History
The Pilatus PC-7 is based on the Pilatus P-3 and the first prototype, actually a P-3 of which the Lycoming engine was replaced by a P & W PT6A-20 turboprop, made its first flight in April 1966.
The program was seriously delayed by a crash and just in 1975 a second prototype, also a converted P-3, made its maiden flight.
There were all kinds of modifications, such as a new wing with integrated fuel tanks, a modified tail and a tear drop cockpit.
In August 1978 the first production exampled rolled out and by the end of the year, the type received its Swiss type certification.
Soon the delivery of the PC-7 to both civilian and military users followed.
The PC-7 Mk. II is actually a development of the PC-9, and adapted to the smaller of the turboprop PC-7. Goal was reducing the cost of operation and maintenance.
Versions.
- PC-7:
- two seat basic trainer with one Pratt & Whitney PT6A-25A rated 410 kW
- PC-7 Mk II:
- a development for the SAAF, based on the airframe and avionics of the PC-9, the wing of the PC-7 and one& Pratt & Whitney PT6A-25C rated 522 kW. In fact it is a hybrid of the PC-7 and the PC-9.
- NCPC-7:
- an upgraded version, developed for the Swiss air force and equipped with a glass cockpit and new avionics.
| Dimensions: | |||
| Length: | 9,78 m | Wingspan: | 10,4 m |
| Height: | 3,21 m | Wing area: | 16,3 m2 |
| Weights: | |||
| Empty weight: | 1670 kg | Max. start weight: | 2700 kg |
| Performances: | |||
| Max. speed: | 500 km/hr | Climbing speed: | - m/min |
| Cruising speed: | 412 km/hr | ||
| Range: | 1050 km | Service ceiling: | 10060 m |
| Miscellaneous: | |||
| Engine type: | One Pratt & Whitney PT-6A-25A rated 650 hp | ||
| Crew: | One instructor plus one pupil | ||
| Armament: | None | ||
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