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”.
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.
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.
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.
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
Engine Williams FJ33-4A-19 turbofan Length 35 ft 1 in Height 11 ft 7 in Wing Span 37 ft 6 in Cabin seating 2 + 3 Pressurization 5.5 psi Cabin altitude 8,000 ft @ FL250 Maximum ramp weight 5,690 lbs Useful load 2,240 lbs Maximum fuel 1,740 lbs Maximum cruise speed 315 ktas Certified ceiling 25,000 ft Time to climb to 25,000 feet 15 min Long range cruise speed 240 ktas Maximum range 1,350 nm
Austria-based Diamond Aircraft announced a change in direction for its DA50 aircraft program, which Diamond introduced in 2017 with five-, six-, and seven-seat variants. Diamond says after spending 2018 re-evaluating all its ongoing projects, it decided to change the DA50’s “engine concept.” As such, Diamond was partnering with Continental Aerospace Technologies to equip the DA50 with Continental’s 300-horsepower CD-300 Jet-A1 engine. Initial ground tests of the DA50 with the new engine occurred 15 March 2019, and the first flight with the new engine happened March 22, marking the official start of the aircraft’s flight test program with the CD-300.
DA50 using a 300-horsepower Continental CD-300 Jet-A1 engine
Diamond Aircraft determined that the CD-300 engine aligned with Diamond’s jet fuel philosophy and that it is a suitable solution for the DA50. Certified in December 2017, the CD-300 is the third platform in Continental’s Jet-A fuelled piston engine line up.
In 2020 Diamond Aircraft offered the DA50 RG. The first production aircraft to be fitted with a CD-300 powerplant. The DA50 RG is powered by a 300hp turbocharged Continental CD-300 V6 diesel.
DA50 RG
In the design phase, close attention was paid to drag reduction, and the aircraft features a retractable undercarriage.
Hinged, double slotted flaps provide high lift and excellent slow speed behaviour. The aeroplane has five seats, including a 60/40 folding back seat with a separate cargo bay hatch. Entry and exit are through big gull-wing doors.
DA50 RG
The aircraft’s avionics include Garmin’s G1000 NXi flight deck with the GFC700 Automated Flight Control System.
Options include a removable right-hand control stick, oxygen system, electric air conditioning, TKS de-icing system, Garmin GCU 476 keypad and a built-in tablet mount.
The aircraft is currently undergoing type certification with EASA, with approval anticipated by late summer of 2020. FAA certification is expected by the end of 2021.
DA50 Magnum Engine Austro Engine AE 300 2.0 l turbo-diesel,170 hp Fuel Jet A1 Propeller MT 3-blade Constant Speed Cruise speed 150+ kts Fuel consumption 9 USgph max power Fuel consumption 6-7 gph cruise Certified altitude 18,000 ft Maximum takeoff weight (MTOW) 3,262 lbs Seating 4 Cabin width 52 inches Doors 3
Diamond’s DA42 Twin Star (now referred to only as the DA42 because of a lawsuit by Aérospatiale) is an all-composite four-seater with twin turbocharged diesel engines that can operate on automotive diesel or Jet A1 fuel. At takeoff the engines develop full power at a quiet 2,300 rpm, and feature automatic prop (FADEC) control and autofeather. The Twin Star was designed to incorporate the Garmin G1000 all class cockpit from the beginning, and trailing landing gear give the twin a smooth transition to landing and taxi. Optional equipment available for the DA42 include oxygen, anti/de-ice and air conditioning.
The first flew on 9 December 2002.
2007 Diamond DA42 Twin Star Engines: Thielert TAE Centurion 1.7, 135 hp@SL to 10,000 feet TBO hrs.: 1000/2400 Fuel type: Diesel/Jet A1 Propeller type: MT 3-blade Landing gear type: Tri./Retr. Max ramp weight (lbs.): 3935 Gross weight (lbs.): 3935 Landing weight (lbs.): 3935 Empty weight, std. (lbs.): 2761 Useful load, std. (lbs.): 1174 Payload, full std. fuel (lbs.): 839 Useful fuel (gals.): 50 Oil capacity (qts.): 8 Wingspan: 44 ft. Overall length: 28 ft. 1 in. Height: 8 ft. 2 in. Wing area (sq. ft.):177.2 Wing loading (lbs./sq. ft.): 22.2 Power loading (lbs./hp.): 14.6 Seating capacity: 4 Cabin doors: 2 Cabin width (in.): 46 Cabin height (in.): 50 Cruise speed (kts.): 80% power: 172 Max range (w/ reserve) (nm): 60% power: 1129 Fuel consumption (USgph): 80% power: 12.5 Turbo critical altitude (ft.): 8000 Vso (kts.): 56 Best rate of climb, SL (fpm): 1280 Service ceiling (ft.): 18,000 Takeoff ground roll (ft.): 1130 Takeoff over 50-ft. obstacle (ft.): 1730 Landing ground roll (ft.): 1069 Landing over 50-ft. obstacle (ft.): 1877
DA42-L360 Engine 2x Lycoming I0-360 counter rotating, 180 hp Propellers 2x MT 3-blade constant speed full-feathering propeller (counter-rotating) Airworthiness category Normal Length 28 ft 1 in Height 8 ft 2 in Wing span 44 ft Maximum take-off weight 3,935 lbs Useful load 1,180 Fuel capacity, total / usable 79 gal / 76 gal Fuel 100 LL Avgas Take-off distance, 50-foot obstacle 1,500 ft Landing distance, 50-foot obstacle 1,877 ft Rate of climb, sea level 2,000 fpm Maximum demonstrated operating altitude: 18,000 ft Maximum single-engine ceiling (standard day): 7,500 ft + Maximum cruise speed: 180+ ktas Economy cruise speed at 55% power: 140 ktas Maximum landing gear extension speed: 195 kias Maximum demonstrated crosswind: 20 kts Range, 55% power (30 min reserve): 700 nm
DA42-NG Engine 2x Austro Engine AE 300 turbocharged, common-rail injected 2.0 liter diesel engine with EECDU single-lever control Horsepower 170 hp Propellers 2x MT MTV-6-R-C-F / CF187-129 3-blade Constant Speed Airworthiness category Normal Length 28 ft 1 in Height 8 ft 2in Wing span 44 ft Wing area 175.3 sq ft Seats 4 Empty weight 3,119 lbs Maximum take-off weight (MTOW) 4,189 lbs Useful load 1,070 lbs Fuel capacity (standard / long range) 50 US gal / 76 US gal Fuel grades Jet A1 / Diesel Rate of climb, sea level MTOW: 1,150 fpm Rate of climb, 10,000 ft MTOW: 1,020 fpm Maximum operating altitude: 18,000 ft Maximum air speed: 192 kts IAS Cruise speed at 75% in 14,000 ft: 175 kts TAS Cruise speed @ 60% in 14,000 ft: 152 kts TAS Range, at 75%, standard / long range tank: 614 nm / 950 nm Range, at 60%, standard / long rang tank: 707 nm / 1,180 nm
DA42 TDI Engines: 2 x TAE Centurion 2.0 Turbo Diesel, 132 hp Propellers: MT 3-blade composite constant speed, full-feathering Airworthiness category: Normal Length: 28 ft 1 in Height: 8 ft 2in Wing Span: 44 ft Maximum takeoff weight: 3,935 lbs Useful load: 1,174 lbs Fuel capacity, usable standard: 50 US gal Fuel capacity, usable extended: 72 US gal Fuel: Jet A-1 Takeoff distance, ground roll: 1,130 ft Takeoff distance, 50-foot obstacle: 1,730 ft Landing distance, ground roll: 1,069 ft Landing distance, 50-foot obstacle: 1,877 ft Rate of climb, sea level: 1,280 ft/min Maximum operating altitude: 18,000 ft Maximum SE ceiling (standard day): 10,000 ft Cruise speed at 80%: 168 kts/12.5 gal/hr total Economy at 60%: 151 ktas/8.8 gal/hr total Stall speed, full flaps gear down: 56 kias Stall speed, clean: 62 kias Maximum landing gear operating speed: 194 kts Maximum demonstrated crosswind: 20 kts Range, at 80% extended fuel: 917 nm Range, at 60% extended fuel: 1,129 nm
An all composite light aircraft. There is a display showing percentage power as well as engine RPM. Dual control sticks instead of wheels allow for better instrument placement on the panel. Control stick actuation is by push rods in¬stead of the more conventional cables and implies a lower maintenance cost. The panel itself is modular allowing for improved main¬tenance access The DA-40 seats four people comfortably. A forward hinged canopy allows access for the pilot and front seat passenger, with a separate access for the rear passengers via a gull wing door in the left fuselage side The cabin struc¬ture contains a carbon fibre roll bar aft of the front seats for crash protection. There is plenty of headroom and legroom for all occupants. As in the Katanas the front seats are fixed in position, but don’t have quite the same reclined aspect as in the Katana. Rudder pedals can be easily adjusted.
At the 2004 Sun’n Fun Diamond showed the DA40-FP. A fixed pitch version of the DA40-180 DiamondStar, powered by a Lycoming O-360-A4D 180 hp, with a fixed pitch metal Sensenich prop.
In 2006 220 Diamond Star four-seaters were delivered.
Diesel-powered DA 40TDI
The DA40 DiamondStar is powered by a Lycoming IO-360-M1A 180 hp engine, with a hydraulic prop governor and a constant speed prop.
DA40 CS Engine: Lycoming IO-360-M1A, 180 hp Propelller: Hartzell 2-blade aluminum constant-speed Airworthiness category: Normal and utility Length: 26 ft 5 in Height: 6 ft 6 in Wing Span: 39 ft 6 in Maximum takeoff weight: 2,645 lbs Useful load: 900 lbs (standard equipped airplane) Fuel capacity, usable (standard/optional): 40 USgal / 50 USgal Fuel: AVGAS 100LL Takeoff distance, ground roll: 1,175 ft Takeoff distance, 50-foot obstacle: 1,700 ft Landing distance, ground roll: 1,155 ft Landing distance, 50-foot obstacle: 2,093 ft Rate of climb, sea level: 1,120 ft/min
2007 Diamond Star DA40 XL Engine: Lycoming IO-360-M1A, 180 hp@SL TBO (hrs.): 2000 Fuel type: 100/100LL Propeller type: MT 3-blade CS Landing gear type: Tri./Fixed Max ramp weight (lbs): 2646 Gross weight (lbs.): 2646 Landing weight (lbs.) 2535 Empty weight, std. (lbs.): 1756 Useful load, std. (lbs.): 890 Useful fuel, ext. (gals.): 50 Payload, full std. fuel (lbs.): 602 Wingspan: 39 ft. 6 in. Overall length: 26 ft. 5 in. Height: 6 ft. 6 in. Wing area (sq. ft.): 145 Wing loading (lbs./sq.ft.): 18.2 Power loading (lbs./hp): 14.7 Wheel size (in.): 6.00 x 6 Seating capacity: 4 Cabin doors: 3 Cabin width (in.): 47 Cabin height (in.): 44 Cruise speed (kts.): 75% power: 150 Fuel consumption (USgph.): 75% power: 10 Range (nm): 75% power: 720 Range (nm): 55% power: 785 Vso (kts.): 49 Best rate of climb, SL (fpm): 1120 Service ceiling (ft.): 16,400 Takeoff distance (ft.): 1027 Takeoff over 50 ft. obstacle (ft.): 1140
DA40 XLS Engine: Lycoming IO-360-M1A, 180 hp Propeller: MT 3-blade composite constant-speed Airworthiness category: Normal and utility Length: 26 ft 5 in Height: 6 ft 6 in Wing Span: 39 ft 6 in Maximum takeoff weight: 2,645 lbs Useful load: 860 lbs (standard equipped airplane) Fuel capacity, usable: 50 gal Fuel: AVGAS 100 LL Takeoff distance, ground roll: 1,175 ft Takeoff distance, 50-foot obstacle: 1,700 ft Landing distance, ground roll: 1,155 ft Landing distance, 50-foot obstacle: 2,093 ft Rate of climb, sea level: 1,120 ft/min
2009 DIAMOND DA40 XLS Price: $348,950 Engine: Lycoming IO-360-M1A, 180 hp@SL Fuel type: 100/100LL Propeller type: 3-blade, CS, composite MT Landing gear type: Tri./Fixed Max takeoff weight (lbs.): 2645 Useful load, std. (lbs.): 860 Usable fuel, std. (USgals.): 50 Baggage capacity (lbs.): 100 Wingspan: 39 ft. 6 in. Overall length: 26 ft. 5 in. Overall height: 6 ft. 6 in. Seating capacity: 4 Cabin width (in.): 45.5 Vso (KIAS): 49 Cruise speed, 75% power (kts.): 150@10 gph Range, 75% power (nm): 720 Range, 55% power (nm): 785 Max speed (KTAS): 157 Best rate of climb, SL (fpm): 1120 Service ceiling (ft.): 16,400 Takeoff ground roll (ft.): 1175 Takeoff over 50 ft. obstacle (ft.): 1700 Landing ground roll (ft.): 1155 Landing over 50 ft. obstacle (ft.): 2093 Max demonstrated crosswind (kts.): 20 Glide ratio: 10.3:1
Engine Lycoming IO-360-M1A,180 hp Propeller MT 3-blade composite constant-speed Airworthiness category Normal and utility Length 26 ft 5 in Height 6 ft 6 in Wing Span 39 ft 6 in Maximum takeoff weight 2,645 lbs Useful load 860 lbs (standard equipped airplane) Fuel capacity, usable US50 gal Fuel AVGAS 100 LL Takeoff distance, ground roll 1,175 ft Takeoff distance, 50-foot obstacle 1,700 ft Landing distance, ground roll 1,155 ft Landing distance, 50-foot obstacle 2,093 ft Rate of climb, sea level 1,120 ft/min
A primary flight trainer based on the HK36 motor glider, with shortened wings, the addition of flaps, and a tricycle landing gear. Production com¬menced in Austria in 1993 with over 150 being produced until 1995. Diamond’s Canada operations were established in June 1992 at London, Ontario, to develop, certify and manufacture a light all-composite, two-place training aircraft. Diamond Aircraft Industries Canada division produced the HK 36 Super Dimona motorglider in four versions. Production of the DV 20 Katana two-seat lightplane stopped in Austria (first flown March 1991 as the HOAC LF 2000, becoming LF2 before DV 20), which evolved into the Diamond DA20 produced in Canada.
A primary training and sport aircraft of composite construction. Some forty changes were made to the Canadian-built Katana DA20-A1 from the original Austrian DV20. Major changes included a wider cabin, electric trim and a doubling of the electrical system capacity. The original Katana A1 was certified in 1994, with first customer deliveries beginning in January 1995. The last of this model was delivered in April 1998 with a total of 331 manufactured. Over 100 significant design changes were incorporated in the Katana DA20-C1, from the original aircraft. Production deliveries of the Katana Cl started early 1998 with a 1999 production rate of three aircraft per week.
May 2000
The Katana’s fuselage is built as one piece from glass reinforced plastic (GRP), with local areas of carbon reinforced plastic (CRP) with reinforcement in high stress areas. The total length of the aircraft is 7.17 metres (23 ft 6 in) and the skin is made of GRP laminate. The skins of the wings, however, are a GRP/foam/GRP sandwich. The wing is a Wortman laminar profile and the inner 50 percent of the wing features slotted flaps. Each wing is attached to the fuselage with three bolts. In the wing several ribs provide structure and mounting surfaces for guides and support for control bellcranks. The rudder, also made of a GRP/foam/GRP sandwich, is cable operated by dual adjustable pedals. The horizontal stabiliser and elevator are of the same construction with local GRP reinforcement. A steel control tube actuates the elevator, but centering and force gradients on the stick are assisted by two compression coil springs which are mounted concentric to the vertical push/pull tube of the elevator control system. The elevator trim function, which is operated on the central control panel, works by moving the common spring base with an electric actuator. The flaps are actuated electrically through a mechanical linkage that operates to both sides. The ailerons, on the other hand, are driven by steel control tubes and aluminium bellcranks. The landing gear is a conventional, non-re¬tractable tricycle system. The main gear struts are spring aluminium, while the nose gear strut is a steel tube sprung on an elastomeric spring pack. The castoring nose wheel is friction damped and the aircraft is steered by differential braking of the main wheels. The engine is mounted on a conventional welded steel tube frame attached to the ceramic fibre matting and stainless steel skin firewall. The maximum gross weight was increased by 66 lb on 8 April 1999 by the FAA to 780 kg (1720 lb). The Katana has a central control stick that is mounted at the front of the comfortable, and rather deep, four-point harness bucket seats. It is interesting to note that this aircraft is built for the changing Canadian weather and a heating system, as well as air vents at the lower position on the instrument panel, make for an easily controlled cockpit environment.
DA20 Engine TCM IO-240-B3B, 125 hp Propeller Sensenich 2-blade fixed pitch Airworthiness category Utility, spin certified Length 23 ft 6 in Height 7 ft 2 in Wing Span 35 ft 8 in Maximum takeoff weight 1,764 lbs Useful load 600 lbs Fuel capacity, usable 24.0 gal Fuel AVGAS 100LL Takeoff distance, ground roll 1,280 ft Takeoff distance, 50-foot obstacle 1,640 ft Landing distance, ground roll 661 ft Landing distance, 50-foot obstacle 1,360 ft Rate of climb, sea level 1,000 ft/min
DA20-A1 Engine: Rotax 912F-1, 81 hp.
DA20-C1 Engine: Teledyne Continental IO-240-B3B, 125 hp. Recommended TBO: 2,000 hr Prop: 1.75-rn dia Sensenich fixed-pitch wood-fibre. Length: 23 ft 6 in Height: 7ft 2 in Wing span: 10.87 m (35 ft 8 in). Wing area: 11.6sq.m (125 sq.ft). Wing Loading: 13.2 lb/sq ft Power Loading: 13.2 lb/hp Seats: 2. Empty weight, typical: 1,166 lb Maximum gross weight: 1,654 lb Fuel capacity, std: 25 US gal / 93 litres (91 litres usable). Fuel usage @ 2500 rpm: 20 lt/hr. Oil capacity: 6 qt Takeoff distance, ground roll: 952 ft Takeoff distance over 50-ft obstacle: 1,263 ft Max demonstrated crosswind component: 15 kt Rate of climb, sea level: 1105 fpm Cruise Speed @ 75% power, 6,000 ft: 132 ktas Endurance: 4.5 hr. Operating ceiling: 13,123 ft Landing distance over 50-ft obstacle: 1,235 ft Landing distance, ground roll: 550 ft W (best angle of climb): 60 kias Vy (best rate of climb): 75 kias Va (design maneuvering): 106 kias Vfe (max flap extended): 78 kias Vne (never exceed): 163 kias Vs (stall, clean): 42 kias Vso (stall, in landing configuration): 34 kias
2008 Diamond DA20-C1 Eclipse Base Price: US$174,495 Engine: Continental IO-240-B3B, 125 hp@SL TBO (hrs.): 2000 Fuel type: 100LL Propeller: 69-in. Sensenich FP Landing gear type: Tri./Fixed Gross weight (lbs.): 1764 Empty weight, std. (lbs.): 1164 Useful load, std. (lbs.): 600 Payload, full std. fuel (lbs.): 456 Usable fuel, std. (USgals.): 24 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.): 14.1 Power loading (lbs./hp.): 14.1 Seating capacity: 2 Cabin doors: 1 Cabin width (in.): 45 Cabin height (in.): 44 Cruise speed (kts.): 75% power: 138 Fuel consumption (USgph): 75% power: 5.5 Vso (kts.): 45 Best rate of climb, SL (fpm): 1000 Service ceiling (ft.): 13,120 Takeoff ground roll (ft.): 1280 Takeoff over 50 ft. obstacle (ft.): 1640 Landing ground roll (ft.): 661 Landing over 50 ft. obstacle (ft.): 1360
DA20 Engine: TCM IO-240-B3B, 125 hp Propeller: Sensenich 2-blade fixed pitch Airworthiness category: Utility, spin certified Length: 23 ft 6 in Height: 7 ft 2 in Wing Span: 35 ft 8 in Maximum takeoff weight: 1,764 lbs Useful load: 600 lbs Fuel capacity, usable: 24.0 USgal Fuel: AVGAS 100LL Takeoff distance, ground roll: 1,280 ft Takeoff distance, 50-foot obstacle: 1,640 ft Landing distance, ground roll: 661 ft Landing distance, 50-foot obstacle: 1,360 ft Rate of climb, sea level: 1,000 ft/min
