Please click on any of the coded models listed on the pages below to learn more about its background and why it came into being, its special features, its specifications and its production history. The following lineage charts are organized in groups:

S-63, Single Turbine Utility Helicopter

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S-63 display model

The S-63 was a prototype for a growth S-62, a single-turbine-engined utility helicopter then in production.  The S-62 used the dynamic systems of the piston-engined S-55 with a new amphibious fuselage, with a boat hull, and a single turbine engine.  It entered production in1960.

The S-63 extended this concept by using the S-62 fuselage with the dynamic components of the larger Sikorsky S-58/H-34.  Whereas the S-62 had the S-55’s 52 ft. diameter three-bladed rotor, the S-63 had the S-58’s four-bladed rotor with the diameter cut down from the 56 ft. on the S-58 to 53 ft.  The S-62 used a General Electric T-58-GE-8 engine derated to 670 horsepower, later upgraded to 730 horsepower.  The S-63 used the same engine at its full rated military power of 1250 horsepower.

Sikorsky Archives records indicate one of the primary potential customers was the Royal Canadian Navy to be based on frigates or destroyer escorts.  Other customers envisioned included those with high-altitude requirements beyond what the S-62 could achieve.

The specific dates for the S-63 development are not clear.  The S-62 had a first flight in May 1958 and its first production delivery July 1960.  The aircraft specification document for the S-63 is dated August 4, 1958.  Other available S-63 documents are dated in late 1958 and early 1959.  All of these are pre-fabrication documents.  The dates for first flight and subsequent activities are not known.

None of these opportunities proved fruitful and only the one prototype aircraft was produced.

Configuration Features

The primary feature of the S-63 was the S-62’s amphibious boat hull fuselage combined with a higher-power dynamic system.  The aircraft was designed for the Navy Utility Mission, including operating from a navy cruiser with a 22’ x 17’ elevator.  It was also suitable for civil utility missions.  The fuselage was sized for 12 passengers or six litters.  The primary structure was of aluminum alloy semi-monocoque construction.  The fuselage below and including the cabin floor was of water tight construction.  Floats were included which, together with the watertight lower fuselage, provided floatation for emergency landing.

The cockpit was designed for two persons in a side-by-side configuration.  The main landing gear was retractable; the tail wheel was fixed.  A rotor brake was included.

The control system was of conventional Sikorsky design at the time.  Complete provisions for an automatic stabilization device (auto-pilot) were included.


General Arrangement Drawing

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Characteristics and Performance




Design Gross Weight

8,100 lbs

9,359 lbs

Maximum Gross Weight

8,300 lbs

12,500 lbs

Empty Weight

5,083 lbs

6,645 lbs

Useful Load

3,017 lbs

2,894 lbs

Rotor Diameter

52 ft

53 ft

No. of Rotor Blades



Rotor Tip Speed

586 fps

600 fps




Military Power


1250 hp

Normal Rated Power


1050 hp

Maximum Speed

95 kts

135 kts

Cruise Speed

85 kts

125 kts

Vertical Rate of Climb

1,080 fpm

2,000 fpm


Prepared by
Art Linden
June 2013