Last site update: 03-10-2008

 

         

 

  

 

Pilatus PC-9

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Pilatus PC-9

The Pilatus PC-9 is a much more powerful evolution of the PC-7. The PC-9 program began in May 1982, with some aerodynamic elements tested on the PC-7 in 1982/83. The first pre-production PC-9 flew on  May 7, 1984, and the second followed two months later on July 20. This one was almost fully representative of the production version, with electronic flight instrumentation and environmental control systems installed. Aerobatic certification was achieved in September 1985.

In 1997, the PC-9M was introduced as the new standard model. It features an enlarged dorsal fin to improve longitudinal stability, modified wing root fairings, stall strips on the leading edges and new engine/propeller controls.

Raytheon T-6A Texan II

On June 22, 1995 a considerably redesigned version of the PC-9 was declared the winner of the JPATS competition to select a standard training aircraft type to be used by both the USAF and US Navy. Approximately 780 aircraft in total will be required under this program, built under license as the Raytheon T-6A Texan II.

Pilatus PC-21

According to Pilatus, the Pilatus PC-21 is designed to maximize training efficiency by combining economies of turboprop operation with high aerodynamic performance and a state-of-the-art training system.

 

 

Developing nation: Switzerland.
Manufacturer/designer:  Pilatus Aircraft.
Production line: Stans.
Task: Advanced turboprop trainer.
First flight:

May 7, 1984  HB-HPA.

  Pilatus PC-9M
Crew: 2
Ejection seat: Martin-Baker Mk.CH11A.
Wing Span: 10,19 m.
Wing Area: 16,29 mē.
Length: 10,13 m.
Height: 3,26 m.
Wheel track: 2,54 m.
Engines:

One Pratt & Whitney Canada PT6A-62 turboprop rated 857 kW.

Propeller: Hartzell four blade, diameter 2,44 m.
Weight:

- Empty: 1.685 Kg.

- Internal fuel: 535 liters.

- External fuel: 2 x 248 liters.

- Max. ordnance: 1.040 Kg.

Max. take off weight: 3.200 Kg.
Max. landing weight: 3.100 Kg.
Cruise speed: 500 km/h.
Max. speed: 556 km/h at 6.100 m.
Service ceiling: 11.580 m.
Range:

- range 1.642 km without drop tanks.

Max. endurance 4 hours, 30 minutes.

Performance:

- max. rate of climb at sea level 1.247 m per minute.

- climb to 4.575 m in 4 minutes, 5 seconds.

- take-off run 242 m at normal take-off weight.

- landing run 350 m at normal landing weight.

g limits: -3.5 / +7.
Underwing hardpoints: 6.
Target-towing duties:

Southwest RM-24 winches under the wings. These winches can reel out a target up to 3,5 kilometers.

 

 

Pilatus PC-9 operators:

Angola.

- 4 PC-9

Australia. - 67 PC-9/A
Croatia.

- 3 PC-9 obtained second-hand. 

- 17 PC-9M.

Cyprus. - 2 PC-9
Iraq.  - 20 PC-9
Ireland. - 8 PC-9M
Myanmar. - 10 PC-9
Oman. - 12 PC-9M
Saudi Arabia. - 50 PC-9
Slovenia.

- 9 PC-9M

- 3 PC-9S from US Army.

Switzerland.

- 12 PC-9 Swiss Air Force.

- 3 PC-9 Pilatus Aircraft.

Thailand. - 36 PC-9
US Army.

- 3 PC-9S to Slovenia.

- 2 PC-9Mk.II for Raytheon.*

- 1 PC-9 to HB-HPB.*

Condor Flugdienst. - 10 PC-9B for target-towing duties.

                                        * JPATS (Joint Primary Aircraft Training System) program contender.

 

 

Pilatus PC-9 written-off by accidents:

 

  •      ?                                  ?                  Myanmar Air Force.

  •     August 6, 1990            A23-035            Royal Australian Air Force.

  •     March 23, 1992            A23-055            Royal Australian Air Force.

  •     October 20, 1992         F19-18/35/18     Royal Thai Air Force.

  •     1996?                         4215                 Royal Saudi Air Arms.

  •     October 14, 1998         C-404                Swiss Air Force.

  •     November 22, 1999      D-                      Private.

  •     February 23, 2004           ?                    Royal Thai Air Force.

  •     March 3, 2004                 ?                    Slovenian Air Force.

  •     January 21, 2005        A23-029/5           Royal Australian Air Force (Roulettes demo team).

 

 

 

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