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Pilatus PC-9  
Initial Operational Capability (IOC): 1986
Maiden Flight: 7 May 1984
Total Production: 259
Unitary Cost: CHF8.8 million   (USD$8.6 million)
Also Known As: Pilatus PC-9 A, Pilatus PC-9 B and Pilatus PC-9 M
Origin: Switzerland
Corporations: Pilatus Aircraft
Parent System: Pilatus PC-9
Initial Operational Capability (IOC): 1986
Maiden Flight: 7 May 1984
Total Production: 259
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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.

Pilatus PC-9 Applications

Combat Aircraft T-6A Texan II

Pilatus PC-9 Specifications

Crew: 2
External Stations: 6
Number of Engines: 1
Propeller Blades: 4
Wing Area: 16.3 square meter (175 square foot)
Height: 3.26 meter (10.7 foot)
Length: 10.1 meter (33.3 foot)
Wingspan: 10.2 meter (33.4 foot)
Max Maneuvering Load Factor: 7 g
Min Maneuvering Load Factor: -4 g
Sustained Load Factor: 3.70 g
Landing Run Distance: 352 meter (1,155 foot)
Max Range: 860 nautical mile (1,593 kilometer)
Take Off Run Distance: 247 meter (810 foot)
Max Power at TakeOff: 950 shp
Climb Rate: 3,880 fpm (19.8 mps)
Cruise Speed: 271 knot (502 kph)
Stall Speed: 69 knot (128 kph)
Top Speed at High Altitude: 320 knot (592 kph)
Empty Weight: 1,725 kilogram (3,803 pound)
Max Takeoff Weight: 2,350 kilogram (5,181 pound)
Payload: 1,040 kilogram (2,293 pound)
CEP: Circular Error Probable
Meters (m)   Kilometers (km)   Nautic Miles (nm)   Inch (in)   Yard (yd)   Foot (ft)   Millimeter (mm)
Pound (lb)   Kilogram (kg)   kN (KiloNewton)   Ton (t)
Meters per Second (mps)   Kilometers per Hour (kph)   Knot (kt)   Miles per Hour (mph)
Liter (l)   Galon (gl)
Year (yr)   Minutes (min)   Second (sec)
Shaft-Horse-Power (shp)

Pilatus PC-9 News

There are 2 news between
25 May 2012 and 10 Aug 2015
Monday, August 10, 2015Royal Jordanian Air Force Orders Nine Pilatus PC-9 M Training Airplanes
Friday, May 25, 2012Royal Saudi Air Force to Take Delivery of First Pilatus PC-21 in 2014

Operators & Related Equipment

PC-9 M
PC-9 B
PC-9 M
Aircraft (9) ordered by the Royal Jordanian Air Force in August 2015

Grand Total 15014
Propulsion Systems
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