Sikorsky S-76

Sikorsky S-76C++ G-WIWI Air Harrods

The Sikorsky S-76 is a medium-size executive helicopter with two turboshaft engines, four-bladed main and tail rotors and retractable landing gear. This reliable helicopter is capable of carrying cargo and passenger offshore, day or night and in instrument weather conditions.

Developing nation: United States of America.
Manufacturer/designer: Sikorsky Aircraft Corporation.
Production Lines: Stratford, Connecticut USA.
Type aircraft: medium-size executive helicopter.
First flight: 13 March 1977.
First delivery: 27 February 1979.
Produced: 1977 – .
Number built:



  • S-76A : Original production version, powered by two 485 kW (650 shp) Rolls-Royce (Allison) 250-C30 turboshaft engines. Large number modified to S-76A+, A++, C, and C+. 284 manufactured.
  • S-76A Utility : Utility transport version, equipped with sliding doors and a strengthened floor.
  • S-76A+ : Unsold S-76s were fitted with two Turbomeca Arriel 1S turboshaft engines. 17 manufactured.
  • S-76A++ : S-76 helicopters fitted with two Turbomeca Arriel 1S1 turboshaft engines.
  • S-76A Mk II : Improved all-weather transport version, fitted with more powerful engines, and other detail improvements.
  • S-76B : Powered by two Pratt & Whitney Canada PT6B-36A or Pratt & Whitney Canada PT6B-36B turboshaft engines. 101 built.
  • S-76C : Powered by two 539-kW (981-shp) Turboméca Arriel 1S1 turboshaft engines. 43 manufactured.
  • S-76C+ : Uprated version, fitted with improved Turboméca Arriel 2S1 turboshafts with FADEC. 35 manufactured.
  • S-76C++ : Turboméca Arriel 2S2
  • S-76D : Powered by two Pratt & Whitney Canada PW210S.


  • AUH-76 – Armed utility transport version, developed from the S-76 Mk. II.
  • H-76 Eagle – Announced in 1985 the Eagle was a military and naval variant of the S-76B, none sold.

Specifications (Sikorsky S-76C++)

General characteristics

  • Crew: two
  • Capacity: seats 12–13
  • Length: 16.00 m (52 ft 6 in) from tip of main rotor to tip of tail rotor
  • Width: 3.05 m (10 ft 0 in) at horizontal stabilizer
  • Height: 4.42 m (14 ft 6 in) to tip of tail rotor
  • Empty weight: 3,177 kg (7,005 lb) in utility configuration
  • Gross weight: 5,307 kg (11,700 lb)
  • Fuel capacity: 1,064 liters (281 US gallons), with 189 or 386 liters (50 or 102 US gallons) available in extra auxiliary tanks
  • Powerplant: 2 × Turbomeca Arriel 2S2 turboshaft, 922 shp (688 kW) each
  • Main rotor diameter: 13.41 m (4× 44 ft 0 in)


  • Maximum speed: 287 km/h (155 kn; 178 mph) at maximum takeoff weight at sea level in standard atmospheric conditions
  • Cruise speed: 287 km/h (155 kn; 178 mph) maximum cruise speed is the same as maximum speed
  • Range: 761 km (411 nmi; 473 mi) no reserves, at long-range cruise speed at 4,000 ft altitude
  • Service ceiling: 4,200 m (13,800 ft)


  • Honeywell four-tube EFIS and Collins Proline II avionics suite
  • Four-axis fully coupled autopilot
  • Integrated Instrument Display System (IIDS)
  • Honeywell ground proximity warning system
  • Honeywell Primus weather radar
  • Dual comm/nav radios
  • Automatic direction finder
  • Dual attitude and heading reference system and air data computers
  • Radio altimeter
  • Mode C transponder
  • Dual VHF omnidirectional range (VOR) and Instrument landing system (ILS)
  • Distance measuring equipment
  • Cockpit voice recorder

All pictures courtesy of Zijde Aviation Photo and Publishing, Rob Vogelaar