Pilatus PC-9
Maiden Flight: Monday, May 07, 1984
IOC: 1986
Total Production: 250
Unitary Cost: CHF8.8 million
Also Known As
Pilatus PC-9 A
Pilatus PC-9 B
Pilatus PC-9 M
Origin
Switzerland
Contractor/s
Pilatus Aircraft
Applications
T-6A Texan II
Power plant:
PT6A-62
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Description:
The Pilatus PC-9 is a single-engine, tandem two-seat turboprop aircraft designed to perform basic and advanced training missions for military customers. It was developed by Pilatus Aircraft based upon the successful Pilatus PC-7 training aircraft which was introduced in 1978. It retains 9 percent airframe commonality with the PC-7. The first PC-9 aircraft performed its maiden flight on May 7, 1984, and the first production aircraft was awarded type certification in September 1985. In 1995, it was selected by the US Air Force and US Navy for the JPATS program which led to the development of the T-6A Texan trainer. More than 250 aircraft have been ordered by 14 air forces worldwide so far.
The Pilatus PC-9 is powered by a single Pratt & Whitney Canada PT6A-62 turboprop driving a four blade Hartzel aluminum propeller. The PT6A-62 is rated at 950-shp of power. The aircraft features ejection seats, On Board Oxygen Generating System OBOGS, six underwing stores, GPS-based navigation system, anti-g system, stepped tandem cockpits, and an airbrake under the center fuselage. The Pilatus PC-9 training system also includes computer-based simulation and synthetic training devices. The current production standard, the PC-9 M, features a glass cockpit and can be equipped with head up display and video recording system.
Specifications
Accommodation: Crew 2
Dimensions: Height 3.3 m, Length 10.1 m, Wing Area 16 square meter, Wingspan 10.2 m
Weights: Max Takeoff Weight 2,350 kg (5,181 lb), Min Weight 1,725 kg (3,803 lb), Payload 1,040 kg (2,293 lb)
Performance: Climb Rate 3,880 fpm (), Cruise Speed 271 kt (501 kph), Landing Run Distance 352 m (1,155 ft), Max Range 860 nautical mile (), Stall Speed 69 kt (128 kph), Take Off Run Distance 247 m (810 ft), Top Speed 320 kt (592 kph)
Power: Power 950 shp
G Loads: Max Maneuvering Load Factor 7 g, Min Maneuvering Load Factor -4 g, Sustained Load Factor 4 g
Other: External Stations 6, Number of Engines 1, Propeller Blades 4
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Angola
Australia / 67 
Bulgaria / 6 
Burma
Croatia
Cyprus
Germany / 10 
Iraq
Ireland / 8 
Saudi Arabia / 30 
Slovenia
Switzerland
Thailand / 20