• Source: Neiva Regente

Neiva Regente is a Brazilian propeller-driven four-seat light utility aircraft manufactured by Indústria Aeronáutica Neiva.




History


The design was started in 1959 for a four-seat cabin monoplane aircraft with a high wing and fixed undercarriage. The prototype, designated the Neiva Regente 360C, was first flown on 7 September 1961 with a 145 hp (108 kW) Continental O-300 piston engine.
The type was ordered into production by the Brazilian Air Force with a more powerful 180 hp (134 kW) Lycoming O-360-A1D engine. Eighty aircraft were built originally designated the U-42 (later changed to C-42) for the utility role. First delivery occurred in February 1975.
Neiva developed a three-seat air observation post version for the Air Force, designated the Regente 420L. Its tailcone was lowered in order to improve visibility, and it used a more powerful Continental IO-360D 210 hp engine. The aircraft was first flown in January 1967 as the YL-42. Forty were built for the Brazilian Air Force as the L-42. It had provision to carry light bombs or rockets on underwing hardpoints.
Neiva also developed a four-seat civil version designated the Lanceiro. The prototype (Registered PP-ZAH) first flew in 1970, followed by production aircraft in 1973. The company's subsequent involvement with Embraer resulted in the Lanceiro's program termination.




Variants


Regente 360C – utility version (80 built)
U-42 – military designation of the Regente 360C
C-42 – military designation changed from U-42
Regente 420L – air observation post version (40 built)
L-42 – military designation of the Regente 420L
Lanciero – civil version (2 built)




Operators


Brazil
Brazilian Air Force
Zimbabwe
Zimbabwe Air Force




Specifications (C-42)


Data from Jane's All the World's Aircraft 1969–70General characteristics
Crew: 1
Capacity: 3 passengers
Length: 7.04 m (23 ft 1 in)
Wingspan: 9.13 m (29 ft 11 in)
Height: 2.93 m (9 ft 7 in)
Wing area: 13.45 m2 (144.8 sq ft)
Aspect ratio: 6:1
Airfoil: NACA 4410
Empty weight: 640 kg (1,411 lb)
Max takeoff weight: 1,040 kg (2,293 lb)
Fuel capacity: 172 L (45 US gal; 38 imp gal)
Powerplant: 1 × Lycoming O-360-A1D air-cooled flat-four engine, 130 kW (180 hp)
Propellers: 2-bladed Hartzell HC-C2YK-1A/A7666 constant-speed propeller
Performance

Maximum speed: 220 km/h (140 mph, 120 kn) at sea level
Cruise speed: 212 km/h (132 mph, 114 kn) (max cruise)
Stall speed: 90 km/h (56 mph, 49 kn) (flaps down)
Range: 928 km (577 mi, 501 nmi) at 1,500 m (4,900 ft) (econ. cruise)
Service ceiling: 3,600 m (11,800 ft)
Rate of climb: 3.5 m/s (690 ft/min)
Takeoff run to 15 m (50 ft): 350 m (1,150 ft)
Landing run from 15 m (50 ft): 460 m (1,510 ft)




References



Taylor, John W. R., ed. (1969). Jane's All The World's Aircraft 1969–70. London: Sampson Low Marston & Company. ISBN 0-354-00051-9.




External links


Media related to Neiva Regente at Wikimedia Commons

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