Mylius My-103 Mistral
# Mylius My-103 Mistral

The Mylius My-103 Mistral is a German two-seat aerobatic trainer of utility aircraft produced by Mylius Flugzeugwerk of Bitburg.

## Design and development

The My-103 is a two-seat development of the My-102 Tornado which was itself a development of the MHK-101. The MHK-101 was an early 1970s proof of concept prototype which led to the MBB Bo 209 Monsun, it had been designed by Hermann Mylius the father of Albert Mylius who had founded Mylius Flugzeugwerk in 1996. The first flight of the My-103/200 basic trainer prototype D-ETMY was on 23 May 1998 which was followed by the first pre-production aircraft in July 2001.

The My-103 is an all-metal low-wing monoplane with a fixed tricycle landing gear, the prototype basic trainer had a 200 hp (149 kW) Lycoming AEIO-360 flat-four engine. It has two-seats side-by-side with dual controls and a rear-sliding bubble canopy and a fixed windscreen. A four-seat variant the My-104 was proposed but no further aircraft have been built.

## Colombian production

Aero Integration & Manufacturing S.A.S. (AIMING) and INDAER announced in July 2013 that the My-103 is in the process of resuming production. Therefore, the Mylius-103, will be manufactured in Medellin, Colombia near José María Córdova Airport by AIMING and INDAER with new avionics and Colombian engineering and personnel with the support from aircraft designer, Albert Mylius, in Germany. The aircraft is in the process of being certified by the Colombian authorities to be able to offer the My-103 in the market. La nueva apuesta de la industria aérea colombiana: Mylius MY-103

## Variants

### My-102

    Single-seat aerobatic trainer or tourer, two built.

### My-103/180

    Two-seat basic variant with a 180 hp (134 kW) Lycoming IO-360 engine, not built.

### My-103/200

    Two-seat basic trainer with a 200 hp (149 kW) Lycoming AEIO-360 engine, four built.

### My-104

    Four-seat variant with a 200 hp (149 kW) Lycoming IO-360 engine, not built.

## Specifications (My-103/200)

Data from Jane's All the World's Aircraft 2003-2004.

General characteristics

* Crew: 2
* Length: 6.50 m (21 ft 4 in)
* Wingspan: 8.65 m (28 ft 5 in)
* Height: 2.34 m (7 ft 8 in)
* Wing area: 10.45 $m^2$ (112.5 sq ft)
* Empty weight: 620 kg (1,367 lb)
* Max takeoff weight: 950 kg (2,094 lb)
* Powerplant: 1 × Lycoming AEIO-360 flat-four, 150 kW (200 hp)
* Propellers: 3-bladed MTV constant speed

Performance

* Maximum speed: 278 km/h (173 mph, 150 kn) max cruise speed at 2440m
* Cruise speed: 259 km/h (161 mph, 140 kn) economical cruise at 3660m
* Stall speed: 95 km/h (59 mph, 51 kn) power off, flaps down
* Never exceed speed: 333 km/h (207 mph, 180 kn)
* Range: 1,574 km (978 mi, 850 nmi)
* Service ceiling: 6,100 m (20,000 ft)
* g limits: +6/-4.5
* Rate of climb: 6.0 m/s (1,180 ft/min)
