Pilatus PC-9: Difference between revisions

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|gross weight kg=2250
|gross weight kg=2250
|gross weight lb=
|gross weight lb=
|lift kg=<!-- lighter-than-air -->
|lift lb=<!-- lighter-than-air -->
|more general='''Maximum takeoff:''' 3,200&nbsp;kg (7,055&nbsp;lb)
|more general='''Maximum takeoff:''' 3,200&nbsp;kg (7,055&nbsp;lb)
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|eng1 kw=857<!-- prop engines -->
|eng1 kw=857<!-- prop engines -->
|eng1 hp=<!-- prop engines -->
|eng1 hp=<!-- prop engines -->
|eng1 kn=<!-- jet/rocket engines -->
|eng1 lbf=<!-- jet/rocket engines -->
|power original= flat-rated at 708&nbsp;kW (950 shp)
|power original= flat-rated at 708&nbsp;kW (950 shp)
|thrust original=
|thrust original=
|eng1 kn-ab=<!-- afterburners -->
|eng1 lbf-ab=<!-- afterburners -->
|more power=
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|max speed mph=
|max speed mph=
|max speed kts=
|max speed kts=
|cruise speed kmh=552
|max speed mach=<!-- supersonic aircraft -->
|cruise speed kmh=<!-- if max speed unknown -->
|cruise speed mph=<!-- if max speed unknown -->
|cruise speed mph=<!-- if max speed unknown -->
|cruise speed kts=
|cruise speed kts=
|stall speed kmh=<!-- aerobatic -->
|cruise speed note=KTAS at 10,000&nbsp;ft
|stall speed mph=<!-- aerobatic -->
|stall speed kmh=<!-- aerobatic -->
|stall speed mph=<!-- aerobatic -->
|stall speed kts=
|stall speed kts=
|never exceed speed kmh=593
|never exceed speed kmh=593
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|range miles=
|range miles=
|range nmi=
|range nmi=
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|range note=<ref>[http://www.pilatus-aircraft.com/html/en/downloads/index_262.asp?NavL1ID=14&NavL2ID=1797&NavL3ID=0&NavL4ID=0&NavL5ID=0&NavL6ID=0&L=2 PC-9 brochure]</ref>
|combat range km=
|combat range km=
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|ferry range miles=
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|ferry range nmi=
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|ceiling m=11580
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*Take-off distance over 50&nbsp;ft (15 m) obstacle at sea level: 1,300&nbsp;ft (397 m)
*Take-off distance over 50&nbsp;ft (15 m) obstacle at sea level: 1,300&nbsp;ft (397 m)
*Landing distance over 50&nbsp;ft (15 m) obstacle at sea level 2,255&nbsp;ft (687 m)
*Landing distance over 50&nbsp;ft (15 m) obstacle at sea level 2,255&nbsp;ft (687 m)
*Max. cruise speed at sea level: 271 KTAS (502&nbsp;km/h)
*Max. cruise speed at 10,000&nbsp;ft 298 KTAS (552&nbsp;km/h)
*Stall speed:
*Stall speed:
- flaps and gear up (Vs) 76 KCAS (141&nbsp;km/h)</br>
- flaps and gear up (Vs) 76 KCAS (141&nbsp;km/h)</br>
- flaps and gear down (Vso) 67 KCAS (124&nbsp;km/h)
- flaps and gear down (Vso) 67 KCAS (124&nbsp;km/h)
⚫
*Max. range<ref>[http://www.pilatus-aircraft.com/html/en/downloads/index_262.asp?NavL1ID=14&NavL2ID=1797&NavL3ID=0&NavL4ID=0&NavL5ID=0&NavL6ID=0&L=2 PC-9 brochure]</ref>


|avionics=
|avionics=

Revision as of 23:32, 1 November 2009

PC-9
Role Basic/Advanced Trainer aircraft
National origin Switzerland
Manufacturer Pilatus Aircraft
First flight 7 May 1984
Primary users Swiss Air Force
Royal Australian Air Force
Royal Saudi Air Force
Royal Thai Air Force
Irish Air Corps
Produced 1984-
Number built 250
Developed from Pilatus PC-7
Variants T-6 Texan II

The Pilatus PC-9 is a single-engine, low-wing tandem-seat turboprop training aircraft manufactured by Pilatus Aircraft of Switzerland.

Design and development

A view of the interior of the cockpit of a Pilatus PC-9 aircraft.

The PC-9 is a more powerful evolution of the PC-7. It retains the overall layout of its predecessor but has very little structural commonality with it. Amongst other improvements, the PC-9 features a larger cockpit with stepped ejection seats and also has a ventral airbrake.

The PC-9 programme officially started in 1982. Although some aerodynamic elements were tested on a PC-7 during 1982 and 1983, the first flight of the first PC-9 prototype took place on 7 May 1984. A second prototype flew on 20 July of the same year; this prototype had all the standard electronic flight instrumentation and environmental control systems installed and was thus almost fully representative of the production version.

Certification was achieved in September 1985. By this time, the PC-9 had lost the RAF trainer competition to the Short Tucano. However, the marketing links that Pilatus built up with British Aerospace during the competition stood them in good stead, as it soon led to their first order from Saudi Arabia.

As of 2004, more than 250 aircraft of this type have been built.

Operational history

The first production aircraft for the Royal Australian Air Force (RAAF) flew on 19 May 1987, under the Australian designation PC-9/A.

Condor Flugdienst of Germany uses 10 examples of the target-towing variant.

Variants

A USAF T-6A Texan II out of Randolph Air Force Base
PC-9
Two-seat basic trainer aircraft.
PC-9/A
Two-seat basic trainer for the Royal Australian Air Force. Built under licence in Australia by Hawker de Havilland. Croatia ordered three second-hand examples from the RAAF in 1997.
PC-9B
Two-seat target-towing aircraft for the German Luftwaffe. This target-towing version has an increased fuel capacity enabling flight for up to 3 hours and 20 minutes as well as two Southwest RM-24 winches under the wings. These winches can reel out a target up to 3.5 kilometres.
PC-9M
This version was introduced in 1997 as the new standard model. It has an enlarged dorsal fin in order to improve longitudinal stability, modified wingroot fairings, stall strips on the leading edges as well as new engine and propeller controls. Croatia bought 17 new units in 1997; Slovenia placed an order for nine (nicknamed Hudournik - Swift) in December of the same year; Oman ordered 12 examples in January 1999; and Ireland signed a contract for eight in January 2003. Bulgaria purchased 12 aircraft in 2004. The last order was made by Mexico, which received at least two in September 2006.
Beech Pilatus PC-9 Mk.2
In order to compete in the United States JPATS competition, Pilatus and Beechcraft developed an extensively modified version of the PC-9, called the Beech Pilatus PC-9 Mk. II which beat out seven other contenders. It was later renamed the T-6A Texan II and is now built and marketed independently by Beechcraft. Over 700 are to be built for the United States Air Force and United States Navy, with Pilatus receiving royalties.
PC-9 Plus
This version is for an upgrade from PC9M standard to PC-9 Plus, this version is armed and is being built by RADOM Aviation [1]

General-purpose bomb:
Mark 81 bomb
Mark 82 bomb

Operators

Australian PC-9 from the RAAF Roulettes aerobatic display team
Croatian Air Force aerobatic team Wings of Storm
Pilatus PC-9M of the Slovenian Armed Forces

Military operators

 Australia
 Bulgaria
 Croatia
  • Croatian Air Force operates 20 aircraft - 17 PC-9M delivered new from 1997, as well as three second-hand examples. PC-9s are used for advanced pilot training and as a national aerobatic aircraft in a group called Wings of Storm.
 Chad
  • Chad's Air Force operates 3 PC-7s and 1 PC-9. The latter was delivered to Chad to replace a PC-7 which it had purchased from France.[2]
 Ireland
  • Irish Air Corps operates 7 PC-9Ms delivered in late-2004. In 2005 planes were upgraded and each aircraft is now equipped with 2x rocket pods and 2x machine gun pods. On 12 October 2009 a PC-9M was involved in a fatal crash near Cornamona, Co.Galway killing both pilots.[1]
 Mexico
  • Mexican Air Force - operates 2 PC-9Ms delivered in late-September 2006, more possibly will be delivered.
 Myanmar
 Oman
 Saudi Arabia
 Slovenia
 Switzerland
  • Swiss Air Force operates 14 aircraft delivered from 1987. Two returned to Pilatus after evaluation.
 Thailand
 United States

Civil operators

 Germany
 United Kingdom

Specifications (PC-9M)

This aircraft article is missing some (or all) of its specifications. If you have a source, you can help Wikipedia by adding them.

General characteristics

  • Crew: one or two pilots
  • Capacity: two seats (tandem)
  • Length: 10.70 m (35 ft 1 in)
  • Wingspan: 10.12 m (33 ft 2 in)
  • Height: 3.26 m (10 ft 8 in)
  • Wing area: 16.3 m2 (175 sq ft)
  • Empty weight: 1,725 kg (3,803 lb)
  • Gross weight: 2,250 kg (4,960 lb)Maximum takeoff: 3,200 kg (7,055 lb)
  • Powerplant: 1 × Pratt & Whitney Canada PT6A-62 turboprop, 857 kW (1,149 hp)flat-rated at 708 kW (950 shp)

Performance

  • Maximum speed: 593 km/h (368 mph, 320 kn)
  • Cruise speed: 552 km/h (343 mph, 298 kn) KTAS at 10,000 ft
  • Never exceed speed: 593 km/h (368 mph, 320 kn)
  • Range: 1,593 km (990 mi, 860 nmi) [3]
  • Service ceiling: 11,580 m (37,990 ft)
  • g limits: + 7.0 g + 4.5 g

– 3.5 g – 2.25 g

  • Rate of climb: 20.8 m/s (4,090 ft/min)
  • Power/Mass: 0.31 kW/kg (0.19 hp/lb)
  • Take-off distance over 50 ft (15 m) obstacle at sea level: 1,300 ft (397 m)
  • Landing distance over 50 ft (15 m) obstacle at sea level 2,255 ft (687 m)
  • Stall speed:

- flaps and gear up (Vs) 76 KCAS (141 km/h)
- flaps and gear down (Vso) 67 KCAS (124 km/h)

See also

Related development

Aircraft of comparable role, configuration, and era

References

  1. ^ RTÉ News: Two pilots die in Air Corps crash
  2. ^ Harding, Stephen (1997). U.S. Army Aircraft Since 1947. Atglen, PA, USA: Schiffer Publishing Ltd. p. 202. ISBN 96-69996. {{cite book}}: Check |isbn= value: length (help)
  3. ^ PC-9 brochure

External links

Wikimedia Commons has media related to Pilatus PC-9.
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