Credit
US Air Force · Public domain · Resized · Public domain · Source ↗ · Modified
FORCETALLY
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At a glance
Measured figures
T-41C · Length
Single source26 ft 11 in (8.20 m)[source]
G 120A · Length
Single sourceConfiguration
| Specification | Cessna T-41 Mescalero | Grob G 120 |
|---|---|---|
| Crew | one[source] | Two[source] |
| Type | Primary pilot trainer[source] | Trainer[source] |
| National origin | United States[source] | Germany[source] |
| Manufacturer | Cessna[source] | Grob Aircraft |
8.605 m (28 ft 3 in)[source]
Maximum; T-41C · Maximum speed
Single source125 kn (144 mph, 232 km/h)[source]
T-41C · 1 × Continental IO-360-D Six-cylinder air-cooled horizontally-opposed piston engine
Single source1 × Continental IO-360-D Six-cylinder air-cooled horizontally-opposed piston engine, 210 hp (160 kW)[source]
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.
| Status | In service[source] | Active in production[source] |
|---|
| Primary users | United States Air Force United States Army Indonesian Air Force Turkish Air Force[source] | French Air and Space Force Israeli Air Force Royal Canadian Air Force German Air Force[source] |
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| Number built | T-41A : 230 T-41B : 255 T-41C : 52 T-41D : 299[source] | — |
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| Manufactured | 1964–1996[source] | 1999-present[source] |
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| Introduction date | 1964[source] | — |
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| Developed from | Cessna 172 Cessna R172[source] | Grob G 115[source] |
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| Capacity | three passengers[source] | — |
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| Propellers | 2-bladed variable-pitch propeller[source] | 3-bladed Hartzell HC-C3YR-1RF/F7663R, 1.98 m (6 ft 6 in) diameter[source] |
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| Alternative designation | T-41 Mescalero[source] | — |
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| First flight | — | 1999[source] |
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| Variant | — | Grob G 120TP[source] |
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| Airfoil | — | Eppler E884[source] |
|---|
| Fuel capacity | — | 256 litres (56 imp gal; 68 US gal)[source] |
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| Stall speed | — | 102 km/h (63 mph, 55 kn) with full flaps[source] |
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| Never exceed speed | — | 435 km/h (270 mph, 235 kn)[source] |
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| g limits | — | +6/-4G[source] |
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| 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 |
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| Country of origin | — | Germany[source]Inventory Origin column; table 1, row 17, cell 4; revision 1377212027; retrieved 2026-10-02 |
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Maximum take-off; G 120A · Utility
Single source