Aircraft T-21 belongs to the normal category according to JAR-VLA classification. It is designed for use as a light multipurpose aircraft.

The base version is the trainer. With no or minimal modification not changing the basic design the aircraft can be used in the following versions: cargo (up to 200 kg), touring, agricultural, patrol.

Short take-off and landing (STOL) capabilities together with strong landing gear allow the aircraft to operate from airfields with short or unpaved strips. Provisions have been made to install floats or skis.

Design Features:

Aircraft T-21 is a monoplane with high parasol-type braced wings, one piston engine, tapered tail surfaces and tricycle landing gear. 

The fuselage consists of triangular pyramid-like truss made of large-diameter steel tubes,  center section and riveted rectangular tail boom. 

A modular design structure is installed at the base of the pyramidal truss. The forward portion of the structure is a streamlined cockpit for pilot and instructor sitting side by side with large area windshield providing excellent vision in the vertical and horizontal planes. Removable tail portion is intended to carry cargo and special equipment. 

The pilot cockpit is provided on its sides with glazed doors fitted with locking and emergency jettisoning mechanisms. The cargo compartment has access cover with built-in handle to hinge the cover upward and locking mechanism. 

The wing is furnished with two-section extendable Fowler flaps having two down positions for short take off and landing. Each wing panel has an aileron. The wing spar mounts a fitting for the wing brace strut. 

The horizontal tail is of conventional type. The stabilizer is a riveted two-spar  structure in which capped web spars are interconnected by means of ribs and metal skin. Elevators with control horn and controllable trim tab have common tubular spar, ribs, tips and are covered with the “Stits” fabric. 

The vertical tail is of conventional type. It consists of fin (vertical stabilizer), rudder with fixed trim tab, dorsal fin and ventral fin. 

The fin is a conventional two-spar structure incorporating stamped ribs between spars and metal skin made of D16T aluminum alloy on leading edge. The fin is covered with the “Stits” fabric. It is secured to the rear spar of the stabilizer by means of strips. The rudder is similar to the elevators. The ventral fin is made of steel tubes and is covered with the “Stits” fabric. 

The landing gear is of tricycle type with the main legs attached to the rear tube of the pyramidal truss base and nose leg installed in front of the pyramidal truss. The nose leg with a hydropneumatic shock absorber is fitted with two castoring wheels 310x125. The main leg is of semi-lever type with torsion shock absorber and return motion damper. The main legs are fitted with wheels 500x150. 

The engine, engine mount, cowls, power plant accessories are arranged in front of the wing. The fuel system has one fuel tank located aft of the rear cockpit bulkhead. The engine and propeller controls are arranged in the pilot cockpit between the seats.  

Main Flight Performances: