Pilatus P-3
Swiss training aircraft From Wikipedia, the free encyclopedia
The Pilatus P-3 was a military training aircraft built by Pilatus Aircraft of Switzerland.
| P-3 | |
|---|---|
| |
| General information | |
| Type | Trainer aircraft |
| Manufacturer | Pilatus Aircraft |
| Status | in use in private hands |
| Primary users | Swiss Air Force |
| Number built | 79 |
| History | |
| Introduction date | 1956 |
| First flight | 3 September 1953 |
| Developed into | Pilatus PC-7 |
Design and development
The Pilatus P-3 was designed for primary and advanced training (including night flying, aerobatics and instrument flying). The military versions were designated P-3-03 to P-3-05. It was of all-metal construction with a retractable tricycle undercarriage and tandem seating. There was provision for underwing racks for light practice bombs or rockets and a machine gun in a pod below the port wing. Although such kits were purchased, they were never used.[1]
Operational history
Summarize
Perspective
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The first prototype P-3.01 was built in 1953 and flew on 3 September the same year[2] with a two-blade propeller. The power of the engine of the aircraft proved to be insufficient. A second prototype to become the military prototype flew in August, 1954, now equipped with a different engine and a three blade propeller. During the evaluation of the military prototype, now designated P-3.02 (HB-HOO, becoming A-801 in January 1956), the aircraft had to perform against a T-34 Mentor that had been brought to Switzerland.[3] The test pilot at the demonstration flight went to the limits and flew a standing "8", knowing, the Mentor would not be able to fly this manoeuvre.[4] After the acceptance by the Swiss Air Force, the service received a pre-series of 12 aircraft type P-3.03 (A-802-A-813). Six additional examples were built and flew with civilian markings, those P-3.04 were later acquired by the Brazilian Navy.[5] The Swiss Air Force then purchased 60 airframes of the type P-3.05 (A-814-A-873)[6] and used their P-3s as a training aircraft until 1983, although it continued to be used as a liaison aircraft for another decade. In 1993–1995, 65 ex-Swiss Air Force aircraft were sold on the private market.[7]
After two crashes resulting from an aircraft going into a flat spin, the aircraft A-858 received a ventral fin. After successful testing, all swiss P-3 received the fin.[4]
The prototype P-3.01 HB-HON was used by Pilatus' sister company Contraves as a target tug before returning to Pilatus to become the prototype of the PC-7 in 1966.[8]
Variants
- P-3-01
- Prototype[2]
- P-3-02
- Military prototype[3]
- P-3-03
- Pre-production aircraft for the Swiss Air Force. 12 built.
- P-3-04
- Six built with and flown in civilian markings. Later acquired by the Brazilian Navy and designated L-3, O-3, and later U-3.[5][9]
- P-3-05
- Production variant for the Swiss Air Force. 60 built.[6]
Operators
The P-3 Flyers is an independent air display team based in Switzerland.[10][11] Formed in 1996. it currently operates five ex-Swiss Air Force P3 aircraft.[12][13]
Specifications (Pilatus P-3-03)
Data from Jane's All The World's Aircraft 1958–59 [14]
General characteristics
- Crew: one
- Capacity: one passenger
- Length: 8.75 m (28 ft 8 in)
- Wingspan: 10.40 m (34 ft 1 in)
- Height: 3.05 m (10 ft 0 in)
- Wing area: 16.55 m2 (178.1 sq ft)
- Aspect ratio: 6.55:1
- Airfoil: NACA 64A series
- Empty weight: 1,090 kg (2,403 lb)
- Gross weight: 1,415 kg (3,120 lb)
- Max takeoff weight: 1,500 kg (3,307 lb)
- Fuel capacity: 160 L (42 US gal; 35 imp gal)
- Powerplant: 1 × Lycoming GO-435-C2-A2 6-cylinder air-cooled four stroke horizontally opposed piston engine, 190 kW (260 hp)
- Propellers: 3-bladed Hartzell constant-speed propeller
Performance
- Maximum speed: 310 km/h (190 mph, 170 kn) sea level to 2,000 m (6,600 ft) at 1,500 kg (3,307 lb) AUW
- Cruise speed: 252 km/h (157 mph, 136 kn) economical cruise
- 275 km/h (171 mph; 148 kn) maximum cruise
- Stall speed: 100 km/h (62 mph, 54 kn)
- Never exceed speed: 500 km/h (310 mph, 270 kn)
- Range: 750 km (470 mi, 400 nmi) maximum in still air
- Service ceiling: 5,500 m (18,000 ft)
- Absolute ceiling: 5,100 m (16,700 ft)
- Rate of climb: 7 m/s (1,400 ft/min)
- Wing loading: 90.63 kg/m2 (18.56 lb/sq ft)
- Power/mass: 0.12 kW/kg (0.073 hp/lb)
- Take-off distance to 15 m (49 ft): 342 m (1,120 ft) on hard runway at sea level
- Landing distance from 15 m (49 ft): 390 m (1,280 ft) on hard runway at sea level
See also
Related development
Aircraft of comparable role, configuration, and era
References
Bibliography
External links
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