JEROEN VOGELAAR: Aviation Photographs

turboprop

Saab 2000

Saab 2000 G-CDEB British Airways

The Saab 2000 is a twin-engined high-speed turboprop airliner built by Saab.

  • Role: Regional airliner
  • National origin: Sweden
  • Manufacturer: Saab Aircraft
  • Production line: Linköping
  • First flight: 26 March 1992
  • Introduction: 30 August 1994
  • Status: In service
  • Produced: 1992–1999
  • Number built: 63
  • Developed from: Saab 340

Saab 2000 G-CDEB British Airways

Specifications Saab 2000

General characteristics

  • Crew: two
  • Capacity: 50–58 passengers
  • Payload: 5,900 kg (13,010 lb)
  • Length: 27.28 m (89 ft 6 in)
  • Wingspan: 24.76 m (81 ft 3 in)
  • Height: 7.73 m (25 ft 4 in)
  • Wing area: 55.7 m² (600 sq ft)
  • Airfoil: NASA MS(1)013
  • Aspect ratio: 11:0
  • Empty weight: 13,800 kg (30,424 lb)
  • Max. takeoff weight: 22,800 kg (50,265 lb)
  • Powerplant: 2 × Allison AE 2100A turboprop, 3,096 kW (4,152 shp) each
  • Propellers: six blade constant speed Dowty propellers, 1 per engine

Performance

  • Cruise speed: 665 km/h (370 knots, 424 mph)
  • Service ceiling: 9,450 m (31,000 ft)
  • Rate of climb: 11.4 m/s (2,250 ft/min)

Avionics

  • Rockwell Collins Pro Line 4 avionics suite with integrated avionics processor (IAP)

Antonov An-12

Antonov An-12AP UR-CCP Cavok Air

The Antonov An-12 is a four-engined turboprop transport aircraft designed in the Soviet Union.

  • Role: Civil and Military transport aircraft
  • National origin: Soviet Union
  • Manufacturer: Antonov
  • First flight: 16 December 1957
  • Introduction: 1959
  • Status: Active service with various airlines (especially cargo) and Air Forces
  • Produced: 1957–1973
  • Number built: 1,248

Specifications (An-12)

General characteristics

  • Crew: 5: 2 pilots, flight engineer, navigator, radio operator
  • Payload: 20,000 kg (44,000 lb)
  • Length: 33.10 m (108 ft 7 in)
  • Wingspan: 38.00 m (124 ft 8 in)
  • Height: 10.53 m (34 ft 7 in)
  • Wing area: 121.7 m² (1,310 ft²)
  • Empty weight: 28,000 kg (62,000 lb)
  • Useful load: 60 paratroopers (two BMD-1 armoured vehicles)
  • Max. takeoff weight: 61,000 kg (130,000 lb)
  • Powerplant: 4 × Ivchenko AI-20L or AI-20M turboprops, 4,000 ehp (3,000 kW) each

Performance

  • Maximum speed: 777 km/h (419 knots, 482 mph)
  • Cruise speed: 670 km/h (361 knots, 415 mph)
  • Range:
    • With maximum fuel: 5,700 km (3,075 nm, 3,540 mi)
    • With maximum load: 3,600 km (1,945 nm, 2,235 mi))
  • Service ceiling: 10,200 m (33,500 ft)
  • Rate of climb: 10m/s (1960ft/min)

Armament

  • Guns: 2× 23 mm (0.906 in) Nudelman-Rikhter NR-23 cannons in a tail turret (some aircraft)

ATR 72

ATR 72-212F EI-SLK Air Contractors

The ATR 72 is a twin-engine turboprop short-haul regional airliner built by the French-Italian aircraft manufacturer ATR. A stretched variant of the ATR 42, the aircraft seats up to 74 passengers in a single-class configuration, and is operated by a two-pilot crew.

 

  • Role: Regional airliner
  • National origin: France/Italy
  • Manufacturer: ATR
  • Production line: Toulouse – Blagnac, France
  • First flight: 27 October 1988
  • Introduction: 27 October 1989 Finnair
  • Status: In service
  • Produced: 1988–present
  • Number built: 754 as of December 2014
  • Developed from: ATR 42

 

Specifications (ATR 72–600)

General characteristics

  • Crew: 2
  • Capacity: 68 (1-class, 31 in (79 cm) pitch) to 74 (1-class, 29 in (74 cm) pitch) passengers
  • Length: 27.17 m (89 ft 2 in)
  • Wingspan: 27.05 m (88 ft 9 in)
  • Width: 2.57 m (8 ft 5 in) (maximum cabin width)
  • Height: 7.65 m (25 ft 1 in)
  • Wing area: 61.00 m2 (656.6 sq ft)
  • Aspect ratio: 12.0:1
  • Empty weight: 13,010 kg (28,682 lb)
  • Max takeoff weight: 22,800 kg (50,265 lb)
  • Fuel capacity: 5,000 kg (11,000 lb)
  • Typical payload: 7,500 kg (16,500 lb)
  • Powerplant: 2 × Pratt & Whitney Canada PW127F turboprops, 1,846 kW (2,475 shp) each
  • Propellers: 568F-bladed Hamilton Standard, 3.93 m (12 ft 11 in) diameter

Performance

  • Cruise speed: 509 km/h; 316 mph (275 kn)
  • Range: 1,528 km; 949 mi (825 nmi)
  • Service ceiling: 7,620 m (25,000 ft)
  • Rate of climb: 6.88 m/s (1,355 ft/min)
  • Takeoff Run at MTOW: 1,333 m (4,373 ft)

Pilatus PC-9

Pilatus PC-9 HB-HPJ Pilatus Aircraft

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

  • Role: Advanced Trainer aircraft
  • Manufacturer: Pilatus Aircraft
  • Designer: Pilatus Aircraft
  • First flight: 7 May 1984
  • Introduction: 1984 – present
  • Status: Active service
  • Number built: 265
  • Developed from: Pilatus PC-7
  • Developed into: T-6 Texan II

Pilatus PC-9 HB-HPJ Demo Pilatus Aircraft

Military operators

  • Royal Australian Air Force
  • Bulgarian Air Force
  • Croatian Air Force
  • Chadian Air Force
  • Cyprus Air Forces
  • Irish Air Corps
  • Mexican Air Force
  • Myanmar Air Force
  • Royal Air Force of Oman
  • Royal Saudi Air Force
  • Slovenian Air Force and Air Defence
  • Swiss Air Force
  • Royal Thai Air Force

Former military operators

  • National Air Force of Angola
  • Luftwaffe
  • United States Army

Pilatus PC-9 HB-HPJ Demo Pilatus Aircraft

Specifications (PC-9M)

General characteristics

  • Crew: one or two pilots
  • Length: 10.14 m (33 ft 3 in)
  • Wingspan: 10.125 m (33 ft 3 in)
  • Height: 3.26 m (10 ft 8 in)
  • Wing area: 16.29 m2 (175.3 sq ft)
  • Empty weight: 1,725 kg (3,803 lb)
  • Gross weight: 2,350 kg (5,181 lb)
  • Max takeoff weight: 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)
  • Cruising speed: 556 km/h (345 mph; 300 kn) at 7,620 m (25,000 ft)
  • Stall speed: 143 km/h (89 mph; 77 kn) EAS flaps and gear up, 128 km/h (80 mph; 69 kn) flaps and gear down
  • Range: 1,537 km (955 mi; 830 nmi)
  • Endurance: 4 hr 30 min
  • Service ceiling: 11,580 m (37,992 ft)
  • g limits: + 7.0 g to −3.5 g
  • Rate of climb: 20.8 m/s (4,090 ft/min)
  • Take-off distance over 50 ft (15 m) obstacle at sea level: 1,280 ft (391 m)
  • Landing distance over 50 ft (15 m) obstacle at sea level: 2,295 ft (700 m)

Armament

  • Hardpoints: Three hardpoints under each wing, inner two rated at 250 kg (550 lb), outer rated at 110 kg (240 lb)

Pilatus PC-9 C-406 Zielflugstaffe Swiss Air Force