View source for Lamco Eurocub

{|{{Infobox Aircraft Begin
 |name=Lamco Eurocub
 |image=Image: Eurocub.jpg
 |caption=<!--image caption; if it isn't descriptive it should be left blank-->
}}{{Infobox Aircraft Type
 |type=Fixed wing ultralight aircraft
 |manufacturer=Danex Engineering Kft
 |unit cost= approx [[Euro|€]]42,000&ndash;53,000
}}
|}

The '''Lamco Eurocub''' is an ultralight aircraft with fixed gear (taildragger), general aviation airplane, manufactured in Hungary by Danex Engineering Kft. It is used primarily for flight training, touring, and personal flying. 

==General Description==
The Lamco Eurocub is a single-engined high-wing monoplane with the two seats placed side-by-side. The Eurocub is manufactured with either an 80 hp (60 kW) Rotax 912 UL engine or a 100 hp (75 kW) Rotax 912 ULS engine. The Rotax engine has a low fuel consumption and relatively low noise. The engine drives the propeller, which has ground-adjustable pitch, through a gearbox with a 2.43:1 reduction ratio.

==Specifications==
These specifications relate to the Lamco Eurocub Mk IV fitted with a Rotax 912 UL engine (80 hp)<ref name=Ref1>Pilot's operating handbook, http://www.barkarbyflygklubb.se/Flyghandbok%20Eurocub%202002-01-09.pdf (Swedish)</ref>.

===Dimensions===
Span 9.55 m 
Wing area 14.00 m2 
Length 5,70 m 
Height ground attitude 2,11 m 
Height flight attitude 2.17 m 

===Engine Plant===
====Engine====
Manufacturers Bombardier Rotax GmbH, Austria 
Engine type: Rotax 912 UL 
Maximum 80 hp @ 5800 RPM
Gearbox with a 2.43:1 reduction ratio

Liquid- and air-cooled 4-cylinder four-stroke engine. 
2 pcs flottörförgasare fitted with the choke knob. 
Ignition: Dual Ignition system with CDI ignition. 
Starting system: Electric Starter Motor. 

Labeling of engine instruments 
Green arc (normal area) 1400-5500 RPM 
Yellow arc (non-continuous power) 5500-5800 RPM 
Red line (max power) 5800 RPM

====Propeller====
Manufacturer: Warp Drive Inc., USA. 
Type Ivo Prop 3-blade carbon fiber laminate with duralnav adjustable on the ground. 
Default 12.5 degrees. at the propeller tip. Disk 68 ". 

====Fuel==== 
Type: Non-alcoholic petrol RON 95 PREMIUM max 100LL. 
Wing Tank 82 liters. A fuel tank of 41 liters is mounted in each wing. 
Wing Tank utnyttjningsbart 78 liters. 

===Electrical=== 
Rotax 912 UL engine is equipped with a generator on the motor shaft, from 13.5 to 14.2 V / 250 W. 

===Trunk===
Volume 20 liters. 
Max load 18 kg. 



===Speed restrictions===
Where a single speed appears, it is applicable to the aircraft at maximum gross weight of {{convert|1040|lb|kg}}. Where a range appears, the lower speed is applicable at empty weight of {{convert|572|lb|kg|}}, while the higher speed is applicable at maximum gross weight.
* '''V<sub>NE</sub> (never exceed):''' 110 Knots
* '''V<sub>NO</sub> (max cruise):''' 95 Knots
* '''V<sub>A</sub> (maneuvering):''' 68 Knots

* '''V<sub>S0</sub> (stall, dirty):''' 33 Knots
* '''V<sub>Y</sub> (best rate of climb):''' 62 Knots


{{aircraft specifications
<!-- if you do not understand how to use this template, please ask at [[Wikipedia talk:WikiProject Aircraft]] -->

<!-- please answer the following questions -->
|plane or copter?=plane
|jet or prop?=prop

<!-- Now, fill out the specs.  Please include units where appropriate (main comes first, alt in parentheses). If an item doesn't apply, like capacity, leave it blank. For additional lines, end your alt units with a right parenthesis ")" and start a new, fully-formatted line beginning with an asterisk "*" -->
|crew=1
|capacity=1 passenger 
|length main=20 ft 6 in
|length alt=6.25 m
|span main=31 ft 0 in
|span alt=9.45 m
|height main=7 ft 4 in
|height alt=2.24 m
|area main=134.5 ft²
|area alt=12.5 m²
|empty weight main=583 lb
|empty weight alt=265 kg
|loaded weight main=<!-- lb-->
|max takeoff weight main= (depends on country) approx 1,041 lb
|max takeoff weight alt= 473 kg

* '''[[Wing loading]]:''' 37.8 kg/m²

|engine (prop)= [[Rotax 912]] UL
|type of prop=[[flat-4|flat-4 engine]]
|number of props=1 
|power main=80 hp
|power alt=
|power more=three-blade, ground adjusted, [[carbon fibre]], fixed-pitch propeller

|max speed main=
|max speed alt=
|stall speed main=
|stall speed alt=
|stall speed more=
|range main=432 miles
|range alt=375 nm, 695 km
|range more=<br/>
* '''Extended range''' 898 miles (780 nm, 1,445 km) with long-range tanks
|ceiling main=
|ceiling alt=
* '''Takeoff roll:''' 262 ft (80 m)
|climb rate main=1050 ft/min
|climb rate alt=320 m/min
|max loading main=
|max loading alt=
|max power/mass main=
|max power/mass alt=
}}

==See also==
{{aircontent
<!-- include as many lines are appropriate. additional lines/entries with carriage return. -->

|related=<!-- related developments -->

|similar aircraft=<!-- similar or comparable aircraft -->
*[[3Xtrim 3X55 Trener]] – [[Flight Design CTSW]]

|sequence=<!-- designation sequence, if appropriate -->


|lists=<!-- related lists -->

|see also=<!-- other relevant information -->
}}

==References==

<references />

==External links==
{{commonscat-inline|Lamco Eurocub}}
* []
* []
* []


{{aviation lists}}

[[Category:High wing aircraft]]
[[Category:Propeller aircraft]]
[[Category:Single engine aircraft]]
[[Category:Ultralight aircraft]]