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Ridernation · CC BY-SA 4.0 · Resized · CC BY-SA 4.0 · Source ↗ · Modified
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At a glance
Measured figures
G 120A · Length
Single source8.605 m (28 ft 3 in)[source]
PC-9M · Only the source-declared variant PC-9M · PC-9M
Configuration
| Specification | Grob G 120 | PC-9M |
|---|---|---|
| Crew | Two[source] | one or two pilots[source]Only the source-declared variant PC-9M |
| Type | Trainer[source] | — |
| National origin | Germany[source] | — |
| Manufacturer | Grob Aircraft[source] | Pilatus Aircraft[source]Manufacturer of the source-named PC-9M only; no base PC-9 geometry or variant feature inherited. |
| Status | Active in production |
10.14 m (33 ft 3 in)[source]Only the source-declared variant PC-9M
Empty; G 120A · Empty weight
Single sourceGross; G 120A · Gross weight
Single sourceMaximum take-off; G 120A · Utility
Single source960 kg (2,116 lb)[source]
1,440 kg (3,175 lb)[source]
1,490 kg (3,285 lb) (Utility)[source]
Empty; PC-9M · Only the source-declared variant PC-9M · PC-9M
Single sourceGross; PC-9M · Only the source-declared variant PC-9M · PC-9M
Single source1,725 kg (3,803 lb)
Cruise; G 120A · at 75% power (1,500 m (5,000 ft))
Single sourceMaximum; G 120A · Maximum speed
Single source319 km/h (198 mph, 172 kn)[source]
307 km/h (191 mph, 166 kn) at 75% power (1,500 m (5,000 ft))[source]
Cruise; PC-9M · Only the source-declared variant PC-9M · PC-9M · at 7,620 m (25,000 ft)
Single sourceMaximum; PC-9M · Only the source-declared variant PC-9M · PC-9M
Single sourceG 120A · 1 × Lycoming AEIO-540-D4D5 air-cooled flat-six
Single source1 × Lycoming AEIO-540-D4D5 air-cooled flat-six , 190 kW (260 hp)[source]
PC-9M · Only the source-declared variant PC-9M · PC-9M · 1 × Pratt & Whitney Canada PT6A -62 turboprop
Single sourcePC-9M · Only the source-declared variant PC-9M · PC-9M · flat-rated at 950 shp
Single source1 × Pratt & Whitney Canada PT6A -62 turboprop, 857 kW (1,149 hp) flat-rated at 708 kW (950 shp)[source]Only the source-declared variant PC-9M
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| — |
| Primary users | French Air and Space Force Israeli Air Force Royal Canadian Air Force German Air Force[source] | — |
|---|
| Manufactured | 1999-present[source] | — |
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| First flight | 1999[source] | — |
|---|
| Developed from | Grob G 115[source] | — |
|---|
| Variant | Grob G 120TP[source] | — |
|---|
| Airfoil | Eppler E884[source] | — |
|---|
| Fuel capacity | 256 litres (56 imp gal; 68 US gal)[source] | — |
|---|
| Propellers | 3-bladed Hartzell HC-C3YR-1RF/F7663R, 1.98 m (6 ft 6 in) diameter[source] | — |
|---|
| Stall speed | 102 km/h (63 mph, 55 kn) with full flaps[source] | 143 km/h (89 mph, 77 kn) EAS flaps and gear up, 128 km/h (80 mph; 69 kn) flaps and gear down[source]Only the source-declared variant PC-9M |
|---|
| Never exceed speed | 435 km/h (270 mph, 235 kn)[source] | — |
|---|
| g limits | +6/-4G[source] | + 7.0 g to −3.5 g[source]Only the source-declared variant PC-9M |
|---|
| Source measurement | The airframe is made of carbon fibre reinforced plastic and is stressed to +6/-4g. Its minimum service life is just over 15,000 flight hours.[source]Grob G 120 · Design and development; only the objects and conditions stated in this passage Piston powered version with a Lycoming AEIO-540-D4D5 six cylinder, four-stroke , air-cooled piston aircraft engine producing 260 hp (194 kW).[source]Grob G 120 · Variants; only the objects and conditions stated in this passage Turboprop powered version with a Rolls-Royce 250-B17F aircraft engine producing 456 shp (340 kW) for take-off and 380 shp (283 kW) for maximum cruise.[source]Grob G 120 · Variants; only the objects and conditions stated in this passage Israeli Air Force : 17 The Snunit used by the IAF has a Lycoming AEIO-540-D4D5 engine that produces a maximum speed of 235 km/h (127 kn).[source]Grob G 120 · Operators; only the objects and conditions stated in this passage Length: 8.605 m (28 ft 3 in)[source]Grob G 120 · Specifications (G 120A); only the objects and conditions stated in this passage Wingspan: 10.19 m (33 ft 5 in)[source]Grob G 120 · Specifications (G 120A); only the objects and conditions stated in this passage Height: 2.57 m (8 ft 5 in)[source]Grob G 120 · Specifications (G 120A); only the objects and conditions stated in this passage Wing area: 13.29 m 2 (143.1 sq ft)[source]Grob G 120 · Specifications (G 120A); only the objects and conditions stated in this passage Empty weight: 960 kg (2,116 lb)[source]Grob G 120 · Specifications (G 120A); only the objects and conditions stated in this passage Gross weight: 1,440 kg (3,175 lb)[source]Grob G 120 · Specifications (G 120A); only the objects and conditions stated in this passage Max takeoff weight: 1,490 kg (3,285 lb) (Utility)[source]Grob G 120 · Specifications (G 120A); only the objects and conditions stated in this passage Fuel capacity: 256 litres (56 imp gal; 68 US gal)[source]Grob G 120 · Specifications (G 120A); only the objects and conditions stated in this passage Powerplant: 1 × Lycoming AEIO-540-D4D5 air-cooled flat-six , 190 kW (260 hp)[source]Grob G 120 · Specifications (G 120A); only the objects and conditions stated in this passage Propellers: 3-bladed Hartzell HC-C3YR-1RF/F7663R, 1.98 m (6 ft 6 in) diameter[source]Grob G 120 · Specifications (G 120A); only the objects and conditions stated in this passage Maximum speed: 319 km/h (198 mph, 172 kn)[source]Grob G 120 · Specifications (G 120A); only the objects and conditions stated in this passage Cruise speed: 307 km/h (191 mph, 166 kn) at 75% power (1,500 m (5,000 ft))[source]Grob G 120 · Specifications (G 120A); only the objects and conditions stated in this passage Stall speed: 102 km/h (63 mph, 55 kn) with full flaps[source]Grob G 120 · Specifications (G 120A); only the objects and conditions stated in this passage Never exceed speed : 435 km/h (270 mph, 235 kn)[source]Grob G 120 · Specifications (G 120A); only the objects and conditions stated in this passage Range: 1,540 km (960 mi, 830 nmi) at 8,000 ft (2,400 m) and 45% power)[source]Grob G 120 · Specifications (G 120A); only the objects and conditions stated in this passage Endurance: 6.35 hours at 10,000 ft and maximum endurance power setting[source]Grob G 120 · Specifications (G 120A); only the objects and conditions stated in this passage Service ceiling: 5,500 m (18,000 ft)[source]Grob G 120 · Specifications (G 120A); only the objects and conditions stated in this passage g limits: +6/-4G[source]Grob G 120 · Specifications (G 120A); only the objects and conditions stated in this passage Rate of climb: 6.5 m/s (1,280 ft/min)[source]Grob G 120 · Specifications (G 120A); only the objects and conditions stated in this passage | — |
|---|
| Country of origin | Germany[source]Inventory Origin column; table 1, row 17, cell 4; revision 1377212027; retrieved 2026-10-02 | Switzerland[source]Inventory Origin column; table 1, row 21, cell 2; revision 1376580369 Switzerland[source]Inventory Origin column; table 1, row 14, cell 2; revision 1372375479 Switzerland[source]Inventory Origin column; table 2, row 19, cell 2; revision 1365898407 |
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| Variant description | — | PC-9M[source]Only the source-declared variant PC-9M This version was introduced in 1997 as the new standard model. It has an enlarged dorsal fin in order to improve longitudinal stability, modified wingroot fairings, stall strips on the leading edges as well as new engine and propeller controls.[source]Only the source-declared variant PC-9M |
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| Take-off distance over 50 ft (15 m) obstacle at sea level | — | 1,280 ft (391 m)[source]Only the source-declared variant PC-9M |
|---|
| Landing distance over 50 ft (15 m) obstacle at sea level | — | 2,295 ft (700 m)[source]Only the source-declared variant PC-9M |
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| Hardpoints | — | seven hardpoints, 3 under each wing, inner two rated at 250 kg (550 lb), outer rated at 110 kg (240 lb)[source]Only the source-declared variant PC-9M Hardpoints: seven hardpoints, 3 under each wing, inner two rated at 250 kg (550 lb), outer rated at 110 kg (240 lb)[source]Only the source-declared variant PC-9M |
|---|
2,350 kg (5,181 lb)[source]Only the source-declared variant PC-9M
3,200 kg (7,055 lb) A view of the interior of the cockpit of a Pilatus PC-9 aircraft.[source]Only the source-declared variant PC-9M