Direct Fly Alto

The Alto aircraft is an all-metal construction aircraft for amateur construction. The Alto aircraft meets both requirements to European category “ultralight aircraft” and “light sport aircraft” (LSA) category that has been defined in the U.S.A.

Different versions were offered. A basic version with the tricycle, nose type landing gear or optional with the tail landing gear with Rotax 912 ULS/UL as standard, but Jabiru on request, and wheel-type control or the stick control, standard is wheel control

Alto is single-engine, two-seat, low-wing, cantilever monoplane. The aircraft is all-metal riveted construction and may be equipped with rescue parachute system.

Alto 912 TG

The TG version (basic) is the tricycle, nose type with the nose landing gear steering. The main wheels are attached to the flexible all-composite legs. The main landing gear wheels brakes are operated by the hydraulic system, by means of break pedals (in the left side only) or with central brake with parking function. The TW version (optional) has the tail wheel landing gear.

The rectangular wing is a monospar construction with an auxiliary spar. The skin is made from duralumin sheet. The wing is equipped with ailerons, slotted flaps and integral fuel tanks with a total capacity of 105 l. All the parts are riveted together. The wing-body attachment forms a wing centre section, which is firmly placed into the fuselage. The wing main spar is connected to the wing centre section by bolts and the rear auxiliary spar is connected by a hinge.

The rectangular fuselage is of semimonocoque, riveted construction and has a bottom and the side walls reinforced by diagonal stiffeners. The dorsal is of oval cross section.

Alto 912 TG

The tail unit is of all-metal, riveted structure and has a standard configuration.

Aeroplane control consist of elevator, ailerons and rudder control surfaces. The manual control is of a wheel-type or a stick and deflections are transmitted by chains, push-pull tubes, and cables. The pedal control deflections are transmitted by cables to the rudder, and by push-pull tubes to the nose landing gear steering. The wing flaps and the elevator trim tabs are operated electrically. The main landing gear wheels brakes are independently operated by the hydraulic system, by means of break pedals on the pedal control.

The cockpit inner width is 106 cm and the wheel-type control and a forward sliding canopy make for easy boarding. The canopy is made from glass, and optionally may has light blue colour, and may be equipped with the wind-wings.

2009 Price: 44000 EURO

Alto TG 912 UL
Engine: Rotax 912UL, 80 hp
Length: 6,15 m / 20,18 ft
Wing span: 8,20 m / 26,9 ft
Wing area: 10,5 sq.m / 114 sq.ft
Height: 2,25 m / 7,38 ft
Cabin width: 1,10 m / 3,61 ft
Seats: 2
Fuel: 118 lt / 31,2 US gal
Take off run: 100 m / 328 ft
Landing run: 150 m / 492 ft
Empty weight: 280 kg / 618 lb
MTOW – ULM: 472 kg / 1041 lb
MTOW – LSA: 600 kg / 1320 lb
Vne: 255 km/h / 158 mph
Maximum speed: 230 km/h / 143 mph
Cruising speed: 185 km/h / 115 mph
Stall speed full flaps 450 kg: 65 km/h / 41 mph
Stall speed no flaps 600 kg: 81 km/h / 51 mph
G factor: +4 / -2
Climb rate 450 kg: 5,6 m/s / 1100 fpm
Climb rate 600 kg: 4,5 m/s / 890 fpm

Alto TG 912 ULS
Engine: Rotax 912ULS, 100 hp
Length: 6,15 m / 20,18 ft
Wing span: 8,20 m / 26,9 ft
Wing area: 10,5 sq.m / 114 sq.ft
Height: 2,25 m / 7,38 ft
Cabin width: 1,10 m / 3,61 ft
Seats: 2
Fuel: 118 lt / 31,2 US gal
Take off run: 90 m / 295 ft
Landing run: 150 m / 492 ft
Empty weight: 285 kg / 628 lb
MTOW – ULM: 472 kg / 1041 lb
MTOW – LSA: 600 kg / 1320 lb
Vne: 270 km/h / 168 mph
Maximum speed: 250 km/h/ 155 mph
Cruising speed: 200 km/h / 124 mph
Stall speed full flaps 450 kg: 65 km/h / 41 mph
Stall speed no flaps 600 kg: 81 km/h / 51 mph
G factor: +4 / -2
Climb rate 450 kg: 6,3 m/s / 1250 fpm
Climb rate 600 kg: 5,1 m/s / 1005 fpm
Take-off distance (50ft obstacle): 440 ft / 135 m
Landing distance (50ft obstacle): 490 ft / 150 m

Diehl Aero-Nautical XTC

Single seat single engined mid wing monoplane with conventional three axis control. Wing has swept back leading edge, swept forward trailing edge, and tapering chord; two fin tail and canard wing. Pitch control by fully flying canard; yaw control by fin-mounted rudders; roll control by one third span spoilers; control inputs through stick for pitch/roll and pedals for yaw. Cantilever wing; wing profile double surface. Undercarriage has three retractable wheels in tricycle formation; steel spring suspension on all wheels. Push right go right nosewheel steering connected to yaw control. Individual brakes on main wheels. Glass fibre fuselage partially enclosed (total enclosure optional). Engine mounted above wing driving pusher propeller. Composite foam/glass fibre construction with spars in carbon fibre.

The appearance of the world’s first purpose designed amphibious ultralight created quite a stir when it appeared in prototype form at the ’82 Oshkosh and it has continued to attract great interest ever since.

This composite construction machine has floats at its wing tips and the entire fuselage forms a hull. The main wheels of the XTC Hydrolight retract sideways and outwards and the nosewheel retracts forward, nestling in the nose of the fuselage. Foot operated individual main wheels brakes are fitted.

Though originally fitted with a twin cylinder Cuyuna 430RR and later with the Kawasaki TA440 developing 39 hp at 6000 rpm, the XTC Hydrolight is now normally supplied with the KFM 107 engine. The title stands for Cross Terrain Craft and, according to its constructor, is pronounced ‘ecstasy’!
To allow trailer transport, the outer wing sections are removable, rigging time being quoted as 10 min with one person. The aircraft is supplied in kit form, requiring some 100 h for completion, for around $6000 in 1982, the exact price depending on the options selected from a long list including bubble canopy, parachute systems, lights, instruments, skis, Tedlar wing covering and a trailer.

Powered by a Rotax 447 it cruises at around 45-50mph at only 4700rpm and uses around eight litres per hour. You can up the cruise to 60-65mph. The hull is constructed of fibreglass and Kevlar, the wing has a fibreglass D-section leading edge and covered with sail cloth, and a carbon fibre capped spar. Wing attach fittings are titanium, and with extensive use of stainless steel and anodised aluminium in a majority of the rest of the metal fittings this is a very low maintenance airframe even if operated in the sea.

Gallery

Engine: KFM 107, 25 hp at 6280 rpm.
Propeller diameter and pitch 52×22 inch, 1.32×0.56m.
V belt reduction, ratio 2.1/1.
Max static thrust 170 lb, 77 kg.
Power per unit area 0.16 hp/sq.ft, 1.7 hp/sq.m.
Fuel capacity 5.0 US gal, 4.2 Imp gal, 18.9 litre.
Length overall 15.2 ft, 4.62 m.
Height overall 4.8ft, 1.44m.
Wing span 32.0ft, 9.75m.
Chord at root 5.0ft, 1.52m.
Chord at tip 3.0ft, 0.91m.
Dihedral 3 degs.
Canard span 12.0ft, 3.65m.
Canard chord 2.5 ft, 0.76 m.
Fin height 3.0 ft, 0.91 m.
Total wing area 155 sq.ft, 14.4 sq.m.
Main wing area 128 sq.ft, 11.9sq.m.
Canard area 27.0 sq.ft, 2.5 sq.m.
Total spoiler area 4.0 sq.ft, 0.37 sq.m.
Fin area 10.0ft , 0.93 sq.m.
Rudder area 8.0 sq.ft, 0.74 sq.m.
Main wing aspect ratio 8.0/1.
Wheel track 6.3ft, 1.93m.
Wheelbase 10.2ft, 3.09m.
Nosewheel diameter overall 11 inch, 26 cm.
Main wheels diameter overall 11 inch, 26 cm.
Floats, dimensions 2.4 x 14.0 ft, 0.71 x 4.26 m.
Empty weight 247 lb, 112kg.
Max take off weight 500 lb, 227kg.
Payload 253 lb, 115kg.
Max wing loading 3.22 lb/sq.ft, 15.8 kg/sq.m.
Max power loading 20 lb/hp, 9.1 kg/hp.
Load factors +4.0, 4.0 design; +8.0, 8.0 ultimate.
Max level speed 62 mph, 100 kph.
Never exceed speed 80 mph, 129 kph.
Max cruising speed 60 mph, 97 kph.
Economic cruising speed 50 mph, 80 kph.
Stalling speed 25 mph, 40 kph.
Max climb rate at sea level 600 ft/min, 3.1 m/s.
Min sink rate 250 ft/min at 37 mph, 1.3 m/s at 59 kph.
Best glide ratio with power off 14/1 at 40 mph, 64 kph.
Take off distance 100 ft, 30 m.
Landing distance 200 ft, 60 m.
Range at average cruising speed 120 mile, 193 km.

Engine: KFM 107 ER, 22 hp.
2.1:1 reduction belt drive.
Wingspan 32ft.
Wing area 150 sq.ft.
Aspect ratio 6:1.
Length 14ft.
Empty weight 280 lbs.
Payload 250-lbs. pilot plus fuel.
Wing loading 3.2 lbs/sq.ft.
L/D 16:1.
Cruise speed 50 mph.
Stall speed 26 mph.
Vmax 60 mph.
Climb rate 600 fpm.
Fuel 5 USgal.

Engine: Rotax 447, 43 hp.
Cruise: 30-50 mph.
Stall: 26 mph.
Fuel consumption: 6.5-7 lt/hr.
Top speed: 70 mph.
Endurance: 4.5 hours.

XTC Hydrolight
Engine: 30-40 hp
Wingspan: 31 ft
Canard span: 12 ft
Wing area: 150 sq.ft
Empty weight: 220 lb
MTOW: 450 lb
Wing loading: 3 lb/sq.ft
Load tested: 4G
Max speed: 70 mph
Cruise: 25-50 mph
Stall: 20 mph
Approach speed: 30 mph
Takeoff speed: 25 mph
RPC: 600 fpm
Glide ratio: 14-1
Range 3USG: 100 mi
TO Dist land: 100 ft
Ldg dist land: 200 ft
TO Dist water: 200 ft
Ldg dist water: 100 ft
Seats: 1
Controls: 3 axis

Diaz La Estrella Errante / Wandering Star

In the 1940s, Benigno Diaz put together Cuba’s first homebuilt, assembled from plans in Popular Mechanics, with the help of a childhood friend, Roberto Gude. In 1938, Diaz and Gude used wood from fish crates and poplin from a fabric store to begin constructing the island’s first experimental aircraft. “It took us years,” Gude says. “We had to beg for every nut and bolt and piece of fabric and wood. Everything on that plane was improvised.”

The landing gear was crafted from automobile exhaust pipes. One friend, a pilot, donated a 65-hp Continental engine and the tires off a Piper J-3 Cub. After seven years, the airplane dubbed La Estrella Errante (Wandering Star) was finished. Diaz’s father was there for the 1945 maiden flight. He approached his son, put his arm around him, and said, “Benigno, are you sure you tightened all the bolts on that thing?” Diaz nodded. He climbed into the cockpit, turned the aircraft onto the grass field, and gave it power. Gaining speed, the little airplane bounced and lifted off. “It flew very well,” says Diaz, who still has a small model of his handiwork. “It was the first flight of the first homemade plane on the island.”

In 1999, the fate of that homebuilt airplane was unknown. Some say it was shipped to a military airfield in Cuba. “We heard it was there in mothballs, but we don’t know for sure. Someone else said the plane had been left outside on a tie-down and simply rotted.” Covered with house paint, its primitive construction “would not have stood up very long outside”.

Diamond DART-750 

The DART-750 will be a certified all composite aerobatic turboprop trainer in tandem seat configuration, equipped with Garmin G3000 avionics and the 750 shp Pratt & Whitney Canada.PT6A-25C turboprop engine.

The first flight of Diamond Aircraft‘s DART-750 aerobatic trainer took place June 12, 2023, at the company’s headquarters in Wiener Neustadt in Austria.

Piloted by Diamond’s Head of Flight Test Sören Pedersen and Senior Test Pilot Niko Daroussis, the maiden flight lasted 30 minutes and covered all basic maneuvers, including performance and handling checks.

“The aircraft and all tested parameters did meet or exceed all expectations,” company officials said in a press release.

The aircraft was expected to be certified by EASA in 2024, with FAA certification soon after.

Diamond DA62

In developing this airplane, Diamond Aircraft founder and CEO Christian Dries challenged his team to create a simple-to-operate, fuel-efficient twin and wrap it around a passenger compartment mimicking the latest luxury SUVs. With its third-row seating option, oversize doors and seats that fold flat to accommodate bulky items, the DA62 is a utility vehicle.

The DA62s twin 180-horsepower Austro AE330 diesel engines burn less than 10 USgallons per hour per side at maximum continuous power, propelling the airplane to a top speed of around 200 knots. At 75 percent power and the speed is 187 ktas, but fuel burn drops to 7.4 gph per side.

The DA62’s diesel engines are encased in cowlings that seem oddly misshapen, a result of packaging Mercedes-Benz diesel car engines on an airplane.

The DA62 has the same center control stick, throttle placement and cockpit display layout as the Diamond DA40 and DA42. Round-dial backup instruments have been replaced with an electronic standby instrument with emergency battery. The seats are leather with seatback adjustments, but they don’t move fore and aft. Instead, the rudder pedals can be adjusted forward and back to accommodate a variety of pilots. An armrest is in the center of the cockpit between the pilots.

The DA62’s three large gull-wing doors and the forward-folding seats, plus smart placement of handholds, make entry and exit from the DA62 easy. There are cup holders for the front-seat occupants and a variety of LED interior lighting options throughout the cabin. Options include air conditioning, a 36-gallon aux fuel tank, Garmin weather radar and satellite data receiver, and Avidyne TAS600 traffic advisory system. New for the DA62 is an upgraded metallic paint option that lets buyers choose colors other than the standard white found on many carbon-composite aircraft.

It features aluminum fuel tanks sandwiched between the carbon-fiber main wing spars for crashworthiness, and incorporates Diamond’s trademark high-impact fixed seats that are attached to strategically located crush points in the floor. The composite monocoque cabin design was borrowed from the Formula 1 racing world. The airplane has undergone crashworthiness testing similar to what is -performed in the auto industry. The DA62 also offers full icing protection with its TKS weeping wing option.

The U.S. spec version offers a 5,071-pound gross weight (versus 4,400 pounds for the European version to avoid the ATC fees levied on heavier airplanes) and a 1,300-nautical-mile range with a full-fuel payload of over 1,000 pounds. Its 2.0-liter Austro compression ignition engines, meanwhile, sip jet-A fuel and a 13,000-foot single-engine service ceiling (at max gross weight) and turbocharged power. There are two baggage compartments in the nose that can accommodate full-size suitcases, golf bags and more. The DA62’s useful load in the international spec version is 1,609 pounds.

At $1.08 million (2016) for the U.S. model before typical options, the DA62 compares well with the competition. The short engine overhaul interval is 1,000 hours at the moment for the new Austro AE330s. Based on the Mercedes-Benz diesels in B-class automobiles, the engine is a proven design, and the 1,000-hour limitation is projected to be short-lived as Diamond gains experience with the aero engine. The company hopes to increase TBO to as high as 2,400 hours eventually. Other required engine maintenance, meanwhile, includes inspection of the generators at 300 hours, and replacement of the high-pressure fuel pump and inspection of the two-mass flywheel at 600 hours.

The Diamond DA62 options include third-row seating accommodating seven people, increased 5,071-pound maximum takeoff weight, built-in oxygen, air conditioning, TKS icing protection, Garmin GWX 70 weather radar and GSR 56 satellite data receiver, Avidyne TAS600 traffic advisory system, 36-gallon auxiliary fuel tank, metallic paint and more.

The DA62 earned its type certification in Europe in April 2015.

The airplane is simple to operate. The engine start procedure involves hitting the master switch, flipping the engine master on, waiting a moment to ensure the glow plug annunciation is out and then pushing the engine start button. That’s it. The Austro diesels come to life in an instant as the dual-channel full authority digital engine controls (fadec) manage rpm and continuously check for faults while the only other job is to glance at the oil pressure indication. As long as the gauges are in the green, it’s good to go.

The before-takeoff run-up procedure is stress free. It involves setting the parking brake, manually selecting the A and B channels of the electronic engine control units (EECU) to ensure both are online, and then pushing and holding the engine run-up buttons. The AE330’s fadec computers automatically increase power to 1,950 rpm and perform a number of health checks, including cycling the props. The throttles never physically move and there aren’t any prop levers to move in the first place. If no fault messages appear on the Garmin G1000 primary flight display when the test sequence is completed, you’re ready for departure.

Rotation is at 80 knots, climb is at 110 kias, and the DA62 cruise climb speed is 128 kias. The left is the critical engine in the DA62 and the ¬propeller automatically feathers. The single-engine best rate-of-climb airspeed is 87-knot (blue line).

Max continuous power of 95 percent at 14,000 feet gives around 195 ktas with the twin AE330s burning 18.6 gph. 60 percent power shows 170 ktas and 11.8 gph fuel consumption. With one engine-out, at 100 knots in level flight, fuel burn is 3.6 gph. Even with less than half fuel on board, at this rate the flight endurance would still be more than 11 hours.

By design, pilot workload is low in all flight regimes. Fitted with the latest generation of Garmin G1000 avionics with synthetic-vision technology (SVT) and electronic stability and protection (ESP), plus a three-axis Garmin GFC 700 autopilot and GWX 70 weather radar, there’s an argument to be made that the DA62 is the among the most capable and easiest-to-fly piston airplanes ever produced.

Landing targets 90 knots on final with full flaps selected. Max demonstrated crosswind component with full flaps in the DA62 is 25 knots, slightly better than in the DA42, even with its slender wing spanning nearly 48 feet.

Gallery

2016 Diamond DA62
Standard price: $1.08 million
Engines: 2 x Austro Engines AE330, 180 hp
Props: MT 3-blade 76 inches)
Wingspan: 47 feet 10 inches
Wing area: 184.1 square feet
Length: 30 feet 1 inch
Height: 9 feet 3 inches
Wing loading: 27.54 lb/sq.ft
Power loading: 14.08 lb/hp
Max takeoff weight: 5,071 lb
Standard empty weight: 3,461 lb
Max useful load: 1,609 lb
Payload with full fuel: 1,021 lb
Max usable fuel: 86.4 USgallons (with aux tanks)
Max rate of climb: 1,346 fpm
Single-engine rate of climb: 288 fpm
Service ceiling: 20,000 ft
Max speed: 204 kias
Cruise speed: (14,000 feet, max cont. power) 193 kias
Max range: 1,275 nm
Stall speed (clean): 70 kias
Stall speed (full flaps): 64 kias
Takeoff distance: 1,265 ft
Takeoff distance over 50 ft: 2,097 ft
Landing distance: 1,259 ft

Diamona HK36 / Hoffman HK-36 Super Dimona

Diamona HK36

The H-36 Dimona side-by-side two-seat motor glider was designed by Wolff Hoffmann, who left Scheibe to form his own company, Hoffmann Flugzeugbau, to put the Dimona into production at Friesach in Austria, where production was due to start in the summer of 1981. Design work began in 1979 using the Worthmann FX63 137 wing profile. The all-fiberglass two-place self-launching HOAC (formerly Hoffmann) Dimona features a folding wing design which allows two people to fold both wings in several minutes and reduce the aircraft hanger space requirement to no more than that of a sailplane trailer. The Limbach engine drives a Hoffmann 2 blade, 3 position propeller. Of glassfibre construction, the Dimona is a low wing monoplane with a T-tail and a fixed tailwheel undercarriage with spats on the main wheels. The wings can be folded alongside the fuselage and are fitted with air brakes. The cockpit canopy hinges upward for entry, and there are two rear windows. The 80hp Limbach SL2000 EB1 ‘flat four’ engine drives a Hoffmann three-position two blade propeller, and a special engine suspension is featured to ensure low noise and vibration levels.

The prototype made its first flight on 9 October 1980, on sale since summer 1981; some 50 Dimonas had been ordered by the spring of 1981.

The Hk 36 Super Dimona has the wing span increased to 16.2 m. with carbon fiber spar and modified fuselage. It is also offered with wingtip extensions to give a span of 17.6 m. Approach control is with top surface Schempp-Hirth type airbrake. In addition to the Limbach, it is offered with a Rotax 912 A of similar power, or a more powerful Limbach L 2400 EB. Dimonas have been manufactured in Germany and Austria, and is Air Transport Certified.

The two-place self-launching glider, a development of the HOAC HK 36 Super Dimona, is produced in four varieties, the HK 36TC with an 60 kW/ 81 bhp engine and tailwheel landing gear, the HK 36TC with the same engine and tricycle gear, the 86 kW/ 115 bhp HK 36TTS with tailwheel gear, and the HK 36TTC with the same engine and tricycle gear. The variants with the larger engine have the capability of towing lighter sailplanes. The wings fold back to stand vertically parallel with the fuselage for storage.

Hoffman HK-36R Super Dimona

Gallery

Hoffmann H-36 Dimona
Engine: Limbach SL2000 EB1, 80hp
Propeller: Hoffmann three-position two blade
Span: 52 ft 6 in
Length: 22 ft 5.75 in
Height: 5 ft 3 in
Wing area: 163.6 sqft
Aspect ratio: 16.8
Empty weight: 882 lb
Max take-off weight: 1,433 lb
Max speed: 130 mph (power on)
Economical cruising speed: 112 mph
Min sinking speed: 2.95 ft/sec at 50 mph
Best glide ratio: 27:1 at 65 mph (power off)
Max rate of climb at sea level: 689 ft/min
Max range: 621 miles

Diamond HK36
Wing span: 16m / 52.5ft
Wing area: 15.24sq.m / 164sq.ft
Empty Weight: 497kg / 1096lb
Payload: 243kg /538lb
Gross Weight: 740kg /1631lb
Wing Load: 48.56kg/sq.m /10.34lb /sq.ft
Aspect ratio: 16.8
L/DMax: 27 @ 105 kph / 57 kt / 65 mph
No. of Seats: 2
MinSink: 0.91 m/s / 3.0 fps / 1.78 kt
Airfoil: Wortmann FX 63-137
Structure: CFRP
Engine: 60 kW/ 80 bhp Limbach L2000 EB1C

Super Diamona HK36
Wing span: 16.2m / 53.1ft
Wing area: 15.24sq.m / 164sq.ft
Empty Weight: 497kg / 1096lb
Payload: 243kg / 538lb
Gross Weight: 48.56kg / 10.34lb
Aspect ratio: 16.8
No. of Seats: 2
L/DMax:27 @ 105 kph / 57 kt / 65 mph
Airfoil: Wortmann FX 63-137
MinSink:0.91 m/s / 3.0 fps / 1.78 kt
Engine: Rotax 912A/ 67 kW/90 bhp Limbach L2400 EB
Structure: GFRP/CFRP

Diamond Katana C1
Price: $123,900
Engine:Cont. IO-240, 125 hp@2700 rpm
TBO hrs.: 2000
Fuel type:100/100LL
Propeller make/type: MT Fixed
Landing gear type: Tri/Fixed
Max ramp weight (lbs.): 1650
Gross weight (lbs.): 1650
Max landing weight (lbs.):1650
Empty weight, std. (lbs.): 1163
Useful load, std. (lbs.): 487
Payload, full std. fuel (lbs.): 337
Usable fuel (gals.): 25
Wingspan: 35 ft. 8 in.
Overall length: 23 ft. 6 in.
Height: 7 ft. 2 in.
Wing area (sq. ft.):125
Wing loading (lbs./sq. ft.): 13.2
Power loading (lbs./hp.): 13.2
Wheel base: 5 ft. 6 in.
Wheel track: 6 ft. 3 in.
Seating capacity: 2
Cabin width (in.): 42
Baggage capacity (lbs.):44
Cruise speed (kts.): 75% power @ 24,000 ft.: 132
Max range (w/ reserve) (nm): 75% power: 482
Fuel consumption (USgph): 75% power: 5.0
Estimated endurance (65%) (hrs): 4.5
Stall speed (flaps up) (knots): 42
Stall speed (flaps down) (knots): 34
Best rate of climb (fpm): 1105
Service ceiling (ft.): 13,000
Takeoff over 50-ft. obstacle (ft.): 1263
Landing over 50-ft. obstacle (ft.): 1235

HK36 Katana Xtreme TS
Wing span: 16.6m / 54.5ft
Wing area: 15.33sq.m / 165sq.ft
Empty Weight: 539kg / 1189lb
Payload: 231kg / 509lb
Gross Weight: 770kg / 7698 lb
Wing Load: 51.53kg /sq.m / 10.29lb/sq.ft
No. of Seats: 2
MinSink: 1.14m/s / 3.75 fps / 2.2 kt
L/DMax: 28
Structure: GFRP/CFRP

HK36 Katana Xtreme TTS
Wing span: 16.6m / 54.5ft
Wing area: 15.33sq.m / 165sq.ft
Empty Weight: 539kg / 1189lb
Payload: 231kg / 509lb
Gross Weight: 770kg / 1698lb
Wing Load: 51.53kg/sq.m / 10.29lb/sq.ft
No. of Seats: 2
L/DMax:28
MinSink:1.14 m/s / 3.75 fps / 2.2 kt
Engine: 86 kW/ 115 bhp Rotax 914F
Structure: GFRP/CFRP

HK36TTC-ECO
Seats: 2.