Credit
e2a2j · Public domain · Resized · Public domain · Source ↗ · Modified
FORCETALLY
Loading the evidence…
Preparing your view.
Preparing your view.
At a glance
Measured figures
T-34C · Length
Single source28 ft 8 + 1 ⁄ 2 in (8.750 m)[source]Only the source-declared variant T-34C Turbo-Mentor
Configuration
| Specification | T-34C Turbo-Mentor | Grob G 120 |
|---|---|---|
| Variant description | T-34C Turbo-Mentor[source]Only the source-declared variant T-34C Turbo-Mentor Two-seat primary trainer, fitted with a turboprop engine.[source]Only the source-declared variant T-34C Turbo-Mentor | — |
| Fuel capacity | 130 US gal (110 imp gal; 490 L)[source]Only the source-declared variant T-34C Turbo-Mentor | 256 litres (56 imp gal; 68 US gal)[source] |
| Propellers | 3-bladed Hartzell constant-speed[source]Only the source-declared variant T-34C Turbo-Mentor | 3-bladed Hartzell HC-C3YR-1RF/F7663R, 1.98 m (6 ft 6 in) diameter[source] |
G 120A · Length
8.605 m (28 ft 3 in)[source]
Empty; T-34C · Empty weight
Single sourceMaximum take-off; T-34C · Max takeoff weight
Single source2,960 lb (1,343 kg)[source]Only the source-declared variant T-34C Turbo-Mentor
4,300 lb (1,950 kg) (T-34C-1 weapons trainer 5,500 lb (2,500 kg))[source]Only the source-declared variant T-34C Turbo-Mentor
Empty; G 120A · Empty weight
Single sourceGross; G 120A · Gross weight
Single sourceCruise; T-34C · at 17,000 ft (5,200 m) (max cruise)
Single source214 kn (246 mph, 396 km/h) at 17,000 ft (5,200 m) (max cruise)[source]Only the source-declared variant T-34C Turbo-Mentor
T-34C · at 180 kn (210 mph; 330 km/h) and 20,000 ft (6,100 m)
Single source708 nmi (815 mi, 1,311 km) at 180 kn (210 mph; 330 km/h) and 20,000 ft (6,100 m)[source]Only the source-declared variant T-34C Turbo-Mentor
G 120A · at 8,000 ft (2,400 m) and 45% power
Single source1,540 km (960 mi, 830 nmi) at 8,000 ft (2,400 m) and 45% power)[source]
T-34C · 1 × Pratt & Whitney Canada PT6 A-25 turboprop , 550 shp (
Single source1 × Pratt & Whitney Canada PT6 A-25 turboprop , 550 shp (410 kW)[source]Only the source-declared variant T-34C Turbo-Mentor
G 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]
G 120A · at 10,000 ft and maximum endurance power setting
Single source6.35 hours at 10,000 ft and maximum endurance power setting[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Stall speed | 53 kn (61 mph, 98 km/h) (flaps down, power off)[source]Only the source-declared variant T-34C Turbo-Mentor | 102 km/h (63 mph, 55 kn) with full flaps[source] |
|---|
| Never exceed speed | 280 kn (320 mph, 520 km/h)[source]Only the source-declared variant T-34C Turbo-Mentor | 435 km/h (270 mph, 235 kn)[source] |
|---|
| g limits | +6, -3[source]Only the source-declared variant T-34C Turbo-Mentor | +6/-4G[source] |
|---|
| Hardpoints | 4 with a capacity of 600 lb (272 kg) inner, 300 lb (136 kg) outer, 1,200 lb (544 kg) total[source]Only the source-declared variant T-34C Turbo-Mentor | — |
|---|
| Manufacturer | Beechcraft[source]Manufacturer of the explicitly named T-34C Turbo-Mentor only. Beechcraft[source]T-34C Turbo-Mentor | Grob Aircraft[source] |
|---|
| Country of origin | USA[source]T-34C Turbo-Mentor | Germany[source]Inventory Origin column; table 1, row 17, cell 4; revision 1377212027; retrieved 2026-10-02 |
|---|
| Type | — | Trainer[source] |
|---|
| National origin | — | Germany[source] |
|---|
| Status | — | Active in production[source] |
|---|
| Primary users | — | French Air and Space Force Israeli Air Force Royal Canadian Air Force German Air Force[source] |
|---|
| Manufactured | — | 1999-present[source] |
|---|
| First flight | — | 1999[source] |
|---|
| Developed from | — | Grob G 115[source] |
|---|
| Variant | — | Grob G 120TP[source] |
|---|
| Airfoil | — | Eppler E884[source] |
|---|
| 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 |
|---|
Maximum take-off; G 120A · Utility
Single source