Coarse G 115

Coarse G 115
Type:	Trainer aircraft
Design country:	Germany
Manufacturer:	Gross Aircraft
First flight:	1985
Commissioning:	1988
Production time:	1985 until today
Number of pieces:	~ 360

The Grob G 115 is a two-seat training aircraft produced by Grob Aircraft AG from Mindelheim in Swabia .

history

The Grob G 115 was created in the 1980s and is designed for pilot selection training, beginner and advanced training, and aerobatic training and training. The prototype was the predecessor G 110 (first flight February 6, 1982) and G 112 (first flight 1984) , which were only built in small numbers . The G 110 was also a GRP low- wing aircraft with a fixed nose wheel chassis and a Lycoming O-235-M1 boxer engine with 87 kW. On July 24, 1982, the machine crashed during the spin tests , whereupon the second prototype was not completed and the G 112 was designed with folding wings , reduced wingspan and modified vertical stabilizer. The first machine received a Grob 2500E engine and the second a Lycoming O-235-P1 boxer engine with 87 kW. However, this was also only a forerunner to the prototype of the successful G 115, which, unlike the G 112, did not have folding wings and a sliding hood instead of the cabin doors.

The first flight of the G 115 took place on 15 November 1985. The aircraft received in March 1987 his approval and was in late 1988 by FAR certified Part 23rd Around 360 copies (81 G 115, 19 G 115A, 3 G 115B) had been produced by March 2006.

Compared to the prototype, the first series version had a lower horizontal stabilizer and faired wheels, but was underpowered with the Lycoming O-235-H2C boxer engine with 85 kW and a two-bladed propeller. The G 115A delivered from 1989 received a controllable pitch propeller , the G 115B delivered from 1988 the more powerful Lycoming O-320-D2A with 111 kW. At this time, the four-seater development G 116 with a Lycoming IO 360 engine with 147 kW was presented, which had its maiden flight on April 29, 1988. However, it stayed with this prototype due to lack of demand. Production of the G 115 ceased in 1990 and was only resumed in 1993 with the G 115C, which was improved in many details. For example, it was powered by the Lycoming IO-320 boxer engine with 119 kW and, instead of the 100-liter fuselage tanks, two flat tanks with a capacity of 75 liters each, creating a luggage compartment in the fuselage.

G 115 E in flight

The G 115 D / E / EC with a Lycoming - twin engine -B1F AEIO-360 / B equipped with 134 kW, of the aerobatics use was modified in order to ensure lubrication and fuel supply in all flight modes. A 3-blade controllable pitch propeller is used for power transmission.

At the end of the 1980s, Grob participated with the G 115T in a tender for a light training aircraft for pilot selection for the US Air Force . This machine flew for the first time in June 1992 and was equipped with a retractable landing gear and a Lycoming AEIO-540 six-cylinder injection engine with 191 kW and a four-blade controllable pitch propeller. Since Grob did not win the tender, the project was suspended and was continued in 2000 as the G 120A .

All G 115 are made entirely of fiber composite materials of high surface quality and therefore have a particularly high aerodynamic quality. Thanks to the maximum permitted load factor of + 6 / −3g, it is fully suitable for aerobatics .

After Grob went bankrupt in 2008, production was initially suspended, but was resumed in 2009 after Grob was taken over by H3-Aerospace .

Versions

• G 115 , G 115A : Original version built until 1990 with Textron Lycoming O-235-H2C (85 kW), two-bladed propeller and 590 kg empty weight
• G 115B : more powerful Lycoming O-320 engine , 670 kg empty weight
• G 115C : slightly modified cell, flat tanks with higher fuel supply
• G 115D : aerobatic version, Lycoming AEIO-360 , three-bladed controllable pitch propeller
• G 115E / EG : military version for the Royal Navy and Royal Air Force

Technical specifications

Parameter	Data (G 115 E)
span	10.0 m
Wing area	12.2 m²
length	7.54 m
height	2.4 m
Max. Takeoff mass	990 kg
Minimum speed	96 km / h CAS
Cruising speed at 75%	230 km / h TAS
Max. Range at 45%	1150 km
drive	Lycoming AEIO-360-B1F / B with 180 PS (132 kW)
Tank capacity	143 l
Take-off distance over 15 m obstacle	461 m
Landing distance over 15 m obstacle	457 m

See also

• List of aircraft types

Web links

Commons : Grob G 115  - Collection of images, videos and audio files

• Type certification of GROB G 115 - EASA-TCDS-A.364 (PDF; 102 kB)
• G 115 story on Airliners Net

Individual evidence

1. ↑ H3 Aerospace takes over the Grob trainer program. February 9, 2009; archived from the original on December 24, 2010 ; Retrieved November 26, 2017 . 
2. ↑ G 115E / EG. (PDF) High-performance training and aerobatics. Grob Aerospace AG, 2009, archived from the original on February 5, 2009 ; accessed on November 26, 2017 (English, brochure with dates).