Seibel S-4

Charles Seibel began development on the S-4 after forming the Seibel Helicopter Company with funding from local Kansas oil investors. The S-4 was a continuation of his work on his previous design, the Seibel S-3, which he flew as a demonstrator for his design concepts; primarily a new design for a two-bladed rotor system and a simplified transmission. These features would also be incorporated into the S-4 design.

In January 1949, the S-4 lifted off the ground for the first time, piloted by Johnny Gibbs. In March 1950, certification tests were completed and on 23 April 1950, the S-4 received civil certification by the CAA. A larger engine, the Lycoming O-290B with 125 hp, would be installed in the aircraft, making it the S-4A.

Gov. Frank Carlson and Charles Seibel at the CAA Certification Ceremony

Based on feedback from the Army during the evaluation, Seibel, shortened the fuselage of the second YH-24 (51-5113) and widened the cockpit for a co-pilot's seat next to the pilot's seat. Seibel also replaced that aircraft's original wheeled, tricycle undercarriage with landing skids. This aircraft would become the S-4B.

The S-4 frame was a welded steel-tube box frame, with two decks. A lower deck supported the control panel, pilot's seat, wheeled, tricycle landing gear, and a small passenger/cargo area accessible from the rear, and an upper deck carried the engine, the fuel and oil tanks, and supported the transmission and rotor assembly. A tapered, monocoque, alloy tail boom with a two-bladed antitorque tail rotor was attached at the rear of the upper deck.

Both the U.S. Army and U.S. Air Force showed interest in the S-4. In early 1951, the U.S. Army ordered two examples for operational and engineering evaluation in the observation, utility, and aeromedical evacuation roles. The Army designated the S-4 as the YH-24 Sky Hawk. The first Sky Hawk, serial number 51-5112, was delivered to Fort Bragg, North Carolina in April 1951; the second YH-24, serial number 51-5113, was delivered to Wright Field.

Despite the simplicity of the S-4, the Army determined that it did not provide a sufficient payload capability and the aircraft were dropped from the inventory and returned to Seibel in 1952.

S-4

Original design, certified by the CAA in 1950.

S-4A

Featured an upgraded, 125 hp Lycoming O-290B engine.

S-4B

Modified airframe based on Army recommendations during YH-24 evaluation. Two-seat cockpit and skid landing gear.

Orthographic projection of the Seibel S-4.

Data from U.S. Army Aircraft Since 1947[1]

General characteristics

• Crew: 1
• Capacity: 1
• Length: 27 ft 10 in (8.48 m)
• Height: 10 ft (3.0 m)
• Empty weight: 960 lb (435 kg)
• Max takeoff weight: 1,540 lb (699 kg)
• Powerplant: 1 × Lycoming O-290-D 4-cylinder air-cooled horizontally-opposed piston engine, 125 hp (93 kW)
• Main rotor diameter: 29 ft 1.5 in (8.877 m)
• Main rotor area: 666 sq ft (61.9 m²)

Performance

• Maximum speed: 65 mph (105 km/h, 56 kn)
• Cruise speed: 58 mph (93 km/h, 50 kn)
• Range: 98 mi (158 km, 85 nmi)
• Service ceiling: 4,300 ft (1,300 m)
• Rate of climb: 700 ft/min (3.6 m/s) [2]

• Bridgman, Leonard (1951). Jane's All The World's Aircraft 1951–52. London: Sampson Low, Marston & Company, Ltd.
• Harding, Stephen (1990). U.S. Army Aircraft Since 1947. Shrewsbury, UK: Airlife. ISBN 1-85310-102-8.

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