Credit
Alan Wilson · CC BY-SA 2.0 · Resized · CC BY-SA 2.0 · Source ↗ · Modified
FORCETALLY
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At a glance
Measured figures
G 115E · Length
Single source7.79 m (25 ft 7 in)[source]
PC-7 · Length
Single sourceConfiguration
| Specification | Grob G 115 | Pilatus PC-7 |
|---|---|---|
| Type | Basic trainer[source] | Trainer aircraft[source] |
| Manufacturer | Grob Aircraft[source] | Pilatus Aircraft[source] |
| Status | active[source] | In service[source] |
| Primary users | Royal Air Force Egyptian Air Force Finnish Air Force Royal Navy Army Air Corps (UK)[source] | Mexican Air Force Indian Air Force South African Air Force Royal Malaysian Air Force |
9.78 m (32 ft 1 in)[source]
Cruise; G 115E · long range cruising speed
Single sourceMaximum; G 115E · Maximum speed
Single source250 km/h (160 mph, 130 kn)[source]
178 km/h (111 mph, 96 kn) (long range cruising speed)[source]
Cruise; PC-7 · (econ. cruise at 6,095 m (19,997 ft))
Single sourceMaximum; PC-7 · (max cruise at 6,095 m (19,997 ft))
Single sourceG 115E · 45% power at FL 80, 45 min reserves
Single source1,150 km (710 mi, 620 nmi) (45% power at FL 80, 45 min reserves)[source]
Ferry; PC-7 · Ferry range
Single sourcePC-7 · standard range without external drop tanks, ferry range with external drop tanks, (cruise power, at 5,000 m (16,000 ft) - 20 min reserves)
Single source1,200 km (750 mi, 650 nmi) standard range without external drop tanks, ferry range with external drop tanks, (cruise power, at 5,000 m (16,000 ft) - 20 min reserves)[source]
2,630 km (1,630 mi, 1,420 nmi)[source]
G 115E · 1 × Lycoming AEIO-360-B1F/B 4-cylinder air-cooled horizontally-opposed piston engine
Single source1 × Lycoming AEIO-360-B1F/B 4-cylinder air-cooled horizontally-opposed piston engine, 130 kW (180 hp)[source]
PC-7 · 1 × Pratt & Whitney Canada PT6A -25A turboprop derated from
Single sourcePC-7 · 650 shp
Single source1 × Pratt & Whitney Canada PT6A -25A turboprop , 410 kW (550 hp)(derated from 485 kW (650 shp))[source]
G 115E · 1,050 ft/min
Single source5.3 m/s (1,050 ft/min)[source]
PC-7 · (2,150 ft/min) climb to 5,000 m in 9 min 0 sec take-off run 780 m at max take-off weight, landing run 505 m at max landing weight
Single source10.9 m/s (2,150 ft/min) climb to 5,000 m in 9 min 0 sec take-off run 780 m at max take-off weight, landing run 505 m at max landing weight[source]
PC-7 · Endurance
Single source4 hr 22 min[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Manufactured | 1985–present[source] | 1966–present[source] |
|---|
| Introduction date | 1999[source] | PC-7 : 1978 PC-7 Mk.II M : 1994 PC-7 MKX : 2021[source] |
|---|
| First flight | November 1985[source] | PC-7 : 12 April 1966 ( 1966-04-12 ) (prototype) 18 August 1978 ( 1978-08-18 ) (production) PC-7 Mk.II M : 28 September 1992 ( 1992-09-28 )[source] |
|---|
| Fuel capacity | 143 L (31 imp gal; 38 US gal) usable[source] | 474 L (104 imp gal; 125 US gal) usable internal fuel, 2x 240 L (53 imp gal; 63 US gal) external fuel drop tanks • Max landing weight: 2,565 kg[source] |
|---|
| Aspect ratio | 8.2:1[source] | 6.5:1[source] |
|---|
| Airfoil | Eppler 696[source] | NACA 64 2 A-415 at root, 64 1 A-612 at tip[source] |
|---|
| Propellers | 3-bladed Hoffmann HO-V343K-V/183GY Constant-speed propeller , 1.83 m (6 ft 0 in) diameter[source] | 3-bladed Hartzell HC-B3TN-2 / T10173C-8 constant-speed propeller , 2.36 m (7 ft 9 in) diameter[source] |
|---|
| Stall speed | 91 km/h (57 mph, 49 kn) (60 degree flap)[source] | 119 km/h (74 mph, 64 kn) (flaps and gear down, power off)[source] |
|---|
| Never exceed speed | 341 km/h (212 mph, 184 kn)[source] | 500 km/h (310 mph, 270 kn) EAS[source] |
|---|
| g limits | + 6.0/ - 3.0[source] | -3 / +6[source] |
|---|
| Country of origin | Deutschland[source]Country of design · Entwurfsland | Switzerland[source] |
|---|
| Number built | — | >618[source] |
|---|
| Developed from | — | Pilatus P-3[source] |
|---|
| Developed into | — | Pilatus PC-9[source] |
|---|
| Capacity | — | two[source] |
|---|
| Hardpoints | — | 6 × underwing hardpoints for bombs and rockets with a capacity of 1,040 kg (2,294 lb)[source] |
|---|
| Alternative designation | — | Pilatus PC-7 Turbo Trainer[source] |
|---|