Main Menu

Lambert Aircraft Engineering Mission M106

mission106


The Mission M106 is a single engine aircraft conventional configuration certified in ULM category in Belgium and France. It has an unswept untapered high wing. The fuselage provides comfortable side-by-side seating. Two upwards hinging doors provide access to the cabin. The large transparent areas of the cabin provide excellent visibility in level flight as well as in turns. Both the seats and rudder pedals are adjustable. Elevator and aileron control is by sticks. The aircraft is standard equipped with full dual controls.
The Mission M106 is available as a factory built Microlight (ULM/UL) category aircraft with tailwheel or nosewheel. It is standard fitted with a UL260i engine and glass cockpit. 2009 Price: 36900 EURO
The fuselage is a welded space frame, which is fabric covered. High strength steel tubing is used throughout. The wings are of aluminium construction and also fabric covered.
Control surfaces are conventional with single slotted flaps, pushrod operated elevator and cable operated rudder and ailerons. The main landing gear consists of composite cantilever leaf springs. The Mission M106 is available as either a tailwheel or a nosewheel version.
The front mounted ULPower UL260i engine produces 82 HP at 2800 rpm and drives a three blade ground adjustable propeller. The four stroke four cylinder engine is air cooled and features FADEC (Full Authority Digital Engine Control).

mission106td


A 'glass cockpit' is standard in the Mission M106. All flight instruments are integrated in the EFIS. Engine instruments are displayed on the EMS. We offer a choice of two instrument panel layouts with displays of different sizes. Optionally, these avionics can be complemented with navigation and communication equipment, such as a GPS with moving map, VHF radio and ATC transponder.

Engine: UL260I, 60 kW (82 hp) at 2800 rpm     
Wing span: 9.32 m (30 ft 6 in)
Wing area: 11.8 sq.m (127 sq.ft)
Aspect ratio: 7.4     
Length: 6.10 m (20 ft)
Height TD: 2.15 m (7 ft 1 in)
Height NW: 1.95 m (6 ft 6 in)
Width wings folded: 2.60 m (8 ft 7 in)
Empty weight: 260 kg / 573 lb approx.     
Max. all up weight: 450 kg / 472.5 kg
Fuel capacity: 78 litres
Baggage capacity: 40 kg (90 lbs)
Max. level speed at S/L: 100 kt (185 km/h)
Never exceed speed: 112 kt (210 km/h )
Cruise speed: 80-85 kt (150-160 km/h)     
Fuel consumption: 11-14 litres/h     
Range (20 min res.): 380 nm (700 km)     
Stall speed, full flaps: 35 kts (65 km/h / 40 mph)     
Max. crosswind TD: 12 kt
Max. crosswind NW: 16 kt
Max. S/L rate of climb: 1000 ft/min (5 m/s)     
Glide Ratio: 9
T-O ground roll: 80-110 m     
Take-off distance (50ft obstacle): 920 ft / 280 m
Landing distance (50ft obstacle): 980 ft / 300 m
Cabin width: 1.08 m (43 in)
Tailplane span: 2.40 m (8 ft 0in)
Wheeltrack: 1.75 m (5 ft 10 in)
Limit load factors: +4.0/-2.0

 

 

 


Copyright © 2017 all-aero. All Rights Reserved.
Joomla! is Free Software released under the GNU General Public License.