The Largest Security-Cleared Career Network for Defense and Intelligence Jobs - JOIN NOW

Military


LASTA-95 / Swallow 95

Lasta 95 is a single-engine, low-winged metal aircraft, with two pilot seats, one in front of the other. It is able to take off and land on concrete and grass landing strips LASTA-95 aircraft is designed for selection, initial and basic training of pilots, it offers low landing and takeoff speeds and pilot-friendly handling, forgiving potential errors by inexperienced pilots. The aircraft was designed in compliance with Federal Aviation Regulations (F.A.R. Part 23: Airworthiness Standards). The BASIC VERSION OF THE AIRCRAFT is built against the requirements for aerobatic category loads of (nz_max = 6.0, nz_min = -3). The ARMED VERSION OF THE AIRCRAFT is built against the requirements for utility category with loads of (nz_ max = 4.4, nz_ min = -1.8).

Flight tests of the Lasta 95 training plane, the first domestically designed aircraft produced at the Utva factory of Pancevo since the breakup of the Socialist Federal Republic of Yugoslavia, were begun successfully at the Batajnica military airport in Febrary 2009. The launch of serial production at the plant is expected after all tests are completed. The Iraqi military has ordered 20 Lastas [some reports state that Serbia has sold 36 Lasta-95 training aircraft to the Iraqi Air Force], while 16 aircraft are to be produced for the Serbian army to replace the Utva 75 plane in pilot training.

Defense Minister Dragan Sutanovac stated at Batajnica air port, after attending the first test flight of Lasta 95 training aircraft, that this was an excellent air craft which would serve for the training of home and foreign soldiers from all over the world. The promotional flight was attended by the Chief of SAF GS LTG Miloje Miletic with his coworkers and the top officials from the defense system as well as numerous reporters. The plane was operated by Lt. Col. Salko Hadzic from the Flight Testing Center of the Technical Testing Center.

Only 4 or 5 European countries produce this type of planes, and only ten in the whole world make these planes.. So this makes us the country with wings of it own, its own aviation industry we take great pride in. this means introducing a new plane into the training process, which means 6 times less money spent on the training of every pilot per hour. For example, an hour on Galeb G4 costs 2000 EUR, while on Lasta it costs only 300, said Minister adding that this was another way of the Ministrys contribution to the savings in the budget.

The attention of the domestic public was drawn to Lasta 95 when it was first represented at the arms fair Partner 2007. In July last year this became the main topic when Yugoimport SDPR first signed the contract with the Iraqi Ministry of Defense on arms export. This contract envisions that 20 propeller planes Laste-95 for training be exported into Iraq. The manufacturer of the final stages of the air craft and the main manufacturer is DOO Utva, Aviation Industry Pancevo. The Utva Aircraft Factory was established in 1937 in Pancevo, outside of Belgrade, and was heavily damaged in NATO air strikes on Yugoslavia in 1999.

With its specifications and updated avionics, the aircraft will ensure full pilot training for all elements of airplane application including:

  • basic flying,
  • figure flying,
  • navigation flying,
  • basic elements of night flying,
  • category II instrumental flight,
  • basic elements of gunning, rocketing and bombing (GRB)
  • Light close air support of counterinsurgency operations and area patrol / light attack missions

Lasta-95 landing gear is equipped with mechanical emergency system for landing gear extension (in the event of failure of hydraulics). This mechanical system ensures positive extending and locking in extended position of all three struts, at horizontal aircraft speeds up to 180 km/h. Minimizing of structural mass was achieved by application of advanced stress calculation methods including numerical simulations to meet strength and rigidity requirements. Aircraft fuselage structural stress was verified by testing, confirming the adopted concept and approach for de-dimensioning of structural components.

Aircraft description

Structure
  • Metal, shell type, with integrated vertical tail, and truss engine support
  • Metal wing with two spars
  • Horizontal metal tail
Engine Lycoming AEIO-540-L1B5D main features:
  • Six cylinders
  • Flat, opposed
  • Direct fuel injection
  • Air cooling
  • Designed for aerobatic flying
  • Propeller Hartzell twin-bladed
  • Maximum continuous output (H = 0 at 2700 r.p.m.) 220 kW
Controls with:
  • All control surfaces are mechanically controlled.
  • Flaps and all three trimmers electrically actuated.
  • Electric trimmers for rudder and ailerons.
  • Mechanical, spring-loaded trimmer for elevator.
Other mechanical controls
  • Engine
  • Fuel
  • Cockpit canopies
  • Landing gear, emergency
  • Cockpit heating and ventilation
  • Armament controls
Aircraft cockpit provides:
  • Ergonomic accommodation for 90% of pilots according to current AF & AD standard, in the range of 5 to 95% of pilot statures and comfortable accommodation for 99% of pilots.
  • Good cockpit visibility and direct visibility of approaching runway (with 2o reserve) from the front seat. Rear seat headroom of minimum 100 mm.
  • Ergonomically built pilot seat, adjustable in height, accepts back-carried pilot parachute, provided with harness that secures the pilot in all stages of flight but allows normal handling of all cockpit controls, as well as rapid and easy aircraft evacuation on the ground and in the air.
  • Adjustable pedals.
  • Pilot rescue by normal cockpit evacuation (without ejection seat), by piercing of cockpit canopy with detonating cutter.
  • Aircraft flying in basic instrumental flight training from the front cockpit. Provided with instrumental flying simulation system which can be easily mounted and removed.
Fuel installation
  • Integral wing fuel tanks fitted ahead of front spar
  • Collecting tank in fuselage
  • Jet supply pump
  • Auxiliary electric pump
  • Fuel unbalance cock
  • Fire protection cock
Hydraulic system features
  • Designed for landing gear retracting/extending and powering the braking system.
  • Hydraulic system is featuring with simplicity and lightweight; system is powered by electro-hydraulic generator that does not use power of aircraft engine, equipped with auxiliary hand pump and reliable and simple hydraulic connectors.
Landing gear features:
  • Enables takeoff and landing on concrete and prepared grass runways. Retracted and extended by hydraulic actuators.
  • Emergency mechanical release.
  • Main wheel tire dimensions 380 ? 150.
  • Nose wheel tire dimensions 330 ? 130.
  • Disc brakes fitted to main wheels.
  • Differentially controlled braking.
  • Nose strut view.
Electrical equipment
  • Electric circuit 28V DC.
  • Main source: Alternator 2 kW.
  • Auxiliary source: Ni-Cd battery 17 Ah.
  • Engine starting by external generator or by battery.
  • Alternating current system (115/26 V, 400 Hz) by means of static converter of 50 VA.
  • Lighting:
  • Position lights
  • Landing spotlight
  • Taxi lights
  • Anti-collision light
The aircraft is outfitted with modern electronic equipment that meets all current international standards and provides the following main functions:
  • Two-way radio communication air-ground and air-air in VHF range, with frequency spacing of 25 and 8.33 kHz, with minimum output of 10 W, simultaneous reception of all audio signals in both cockpits and enabling permanent communication between two pilots.
  • On customers request an UHF transceiver could be installed, with channel spacing of 25 kHz and minimum power output of 10 W.
  • Satellite navigation and radio navigation, employing satellite navigation receivers and ground radio beacon, VOR and radio compass.
  • Landing in adverse weather conditions of category II, day and night, based on existing ILS system of GPS equipment.
  • Radar identification of aircraft with transponder (operating in mode S).
  • Controls for all electronic equipment provided in front cockpit, in second cockpit only for equipment where feasible.
Operational characteristics
  • Service life 6,000 flight hours, or 20 years
  • Optimum annual utilization 300 flight hours.
  • General repair of airframe and engine after 1400 flight hours.
  • Mean time of systems failure greater than 300 hours; for the aircraft as a whole over 50 hours.
  • Pre-flight inspection and fuel filling, up to 20 minutes.
  • Post-flight inspection, up to 30 minutes.
Aircraft armament
  • The aircraft can perform training in gunning, rocketing and bombing with application of collimator sight (optionally, upon customers request, with optoelectronic sight), engaging the following airborne ordnance:
  • Pods with machine guns cal. 7.62 mm or 12.7 mm
  • Honeycomb-type multiple rocket launchers 57 mm
  • 2 x 100 kg aerial bombs:
Optionally, aircraft can be used for homeland security misions, as follows:
  • Light close air support of counterinsurgency operations and
  • Area patrol / light attack missions



NEWSLETTER
Join the GlobalSecurity.org mailing list


One Billion Americans: The Case for Thinking Bigger - by Matthew Yglesias


 
Page last modified: 23-09-2013 18:21:10 ZULU