16.35 m)

Height: 17 ft 2 in (5.2 m)

Disc area: 2,262 ft² (210 m²)

Empty weight: 15,200 lb (6,895 kg)

Loaded weight: 17,758 lb (8,055 kg) ; for ASW mission

Useful load: 6,684 lb (3,031 kg)

Max. takeoff weight: 21,884 lb (9,927 kg)

Powerplant: 2 × General Electric T700-GE-401C turboshaft, 1,890 shp (1,410 kW) take-off power each



Never exceed speed: 180 kn (333 km/h; 207 mph)

Maximum speed: 146 kn (270 km/h; 168 mph)

Range: 450 nmi (518 mi/834 km) at cruise speed

Service ceiling: 12,000 ft (3,580 m)

Rate of climb: 1,650 ft/min (8.38 m/s)



Up to three Mark 46 torpedos or Mark 50 torpedos,

AGM-114 Hellfire missile, 4 Hellfire missiles for SH-60B and HH-60H, 8 Hellfire missiles for MH-60S Block III.

AGM-119 Penguin missile (being phased out),

M60 machine gun or, M240 machine gun or GAU-16/A machine gun or GAU-17/A Minigun

Rapid Airborne Mine Clearance System (RAMICS) using Mk 44 Mod 0 30 mm Cannon

Main article: U.S. Helicopter Armament Subsystems