JEROEN VOGELAAR: Aviation Photographs

Pilatus

Pilatus PC-7

Pilatus PC-7 A-912/1 PC-7 Team Swiss Air Force

The Pilatus PC-7 Turbo Trainer is a low-wing tandem-seat training aircraft, manufactured by Pilatus Aircraft of Switzerland. The aircraft is capable of all basic training functions including aerobatics, instrument, tactical and night flying.

  • Role: Light Trainer aircraft
  • Manufacturer: Pilatus Aircraft
  • Designer: Pilatus Aircraft
  • First flight: 12 April 1966 (prototype), 18 August 1978 (production)
  • Produced: 1966 – present
  • Status: Active service
  • Number built: 618
  • Developed from: Pilatus P-3
  • Developed into: Pilatus PC-9

Variants

  • PC-7 : two-seat basic trainer aircraft, powered by PT6A-25A engine rated at 410 kW (550 shp).
  • PC-7 Mk II is a development of the PC-9’s airframe and avionics, retaining the PC-7’s wing to mount external stores. Powered by PT6A-25C of 522 kW (700 shp) rather than more powerful PT6A-62 of PC-9.
  • NCPC-7 : upgraded version of the standard PC-7 with fully IFR glass cockpit avionics, developed for the Swiss Air Force.

Military operators

  • National Air Force of Angola: 25
  • Austrian Air Force: 16
  • Bolivian Air Force: 24
  • Botswana Defence Force Air Wing: 7 PC-7, 5 PC-7 MK II
  • Royal Brunei Air Force: 4
  • Chad Air Force: 2
  • Chilean Navy: 10
  • Guatemalan Air Force: 12
  • Indian Air Force: 75
  • Iran Air Force: 35
  • Royal Malaysian Air Force:47
  • Mexican Air Force: 88
  • Myanmar Air Force: 17
  • Royal Netherlands Air Force: 13
  • South African Air Force: 60
  • Swiss Air Force: 40 (delivered from 1979), 28 NCPC-7s in service in 2011
  • United Arab Emirates Air Force: 7
  • Uruguayan Air Force: 6

Former military operators

  • Bophuthatswana Air Force: 3
  • French Air Force: 5
  • Iraq Air Force: 52
  • Nigerian Air Force: 2
  • Surinam Air Force: 3

Specifications (PC-7)

General characteristics

  • Crew: Two, student and instructor
  • Length: 9.78 m (32 ft 1 in)
  • Wingspan: 10.40 m (34 ft 1 in)
  • Height: 3.21 m (10 ft 6 in)
  • Wing area: 16.60 m² (179.0 ft²)
  • Empty weight: 1,330 kg (2,932 lb)
  • Max. takeoff weight: 2,700 kg (5,952 lb)
  • Powerplant: 1 × Pratt & Whitney Canada PT6A-25A turboprop, 410 kW (550 shp)

Performance

  • Never exceed speed: 500 km/h (270 knots, 310 mph)
  • Maximum speed: 412 km/h (222 knots, 256 mph) (max cruise at 6,100 m (20,000 ft))
  • Stall speed: 119 km/h (64 knots, 74 mph) flaps and gear down, power off
  • Range: 2,630 km (1,420 nmi, 1,634 mi) (cruise power, at 5,000 m (16,400 ft) – 20 min reserves)
  • Service ceiling: 10,060 m (33,000 ft)
  • Rate of climb: 10.9 m/s (2,150 ft/min)
  • Wing loading: 114.5 kg/m² (23.44 lb/ft²)

Armament

  • Hardpoints: 6 × hardpoints for bombs and rockets with a capacity of 1,040 kg (2,294 lb)

 

Pilatus PC-6 Porter/Turbo-Porter

Pilatus PC-6B1-H2 Turbo Porter HB-FCF Swiss Air Force

The Pilatus PC-6 Porter is a single-engined Short Take-Off and Landing (STOL) utility aircraft designed by Pilatus Aircraft of Switzerland. It has been built in both piston engine and turboprop powered versions (Turbo-Porter) and was produced for a time by Fairchild Hiller in the United States.

  • Role: STOL Passenger and utility aircraft
  • National origin: Switzerland
  • Manufacturer: Pilatus Aircraft
  • First flight: Porter – 4 May 1959, Turbo-Porter – 2 May 1961.
  • Produced: 1959-present
  • Number built:581 (As of August 2014)
  • Status: Active service

Military variants

  • AU-23A Peacemaker – Armed gunship, counter-insurgency, utility transport version for the U.S. Air Force
  • UV-20A Chiricahua – STOL utility transport version for the U.S. Army

Civil Pilatus PC-6 Porter/Turbo-Porter

Military operators

  • National Air Force of Angola
  • Argentine Navy
  • Gendarmeria Nacional Argentina
  • Austrian Air Force
  • Myanmar Air Force
  • Chad Air Force
  • Ecuadorian Army
  • Islamic Republic of Iran Air Force
  • Mexican Air Force
  • Peruvian Air Force
  • Slovenian Air Force and Air Defence
  • Swiss Air Force
  • Royal Thai Air Force
  • United States Army

Specifications PC-6 B2 Turbo-Porter

General characteristics

  • Crew: one, pilot
  • Capacity: up to ten passengers
  • Payload: 1,130 kg (2,491 lb)
  • Length: 11.00 m (36 ft 1 in)
  • Wingspan: 15.87 m (52 ft 0¾ in)
  • Height: 3.20 m (10 ft 6 in)
  • Wing area: 30.15 m² (324.5 sq ft)
  • Airfoil: NACA 64-514
  • Aspect ratio: 8.4:1
  • Empty weight: 1,270 kg (2,800 lb)
  • Max. takeoff weight: 2,800 kg (6,173 lb)
  • Powerplant: 1 × Pratt & Whitney Canada PT6A-27 turboprop, 410 kW (550 shp)(downrated from 507 kW (680 shp))

Performance

  • Never exceed speed: 280 km/h (151 knots, 174 mph)
  • Maximum speed: 232 km/h (125 knots, 144 mph)
  • Cruise speed: 213 km/h (115 knots, 132 mph) at 3,050 m (10,000 ft)
  • Stall speed: 96 km/h (52 knots, 60 mph) (flaps down, power off)
  • Range: 730 km (394 nmi, 453 mi) with maximum payload
  • Ferry range: 1,612 km (870 nmi, 1,002 mi) with maximum internal and underwing fuel
  • Service ceiling: 8,197 m (25,000 ft)
  • Rate of climb: 4.8 m/s (941 ft/min)

Pilatus PC-6 Porter

Pilatus PC-6B2-H4 Turbo Porter HB-FNI Pilatus Aircraft

The Pilatus PC-6 Porter is a single-engined Short Take-Off and Landing (STOL) utility aircraft designed by Pilatus Aircraft of Switzerland. It has been built in both piston engine and turboprop powered versions (Turbo-Porter) and was produced for a time by Fairchild Hiller in the United States.

  • Role: STOL Passenger and utility aircraft
  • National origin: Switzerland
  • Manufacturer: Pilatus Aircraft
  • First flight: Porter – 4 May 1959, Turbo-Porter – 2 May 1961.
  • Produced: 1959-present
  • Number built:581 (As of August 2014)
  • Status: Active service

Military variants

Specifications PC-6 B2 Turbo-Porter

General characteristics

  • Crew: one, pilot
  • Capacity: up to ten passengers
  • Payload: 1,130 kg (2,491 lb)
  • Length: 11.00 m (36 ft 1 in)
  • Wingspan: 15.87 m (52 ft 0¾ in)
  • Height: 3.20 m (10 ft 6 in)
  • Wing area: 30.15 m² (324.5 sq ft)
  • Airfoil: NACA 64-514
  • Aspect ratio: 8.4:1
  • Empty weight: 1,270 kg (2,800 lb)
  • Max. takeoff weight: 2,800 kg (6,173 lb)
  • Powerplant: 1 × Pratt & Whitney Canada PT6A-27 turboprop, 410 kW (550 shp)(downrated from 507 kW (680 shp))

Performance

  • Never exceed speed: 280 km/h (151 knots, 174 mph)
  • Maximum speed: 232 km/h (125 knots, 144 mph)
  • Cruise speed: 213 km/h (115 knots, 132 mph) at 3,050 m (10,000 ft)
  • Stall speed: 96 km/h (52 knots, 60 mph) (flaps down, power off)
  • Range: 730 km (394 nmi, 453 mi) with maximum payload
  • Ferry range: 1,612 km (870 nmi, 1,002 mi) with maximum internal and underwing fuel
  • Service ceiling: 8,197 m (25,000 ft)
  • Rate of climb: 4.8 m/s (941 ft/min)

Pilatus PC-12

Pilatus PC-12.47E HB-FVY Pilatus Aircraft Factory

  • Role: Passenger and cargo aircraft
  • National origin: Switzerland
  • Manufacturer: Pilatus Aircraft
  • First flight: 31 May 1991
  • Introduction: 1994
  • Status: Active service, in production

Pilatus PC-12 HB-FVJ Privat

Specifications

General characteristics

  • Crew: one or two pilots
  • Capacity: 9 passengers standard, 6-8 executive
  • Payload: 1,500 kg (3,502 lb)
  • Length: 14.40 m (47 ft 3 in)
  • Wingspan: 16.23 m (53 ft 3 in)
  • Height: 4.26 m (14 ft 0 in)
  • Wing area: 25.81 m² (277.8 ft²)
  • Empty weight: 2,761 kg (5,867 lb)
  • Loaded weight: 4,700 kg (10,450 lb)
  • Max. takeoff weight: 4,740 kg (10,450 lb)
  • Powerplant: 1 × Pratt & Whitney Canada PT6A-67B or -67P turboprop, 895 kW (1,200 shp)
  • Maximum landing: 4,500 kg (9,921 lb)
  • Maximum payload full fuel: 539 kg (1,189 lb)
  • Tail wingspan: 5.20 m (17 ft 1 in)
  • Propeller: Hartzell HC – E4A – 3D/E10477K – 4 blade aluminum
  • Propeller diameter: 2.67 m (8 ft 9 in)
  • Propeller RPM: 1,700 rpm

Performance

  • Cruise speed: 500 km/h (312.5 mph/270 KTAS/280 KTAS @ 20000 ft (PC-12NG))
  • Stall speed: 120 km/h (74.8 mph/ 65 KCAS/66 KCAS (PC-12NG))
  • Service ceiling: 9,150 m (30,000 ft)
  • Rate of climb: 512 m/min at sea level (1,680 ft/min)
  • Wing loading: 174.3 kg/m² (35.7 lb/ft²)
  • Power/mass: 3.7 kg/shp (8.2 lb/shp)
  • Range 0 passenger: 3,389 km (1,830 nm)
  • Range 9 passenger: 2,804 km (1,753 mi) (1,513 nm)
  • Takeoff distance over 15 m (50 ft) obstacle: 701 m (2,300 ft)
  • Takeoff distance ground roll: 450 m (1,475 ft)
  • Landing distance over 15 m (50 ft) obstacle: 558 m (1,830 ft)
  • Landing distance ground roll: 228 m (945 ft)
  • Climb to 30,000 ft: 26.5 minutes
  • Fuel consumption: 360 pounds per hour (54 gph)

Avionics
Honeywell Primus Apex (PC-12NG)