Katana DA20-A 1
Diamond DA20-A1 Katana · Pilot's Operating Handbook
Overview
The document is a Pilot's Operating Handbook (POH) for the Diamond DA20-A1 Katana, a two-seat aircraft designed primarily for flight training. It provides detailed specifications, performance data, and operational guidelines for pilots. The DA20-A1 features a composite structure, a low wing configuration, and is powered by a Bombardier Rotax 912F3 engine. This handbook is essential for understanding the aircraft's capabilities, limitations, and maintenance requirements, ensuring safe and effective operation.
- Maximum gross weight: 1,609 lb
- Empty weight: 1,095 lb
- Fuel capacity: 20.1 gal (19.5 gal usable)
- Takeoff distance over 50-ft obstacle: 1,560 ft
- Rate of climb: 680 fpm at sea level
- Service ceiling: 14,000 ft
- Max demonstrated crosswind component: 15 kt
Document
Source
Originally published by aeroresourcesinc.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Pilot's Operating Handbook
- Pages
- 2
- File size
- 1.2 MB
- Publisher
- aeroresourcesinc.com
Specifications & performance
Extracted from this document.
Specifications
- Engine (hp)
- 81
- Height (ft)
- 6
- Length (ft)
- 23
- Propeller
- Hoffmann HO-V352F
- Wingspan (ft)
- 35
- Engine model
- Rotax 912F3
- Max speed (kt)
- 117
- Cruise speed (kt)
- 117
- Empty weight (lb)
- 1,095
- Fuel capacity (gal)
- 20.1
- Rate of climb (fpm)
- 680
- Service ceiling (ft)
- 14,000
- Max takeoff weight (lb)
- 1,609
Performance
- Fuel burn (gph)
- 4.3
- Landing over 50ft
- 1,490
- Max crosswind (kt)
- 15
- Takeoff over 50ft
- 1,560
- Landing distance (ft)
- 748
- Takeoff distance (ft)
- 1,120
- Stall speed clean (kt)
- 41
- Stall speed landing (kt)
- 37
V-speeds
- VA
- 104
- VR
- 65
- VX
- 57
- VY
- 65
- VFE
- 81
- VNE
- 161
- VNO
- 118
- VS1
- 41
- VSO
- 37
Weight & balance
- Useful load (lb)
- 394
- Basic empty weight (lb)
- 1,095
- Max takeoff weight (lb)
- 1,609
Common. Rarer than 8% of the aircraft models we track.
Most owners only have the POH. Here's the essential set for the Diamond DA20-A1 Katana.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
Free — save the DA20-A1 Katana to your watchlist and track it in one place.
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- Diamond DA20 / DV20 Engine and Propeller conversionFlight Manual
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- SERVICE BULLETIN INDEXService Bulletins
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In this document
Specifications
The DA20-A1 Katana has a length of 23 ft 6 in, height of 6 ft 11 in, and a wingspan of 35 ft 7 in. It has a maximum gross weight of 1,609 lb and an empty weight of 1,095 lb, allowing a payload of 394 lb with full fuel. The fuel capacity is 20.1 gallons, with 19.5 gallons usable. The oil capacity is 3.2 quarts.
Performance
The aircraft has a takeoff distance of 1,120 ft over ground and 1,560 ft over a 50-ft obstacle. The maximum demonstrated crosswind component is 15 knots. It has a rate of climb of 680 feet per minute at sea level and a service ceiling of 14,000 ft. The landing distance over a 50-ft obstacle is 1,490 ft, with a ground roll landing distance of 748 ft.
Limiting and Recommended Airspeeds
Key airspeeds include Vx (best angle of climb) at 57 KIAS, Vy (best rate of climb) at 65 KIAS, Va (design maneuvering) at 104 KIAS, Vfe (max flap extended) at 81 KIAS, Vno (max structural cruising) at 118 KIAS, Vne (never exceed) at 161 KIAS, Vs (stall clean) at 41 KIAS, and Vso (stall in landing configuration) at 37 KIAS.
Powerplant
The DA20-A1 is powered by a Bombardier Rotax 912F3 engine, producing 81 hp. It is a four-cylinder, horizontally opposed engine featuring liquid cooling, dual ignition, and a dry sump lubrication system. The propeller is a Hoffmann HO-V352F, a hydraulically controlled, constant speed propeller.
Fuselage and Wings
The fuselage is constructed of glass reinforced plastic (GRP) with carbon reinforced plastic (CRP) in high-stress areas. The wings feature a Wortman FX 63-137/20 HOAC laminar profile and include electrically actuated flaps for takeoff and landing.
Safety notes
- All specifications are subject to change without notice.
- Illustrations may show optional equipment.
Full document text
Katana DA20-A 1 All specifications are subject to change without notice. Illustrations may show optional equipment. Powerplant Bombardier Rotax 912F3. 81 hp. four-cylinder, horizontally opposed Specifications Recommended TBO 1.200 hr Length 23 ft 6 in Height 6 ft 11 in Wingspan 35 ft 7 in Wing Area 125 sq ft Wing Loading 12.9 Ib/sq ft Power Loading 19.7 Ib/hp Seats 2 Empty weight, typical 1,095 Ib Maximum gross weight l ,609 Ib Payload w/full fuel 394 Ib Fuel capacity. std 20.1 gal 119.5 gal usable} Oil capacity 3.2 qt ..• . , "(\to' ... ..• Performance Takeoff distance, ground roll 1.120 ft Takeoff distance over 50-ft obstacle l,560 ft Max demonstrated crosswind component 15 kt Rate of climb, sea level 680 fpm Cruise speed/fuel consumption 7,500 feet @ 75% power, best economy 117 kt/4.3 gph Service ceiling 14.000 ft Landing distance over 50 ft obstacle 1,490 ft Landing distance, ground roll 748 ft Limiting and Recommended Airspeeds Vx (best angle of climb) 57 kias Vy (best rate of climb) 65 kias Va (design maneuvering) ..104 kias Vfe (max flap extended) 81 kias Vno (max structural cruising) 118 kias Vne (never exceed) 161 kias Vs (stall. clean) .41 kias Vso (stall. in landing configuration) 37 kias Printed in Canada Dimensions ore approximate - for Reference Only. Dimensions are in mm [feet-inches). AFTER SALE & CUSTOMER SUPPORT Technical & Parts Support Factory technicians available 7 days a week for technical and A.O.G. parts support. Maintenance Training A five day course, comprised of four days of engine, propeller and airframe systems/troubleshooting procedures. and one day of com- posite theory and practical repair workshop. Field Service Support Factory technician network available for onsite training, troubleshooting. and repairs. Warranty Airframe: 2 year "tip to tail" parts and labor warranty with unlimited hours. 10 year, 12,000 hr warranty on major structural components. Engine: 1 year or 200 hrs parts and labor. Parts prorated to TBO. Propeller: 1 year or 500 hours parts and labor prorated to TBO. Avionics: Manufacturer's warranty. Repair and overhaul Engine: overhaul and factory exchange engines available. includ- ing "firewall forward" quick engine changes (QEC). Propeller: overhaul and factory exchange propellers available. A1RS·1097 Katana DA20-A 1 Instrument Panel 17. Taxi Light Switch 18 Nav. Light Switch 19. Avionics Master 20. Master Switch 21. Ignition Switch 22. Flap Control 23. Compass Card 24. Trim Indicator 25. Annunciator Lights 26. Hobbs Meter 27. Not used 28. Radio 29. Transponder 30. Not Used 31. Intercom 32. Manifold Pressure The DA20-A 1 Katana is a two seat aircraft designed and manu- factured by Diamond Aircraft Industries of London, Canada. It is principally intended for primary flight training. The DA20-A 1 Katana features advanced composite structure, single engine, conventional configuration with low wing, T-tail, and tricycle landing gear. The design of DA20-A 1 Katana is based on the DV20 Katana, designed and manufactured by Diamond (HOAC) Aircraft of Austria. The DV20 was type certified by Austrian and German Airworthiness Authorities in 1993, and by Canadian and American Airworthiness Authorities in 1994. The principal differences are detail design improvements and changes to facilitate production with usage of North American standard parts and materials. Approval The Katana is currently certified for day/night VFR operations and spin- ning in Canada and the United States as well as being certified by Airworthiness Authorities in the United Kingdom, Austria, Germany, Switzerland, Holland, Turkey, Portugal, France, Australia, Denmark, Czech Rep., Italy, Russia, and South Africa. Fuselage The fuselage is of GRP (Glass Reinforced Plastic) construction with local CRP (Carbon Reinforced Plastic) reinforcement in high stress areas. The stressed fuselage skin is primarily made of single GRP laminate with local GRP/PVC- foam/GRP sandwich construction to increase stiffness and reduce noise. The two fuselage shells (halves) are bonded together along the joint flange in the vertical plane. Internal structure consists of the firewall, a number of transverse bulkheads, a longitudinal bulkhead in the tail tube (cone), and a main bulkhead (spar bridge) that receives the wing spar stubs. The vertical stabilizer is integrated with the fuselage. The fixed seat shells are of GRP construction (rudder pedals are adjustable). Aft of the seats a baggage compartment is provided. Baggage is secured with a fabric net. The fuel tank is located beneath the baggage Printed in Canada compartment. The one-piece canopy provides excellent visibility and tilts up and back to provide unrestricted cockpit access. Wings The wing section is a Wortman FX 63-137/20 HOAC laminar profile. The inner 50% of the wing span features flaps for take-off and land- ing. Each wing is attached to the fuselage with three bolts: two transverse at the root rib, and one longitudinal through the spar bridge and the wing spar stub. The wing skins are of GRP/FOAM/GRP sandwich construction. The I-section spar is constructed of CRP poltruded spar caps that are joined with a GRP/FOAM sandwich construction spar web. Several ribs provide mounting surfaces for guides of control tubes and support for control bellcranks. The flaps are actuated electrically via mechanical linkages that also provide synchronization. The ailerons are actuated via steel control tubes and aluminum bellcranks. The left wing approximately one foot inboard of the wing tip houses individual quartz halogen landing and taxi lights. Landing Gear The conventional tricycle landing gear is non-retractable. The main gear struts are aluminum. The nose gear strut is steel tube sprung via an elastomeric spring pack. Steering is provided by dif- ferential braking of the main wheels and the friction damped castoring nose wheel. Powerplant The engine is a Rotax 912F3 with
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a take-off power rating of 81 HP (DIN). The 912F3 is a horizontally opposed 4-cylinder, 4-stroke engine. It features liquid cooled cylinder heads, dual ignition, dry sump lubrication, dual carburetors, and a propeller drive reduction gear box (2.2727: 1). The engine features an integral 20A alternator directly driven by the crankshaft and a 40A alternator which is belt driven off the pulley that is mounted to the propeller drive flange. The DA20-A 1 Katana uses the 40A alternator to power avionics, instruments and electrical accessories. The integrated 20A alternator is used exclusively to power the dual capacitance 1. Outside Air Temp Ind. 2. Not used 3 Air Speed Ind 4. Artificial Horizon Ind 5. Altimeter 6. COI 7. Stall Warning Horn 8. Turn and Bank Ind 9. Directional Gyro 10. Vertical Speed Ind. 11. Not used 12. Microphone Jack 13. Air Vent 14. Fuel Pump Switch 15. Strobe Light Switch 16. Landing Light Switch discharge, electronic ignition system. The engine mount is of conventional welded steel tubing construction. The hydraulically controlled, 2 blade constant speed propeller is the Hoffmann HO-V352F. The prop blades are of wood core construction, with composite skins and aluminum or polycarbonate bonded edge inserts. The GRP firewall is clad with insulating Fibrefrax and stainless steel skin. Cowlings are fire protected by fire resistant paint. Empennage The rudder halves are of GRP/ foam/GRP sandwich construction. The rudder is cable actuated via dual, adjustable pedals. The hori- zontal stabilizer and elevator are GRP/Foam/GRP sandwich con- struction with local CRP reinforce- ment. The anti-servo tab is made of CRP. The elevator is actuated by steel control tubes. Centering and increased control forces are provided by two compression coil springs mounted concentric to the vertical push-pull tube of the elevator control system. The common spring base can be moved by an electric actuator 33 Tachometer 34 Oil Pressure Ind. 35. Oil Temp Ind. 36. Voltmeter 37. Cylinder Head Temp. Indicator 38. Ammeter 39. Fuel Indicator 40. Circuit breakers 41. Compass 42. Canopy Locking Warning Light 43 I·Panel Reostat 46 Trim Ind. Dimmer which provides elevator trimming function. Electrical/ Avionics Electric power (nominal 12 V) is provided by the 20 Alhr battery and the 40A alternator which fea- tures internal voltage regulation. The alternator is belt driven off the propeller shaft drive flange pulley. Electric power is supplied to the user systems via the main or avionics bus, as applicable. Circuit protection is provided by reset- table panel mounted circuit break- ers for each circuit. Instrumentation and Avionics equipment is tailored to individual customer requirements. A typical equipment suite and layout are depicted in the above diagram. Documentation The following documentation is available: • Airplane Flight Manual • Airplane Maintenance Manual • Airplane Illustrated Parts Catalogue • Miscellaneous Vendor Technical Documentation (i.e. Engine, Propeller, Avionics etc.) All specifications are subject to change without notice. Illustrations may show optional equipment. A1R5·1097