North American T-28 Trojan

$220,000 trainer aircraft

Overview

North American Aviation (NAA) United States ICAO: T28 1950–1957 Active $220,000 (2016)

The North American T-28 Trojan was developed by North American Aviation as a piston-engine military trainer aircraft that first flew in September 1949. It was in service with the United States Air Force and United States Navy since the 1950s. Aside from being a trainer, the T-28 Trojan also served as a counter-insurgency aircraft mainly during the Vietnam War. It carried on its use in the civilian market as an aerobatic and warbird aircraft.

Live Fleet Activity (T28)

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Specifications

Units
Engine
1 × Wright R-1820-86 Cyclone
Engine type
Piston
Power
1,425 hp · 1,063 kW
Avionics
—
Wing tips
No winglets
Seats
2
Crew
—
Cabin width
—
Cabin height
—
Cabin length
—
Exterior length
34 ft 1 in  ·  10.40 m
Tail height
12 ft 8 in  ·  3.86 m
Fuselage diameter
5 ft 3 in  ·  1.60 m
Wing span
40 ft 4 in  ·  12.30 m
Baggage volume
—
Gross weight
—
Empty weight
—
Max takeoff weight
8,500 lb  ·  3,850 kg
Max landing weight
7,800 lb  ·  3,550 kg
Max payload
1,300 lb  ·  600 kg
Fuel capacity
180 gal · 700 L · 500 kg (AvGas)
Max cruise speed
300 kt  ·  345 mph  ·  556 km/h
Maximum speed
—
Cruise speed
—
Approach speed
62 kt  ·  71 mph  ·  115 km/h
Range
920 nm  ·  1,060 mi  ·  1,700 km
Fuel burn
—
Ceiling
35,500 ft  ·  10,800 m
Rate of climb
3,540 ft/min  ·  18 m/s
Takeoff distance
1,310 ft  ·  400 m
Landing distance
1,310 ft  ·  400 m
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North American T-28S Fennec ‘No119’ .

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Operational Context

On September 24, 1949, the prototype XT-28 took its maiden flight. It was built as a replacement on the T-6 Texan single-engined trainer. In mid-June 1950, the United States Air Force version T-28A went to the Air Proving Ground at Eglin Air Force Base, Florida to perform suitability tests.

The aircraft was produced from 1950 to 1957 with a total number of 1,948 built. In 1962, the T-28Bs were modified for the United States Air Force for roles such as counter-insurgency, forward air controller, reconnaissance, and search and rescue in Vietnam. The converted aircraft were designated as T-28Ds.

The T-28D has a crew member of two. It has an external length of 10.06 meters, an external height of 3 meters, and a fuselage width of 1.6 meters. The tail height is 3.86 meters and the wheelbase is 2.8 meters. The aircraft has a wingspan of 12.22 meters and a wing area of 24.90 square meters. It has an empty weight of 2,914 kg and a maximum payload of 600 kg. The maximum takeoff and landing weights are 3,856 kg and 3,542 kg, respectively.

The T-28D version is powered by a single Wright R-1820 Cyclone engine. It is a nine-cylinder, single-row, supercharged, air-cooled radial engine rated at 1,425 horsepower thrust. It has two overhead valves per cylinder with a sodium-filled exhaust valve, a single-speed centrifugal supercharger, a Stromberg downdraft carburetor with an automatic mixture control fuel system, a dry sump with one pressure and one scavenging pump, and an air cooling system. The Th-28D has a maximum speed of 298 knots at 10,000 feet and a ferry range of 920 nautical miles. It can fly up to 35,500 feet and can climb at a rate of 3,540 feet per minute. The aircraft could also be loaded with six hardpoints with a total capacity of 540 kg.