“LASTA”

Description

Light, agile, manoeuverable and forgiving advanced trainer

“LASTA” aircraft is intended for initial and basic training of pilots and easy transition to the advanced levels of training. It has low landing and takeoff speeds and is very pilot-friendly, i. e. it ‘forgives’ potential errors made by inexperienced pilots.

The aircraft was designed in compliance with Federal Aviation Regulations (F.A.R. – Part 23: Airworthiness Standards), basic version in acrobatic category (+6/-3g) and armed version of the aircraft in utility category (+4,4/-1,8g).

Lasta landing gear is equipped with an emergency landing gear extension system (used in the event of hydraulic system failure). This mechanical system ensures extension and locking of all three struts, at horizontal aircraft speeds of up to 180 km/h.

Light, agile, manoeuverable and forgiving advanced trainer

The aircraft specification and upgraded avionics enable full pilot training for all applications, such as:

basic flying,
formation flying,
air navigation
night flying,
instrument flying
light attack/CAS operations

Aircraft description

Airframe

All metal semi – monocoque fuselage, with integrated vertical stabilizer and engine truss mount
Меtаl wing with two spars
Horizontal stabilizer

PowerPlant

LYCOMING AEIO – 540 – L1B5D Engine
Six cylinders
Flat, horizontally opposed engine
Direct fuel injection
Air cooling
Designed for aerobatic flying
Hartzell twin-blade propeller
Maximum continuous output (H = 0 at 2700 r.p.m.) 224 kW

Controls:

Mechanically controlled control surfaces
Electrically controlled flaps
Electrically controlled elevator and rudder trimmers
Both ailerons have flatteners, and electrically controlled left-side trimmer

Cockpit:

Ergonomic design meets 90% accommodation requirement according to current AF & AD standard, and comfortable accommodation for 99% of pilots.
Glass cockpit provides good visibility and direct visibility of approaching runway (with 2º reserve) from the front seat, while rear seat headroom is minimum 100 mm
Ergonomic pilot seat, adjustable in height, is designed to allow the pilot to wear a backpack parachute. It is equipped with a safety harness that secures the pilot in all stages of flight and allows easy operation of all cockpit controls and rapid and easy evacuation, both when the aircraft is on the ground and in the air.
Adjustable pedals
Cockpit evacuation after the explosive cord shatters the canopy
Flight control from the front cockpit (even during basic instrument flying training)
Easily detachable flight simulator

Fuel installation

Integral wing fuel tanks fitted ahead of front spar
Fuselage collector tank
Engine fuel supply pump
Auxiliary fuel supply pump, electric
Fuel selector
Fuel cut-off valve

Hydraulic system:

Designed for landing gear retraction/extension and for braking system control
Simple and lightweight design, powered by the electro-hydraulic generator
Equipped with an auxiliary hand pump and with simple and reliable hydraulic connectors
Independent braking system activated by four hydraulic foot pumps

Landing gear:

Enables takeoff and landing on concrete and prepared grass runways
Retraction/extension by hydraulic actuators
Mechanical release of the landing gear
Main wheel tire dimensions 15 x 6.00 – 6 (6 PR)
Nose wheel tire dimensions 5.00 – 4 (6 PR)
Main wheels fitted with disc brakes
Differential braking
Self-centering nose leg

Electrical equipment:

Electric circuit 28 V DC
Main source: Alternator 2,6 kW
Auxiliary source: Ni-Cd battery 17 Ah
Engine starting: external generator or battery.
Alternating current system (115/26 V, 400 Hz) by means of 50 VA static converter
Cockpit lighting, control and signaling units
Position lights
Landing light
Taxi lights
Anti-collision light

Electronic equipment:

The aircraft is outfitted with modern electronic equipment that meets all current international standards and has the following main functions:
Intercom communication between the front and the rear cockpit
Two-way radio communication, air-ground and air-air, in VHF range
Radio navigation: radio beacon, VOR and GPS
Instrument landing: ILS and marker beacons
LCD display: flight and navigation data
Navigation with pilot’s 3D map, with collision alarms (visual and sound),
Display of a situational map with the aircraft position
Traffic Information System with collision sound alarms
Inertial navigation and aircraft position display with respect to the magnetic or geographic north pole
Display of corrected barometer height readings, indicated airspeed, ground speed, true airspeed, deviations from the preset course when using GPS or VOR
Electronic measurement of the slant range to the DME ground station, and the approach time/speed to the ground station
Aircraft identification and tracking on flight control displays and on displays of other aircraft
Display and monitoring of engine and fuel parameters in both cockpits

Maintenance and service life :

Service life 6,000 flight hours or 20 years
Optimum annual aircraft utilization: 300 flight hours.
General repair of the airframe and engine after 1400 flight hours
System MTBF over 300 hours; for the whole aircraft over 50 hours
Pre-flight inspection and fuel filling, up to 20 minutes
Post-flight inspection up to 30 minutes

Aircraft armament systems

The aircraft can perform training in gunning, rocketing and bombing using the collimator sight (optionally, upon customer’s request, with optoelectronic sight), engaging the following airborne ordnance:

7.62 mm or 12.7 mm machinegun pod
Honeycomb-type multiple rocket launchers
2 x 100 kg aerial bombs
Optionally, aircraft can be used for the following homeland security missions:

Close air support in counterinsurgency operations
Air patrol / light attack missions