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: 800+.
Variants
Civil
- 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.
Military
- 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)
Performance
- 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)
Avionics
- 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
