The North American BT-14 was developed and produced by North American Aviation as a low-wing cantilever monoplane used by the United States Army Air Corps and the United States Navy. The BT-14 is an improved version of the BT-9 with a longer fuselage, T-6 outer wing panels, and Pratt and Whitney R-985-25 radial piston engine.

North American Aviation NAA
United States
1936 to: 1938
US$0.02 million (1936)
1x Pratt & Whitney R-975-E3
420 horsepower
Max Cruise Speed:
150 knots
278 Km/h
Approach Speed (Vref):
56 knots
Travel range:
762 Nautical Miles
1,411 Kilometers
Fuel Economy:
Service Ceiling:
21,650 feet
Rate of Climb:
1100 feet / minute
5.59metre / second
Take Off Distance:
Landing Distance:
Max Take Off Weight:
2,065 Kg
4,552 lbs
Max Landing Weight:
2,030 Kg
4,475 lbs
Max Payload:
280 Kg
617 lbs
Fuel Tank Capacity:
104 gallon
394 litre
Baggage Volume:
Seats - Economy / General:
2 seats
Seats - Business Class:
Seats - First Class:
Cabin Height:
Cabin Width:
Cabin Length:
Exterior Length:
8.7 metre - 28.54 feet
Tail height:
4.1 metre - 13.45 feet
Fuselage Diameter:
1.1 metre - 3.61 feet
Wing Span / Rotor Diameter:
13.1 metre - 42.98 feet
Wing Tips:
No Winglets

The North American BT-14 is a two-seat primary training monoplane with a lengthened fuselage of welded chrome-molybdenum steel-tube framework. The fuselage is fabric-covered and has an external length of 8.7 meters, an external height of 2.7 meters, and a fuselage diameter of 1.1 meters.

The cantilever tail and fin were made of metal and covered in sheets and the rudder and elevators were of light-alloy frames covered in fabric. The tail height is 4.1 meters. It has a low wing with a wingspan of 13.1 meters and a wing area of 23 square meters.

The wing has five sections such as a center-section of parallel cord and thickness, two outer sections with back-swept leading edge and straight trailing edge, and wingtips.

It has a single-spar structure that carries most of the forces with spaced ribs and was covered with stressed aluminum-alloy skin. The ailerons have aluminum-alloy frames and were fabric-covered. The aircraft has divided undercarriage with two cantilever oleo struts, hydraulically-operated, wheel brakes, and an oleo-sprung steerable tail wheel. It has a wheelbase of 5.9 meters.

The BT-14 is powered by a single Wright R-975-E3 Whirlwind engine on welded chrome-molybdenum steel-tube mounting. It is a nine-cylinder supercharges air-cooled piston engine with two valves per cylinder pushrod-actuated, gear-driven supercharger, and direct drive reduction gear.

The engine produces a maximum thrust of 420 horsepower at 14,000 feet. The aircraft has two welded aluminum-alloy fuel tanks with a normal fuel capacity of 104 US gal, while the oil tank in the engine compartment can carry 9.5 US gal. The aircraft has a maximum speed of 150 knots at 1,500 feet and a cruise speed of 130 knots. The landing speed is 57 knots. It has a travel range of 762 nautical miles and a service ceiling of 21,650 feet. The aircraft can climb at a rate of 1,100 feet per minute.

The aircraft has a maximum takeoff and landing weights od 2,065 kg and 2,030 kg, respectively.

All North American Aviation NAA Aircraft

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