Diamond DA20 Katana
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.
The Katana’s fuselage is built as one piece from glass reinforced plastic (GRP), with local ar-eas 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 wingis 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 el-evator 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-retractable 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.
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
Engine: Rotax 912F-1, 81 hp.
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
Empty weight, typical: 1,166 lb
Maximum gross weight: 1,654 lb
Fuel capacity, std: 25 US gal / 93 li-tres (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
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