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L-6.

The L-6 amphibian aircraft is a cantilever monoplane with a seagull-like high wing, a tail plane mounted in the propeller blow-off area and a tricycle-equipped landing gear with a nose-wheel.
The embarkation and disembarkation of the pilot and passengers afloat is done along the tail boom between the fins through an upwards opening access hatch, which allows getting on board without ladders and pontoons.
The airplane may have a Russian RPD-416 rotor-piston engine, a Chech М337С piston engine or a Canadian SXE turbo-prop.
The instrumentation of the L-6 amphibian aircraft of all modifications allows daylight flying according to visual flight rules.
Any custom equipment may also be installed on the airplane.
The airplane’s tricycle-equipped retractable landing gear with a nose-wheel allows to operate the plane on unpaved runways. The dimension of the castor nose-wheel is 400x150, the dimension of the main landing gear is 500x150. The gear has a hydro-pneumatic shock absorption system. Gear extension, retraction and braking is provided by the airplane’s pneumatic system. The braking system has the differential braking ability.
The fuel is carried in two fuel tanks located in the port and starboard wings. Fueling is done through fillers with a standard flow area of each tank.
The control of the plane and engine is duplicated.
The heating and ventilation system maintains the necessary air temperature in the cockpit and keeps the pilot’s glass panes from misting up.
The aircraft’s detachable wing assemblies are easy to remove, allowing to quickly prepare the plane for or to assemble it after transportation.
The airplane has no special pilot technique features, is easy to control, reliable and safe. Retraining of flying personnel as well as training of beginner private pilots requires minimum time and is carried out by the personnel of the manufacturer according to the training program for L-4 and L-6 pilots.
| Performance: |
L-6 with the
RPD-416 engine |
L-6 with the
М337С engine |
L-6 with the
SXE engine |
| Maximum
takeoff weight, kg |
2000 |
2000 |
2000 |
| Empty weight, kg |
1250 |
1250 |
1250 |
| Engine type |
RPD-416 rotor-piston engine |
Lom Praga М337С |
SXE turboprop</td>
|
| Engine unit power, hp |
2 х 165 |
2 х 250 |
2 х 280 |
| Applied fuel |
Motor petrol Ai-92 |
Motor petrol Ai-95 |
Aviation kerosine,
diesel fuel |
| Propeller type |
Controllable-pitch propeller Ivoprop «Magnum» |
Controllable-pitch propeller V-546 |
Controllable-pitch propeller V-546 |
| Speed at liftoff, km/h |
80-95 |
80-95 |
80-95 |
| Cruising speed, km/h |
180 |
230 |
280 |
| Maximum speed, km/h |
220 |
280 |
320 |
| Cervice ceiling, m |
4000 |
4000 |
4000 |
| Flight range, km |
1200 |
1200 |
1500 |
| Takeoff run with maximum takeoff weight, m |
350 |
250 |
220 |
| Landing run, water/land, m |
200/150 |
200/150 |
200/150 |
| Crew, men |
1 |
1 |
1 |
| Number of passenger seats |
5 |
5 |
5 |
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