Grob G 120

Grob G120A-F F-GUKM

The Grob G 120A is a two seated training and aerobatic low-wing aircraft with a carbon composite airframe, built by Grob Aircraft. It is based on the Grob G 115TA training aircraft and is specially designed for military and civil pilots training. It has a tricycle landing gear and a cross empennage.

Developing nation: Germany.
Grob Aircraft AG.
Production line: Tussenhausen, Germany.
Type aircraft:  training and aerobatic.
First flight: 1999.
First delivery: Lufthansa Flight Training the launch customer, which operates six aircraft on behalf of the German Air Force in Phoenix, Arizona (USA).
Produced: 1999 – .

The G 120A is certified by both the EASA and the FAA to +6/-4 g. It  providesthe ideal training platform for the full range of conventional  high-performance aerobatic maneuvers, including spins, inverted spins,  loops, rolls, stall turns, outside turns and recovery from unusual  attitudes.
This versatile aircraft also offers excellent handling at  both high and low airspeeds, making it ideal to tackle the full spectrum of primary training requirements, including pilot screening, instrument flying, navigation and missionoriented tasks.

The ample power of its well-proven and reliable 260 HP Lycoming engine fitted with a 3-bladed constant-speed propeller, combined with a super lightweight composite airframe, provides the ideal power-to-weight ratio for primary pilot training and translates into superb flight characteristics in any situation.
The aircraft is equipped with robust, retractable landing gear, specifically designed for the high number of cycles and hard landings typical of a training environment.

Martin Baker MK.15B – Ultra Lightweight Escape System for the G 120TP has been developed to provide a very lightweight and compact escape system for lightweight aircraft with limited space within the cockpit.


Canadian Air Force, Kelowna – 11 G 120A-C
French Air Force, Cognac – 18 G 120A-F
German Air Force, Phoenix, USA – 6 G 120A
Israel Air Force, Haifa – 17 G 120A-I

General characteristics

  • Crew: Two
  • Length: 8.11 m (26 ft 7 in)
  • Wingspan: 10.18 m (33 ft 5 in)
  • Height: 2.66 m (8 ft 9 in)
  • Wing area: 13.3 m² (143.1 ft²)
  • Empty weight: 1100kg (2425lb)
  • Useful load: 360 kg (792 lb)
  • Max takeoff weight: 1440 kg (3,175 lb)
  • Powerplant: 1 × Lycoming AEIO-540-D4D5 6-cylinder, horizontally opposed engine, 194 kW (260 hp)
  • Propeller: 3-blade constant speed
  • Max. landing weight: 1440kg (3,168 lb)
  • Usable fuel: 252 ltr / 66.6 US Gal
  • Aspect ratio: 7.82


  • Maximum speed: 320 km/h (172 knots, 197 mph)
  • Cruise speed: 307 km/h (166 knots, 189 mph)
  • Stall speed: 102 km/h (55 knots, 63 mph)
  • Range: 1535 km (830 nm, 947 mi)
  • Rate of climb: 6.51 m/s (1,280 ft/min)
  • Take-off distance to 15m/50ft: 654 m (2,150 ft)
  • Landing distance to 15m/50ft: 562 m (1,845 ft)
  • Max. load factors: +6g / -4g
  • Min structural service life (aerobatic): 15,000 flight hours

All pictures courtesy of Zijde Aviation Photo and Publishing, Rob Vogelaar