No. 10757. Evangel-Air 4500-300 (N4501L c/n 001)
Photographed at Long Beach, California, USA, May 1972, by W.T. Larkins

Evangel-Air 4500-300

08/31/2011. Remarks by Johan Visschedijk: "The Evangel Aircraft Corporation of Orange City, Iowa manufactured a twin-engined STOL aircraft designated Evangel 4500-300. The aircraft was intended specifically for heavy-duty bush operations, and this was reflected in its boxlike fuselage and rugged appearance. Ease of maintenance was a prime consideration, and surface skins were of 2024-T3 light alloy to permit easy repairs in the field.

Design of the prototype started in 1962 and construction began in the following year. First flight was made in June 1964 and the first production aircraft flew in January 1969, with FAA certification being granted on July 21, 1970. It was intended to obtain certification for operation on floats or skis, but in event was not pursued. A turbocharged version, which had an increased max takeoff weight of 5,700 lb (2,585 kg), was awarded a Supplemental Type Certificate on March 8, 1973 and was known as the 4500-300-II.

Seven production aircraft had been completed by January 1974, and demand for the aircraft was such that Evangel planned to increase production to three aircraft per month by November 1974, however, no further aircraft were produced.The pictured prototype was eventually modified to the turbocharged Model 4500-300-II and is still registered to a private owner in Alaska. The following data relate to the Model 4500-300.

TYPE. Nine-seat light passenger/cargo aircraft.
WINGS. Cantilever low-wing monoplane. Dihedral on outer panels 9 30'. Incidence 3 15'. Conventional all-metal light alloy structure. Cambered wingtips. Frise-type light alloy ailerons. Single-slotted trailing-edge flaps of light alloy construction. Ground-adjustable trim tabs on ailerons.
FUSELAGE. Rectangular-section all-metal structure.
TAIL UNIT. Cantilever all-metal structure. Large dorsal fin faired into upper surface of fuselage. Dihedral on tailplane. Horn-balanced elevators. Controllable trim tabs in rudder and elevators.
LANDING GEAR. Tailwheel type, main units only retracting rearward into undersurface of wings. Hydraulic retraction. Hand-pump for emergency retraction or extension. Allied Machinist oleo-pneumatic shock-absorbers on main units. Goodyear main wheels and tires size 24 X 7.7, pressure 40 lb/sq.in (2,81 kg/sq.cm). Castoring tailwheel with Cleveland wheel and tire size 40-77, pressure 35 lb/sq.in (2.46 kg/sq.cm). Goodyear hydraulic brakes.
POWER PLANT. Two 300 hp Lycoming IO-540-K1B5 six-cylinder horizontally-opposed air-cooled fuel-injection engines, each driving a Hartzell two-blade constant-speed fully-feathering metal propeller with spinner. Alternatively, a version designated 4500-300-II with Rajay turbochargers was available. Two integral wing fuel tanks, total capacity 111 gal (420 l). Refueling points in upper surface of wings. Oil capacity 6 gal (23 l).
ACCOMMODATION. Pilot and eight passengers in enclosed cabin. In initial layout two passengers accommodated on forward-facing seats, remaining passengers seated on inward-facing seats. Cockpit doors on each side of fuselage, hinged at forward edge. Large cabin doors, one on each side of fuselage, at rear of cabin, hinged at forward edge. Cockpit and cabin heated and ventilated.
SYSTEMS. Hydraulic system, for operation of flaps and main landing gear, supplied by electrically-driven hydraulic pump. Electrical system powered by 12V 50A engine-driven generators.
ELECTRONICS AND EQUIPMENT. Full IFR instrumentation standard. Narco and King nav/com radios to customer's requirements.

Created August 31, 2011