Terzi T30 Katana

The development of each new aerobatic aircraft takes many years, and the first flight of the prototype is a celebration for both designers and future pilots. The design of a similar single-purpose special, its construction, small-series production and sale are certainly not profitable matters, but nevertheless, new aerobatic aircraft continue to be developed thanks to the immeasurable enthusiasm and dedication of their followers. For all the financial expenses and hundreds of hours worked, the greatest reward for all the people who were "there" is the sight of their child's flight. A similar festive moment was experienced by the invited guests together with the constructors on March 2 last year at the airport of the Milan Aeroclub, when it was presented to the public new competition "grind" T-30 Katana.

The father of the idea for its construction and the author of the initial project is the forty-year-old engineer Pietro Terzi, an active pilot who has already designed the construction of the T-7, T-8 Leone and T-9 Stiletto aircraft. The final shape of Terzi's project was given by Edoardo Ponti and Antonio Garengani, and the final assessment was carried out by international competition-tested pilot Sergio Dalian.

The fuselage of the T-30 Katalan, named after the samurai sword, resembles at first glance the Zlín "fifty". However, its wing has a completely different shape, connected to the fuselage by large transitions, which give the aircraft a characteristic and unmistakable appearance.
The company Terzi Aerodine supplies the aircraft, approved for the experimental class, as a kit, or ready and flown. The T-30 C and E versions are distinguished by the power unit used. The "Céčko" is powered by a six-cylinder Lycoming flat engine with a three-blade Hoffmann propeller, the E version is powered by an eight-cylinder Lycoming engine with a four-blade adjustable propeller.

Terzi T-30 Katana aerobatic plane plans

The Terzi T-30 Katana is a single-seat, single-engine, all-metal self-supporting mid-airplane with a closed cabin and fixed tail landing gear.

Hull. The frame is welded from thin-walled chrome-molybdenum tubes, and a removable composite body is mounted on it. A simple seat is attached to a frame made of metal tubes under a large cover made of organic glass that folds to the right.

The wing, equipped with a symmetrical profile developed especially for this aircraft, is a self-supporting, all-metal structure. The wings along the entire span are attached with four hinges each.

Tail surfaces are classic self-supporting structures. The right half of the VOP is equipped with a balancing plate, the elevator and the rudder with corner balancing.

Landing gear. Both the main undercarriage wheels and the spur wheel are supported by composite flat leaf springs.

Power unit. The T-30C version is powered by a 224 kW Lycoming AE'O-540-L1 B5 six-cylinder air-cooled engine with a Hoffmann HO-V123 K-V/200 AH three-bladed propeller; in the T-30E version, the power unit is an eight-cylinder Lycoming 10-720 with a power of 298 KW, equipped with a Muhlbauer MTV-14-B-C/C 190-17 four-bladed propeller. Two internal fuel tanks are in the leading part of the wing root; the aerobatic tank equipped with a fuel symbol is in the fuselage in front of the cockpit. All three tanks hold a total of 195 liters of fuel.

Coloring. The prototype was sprayed white on all surfaces. The l-KTAN markings on the sides of the fuselage are red, as are the Terzi lettering and Japanese emblem on the engine cowling, the stripes on the tips of the propeller blades and the spiral on the pitot tube. The interior of the cabin is light gray, the seat is covered with a blue fabric seat and the straps are red and blue. The triangular walkway on the left half of the wing below the cabin is matte black, the main landing gear legs grey.

Technical data and performance of the T-30C (E): Span 7.77 m, length 6.30 m, height 2.57 m, bearing area 10.60 m2, weight of the empty aircraft 640 (660) kg, take-off weight 800 (880 ) kg, load per unit area 75.47 (83.02) kg/m2, maximum speed 505 km/h, cruise speed 370 km/h, landing speed 90 km/h, rate of climb 16 (23) m/s, operational multiples of ±12 g.