Credit
Alan Wilson · CC BY-SA 2.0 · Resized · CC BY-SA 2.0 · Source ↗ · Modified
FORCETALLY
Loading the evidence…
Preparing your view.
Preparing your view.
At a glance
Measured figures
G 115E · Length
Single source7.79 m (25 ft 7 in)[source]
TB 21 TRINIDAD TC · Length
Single sourceConfiguration
| Specification | Grob G 115 | SOCATA TB family |
|---|---|---|
| Type | Basic trainer[source] | Light single-engine piston aircraft[source] |
| Manufacturer | Grob Aircraft[source] | Socata[source] |
| Status | active[source] | Out of production, in active service[source] |
| Primary users | Royal Air Force Egyptian Air Force Finnish Air Force Royal Navy Army Air Corps (UK)[source] | — |
7.75 m (25 ft 5 in)[source]
Empty; G 115E · Empty weight
Single sourceMaximum take-off; G 115E · Max takeoff weight
Single source670 kg (1,477 lb)[source]
990 kg (2,183 lb)[source]
Empty; TB 21 TRINIDAD TC · EFIS and MTV 9 propeller
Single sourceMaximum take-off; TB 21 TRINIDAD TC · Max takeoff weight
Single sourceCruise; 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; TB 21 TRINIDAD TC · Cruise speed
Single source280 km/h (170 mph, 150 kn)[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]
TB 21 TRINIDAD TC · 1 × LYCOMING TIO-540-AB1AD Six-cylinder, horizontally opposed, direct drive, air-cooled and fitted with an automatically regulated turbocharger
Single source1 × LYCOMING TIO-540-AB1AD Six-cylinder, horizontally opposed, direct drive, air-cooled and fitted with an automatically regulated turbocharger, 190 kW (250 hp)[source]
G 115E · Wing area
Single source12.21 m 2 (131.4 sq ft)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Manufactured | 1985–present[source] | 1975–2012[source] |
|---|
| Introduction date | 1999[source] | 1975[source] |
|---|
| First flight | November 1985[source] | — |
|---|
| Fuel capacity | 143 L (31 imp gal; 38 US gal) usable[source] | 336 Liters (88.8 U.S. Gallons)[source] |
|---|
| Aspect ratio | 8.2:1[source] | — |
|---|
| Airfoil | Eppler 696[source] | RA 16 3C3[source] |
|---|
| Propellers | 3-bladed Hoffmann HO-V343K-V/183GY Constant-speed propeller , 1.83 m (6 ft 0 in) diameter[source] | 2-bladed Hartzell (option for 3 bladed MT-propeller)[source] |
|---|
| Stall speed | 91 km/h (57 mph, 49 kn) (60 degree flap)[source] | 109 km/h (68 mph, 59 kn) Full flaps[source] |
|---|
| Never exceed speed | 341 km/h (212 mph, 184 kn)[source] | 350 km/h (217 mph, 189 kn)[source] |
|---|
| g limits | + 6.0/ - 3.0[source] | — |
|---|
| Country of origin | Deutschland[source]Country of design · Entwurfsland | France[source]Inventory Origin column; table 2, row 8, cell 3; revision 1348750748; retrieved 2026-10-01 |
|---|
| Number built | — | 2,150 (2007)[source] |
|---|
| Capacity | — | 4 passengers[source] |
|---|