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Overview of aircraft



Amphibian aircraft LA-8 is designed and made from modern high-strength material in accordance with the FAR-23/21 (AP-23/21). The avionics and equipment, parts and components available in any country of the world are used in airframe and in aircraft systems. The hoses, fittings, pipeline accessories and flexible hoses manufactured in accordance with AN and MS international standards are used in fuel, oil, hydraulic and brake systems.
The aircraft can be delivered to Customer either with single or with dual control. Total number of seats – 8 with two pilots included.
Basic model of the aircraft is designed for VFR operations day/night. Empty weight for basic model of the aircraft LA-8C (with oil, technical fluid and the standard set of equipment) is 1 685 kg (1 650 kg for RS-version), maximum take-off weight is 2 720 kg for all versions.

The hydroplane is designed to operate in all latitude and climatic zones, in fresh and salt water. The aircraft’s landing gear allows operating from paved and unpaved runways, including ground, asphalt, and snow-covered runways. Seagoing ability allows operating with wave height up to 0,6 m. Minimum length of runway is 400 m. Runway absolute altitude up to 1 500 m  for piston version and 2 500 m for turboprop version.

The aircraft amphibian can be equipped with avionics and other system for instrument flight rules (IFR) operations. The 3-axis autopilot system with auto-trim and yaw dumper function is available too.

The aircraft has improved heating system by the hot air from heaters of exhaust system, and ventilation of flight deck and passenger cabin.
Maximum range of the aircraft in RS-version is 4 000 km. Range of the aircraft in C-version with payload of 630 kg with additional tanks in wingtips is 1 400 km.

Maximum useful load is
In standard version “C” – 1 035 kg
In RS-version – 1 070 kg
Cargo can be allocated in the nose luggage compartment and in the passenger cabin.

In piston version of the aircraft the maximum cruise speed is 270 km/h (145 knots) on altitude of 2 000 m (TAS). The cruise speed with full payload and full fuelling is 220 km/h (120 knots) on the altitude of 2 000 m (TAS) with engine at 65 %. The maximum duration of flight providing speed 180 km/h (100 knots) is up to 20 hours for RS-version. The estimated maximum cruise speed is 300 km/h (TAS) on the altitude of 4 000 m for turboprop version.
The ceiling is 4 500 m for piston version of the aircraft and 6 000 m for turboprop version of the aircraft.

The basic version of the power plant (C-version) is two piston engines LOM PRAHA M337C-AV with take off power 235 HP. The engines are equipped with supercharge and timing fuel injection system. Time between scheduled maintenance of engines is 100 hours, motor oil replacing time is 200 hours.
The piston engines Lycoming O-540 or TIO-540. (235-310 HP) or turboprop engines TP-100 (250 HP) or АI-450 (300 HP).

Operational cost of the aircraft with piston engine according to the standard method of calculation is USD450 per hour (for USA market).

Depending on the objects, operational conditions and Customer’s requirements SPU “AeroVolga” ltd will provide the Customer a wide choice of aircraft modification. You can familiarize with available configuration of the aircraft below (The detailed configuration of the aircraft should be specified when ordering).



The design of the aircraft
Two-engine composite high wing, with T-shaped stabilizer. The wing can be equipped f with winglets reducing the resistance of the wing at cruising.

The airframe is painted by high-quality American paints in white color with ability to make additional tints. Such paint provides practically unlimited life time of composite construction, protecting it from harmful solar radiation. Almost anywhere it is possible to apply decorative stripes and emblems, logos and labels in the fuselage. The layer of transparent polyurethane varnish is applied over paint and provides additional protection for the paint.
The main fuel tanks with a capacity of 455 liters (for RS-version – 1 400 liters) are located in the wing of the aircraft. For C-version and L-version it is possible to install the additional fuel tanks in winglets, with total capacity 100 liters.

There are special units for aircraft mooring on land and in water. Two mooring rings are located on the lower surface of the wing, one – in the nose part, one – on the aft. Two cleats are located near the hatch. The cleats can be either fixed or retractable into frame.

There are four knots on the top of the aircraft, for which the aircraft can be lifted by crane onto the deck of the ship and the dock with using a standard four-point brace. For that purpose the aircraft can be equipped with lifting eye bolts and two sling-adapters.

Ground power unit (GPU) is plugged to the standard onboard socket and allows starting the engines and charging on-board batteries.

The landing/taxi LED lights cluster is installed in the left wing. The quad xenon land light is installed in the right wing. The navigation lights (left and right) are located in the winglets, in the tail part of the fuselage the tail light and anti-collision light are installed, on the fin tip is located the parking light switched on in the water.

Landing gear is tricycle type, with the nose strut.  Wheel suspension is wishbone, with gas-fluid absorbers. For manufacture of landing gear it is used special high-quality stainless steel and special coverings with high resistance to seawater. The specially designed landing gear allows to land on unpaved ground. The landing gear retraction/extension is performed by hydraulic drive; emergency main struts extension is performed under its own weight, the nose strut extension is performed by backup pneumosystem.

The emergency extension of all struts is performed under their own weight in RS-version. The working of hydraulic system and emergency pneumosystem is controlled by two pressure gauges mounted on the pilot’s instrument panel.

Indication of the landing gear position is designed specifically for amphibian aircraft, when landing on the water surface is performed with retracted landing gear. So the position of retracted landing gear is displayed as bright-blue color (the color of the sea and sky), extended – as yellow color (the color of the earth). The additional visual control of position of the landing gear can be made by using panoramic mirrors located on the floats.

For controlling the aircraft when moving on water the different engine thrust or reverse thrust is used, for controlling the aircraft movement on land – separate braking wheels. The brakes are hydraulic, on control pedals. Both main wheels can be stopped by parking brake.

Control of the aircraft is possible from the right or left pilot’s seats which are equipped with control columns and pedals. For locking the elevators and ailerons when standing the safety pin with bright red marker is inserted into the control column support.

Autopilot is controlled from the central instrument panel and the button of autopilot emergency cutoff is on the control wheel. Control of engines, propellers and trimmers are located on the centre console between pilots.

Engine control levers allow operate as straight thrust as reverse thrust. In order to prevent the propellers transition to reverse mode during flight engine, control console is equipped with computer controlled reverse lever lock disabling reverse activation at speed over 100 km/h and more than 1 400 RPM.

Flaps are controlled by electric drive. The flaps position is controlled by indicator or visually. RS-version of the aircraft normally (other versions – optional) is equipped with automatic follower-up control system of the flaps, where required flap angle from 0 to 40 degrees is set by flap position selector, after that automatic equipment set the flaps into appointed position.
Pilot’s seats have a system of longitudinal movement which provides comfortable seating and adjustment for pilots which are from 160 to 200 cm in height. For convenient seat adjustment the handrail is mounted in the cabin. The design of the seat pan allows using individual anatomic cushion.

The main access door is located in the top tail part of fuselage and designed to provide boarding the aircraft as well on land as in water. The hatch opens up. The dimensions of hatch allow to load long-measuring freight and as well a patient on special stretcher.  Gas jacks provide easy hatch opening and closing and locking device – fixing the hatch opened. Hatch lock mechanism provides a two-level protection against accidental opening, allowing, at the same time, almost instantaneous opening hatch, both inside and outside. To access to the cabin is used embedded folding ladder, the design of which allows, if necessary, to climb back on board diver or swimmer.

In the cabin there is standard set of equipment needed to aircraft operation on land and in water.

It consists of

- anchor
- towing & anchor ropes
- moorage ropes
- tie down ropes
- boat-hook

There are two emergency exits on left and right sides. The design of hatches allows pilot to abandon the aircraft with parachute during the flight (including emergency situation). Sliding transparent vents are embedded in windshield of hatches. At the top of the cabin there is the access hatch which allows go up to the top of fuselage.

The windscreen of the cabin is made from acrylic (PMMA) plastics, with improved athermical properties. The windshield is capable to stand standard bird strike. The left windscreen of pilot can be equipped with electrical defrost heating for deicing and besides the left windscreen can be equipped with washer which feed water on a glass to remove salt stains.

In the cabin up to eight seats can be installed with two pilot seats included. The rear seats have fold-back and lockers under the seat pan. Each seat is equipped with a mandatory safety belt system. Under the customer desire a dry closet can be installed in the aircraft.

Above each seat individual lighting, adjustable air ball vent and intercom are installed. Under each seat is placed individual life vest approved type. Cabin floor is covered with nonslip polyurethane paint (possible carpeting).

Cabin ventilation is produced through two air intakes located far from water. The air goes to the vent Air is supplied to the individual adjustable air ball vent for pilots and passengers, and out through the labyrinth device in the entrance hatch.

Heating of the cabin is made from two powerful air heaters located on the engines. Part of the hot air is supplied into the passenger cabin, a part of hot air – on the windshields inside the fuselage which prevents their getting misted even at 100% humidity.

The aircraft is equipped with carbon monoxide indicator.

The seats and interior panels are made of special fire resistant fiberglass and covered with high-quality lather impregnated with fire-resistant composition.

For baggage there are two storage compartments - in the nose of the aircraft and in the rear part of the cabin. For small items there are special pockets and niches. The aircraft LA-8C-RS can be equipped with lockable luggage racks.

In each part of the cabin LED lamps are installed. The entrance hatch and front luggage compartment are lighted also. For connecting external electrical devices (portable lamps, GPS-receivers, etc.) the standard cigarette lighter sockets are used.

The aircraft is equipped with two bilge pumps for pumping water before taking off from the water area.


In the design of the aircraft, the main task performed by designers is its safety for passengers and pilots. LA-8 aircraft is designed so that all the systems surpass the mandatory requirements of fail-safe, under the standards of airworthiness for the aircraft of this type.
The power plants is designed so that if one of the engines gets failure it is not required from pilot to put exceeding force and travel of control wheel and pedals to prevent turning the aircraft and maintain straight flight. Feathering of the propellers of failed engine may be performed automatically.

As it is known one of the most frequent causes of flight accidents is CFIT (controlled flight into terrain). For minimization probability of such accidents LA-8 aircraft is equipped with flight navigation system which allows operating in intricate meteorological conditions. For controlling the altitude the aircraft is equipped with two pilot-static sources with heated pitot displayed on three independent indicators; reserve static source from the cabin. Radio technical devices for preventing CFIT the aircraft is equipped with altimeter with two indicators, glideslope information is displayed on three independent indicators from two independent receivers. For providing rear visibility during the flight and while taxiing the camera is used. For determination the relative altitude is used GPS (altitude MSL  and GND) these are two on-board systems (GTN-650) and removable GPS 400 series and (or) 600, as well as a removable iPad with a program chosen by the customer. Approach procedures at airports using two independent systems (G-500 and GTN -750).  Also the aircraft can be equipped with highly sensitive optical-infrared camera for better forward visibility in poor visibility conditions while landing with information displayed on G500. Also on the left screen of flight display can be inferred: a synthetic view of the 3-D terrain generated by the database navigation system, which also makes easier the detection of spatial position in bad conditions and Terrain Awareness and Warning System TAWS, with the information put on the right display G500.

For preventing collision with other aircrafts in the air the Traffic Advisory System TAS is used in the aircraft, self-activating the transponders of other aircraft and displaying information on the background of the map on the right display G500. The aircraft is equipped with a transponder mode “S”, it can be duplicated if necessary and also can be added by “ADS-B”.

Basic instruments have emergency power through the independent bus from the reserve battery counted on 30/60 minutes of flight.

The heated stall warning indicator located on the left wing warns about approaching of the aircraft to stall. Dangerous warning is displayed by a bright red flash light with a warning signal of intercom speaker at the same time.

For minimizing probability to operate in intricate weather conditions the aircraft can be equipped with stormscope (all versions of the aircraft) or meteorological radar (only LA-8RS).

De-icing system includes electric system of heating the pitot tube, the stall warning indicator, the left pilot windshield, the propeller and the leading edges of wing and tail.
Using the M337C-AV engines with compressors and dispersed fuel injection allows eliminating such a dangerous effect as icing the intake system of the engine.

Failure situations of all systems displayed on a special annunciate light panel (red and yellow lights with brightness which allows determining failure in sunlight cabin).   Mounted on floats panoramic mirrors allow not only visually monitoring the position and condition of the landing gear, but also provide oversight for almost the entire glider. Also the mirror allowing to observe passengers, freight and the entrance hatch is installed inside the cabin.
For using the exterior mirrors in the darkness special lamps for lighting the landing gear and the entrance hatch are installed on the floats. Also these lamps are used to make easier boarding and debarkation at night. The LA-8RS can be equipped with an additional (third) landing light mounted on the front of the landing gear.
Failure of control pitch, roll and direction is compensated by trimmers and changes of engines power.

The aircraft is equipped with a speed computer-analyzer which prevents the reverse activation at speed exceeding 100 km/h, as well as the landing gear retraction at speed below 100 km/h. If necessary to retract or extend the landing gear at slow speed (for example on the water or at maintenance works) the lock should be turned off by special switch.

Each propeller is equipped with a centrifugal lock, making it impossible to shift the propeller blades to reverse at 1,400 RPM. Thus to prevent accidental reverse activation in flight there is backup locking system.

In addition to the described systems engine control levers are equipped with breaker preventing the deliberate reverse activation by pilot in flight, as well as preventing forward thrust activation on the run due to premature reverse activation by pilot.

The operating experience of the aircraft on the water showed the effectiveness of the outward alarm siren which the LA-8 aircraft is equipped with. The siren is also used for giving sound signal by standard maritime code while moving on the water or mooring.

Maximum flight altitude of LA-8 is limited by the regulations to 3 000 meters due to its unpressurized cabin. However there can be installed individual oxygen devices for crew and passengers onboard, in this case the Airworthiness Regulations allow to operate  up to an altitude of 4 500 meters.

Rescue equipment includes radio transmitter 406 MHz KOSPAS-SARSAT and emergency hand VHF radio. Onboard there is rescue equipment set including first-aid kit, emergency axe, fire extinguisher, life vests for every seat, rescue raft for 4-6-8 people, waterproof floating battery lamp, oxygen apparatuses for the crew in case of cabin smoke.

The aircraft can be equipped with emergency dictaphone recording crew talks, video recorders, flight data recording system and voice information reporting system.

The airframe is designed for impact overload resulting from the landing on the water, so in case of emergency landing on ground the passengers and crew are protected by a powerful hull of the boat. Also composite materials of fuselage have a high coefficient of energy absorption at breaking, which provides additional protection for people inside the aircraft.


Basic power plant is based on the two engines LOM PRAHA M337C-AV with take-off power 235 HP and continuous power of 210 HP each. Each engine has six cylinders in line (capacity of 6 liters, 366 cubic inches). The engines are invert. Such design of the engine provides the minimum aerodynamic resistance of power plant. The engines are equipped with mechanical superchargers and keep power to altitude of 1 200 m. Also the engines are equipped with timing fuel injection which provides record low fuel consumption up to 0,195 kg (kw/h) and have automatic altitude fuel-air mixture correction

On the aircraft are installed the propellers of German production. The propeller MTV-12-D-C-F-R(M)/CFR190-53 with constant speed, hydraulic control, reverse and feathering. (It is possible to use the propeller with ability to start at zero thrust mode – that makes operation on the water easier and provides a quick warming-up in cold weather).

For operation on the North are installed engine starting preheaters, oil cooler boot and adjustable cowl flaps. To facilitate cold start the engine is equipped with specially updated ignition system.

The oil cooling system includes thermostat maintaining constant oil temperature at low air temperature and the oil cooler - in the standard and in the tropical climate.

Standard noise level in the cabin as on the ground is provided by special propeller blade profile and specially designed exhaust system.

Except for the engine LOM PRAHA M-337C-AV the aircraft can be equipped with engines LYCOMING 540 of 235HP to 300HP, as well as turboprop TP-100 or AI-450 with propellers "AVIA" or MT.

In case of using LYCOMING engines it is possible to install HOFFMAN V-123 propellers with increased starting thrust.

All the proposed engines can be equipped with additional generators which provide additional electric power in case of using de-icing devices.

The aircraft can be equipped with auxiliary power unit with generator of 1 500W to increase the independency of the aircraft.

The engine operating is controlled by combined electronic indicating system EDM 960 produced by JPI Instruments which displays operating parameters. The engine monitoring system is specially updated and certified for installation on LA-8 aircraft. The instrument displays the following engine performance and has the following features:
- revolution per minute sensor
- manifold pressure sensor
- oil pressure sensor
- fuel pressure sensor
- oil temperature sensor
- cylinder head temperature sensor
- exhaust gas temperature sensor (for LYCOMING engines)
- carburetor air temperature sensor (for LYCOMING engines)
- main bus voltmeter
- main bus ammeter
- fuel flow indication
- fuel level measure
- remain fuel counter
- estimated flight duration
- engine log recorder
- operating time register
- outside air temperature sensor
- engine power indicator
- indicator of asynchrony of propeller turns

In addition to main display the computer controlling the engine has two independent monitors with alarm abnormal parameters.


The main electrical network of the aircraft is DC 27V. Energy supply is DC generators. Basic battery of 24V/16 A*h or also the battery of 24V/20 a*h can be installed. The aircraft is equipped with ground power unit of 24V – 250A which allows charging the batteries and starting the engines from an external supply.

For the aircrafts equipped with flight control equipment which provide IFR operation is used the additional independent power bus from back-up power supply which has sufficient capacity for providing the main radio-navigation equipment operation during 30/60 minutes of flight in case of failure of all other generators.

Power supply of power-consuming devices such as de-icing devices is performed by AC 42V from the additional generators mounted on the engines. To be able to connect devices with a voltage of 12V can be installed static converter with power up to 250 W.


The main flight instrument is GARMIN G500 avionics display system certified for multiengine piston aircrafts with take off weight up to 5 700 kg and flight altitude up to 6 000 m. The display consists of two monitors. The left one shows:
- attitude indication, synthetic vision is available
- indicator airspeed
- true airspeed
- altitude
- vertical speed
- turn coordinator
- slip indicatior
- magnetic heading
- true heading
- glideslope indication
- outside air temperature
- radio altimeter readings

The right display shows navigation information: maps with flight track, approach charts according to Jeppesen database, taxiing and stopping charts, actual ground speed, track angle, wind, etc., and as well displaying terrain database TAS, radar screen and video screening from front and back view cameras.

The aircraft can be equipped with one or two flight displays G-500.

The main GPS/NAV/COMM system is GARMIN GTN-650 that combines the following functions:
- GPS receiver
- touchscreen graphical flight planning
- VHF with transmitter of 10 or 16 W (optional)
- VOR/ILS receiver
- remote transponder interface
- router for avionics network
- navigation information source for autopilot
- moving map.

The aircraft can be equipped with one or two GTN-650.

Instead of GTN-650 can be installed GTN-750 with large display and additional audio panel control, transponder and approach charts viewing.

When one GTN-650 is installed as a second VHF radio is used SL30 NAV/COMM with transmitter of 10 W and receiver VOR/ILS, or/and SL-40 (GTR 225,10/16 W). If necessary the aircraft can be equipped with radio compass ADF, distance-measuring equipment DME, short-wave and satellite communication with Internet access.
Equipment switching is performed through the audio panel with built-in intercom for 6 users. Also the audio panel provides loud-speaking communication and can be marker receiver when proper antennas are installed. It is possible to use audio panels with stereo and MP3-player.

To reduce crew workload and increase safety of the aircraft 3-axis autopilot with autotrim on three channels and yaw damper is installed. The autopilot allows operation in automatic mode according to flight plan information, using previously generated data from the navigation system.

As backup instruments are used barometric instruments: airspeed indicator, altimeter and electric (electronic): gyro horizon, clock, magnetic compass. On the left instrument panel can be installed the additional backup devices: turn indicator, vertical speed indicator, CDI indicator, ADF indicator or G-meter

The aircraft can be equipped with removable iPad with air navigation data and navigation programs, for standard version – AirNavPro with Jeppesen Navigation Database.



 (For improving the crew efficiency and convenience of passengers)


In addition to main ventilation system the pilot seats can be equipped with electric fans and special lock of the top hatch providing small opening (on 10…15 mm) for better ventilation.

The pilots’ seats are equipped with glass-holders, pockets for cards, holders of briefcases. On the instrument panel or control wheels are mounted locks for portable navigation devices, and for the power supply is possible to install additional electrical connectors.

Individual interior solutions (tables, side sofa) and individual equipment (dry closet, galley, video screens, special holders for fishing or hunting equipment, drawer fridge for fish, etc.) are possible.

In the windows of passenger cabin or/and in the entrance hatch it is possible to embed hatches for photo and video shooting.

For better maneuverability of the aircraft on the water is provided the small boat engine installation.



The design of the aircraft allows its quick (within 15 minutes) transformation from a passenger (main) version into cargo version. Thus on the forcing rails of the floor are installed strapping shoes for mooring cargo or cargo mash. The cabin of the aircraft allows carrying cargo of 4 meters length.

In the cabin can be equipped 2 seats for bed-ridden patients and 1 seat for accompanying physician. Re-equipment of the aircraft is performed from passenger modification into air ambulance less than 30 minutes.

The long duration of the flight makes LA-8 aircraft unique and low-cost facility for aerial surveillance and monitoring, collection of water samples, monitoring underwater area. On the aircraft can be installed echo-sounding devices, sonars, optical and radar equipment. The design of the wing (version RS) allows to mount two underwing containers weighing up to 150 kg each and to put the equipment set in the nose compartment.

For operation in the winter the LA-8 aircraft can be equipped with non-retractable ski set allowing operation not only from prepared snow-covered runways, as from deep snow.

It is possible to deliver LA-8 as hydroplane with fast mounted undercarriage (mounting and dismantling take not more 10 minutes) and removable ski set for winter operation. The useful load of LA-8H is 1180 kg (1215 kg for RS-version) at a price is lower at 15%. 


SPU “AeroVolga” offers a unique modification of the fire-monitoring aircraft LA-8 FF (2 person crew) with the possibility of taking onboard 1000 liters of water in the planing mode, water drop (foam-water mixture) during 2 sec from the altitude up to 5 m at speed of 180 km/h and duration for fire monitoring up to 5 hours.

The patrol modification of the aircraft based on LA-8C-RS with radio and video monitoring set of surrounding area can stay in the air up to 14 hours with crew of 4 people. The crew is provided by dry closet, galley and a place for rest for one person as well as multi-channel communication protected system

The first-aid modification of the aircraft based on LA-8C-RS with medical equipment weighing up to 180 kg allows two doctors to resuscitate a patient (injured) during the flight up to 5 hours (1000 km).


SPU “AeroVolga” performs training of the Customer’s flying staff. The training program includes special flight training course (12 hours) and two-week basic engineering training course.
The extensional training courses are possible with providing eligibility to perform complex maintenance and overhaul. The theoretical training pilot for hydroplane is conducted in ASC in Kazan and Sankt-Petersburg.




The following documentation is delivered with the aircraft:

- Flight manual

- Maintenance schedule

- Maintenance manual

- Wiring diagrams

- Equipment and instrument certificates

- Factory flight test certificate
- Acceptance certificate

- Engine, propeller, airframe logbooks

- 3-years subscription to bulletins

- Aircraft part catalog (optional)

- Airframe repair manual (optional)


Handling facilities and spare parts, possible to order:

- Fitting fastening of cargo
- Stretchers
- Reanimation medical equipment, RS-version
- Expendable spare parts and materials for 200 hours
- Spare parts
- Parking plug
- Parking shoe
- Cabin and propeller cover
- Airframe cover
- Towing bar
- Instrumental Kit for line maintenance
- Instrumental Kit for scheduled maintenance
- Instrumental Kit and materials for minor repair
- Jack adapter
- Jacks for wheel replacing
- Jacks for landing gear maintenance
- Stepladder for wing maintenance
- Stepladder for tail maintenance


Engine life is 2 000 hours till complete overhaul, number of repairs is unlimited, there is no hard maintenance forms.

Propeller life is 2 000 hours till complete overhaul, number of repairs is unlimited.

Airframe life is under condition, airframe checks every 2 000 hours or once in 5 years.

Periodicity of maintenance for LA-8C: 100 hours and replacing the oil - 200 hours,
Periodicity of maintenance for LA-8L: 100 hours and replacing the oil - 50 hours,



(a) unleaded gasoline, octane number not less than 95, alcohol content not more than 5%

 (b) aviation gasoline AVGAS 100LL

Oil: in accordance with specification MIL-L-6082E - without additives or
in accordance with specification MIL-L-22851D  - with additives

Hydraulic fluid/brake fluid
(a) AMG-10
(b) MIL-5606H hydraulic fluid



The aircraft is delivered after check flight from the Krasniy Yar airdrome, Russia. Transportation by land is performed on a trailer, by sea – on a ship. Also the Customer can perform the flight from Krasniy Yar airdrome (UWWQ). Delivery of LA-8C-Kit under agreed specification is possible.


SPU “AeroVolga” provides its Customers with bulletins, technical publications and newsletters. The company provides support by spare parts, materials and tools.

Under the additional agreement SPU “AeroVolga” can organize maintenance at its service base or send specialists to the Customer.


First flight of amphibian aircraft LA-8 happened in autumn 2004.
Total flying time of all aircrafts for this period is over 2 000 hours including factory test of more than 500 hours.
The aircraft flew from the Caspian, Black, Baltic and White seas.
The flights were performed in different climatic zones from Arctic Circle to the subtropics, at temperatures from -35 to + 42 Celsius, including in the conditions of moderate icing.



Certification of the aircraft is being realized in the meantime in accordance with requirements of the rules АП-23/21, the supposed completion date of certification is 2014. The aircraft is delivered with airworthiness certificate under FAP-118 Russian Federation at the moment.

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