Download - DA-20 Katana
DA 20 Flight Manual < Introduction
Congratulations on your choice of the DA 20 'Katana'. We hope you will enjoy the virtual counterpart of this stunning high quality two seater airplane. It is easy to fly and has an excellent performance. A comfortable cockpit with a great view, low noise and low fuel consumption are just a few qualities that make this plane so special and successfull.
We wish you many hours of fun and enjoyment with the DA 20 'Katana'!
DEVELOPMENT TEAM
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PREFACE
DA-20
FLIGHT MANUAL
Dr. Achim BürgerMarcel FeldeHans HartmannAlexander M. Metzger
SoundsGraphics, Aircraft, ManualProgrammingAerodynamics
Authors
Diamond Aircraft Industries GmbH, Wiener Neustadt Diamond Aircraft Industries Deutschland GmbH, Egelsbach
Knuth Glass, Diamond Air Service GmbH
Markus Rheinländer and Thomas Wolff, Katana pilots
Support
Boerris Kuhn, Marco Butze, Martin Georg, Michael Garbers, Rainer Duda, Roland Pohl, Siegfried Schulz, Thomas Esser.
Beta Test Team
A big thank you to all that supported us in our work on this project - the employees of Diamond Aircraft, Diamond Air Service and Aerosoft, the pilots and testers, our families and friends that had to stand back from time to time, while we were working on this project.
0.1.
0.2.
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DA 20 Flight Manual
0.3. TABLE OF CONTENTS
GENERAL 1
Chapter
OPERATING LIMITATIONS 2
NORMAL OPERATING PROCEDURES 4
PERFORMANCE 5
WEIGHT AND BALANCE / EQUIPMENT LIST 6
DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS 7
This manual is based on the real Katana documentation. Passages and chapters that make no sense for a flight simulator addon have been left out.
All material contained in this manual is solely intended for flight simulation use and may under no circumstances be used for real-world aviation!
< Introduction
DA 20 Flight Manual
0.4. SYSTEM REQUIREMENTS
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0.5. INSTALLATION
0.6. DEINSTALLATION
< Introduction
Pentium 1 Gh128 MB RAM240 MB of free available SPACE on the hard diskSound card
A 3D video board with at least 32Mb RAM, 256 Mb RAM internal memory and a Pentium III 600 are highly recommended.
Microsoft Flight Simulator 2004 (NOT compatible with older versions) Windows 98, Windows 98 SE, Windows ME, Windows 2000, Windows XP
Adobe Acrobat® Reader 5 to read and print the manual
Available for free, download at: http://www.adobe.com/prodindex/acrobat/readstep.html
*
*
If you use Windows 2000 or Windows XP and must logging as administrator before you start the installation.
If the setup programme does not start automatically, click on START | RUN and enter "d:\setup.exe" (d represents the drive letter of your CD-ROM drive. If yours is different, please replace it with the appropriate drive letter). After you have chosen your preferred installation language, the welcome screen appears and you will be presented with some important information. Now it is time to register your version of the DA-20 Katana. Please notice, you need your login-name, login-passwort and the registration key ( or ) to install the DA-20 Katana. You will find this key in your Aerosoft Download Shop confirmation email.The installation programme will attempt to locate the correct path to Microsoft Flight Simulator 2004. If this path cannot be successfully located, or you wish to install to another location, then you will have to enter the correct path to your installation of the flight simulator manually. In order to do this, click on "Browse" and navigate to the correct path. Before the installation program starts to copy the files onto your hard disc, you will be presented with the all installation details. The installation program will now copy all files of the DA-20 Katana onto your hard disc.
www.simmarket.com www.aerosoft-shop.com
Removing the DA-20 KatanaThe DA-20 Katana can be removed at any time if you have one of the following ope- rating systems - Windows 98/ME or NT 4.0/2000 or XP. In order to completely rem- move the Katana click on the "Start" Button on the Windows task bar, choose "Settings" and then "Control Panel". Here you will see an icon named "Software". Double click on thid icon to open it and you will see a list of all installed programmes. Locate "aerosoft's - DA-20-Katana - FS2004", click once with the left mouse button and thenclick on the "add-remove" button. The deinstallation program will now begin to remove the DA-20 Katana files from you hard disc.
DA 20 Flight Manual
0.7. CONFIGURATION
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Before the first flight, an aircraft has to be configured, it is the same matter with our virtual Katana. Additionally, you need to set up some items in your flight simulator.
Settings - Realism
Engines
Enable automixture
Unlimited fuel
The Rotax 912 engine is equipped with a dual automatic altitude-compensating carburetor. To make automixture work properly, enable it under the realism settings.
Settings - International
The Outside Air Temperature display (OAT) and the altimeter pressure settings depend on the international settings of the flight simulator:
Use 'U.S. System' for OAT in '°F' and altimeter setting in 'in.Hg'.
'Metric (altimeter in feet)' will show OAT in '°C' and altimeter setting in'mbar'
Virtual cockpit - point of view
We strongly recommend not to change the point of view in the virtual cockpit. Polygons in FS disappear when they get to close to the viewer. So parts of the canopy could get invisible when you move your head up via 'SHIFT+ENTER' or Active Camera.
< Introduction
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DA 20 Flight Manual
0.8. LOADING EDITOR
PrefaceTeamThanks for Support, Betateam etc.SystemInstallationDeInstallationConfiguration(Viewpoint)Loadingtool
About DiamondAbout Katana
The Loading Editor that comes with the DA-20 Katana lets you easily configure the addon to fit your needs.
Please do not forget to save the actual configuration before you select another model type. Switching the model clears the settings for the one you have been working on.
Click on the passenger to load/unload it. This effects the exterior model and the virtual cockpit, not the 'Loading'.
Toggle Passenger
Define the weight of the pilot, passenger and the baggage. If the passenger has been made invisible as described above, there is a loading called 'sandbag' to position a weight on the right seat.
Loading
Enable or disable the GPS in the virtual cockpit. Keep in mind, that the GPS can effect the framerate of the gauges. If the instruments don't move fluently, you should disable it. There is a clickspot on the 3d GPS, that opens the GPS window.
GPS
If you find it too difficult, to control the aircraft on ground via differential braking, you can make the nose gear steerable. Well, it is not realistic at all, but it makes steering more comfortable.
Easy Ground Steering
Is Your aircraft configured and loaded? Don't forget to save the file. Flight Simulator has to be restarted.
Save
< Introduction
DA 20 Flight Manual < General
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1.1. INTRODUCTION - about Diamond Aircraft
CHAPTER 1
GENERAL
Diamond Aircraft Industries is a worldwide operating composite aircraft manufacturer with offices in major centers across North America, Europe, Japan, England, Austria, South Africa and Australia. There are two production facilities: one located in Wiener Neustadt (Austria) where head office, research and development operations are conducted, and one in London Ontario (Canada). At both facilities innovative aircraft solutions, of the highest level and quality are produced for flight schools and private operators.
The company employs over 500 people, and has already produced over 2,500 aircrafts. Diamond Aircraft Industries (Canada) is the largest general aviation manufacturer of single engine aircrafts in Canada, and the third largest in North America.
The DA20 Katana was just the beginning of a story of success. In the year 2000 began the serial production and delivery of the four-seat DA40-180 'Diamond Star'.The DA40-180 was the first general aviation aircraft (below 2.000 kg) which received international JAA certification (according to JAR 23) on October 24, 2000.
In November 2001 the DA40 TDI had its first flight. Within one year Diamond engineers have achieved what was called 'impossible' before. With the innovative, light turbo-diesel engine Centurion 1.7, made by the Thielert Aircraft Engine Company in Germany, and the appropriately modified and advanced DA40 Diamond Star, the first production aircraft worldwide with a diesel engine in this category was created.
The DA42 Twin Star, which had its maiden flight in 2002, established a new standard in performance and value for the light twin-piston market. It offers pilot workload- reducing single-lever power controls for each engine, exceptionally low fuel consumption and available all glass cockpit. The new twin also offers familiar Diamond characteristics such as dual control sticks, all composite construction, low stall speed and unparalleled visibility.
A new project was started in june 2003: The D-JET, which can carry five people up to 25,000 feet. It is powerd by an engine which has proven its reliability in thousands of operating hours and provides a speed of 315 kts.
DA 20 Flight Manual
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< General
Based on the successful DV20 Katana, Diamond Aircraft Canada developed and produced a light, two-seat airplane the DA20-A1 Katana, a training airplane that meets North American desires and needs for flight training.
In its very first year of production the Katana received the famous Eagle Award as best VLA.
All DA20-80 and DA20-100 Katanas start out as previously-owned Katana DA20-A1s and are equipped with Rotax engines. This conversion is a factory modification that is completed by qualified Diamond Aircraft technicians.
1.2. INTRODUCTION - about the Katana
1.3. WARNINGS, CAUTIONS, NOTES etc.
The following definitions apply to warnings, cautions, and notes used in the Flight Manual:
>>In Flight Simulator:
points out differences between reality and the flightsimulator, or shows how things have to be done in "virtuality".
!!CAUTION:
means that the non-observation of the corresponding procedure leads to a minor or to a more or less long term degradation of flight safety.
!!NOTE:
draws the attention to any special item not directly related to safety butwhich is important or unusual.
!!WARNING:
means that the non-observation of the corresponding procedure leads to an immediate or important degradation of the flight safety.
TIP:
a hint or an information.ii
1.4. THREE-VIEW-DRAWING OF AIRPLANE
DA 20 Flight Manual < General
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1.5. DIMENSIONS
DA 20 Flight Manual < General
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1.5.1. Overall Dimensions
Span: 10.84 m (35 ft 6.7 in)
Length: 7.17 m ( 23 ft 6.0 in)
Height: 2.11m (6 ft 11.0 in)
Airfoil: Wortmann FX 63-137/20 HOAC
Wing Area: 11.6 m2. (125 sq.ft)
Mean Aerodynamic Chord (MAC): 1.09 m (3 ft 6.9 in)
Aspect Ratio: 10.0
Dihedral: +4° nominal
Sweep of Leading Edge: +1° nominal
1.5.2. Wing
Angle of Incidence : -2.5° ±0.5°
Span: 2.65 m (8 ft 8 in)
1.5.3. Horizontal Stabilizer
Track: Track: 1.90 m (6 ft 2.8 in)
Wheel Base: 1.75 m (5 ft 8.9 in)
Tire Size: Nose: 4.00-4 (TOST)
5.00-4 (GOODYEAR)
Main: 15 x 6.00-5 (GOODYEAR)
5.00 x 5, 6 Ply (TSO C62)
1.5.4. Landing Gear
Tire Pressure: Nose: 1.8 bar (26 psi)
Main: 2.3 bar (33 psi)
1.6. ENGINE
DA 20 Flight Manual < General
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Reduction Ratio: 2.2727 : 1
Displacement: 1.211 litres. (73.9 cu.in)
Output Power: 59.6 kW (80 hp)
Rotax 912, 4 Cylinder, 4 Stroke-Engine, horizontally opposed, liquid cooled cylinder heads, air-cooled cylinders. Propeller drive via integrated reduction gear.
at 2550 RPM
1.7. PROPELLER
Constant speed, hydraulic pitch control
Range of Pitch Angle: 10° - 35°
Diameter: 1.70 m (5 ft 6.9 in)
Two-bladed variable pitch propeller, manufactured by HOFFMANN
model HO-V352F/170FQ
1.8. FUEL
Total Fuel Capacity:
Usable Fuel: 74 litres (19.5 US gal.)
76 litres (20.1 US gal.)
Unusable Fuel: 2 litres (0.6 US gal.)
Approved Fuel Grades: AVGAS 100LL
1.10. WEIGHT
DA 20 Flight Manual < General
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Maximum Take-off Weight 730 kg (1609 lbs)
Maximum Landing Weight 730 kg (1609 lbs)
Empty Weight See Chapter 6
Maximum Weight in Baggage 20 kg (44 lbs)only if restraining devices available
Wing Loading
At Maximum Take-off Weight 62.80 kg/m2. (12.86 lbs/sq.ft)
Performance Load at Max. Take-off Weight 12.24 kg/kW (20.1 lbs/hp)
1.4. LIST OF DEFINITIONS AND ABBREVIATIONS
DA 20 Flight Manual < General
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AGL: Above Ground Level
CAS: Calibrated airspeed; Indicated speed corrected for installation and instrument errors. CAS is equal to TAS at standard atmospheric conditions at MSL.
KCAS: CAS in knots.
1.11.1. Speed
IAS: Indicated airspeed as shown on the airspeed indicator.
KIAS: IAS indicated in knots.
GS: Ground Speed. Speed of the airplane relative to the ground.
TAS: True airspeed. Speed of the airplane relative to air. TAS is CAS corrected for altitude
VA: Maneuvering speed. Maximum speed at which the airplane is not overstressed at full deflection of control surfaces.
VFE: Maximum speed with flaps extended.
VNE: Speed which must never be exceeded in any operation.
VNO: Maximum structural cruising speed which should only be exceeded in calm air, and then only with caution.
VS: The power-off stall speed with the airplane in its standard configuration.
VSO: The power-off stall speed with the airplane in landing configuration.
VX: Best angle-of-climb speed.
VY: Best rate-of-climb speed.
DA 20 Flight Manual < General
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ISA: International Standard Atmosphere at which air is identified as a dry gas. The temperature at mean sea level is 15° Celsius (59° F), the air pressure at sea level is 1013.25 mbar (29.92 inHg), the temperature gradient up to the altitude at which the temperature reaches -56.5° C (-67.9° F) is -0.0065° C/m (-0.0036° F/ft) and 0° C/m (0° F/ft) above.
OAT: Outside air temperature.
AGL: Above Ground Level
Indicated Pressure Altitude: Altitude reading with altimeter set to 1013.25 mbar (29.92 inHg) air pressure.
Pressure Altitude: Altitude measured at standard pressure at MSL (1013.25 mbar / 29.92 inHg) using a barometric altimeter. Pressure altitude is the indicated altitude corrected for installation and instrument errors. Within this manual the instrument errors are assumed to be zero.
Aerodrome/Airport Pressure:
Actual atmospheric pressure at the aerodrome/airport altitude.
Wind: The wind speeds used in the diagrams in this manual should be referred to as headwind or tailwind components of the measured wind.
Take-off Power: Maximum engine power for take-off.
Maximum Continuous Power: Maximum permissible continuous engine output power during flight.
1.11.2. Meteorological Terms
1.11.3. Powerplant
DA 20 Flight Manual < General
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Demonstrated Crosswind Component:
The max. speed of the crosswind component at which the maneuverability of the airplane during take-off and landing has been demonstrated during type certification test flights.
Service Ceiling:
The altitude at which the maximum rate of climb is 100 ft/min. (0.5 m/s).
1.11.4. Flight Performance and Flight Planning
Reference Datum (RD):
An imaginary vertical plane from which all horizontal distances for the centre of gravity calculations are measured. It is the plane through the leading edge of the wing root rib, perpendicular to the longitudinal axis of the airplane.
Station:
A defined point along the longitudinal axis which is generally presented as a specific distance from the reference datum.
1.11.5. Weight and Balance
Lever Arm:
The horizontal distance from the reference datum to the centre of gravity (of a component).
Moment:
The weight of a component multiplied by its lever arm.
Centre of Gravity (CG):
Point of equilibrium for the airplane weight.
CG position:
Distance from the reference datum to the CG. It is determined by dividing the total moment (sum of the individual moments) by the total weight.
DA 20 Flight Manual < General
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Center of Gravity Limits:
The CG range which an airplane with a given weight must be operated within.
Usable Fuel:
The amount of fuel available for the flight plan calculation.
Unusable Fuel:
The amount of fuel remaining in the tank, which cannot be safely used in flight.
Empty Weight:
Weight of the airplane including unusable fuel, all operating fluids and maximum oil amount.
Useful Load:
The difference between take-off weight and empty weight.
Maximum Take-off Weight:
Maximum weight permissible for take-off.
ACL:
Anti collision light
1.11.6. Equipment
GFRP: Glass Fibre Reinforced Plastic
CFRP: Carbon Fibre Reinforced Plastic
1.11.7. Miscellaneous
1.12. CONVERSION FACTORS
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1.12.1. Length or Altitude
1 [ft.] = 0.3048 [m]
1 [in.] = 25.4 [mm]
1.12.2. Speed
1 [kts] = 1.852 [km/h]
1 [mph] = 1.609 [km/h]
1.12.3. Pressure
1 [hPa] = 100 [N/m2] = 1 [mbar]
1 [in. Hg] = 33.865 [hPa]
1 [psi] = 68.97 [mbar]
1.12.4. Weight
1 [lbs] = 0.454 [kg]
1.12.5. Volume
1 [US gallon] = 3.78 [litres]
1 [Imperial gallon] = 4.546 [litres]
DA 20 Flight Manual < OPERATING LIMITATIONS
Chapter 2 of this Flight Manual addresses the operating limitations, instrument markings, airspeed indicator markings, and the limitation placards which are necessary for the safe operation of the airplane, its engine, and standard systems and equipment.
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2.1. INTRODUCTION
CHAPTER 2
OPERATING LIMITATIONS
!!WARNING:
These limitations must be complied with for all operations.
DA 20 Flight Manual < OPERATING LIMITATIONS
2.2. AIRSPEED LIMITATIONS
IAS
IAS kts mph km/h Remarks
104 120 193
81 93 150
118 135 218
161 185 298
Do not make full or abrupt control movement above this speed, because under certain conditions the airplane may be overstressed by full control movement.
Do not exceed this speed with flaps extended.
Do not exceed this speed except in smooth air, and then only with caution,
Do not exceed this speed in any operation.
VA
Maneuvering Speed
VFE
Maximum FlapExtended Speed
VNO
Maximum StructuralCruising Speed
VNE
Never Exceed Speed
2.3. AIRSPEED INDICATOR MARKINGS
IAS
Marking kts mph km/h Explanation
37-81 43-93 69-150 Operating range with extended flaps.White Arc
41-118 47-135 76-218 Normal operating range.Green Arc
118-161 135-185 218-298 Maneuvers must be conducted withcaution and only in smooth air.
Yellow Arc
161 185 298 Maximum permissible speed for alloperating modes.
Red Line
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2.4. POWER PLANT LIMITATIONS
DA 20 Flight Manual < OPERATING LIMITATIONS
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2.4.1. Engine
(a) Engine Manufacturer : Bombardier Rotax, Gunskirchen/Austria
(b) Engine Type Designation : 912 A3 (up to aircraft S/N 10092, inclusive): 912 F3 (aircraft S/N 10093 and subsequent)
!!NOTE:
The propeller is driven by the engine via a reduction gear with a ratio of 2.2727:1. The RPM indicator indicates the propeller speed. For that reason, all speed references within this manual - contrary to the engine manual - are propeller speeds.
(c) Engine Operating Limitations
: 59.6 kW / 80 hpMax. T/O Power (5 min.)
: 2550 RPMMax. Permissible T/O RPM
: 58 kW / 78 hpMax. Continuous Power
: 2420 RPMMax. Permissible Continuous RPM
(d) Oil Pressure
: 22 psi (1.5 bar)Minimum
: 73 psi (5.0 bar)Maximum
: 102 psi (7.0 bar)Max. in case of Cold-start (short-term)
(e) Fuel Pressure
: 2 psi (0.15 bar)Minimum
: 6 psi (0.40 bar)Maximum
(f) Oil Temperature
: 122°F (50°C)Minimum
: 284°F (140°C)Maximum
(g) Cylinder Head Temperature
: 302°F (150°C)Maximum
DA 20 Flight Manual < OPERATING LIMITATIONS
(h) Fuel Specifications
: AVGAS 100LLApproved Fuel Grades
(i) Oil Grades : Name-Brand Automotive Oil
2.4.2. Propeller
(a) Propeller Manufacturer : Hoffmann Propeller, Rosenheim/Germany
(b) Propeller Type : HO-V352F/170FQ
(c) Propeller Diameter : 1.70 m in (5 ft 6.9)
(d) Propeller Pitch (at 3/4 radius) : 10° - 35°
(e) Propeller Speed Limitations
: 2550 RPMMax. T/O RPM (max. 5 min.)
: 2420 RPMMax. Continuous RPM
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Instrument Red Line =
Lower Limit
Green Arc =Normal
OperatingRange
Yellow Arc =
Caution Range
Red Line =Upper Limit
Tachometer
Oil TemperatureIndicator
Cylinder HeadTemperature
Indicator
Oil PressureIndicator
- 950-2420 RPM 2420-2550 RPM 2550 RPM
122°F
50°C
122-284°F
50-140°C
- 284°F
140°C- - - 302°F
150°C
22 psi
1.5 bar
22-73 psi
1.5-5 bar
73-102 psi
5-7 bar
102 psi
7 bar
Instrument Red Line =
Lower Limit
Green Arc =Normal
OperatingRange
Yellow Arc =
Caution Range
Red Line =Upper Limit
Voltmeter 8-11 Volts 12.5-16 Volts 11-12.5 Volts 16.1 Volts
2.5. POWERPLANT INSTRUMENT MARKINGS
DA 20 Flight Manual < OPERATING LIMITATIONS
Powerplant instrument markings and their color code significance are shown below:
2.6. MISCELLANEOUS INSTRUMENT MARKINGS
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2.7. WEIGHT
DA 20 Flight Manual < OPERATING LIMITATIONS
: 730 kg (1609 lbs)Maximum permissible weight
: 20 kg (44 lbs) only permissible with baggage harness
Maximum permissible weight in the baggage compartment
: 250 mm (9.84 in) aft of RDMost forward CG (all weights)
: 390 mm(15.35 in) aft of RDMost rearward CG (all weights)
!!WARNING:
Exceeding the weight limitations may lead to overloading of the airplane, as well as degrading of the handling characteristics and flight performance.
2.8. CENTER OF GRAVITY
The reference datum (RD) for the center of gravity (CG) calculation is tangent to the leading edge of the wing at the root rib. This plane is vertical when the fuselage is horizontal.
!!WARNING:
Exceeding the center of gravity limitations reduces the maneuverability and stability of the airplane.
The procedure used to determine the center of gravity is described in Chapter 6.
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2.9. APPROVED MANEUVERS
DA 20 Flight Manual < OPERATING LIMITATIONS
This airplane is certified in the NORMAL Category in accordance with JAR-VLA.Permissible Normal Category Maneuvers:
a) All normal flight maneuvers
b) Stalls (except dynamic stalls)
c) Lazy Eight’s Entry speed: 116 kts (215 km/h)
Chandelles: Entry speed: 116 kts (215 km/h)
Steep turns in which the angle of bank does not exceed 60°
!!NOTE:
Aerobatics are prohibited.
2.10. MANEUVERING LOAD FACTORS
Table of structural maximum permissible load factors:
+4.4 +4.4 + 2.0
-2.2 -2.2 0
at vA at vNE with fully ext. flaps
Positive
Negative
!!WARNING:
Exceeding the maximum load factors will result in overstressing the airplane.Simultaneous full deflection of more than one control surface can result in overstressing the structure, even at speeds below the maneuvering speed.
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2.11. MAXIMUM PASSENGER SEATING
DA 20 Flight Manual < OPERATING LIMITATIONS
Maximum Passenger Seating: one passenger.
2.12. FLIGHT CREW
Minimum Flight Crew: one pilot, aircraft to be flown solo from left seat only
2.13. KINDS OF OPERATION
Flights are permissible in accordance with day visual flight rules.
Minimum Equipment, Flight and Navigation Instruments:Airspeed IndicatorAltimeterMagnetic Compass
Minimum Equipment, Powerplant Instruments:Fuel Quantity IndicatorOil Pressure IndicatorOil Temperature IndicatorManifold Pressure IndicatorCylinder Head Temperature IndicatorTachometerFuel Pressure Warning LightVoltmeterAmmeterGenerator Warning Light
Note: Additional equipment may be required for compliance with specific operational or specific national requirements. It is the operators responsibility to ensure compliance with any such specific equipment requirements.
Fuel Capacity
Total Fuel Quantity: 20.1 US gal. (76 litres)Usable Fuel: 19.5 US gal. (74 litres )Unusable Fuel: 0.6 US gal. ( 2 litres)
2.14. FUEL
DA 20 Flight Manual < NORMAL OPERATING PROCEDURES
Chapter 4 provides checklists and amplified procedures for the normal operation. For normal procedures and supplementary information associated with optional systems refer to Chapter 9. Items written in can not be done in flight simulator.red
Unless stated otherwise, the following table contains the applicable airspeeds for maximum take-off and landing weight. The airspeeds may also be used for lower flight weights.
4.1. INTRODUCTION
CHAPTER 4NORMAL OPERATING PROCEDURES
4.2. AIRSPEEDS FOR NORMAL FLIGHT OPERATION
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V IAS
kts mph km/h
TAKE-OFF
Climb Speed during normal take-off for 15 m (50 ft) obstacle
Best Rate-of-Climb speed at sea level vy (Wing Flaps T/O)
Best Angle-of-Climb speed at sea level vx (Wing Flaps T/O)
57 66 106
65 75 120
57 66 106
V IAS
kts mph km/h
LANDING
Approach speed for normal landing. Wing Flaps in landing position
Balked landing climb speed, Wing Flaps in landing position
Maximum demonstrated crosswind speed during take-off and landing
57 66 106
57 66 106
15 17 27
V IAS
kts mph km/h
CRUISE
Maximum permissible speed in rough air vNO
Maximum permissible speed with full control surface deflections vA
Maximum permissible speed with Wing Flaps extended vFE
118 135 218
104 120 193
81 93 150
DA 20 Flight Manual
4.4. NORMAL OPERATION CHECKLIST
4.4.1. Preflight Inspection
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I. Structural Temperature Indicator Check that temperature does not exceed 55°C (131°F)
2. Airplane Documents Checked
3. Flight Controls Lock Removed
4. Flight Controls
5. Ignition Key
Check proper direction of movement
Pulled out
6. Carburetor Heat Free, OFF
7. Cabin Heat Free
8. Choke
9. Parking Brake
Free, self-resetting
Free
10. Throttle Free, IDLE
12. Master Switch (Battery) ON
13. Warning Lights (Gen, Fuel Press, Illuminated
14. Fuel Quantity
15. Engine Gauges, Ammeter and Voltmeter
Sufficent
Check
16. Circuit Brakers Pressed in
17. Map Light Operational
18. Instrument Lights
19. Trim
Operational and dimmable
NEUTRAL
20. Wing Flaps (Indicator and Flap Actuation) Check extend and retract fully
11. Propeller Speed Control Lever
22. Exterior Lights Operational as required
23. Master Switch (Battery) OFF
24. Foreign Object Inspection
25. Emergency Locator Transmitter (ELT)
Done
26. Fire Extinguisher Check
27. Baggage Stowed, baggage net attached
28. Canopy Clean, undamaged
21. Trim and Flap Indication Lights Operational and dimmable
EBC Model 502 ARMEBC Model 102A OFF
Free, max RPM
I. In-Cabin Check
< NORMAL OPERATING PROCEDURES
II. Walk Around Check and Visual Inspection
!!CAUTION:
Visually inspect for the following conditions: Defects, contamination, cracks, delaminations, excessive play, insecure or improper mounting and general condition. Additionally, check the control surfaces for freedom of movement.
!!CAUTION:
Set PARKING brake prior to removing wheel chocks
1. Left Main Landing Gear
a) Landing Gear Strut
b) Wheel Fairing
visual inspection
visual inspection
c) Tire Pressure (33 psi / 2.3 bar) check
d) Tire, Wheel, Brake visual inspection
e) Wheel Chocks remove
2. Left Wing
a) Entire Wing
b) Stall Warning
visual inspection
check (suck on opening)
c) Pitot-Static Probe clean, holes open
d) Tie down remove
e) Taxi and Landing Lights visual inspection
f) Wing Tip, Position Lights and Strobe visual inspection
g) Aileron Balancing Weight visual inspection
h) Aileron including Inspection Panel visual inspection
i) Wing Flap including Inspection Panel visual inspection
Page 4 - 3
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual < NORMAL OPERATING PROCEDURES
3. Fuselage
a) Skin
b) Tank Vent
visual inspection
check
c) Tank Drain drain water
d) Fuel Quantity visual inspection (use fuel pipette)
e) Antennas visual inspection
4. Empennage
a) Stabilizers and Control Surfaces
b) Tie down
visual inspection
remove
c) Trim Tabs visual inspection
DA 20 Flight Manual < NORMAL OPERATING PROCEDURES
Page 4 -4
Document based on the DA-20 Flight Manuals by
5. Right Wing
a) Entire Wing
b) Wing Flap including Inspection Panel
visual inspection
visual inspection
c) Aileron including Inspection Panel visual inspection
d) Aileron Balancing Weight visual inspection
e) Wing Tip, Position Lights and Strobe visual inspection
f) Tie down remove
6. Right Main Landing Gear
a) Landing Gear Strut
b) Wheel Fairing
visual inspection
visual inspection
c) Tire Pressure (33 psi / 2.3 bar) check
d) Tire, Wheel, Brake visual inspection
e) Wheel Chocks remove
DA 20 Flight Manual < NORMAL OPERATING PROCEDURES
Page 4 -5
Document based on the DA-20 Flight Manuals by
3. Fuselage
a) -Oil check level by using dip-stick.min / max range is indicated by flat area
b) Cowling visual inspection
c) Air Intakes (five) free
d) Propeller visual inspection, Ground Clearance;minimum: approx. 25 cm (10 in).
e) Propeller Blades perform Pitch Check by Hand
f) Spinner visual inspection
g) Nose Gear visual inspection
h) Wheel Fairing visual inspection, towbar removed
i) Tire Pressure (26 psi / 1.8 bar) check
j) Tire and Wheel visual inspection
k) Wheel Chocks remove
-Coolant Level must be between dip-stickmarkings, refill if required.
DA 20 Flight Manual < NORMAL OPERATING PROCEDURES
Page 4 -6
Document based on the DA-20 Flight Manuals by
4.4.2. Before Starting Engine
1. Preflight Inspection performed
2. Pedals adjust, lock
3. Passenger Briefing performed
4. Safety Belts fasten
5. Parking Brake set
6. Controls free
7. Fuel Shut-off Valve OPEN
8. Carburetor Heat OFF
9. Throttle IDLE
10. Propeller Speed Control Lever max. RPM
11. Friction Device of Throttle Quadrant adjust
12. Avionics Master Switch OFF
13. Master Switch (Battery/Generator) ON
14. Generator Warning Light illuminated
15. Fuel Pressure Warning Light illuminated
16. Exterior Lights as required
17. Instrument Panel Lighting as required
18. Canopy Close and Secure
19. Canopy Locking Warning Light OFF
!!NOTE:
Under certain circumstances, activation of the fuel pressure warning light might take as long as 10 minutes after shutting down the engine or switching off the electric fuel pump.
!!NOTE:
Extreme low temperatures require that the engine be preheated prior to engine start. Satisfactory engine starts have been demonstrated at -31ºF (-35ºC) OAT after a 2 hour preheat with the Tannis TAS100-27 preheat system.
DA 20 Flight Manual < NORMAL OPERATING PROCEDURES
4.4.3. Starting Engine
1. Electric Fuel Pump ON (noise of pump audible)
2. Fuel Pressure Warning Light OFF
3. Throttle - Cold Start - Warm Engine
IDLEapproximately 3/4 in (2 cm) forward
4. Choke - Cold Start - Warm Engine
ON, fully pulled and holdOFF
5. Toe Brakes Hold
6. Propeller Area Clear
!!WARNING:
Ensure that propeller area is clear!
7. Ignition Key START
!!NOTE:
During extreme cold weather starts, hold the choke on until the engine starts to warm up.
8. Choke OFF
9. Throttle maximum 1500 RPM
10. Oil Pressure within green range after max. of 10 sec.
!!CAUTION:
If Oil Pressure is below 12 psi (0.8 bar) shut down engine immediately (max. 10 seconds delay).
!!NOTE:
Oil Pressure may advance to the yellow arc until Oil Temp. reaches normal operating temperatures.
!!NOTE:
Activate starter for max. 10 sec. only, followed by a cooling period of 2 min.
11. Generator Warning Light OFF
12. Exterior Lights as required
13. Electric Fuel Pump OFF
Page 4 -7
Document based on the DA-20 Flight Manuals by
4.4.4. Before Taxiing
1. Avionics Master Switch ON
2. Flight Instruments and Avionics set
3. Engine Gauges check
4. Voltmeter
push to test5. Warning Lights (Gen., Fuel Pr.,Canopy)
check, ensure needle is in thegreen arc. Increase RPM toachieve or turn OFF non-flightessential electrical consumers
6. Parking Brake release
DA 20 Flight Manual < NORMAL OPERATING PROCEDURES
!!CAUTION:
Warm-up engine to a minimum Oil Temperature of 122° F (50° C) at 1100 to1500 RPM (also possible during taxi).
4.4.5. Taxiing
1. Brake check
2. Direction Control check
3. Flight Instruments and Avionics check
4. Compass check
!!CAUTION:
At high Propeller RPM the propeller may be damaged by loose sand, gravel or water.
Page 4 -8
Document based on the DA-20 Flight Manuals by
4.4.6. Before Take-Off (Engine Run-Up)
DA 20 Flight Manual < NORMAL OPERATING PROCEDURES
Page 4 -9
Document based on the DA-20 Flight Manuals by
1. Toe Brakes hold
2. Safety Belts fastened
3. Canopy closed and locked
4. Fuel Pressure Warning Light
check OPEN5. Fuel Shut-off Valve
OFF (If light illuminates,maintenance action is required andflight should not be initiated )
6. Fuel Quantity Indicator check
within green range7. Engine Gauges
8. Trim NEUTRAL
9. Controls free
1700-1800 RPM10. Throttle
11. Propeller Speed Control Lever Cycle 3 times(RPM drop: 50 - 250 RPM)
12. Ignition Switch Cycle L - BOTH - R - BOTH(Max. RPM drop: 150 RPM)(Max. RPM difference (L/R): 50 RPM)(Min. RPM difference (L/R): none, butRPM drop must be noticeable)
1500 RPM13. Throttle
14. Carburetor Heat ONRPM drop: max. 50 RPM;
IDLE15. Throttle
16. Carburetor Heat OFF
check pressed IN17. Circuit Breakers
18. Electric Fuel Pump ON
19. Wing Flaps T/O
release20. Parking Brake
4.4.7. Take-off
DA 20 Flight Manual < NORMAL OPERATING PROCEDURES
1. Electric Fuel Pump check ON
2. Master Switch (Battery/Generator) check ON
3. Ignition Switch check BOTH
4. Carburetor Heat check OFF
5. Wing Flaps check T/O
6. Propeller Speed Control Lever check max. RPM
7. ThrottleCheck RPM
FULL2260 RPM to 2385 RPM 2400 RPM to 2550 RPM
(DA20-100)(DA20-80)
8. Elevator - at beginning of rolling NEUTRAL
9. Directional Control maintain with rudder
!!NOTE:
In crosswind conditions, directional control can be enhanced by using the single wheel brakes. Note that using the brakes for directional control increases the take-off roll distance.
10. Rotate (vIAS) 51 kts / 59 mph / 95 km/h
11. Climb Speed (vIAS) 57 kts / 66 mph / 106 km/h 60 kts / 69 mph / 111 km/h
(DA20-100)(DA20-80)
!!CAUTION:
For the shortest possible take-off distance to clear a 15 m (50 ft) obstacle:
Lift-off Speed (vIAS) 54 kts / 62 mph / 100 km/h 57 kts / 66 mph / 95 km/h Climb Speed (vIAS) 57 kts / 66 mph / 106 km/h 60 kts / 69 mph / 111 km/h
(DA20-100)(DA20-80)(DA20-100)(DA20-80)
12. Propeller Speed Control Lever 2260 RPM 2400 RPM (after reaching safe height)
(DA20-100)(DA20-80)
13. Electric Fuel Pump OFF
!!NOTE:
In order to avoid excessive noise, the propeller speed should be reduced to 2260 RPM or 2400 RPM as soon as a safe flight altitude has been reached.
(DA20-100) (DA20-80)
Page 4 -10
Document based on the DA-20 Flight Manuals by
4.4.8. Climb
1. Propeller Speed Control Lever 2260 RPM
2. Throttle FULL
3. Engine Gauges within green range
4. Wing Flaps T/O
5. Airspeed 65 kts / 75 mph / 120 km/h
6. Trim adjust
DA 20 Flight Manual < NORMAL OPERATING PROCEDURES
Page 4 -11
Document based on the DA-20 Flight Manuals by
!!NOTE:
The best rate of climb speed decreases with increasing altitude.
!!NOTE:
Electric fuel pump ON above 13000 ft.
Speeds [vIAS]
Flaps T/O Flaps UPAltitude
ktsfeet mph km/h kts mph km/h
0 - 4.000
4.000 - 7.000
7.000 - 10.000
above 10.000
65 75 120 69 79 128
63 73 117 65 76 120
62 71 115 - - -
59 68 110 - - -
4.4.9. Cruise
1. Throttle as required
2. Propeller Speed Control Lever 1700 - 2260 RPM
!!NOTE:
For favorable manifold pressure/RPM combinations refer to Chapter 5.
!!NOTE:
Electric fuel pump ON above 13000 ft.
3. Wing Flaps UP
4. Trim as required
5. Engine Gauges check
4.4.10. Descent
1. Flight Instruments and Avionics adjust
2. Throttle as required
3. Propeller Speed Control Lever 1700 - 2260 RPM
4. Carburetor Heat as required
DA 20 Flight Manual < NORMAL OPERATING PROCEDURES
!!NOTE:
To achieve a fast descent:Propeller Speed Control Lever 2260 RPMThrottle IDLECarburetor Heat ON
!!NOTE:
If RPM drops and then rises, suspect carburetor icing and leave Carb Heat ON. Otherwise turn Carb Heat OFF.
Wing Flaps UPAirspeed 118 kts / 135 mph / 218 km/h
4.4.11. Landing Approach
1. Seat Belts fastened
2. Electric Fuel Pump ON
3. Lights as required
4. Master Switch (Battery/Generator) check ON
5. Ignition Switch check BOTH
6. Carburetor Heat ON
Page 4 -12
Document based on the DA-20 Flight Manuals by
7. Throttle as required
8. Airspeed max. 81 kts / 93 mph / 150 km/h
9. Wing Flaps T/O
10. Trim as required
!!NOTE:
If RPM drops and then rises, suspect carburetor icing and leave Carb Heat ON.Otherwise turn Carb Heat OFF.
11. Propeller Speed Control Lever max. RPM
12. Wing Flaps LDG
13. Approach Speed 57 kts / 66 mph / 106 km/h
!!CAUTION:
For strong headwind, crosswind, danger of wind-shear or turbulence, a higher approach speed should be selected.
4.4.12. Balked Landing
1. Propeller Speed Control Lever max. RPM
2. Throttle FULL
3. Carburetor Heat OFF
4. Wing Flaps T/O
DA 20 Flight Manual < NORMAL OPERATING PROCEDURES
5. Airspeed 57 kts / 66 mph / 106 km/h
4.4.13. After Landing
1. Throttle as required
2. Wing Flaps UP
3. Carburetor Heat OFF
4. Exterior Lights as required
5. Electric Fuel Pump OFF
4.4.14. Engine Shut-down
1. Throttle IDLE
2. Parking Brake set
3. ELT Check (by listening to121.5 MHZ for signal)
4. Avionics Master Switch OFF
5. Electric Consumers OFF
6. Ignition Switch OFF
7. Instrument Panel Lighting OFF
8. Master Switch (Battery) OFF
9. Tie Downs and Wheel Chocks as required
!!NOTE:
In case of post ignition due to hot weather conditions, the ignition shouldbe switched on, choke pulled and after approximately 3 seconds, ignitionshould be turned off again.
4.4.15. Flight in Rain
!!NOTE:
Flight performance might be reduced, especially for the T/O-distance and the maximum horizontal air speed. The influence on flight characteristics of the airplane is negligible. Flights through heavy rain should be avoided due to the reduced visibility.
Page 4 -13
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual < Performance
5.1. Introduction
The performance tables and diagrams on the following pages have been prepared to illustrate the performance you may expect from your airplane as well as to assist you in precise flight planning. The data presented in these tables and diagrams has been derived from test-flights using an airplane and engine in good operating condition, and was corrected to standard atmospheric conditions (15° C (59° F) and 1013.25 mbar (29.92 in. Hg) at sea level ).
The performance tables do not take into account the expertise of the pilot or the maintenance condition of the airplane. The performance illustrated in the tables can be achieved if the indicated procedures are followed and the airplane is in good maintenance condition. Note that the flight duration data does not include a fuel reserve. The fuel consumption during cruise is based on propeller RPM and manifold pressure settings. Some undefined variables such as the operating condition of the engine, contamination of the aircrafts surface, or turbulence could have influences on flight distance and flight duration. For this reason, it is of utmost importance that all available data is used when calculating the required amount of fuel for a flight.
For flight operation without wheel fairings the resulting performance variations is givenin %.
5.2. USE OF PERFORMANCE TABLES AND DIAGRAMS
The performance data is shown in the form of tables and diagrams to illustrate the influence of the different variables. These tables contain sufficiently detailed information to plan any flight with the necessary precision and safety on the conservative side.
Page5 - 1
5.1. Introduction
CHAPTER 5
PERFORMANCE
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual < Performance
5.3. PERFORMANCE TABLES AND DIAGRAMS
Assumes zero indicator error
5.3.1. Figure 5.1: Airspeed System Calibration
160
150
140
130
120
110
100
90
80
70
60
50
4040 50 70 80 90 100 110 120 130 140 150 16060
T/O, LDG
UP
VIAS [kts]
VCAS [kts]
Example: v = 93 kts equals v = 95 ktsIAS CAS
Page5 - 2
Document based on the DA-20 Flight Manuals by
Revolutions per Minute: RPM * 100
5.3.2.A Figure 5.2A: Cruising Performance DA20-80
Pressure Altitude
StandardTemp.
Engine power as % of max. continuous power
55% 65% 75%
[ft] [m] [°F] ([°C]) RPM MP RPM MP RPM MP
0 0
2000 600
4000 1200
6000 1800
8000 2400
10000 3000
12000 3600
13000 4000
59 (15)
52 (11)
45 (7)
37 (3)
30 (-1)
23 (-5)
16 (-9)
12 (-11)
19 24.7
19 24.0
19 23.3
19 23.0
20 21.3
21 20.0
22 18.7
23 17.3
21 25.3
21 24.7
21 24.0
21 23.7
23 21.7
24 20.3
--- ---
--- ---
22 26.3
22 25.7
22 25.0
23 23.7
24 22.0
--- ---
--- ---
--- ---
Consumption (per hour): 3.25 US gal.(12.3 liters)
3.83 US gal.(14.5 liters)
4.39 US gal.(16.6 liters)
DA 20 Flight Manual < Performance
Pressure Altitude
StandardTemp.
Engine power as % of max. continuous power
85% 95% 104%
[ft] [m] [°F] ([°C]) RPM MP RPM MP RPM MP
0 0
2000 600
4000 1200
59 (15)
52 (11)
45 (7)
23 27.7
23 27.0
24 25.3
24 28.3
24 27.7
--- ---
25.5 29.7
--- ---
--- ---
Consumption (per hour): 5.10 US gal.(19.3 liters)
6.00 US gal.(22.7 liters)
6.52 US gal.(24.7 liters)
To maintain constant performance at non standard temperature gradient:
Raise manifold pressure by 0.7 in.Hg at ISA + 18° F (10° C)Lower manifold pressure by 0.7 in.Hg at ISA - 18° F (10° C)
! NOTE: To keep engine wear to a minimum, engine operation below 1900 RPM is not recommended.
Page5 - 3
Document based on the DA-20 Flight Manuals by
5.3.2.B Figure 5.2B: Cruising Performance DA20-100
DA 20 Flight Manual < Performance
Fuel flow is given in US-gal.
Data labelled * give a basis for interpolation. These values may not be attained at the stated altitude.
To maintain constant performance at non standard temperature gradient:
Raise manifold pressure by 0.7 in.Hg at ISA + 18° F (10° C)Lower manifold pressure by 0.7 in.Hg at ISA - 18° F (10° C)
! NOTE: To keep engine wear to a minimum, engine operation below 1900 RPM is not recommended.
Pressurealtitude
StandardTemp.
Engine Power in % of maximum continuous power
55% 65%
Ft. M °C °FRPMX100
MPIn.Hg
Fuel FlowL/hr Gal/hr
RPMX100
MPIn.Hg
Fuel FlowL/hr Gal/hr
02000400060008000
1000012000
0600
12001800240030003600
13000 4000
151173-1-5-8
-11
5952453831241712
191919202122
22.622.6
24.724.023.322.021.019.718.0*17.0*
13.614.415.616.818.019.220.4*21.5*
3.63.84.14.44.85.15.4*5.7*
2020212222
22.6
25.724.723.322.721.720.3*
15.616.016.819.621.222.4*
4.14.24.45.25.65.9*
Pressurealtitude
StandardTemp. 75% 85%
Ft. M °C °FRPMX100
MPIn.Hg
Fuel FlowL/hr Gal/hr
RPMX100
MPIn.Hg
Fuel FlowL/hr Gal/hr
02000400060008000
0600
120018002400
151173-1
5952453831
2122
22.622.622.6
27.025.724.323.322.0*
18.018.419.623.223.6*
4.84.95.26.16.2*
22.622.622.6
27.726.725.7*
22.022.425.2*
5.85.96.7*
Pressurealtitude
StandardTemp.
Maximum ContinousPower
Maximum Take-OffPower
Ft. M °C °FRPMX100
MPIn.Hg
Fuel FlowL/hr Gal/hr
RPMX100
MPIn.Hg
Fuel FlowL/hr Gal/hr
0200040006000
0600
12001800
151173
59524538
22.622.622.6
28.327.7*25.7*
26.026.8*25.2*
6.97.1*6.7*
23.8 29.7* 30.0 7.9*
Page5 - 4
Document based on the DA-20 Flight Manuals by
Configuration:
Idle, most forward center of gravity, max. weight (this is the most adverse configuration)
5.3.3. Figure 5.3: Stall Speeds
DA 20 Flight Manual < Performance
Flaps
UP
T/O
LDG
Bank Angle
0° 30° 45° 60°
IAS CAS IAS CAS IAS CAS IAS CAS
41 50 46 53 55 59 69 70
39 46 44 49 51 54 63 65
37 33 41 47 49 52 59 62
Stall speeds in kts
Flaps
UP
T/O
LDG
Bank Angle
0° 30° 45° 60°
IAS CAS IAS CAS IAS CAS IAS CAS
47 57 53 62 63 68 79 81
45 52 51 56 59 62 72 75
43 50 47 54 56 60 68 72
Stall speeds in mph
Flaps
UP
T/O
LDG
Bank Angle
0° 30° 45° 60°
IAS CAS IAS CAS IAS CAS IAS CAS
76 93 85 99 101 109 127 130
72 84 81 91 94 100 117 120
69 81 76 87 91 96 109 115
Stall speeds in km/h
Page5 - 5
Document based on the DA-20 Flight Manuals by
Maximum demonstrated crosswind component: 15 kts (27 km/h)
5.3.4. Figure 5.4: Wind Components
DA 20 Flight Manual < Performance
10
5
0
5
10
15
200° 10° 20° 30° 40°
160° 150° 140° 130° 120°170°
HE
AD
WIN
D C
OM
PO
NE
NT
10
0
10
20
30
[km/h] [kts]
0 10 20 30
0 5 10 15 20
[km/h]
[kts]
50°
60°
70°
80°
90°
100°
110°
FL
IGH
T D
IRE
CT
ION
ma
x. d
em
on
stra
ted
cro
ssw
ind
tw
l
a
n
igh
n
nge
eee
n w
d an
d f
dire
c
b
i
tio
l
t
ee
w
d k
indp
in
s
ts
Example:Wind speed: 11 kts (20 km/h)Angle between wind direction and flight direction: 30°Headwind component: 9.5 kts (18 km/h)Crosswind component: 5.5 kts (10 km/h)
Page5 - 6
Document based on the DA-20 Flight Manuals by
5.3.5.A Figure 5.5A: Take-Off Distance DA20-80
DA 20 Flight Manual < Performance
Conditions:- maximum take-off power- lift-off speed 57 KIAS and speed for climb over obstacle 60 KIAS- level runway, paved- Wing Flaps in Take-Off Position (T/O)
Outside Air Temperature [°F]
Outside Air Temperature [°C]
Aircraft Weight [lbs]
-20 0 20 40
68 86 104503215
01
.000 ft l
pre
ssure
at.
80
0.
0 ft
sal
pre
sure
t.
6.00
0 ft
pre
sure
alt.
s
400
0 ft
.pr
essu
real
t.
2.000 ft
ra
press
ue
lt.
0 tf
Aircraft Weight [kg]
1600 1490 1380
725 700 675 650 650Headwind
Component [kts]
0 5 10 15 0 5 10 15Obstacle
Height [m] [m] [ft]
Obstacle Height [ft]
4916 3301000
900
800
700
600
500
400
300
200
[m] [ft]
3200
2200
1200
3000
2000
1000
2800
1800
800
2600
1600
2400
1400
Ta
ke-O
ff D
ista
nce
Example: - Pressure altitude: 3000 ft- Outside temperature: 15° C (59° F)- Weight : 675 kg(1488 lbs)- Wind: 10 kts
Result: - Take-Off roll distance: 330 m(1080 ft- Take-Off distance to clear a 15 m (50 ft) obstacle: 470 m(1540 ft)
! NOTE: Poor maintenance condition of the airplane, deviation from the given procedures as well as unfavorable outside conditions (i.e. high temperature, rain, unfavorable wind conditions, including cross wind) could increase the take-off distance considerably. For take-off from dry, short-cut grass covered runways compared to paved runways, a 25% increase in take-off roll distance must be taken into account.On soft grass covered runways with grass deeper than 10 cm, (4 in) the take-off roll distance might be increased by as much as 40%.
Page5 - 7
Document based on the DA-20 Flight Manuals by
5.3.5.B Figure 5.5B: Take-Off Distance DA20-100
DA 20 Flight Manual < Performance
Conditions:- maximum take-off power- lift-off speed 53 KIAS and speed for climb over obstacle 57 KIAS- level runway, paved- Wing Flaps in Take-Off Position (T/O)
Outside Air Temperature [°F]
Outside Air Temperature [°C]
Aircraft Weight [lbs]
-20 0 +20 +40
68 86 104503215
01
.000 ft l
pre
ssure
at.
80
0.
0 ft
sal
pre
sure
t.
6.00
0 ft
pre
sure
alt.
s
400
0 ft
.pr
essu
real
t.
2.000 ft
ra
press
ue
lt.
0 tf
Aircraft Weight [kg]
1600 1490 1380
725 700 675 650 650Headwind
Component [kts]
0 5 10 15 0 5 10 15Obstacle
Height [m] [m] [ft]
Obstacle Height [ft]
4916 3301000
900
800
700
600
500
400
300
200
[m] [ft]
3200
2200
1200
3000
2000
1000
2800
1800
800
2600
1600
2400
1400
Ta
ke-O
ff D
ista
nce
Example: - Pressure altitude: 3000 ft- Outside temperature: 15° C (59° F)- Weight : 675 kg(1488 lbs)- Wind: 10 kts
Result: - Take-Off roll distance: 299 m (980 ft)- Take-Off distance to clear a 15 m (50 ft) obstacle: 427 m (1400 ft)
! NOTE: Poor maintenance condition of the airplane, deviation from the given procedures as well as unfavorable outside conditions (i.e. high temperature, rain, unfavorable wind conditions, including cross wind) could increase the take-off distance considerably. For take-off from dry, short-cut grass covered runways compared to paved runways, a 25% increase in take-off roll distance must be taken into account.On soft grass covered runways with grass deeper than 10 cm, (4 in) the take-off roll distance might be increased by as much as 40%.
Page5 - 8
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual < Performance
5.3.6.A Figure 5.6A: Climb Performance / Cruising Altitudes DA20-80
Max. Cruising Altitude (in standard conditions): 13120 ft (4000 m)
Best Rate-of-Climb Speed with Wing Flaps in Take-Off Position (T/O): 65 kts / 75 mph / 120 km/h
Temperature [°C]-20 -10 0 +10 +20 +30
m/Sec
Pre
ssu
re A
ltitu
de
[ft]
0
-2000
2000
4000
6000
8000
10000
12000
14000
16000
18000
0.5 1.0 1.5 2.0 2.5 3.0 3.5 4.0 4.5
100 200 300 400 500 600 700 800-4 +14 +32 +50 +68 +86
Temperature [°F]ft/Min
1433lbs/650kg
1544lbs/700kg
1609lbs/730kg
Example: Pressure Altitude: 5000 ft (1524 m)OAT: 8° C (46° F)Weight : 670 kg (1477 lbs)
Result: Climb performance: 490 ft/min (2.5 m/s)
! CAUTION: In case of operation without wheel fairings the climb performance is reduced by approximately 3%.
SA
ND
AD
TEM
PER
AT
E
TR
UR
Page5 - 9
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual < Performance
5.3.6.B Figure 5.6B: Climb Performance / Cruising Altitudes DA20-100
Max. Cruising Altitude (in standard conditions): 17600 ft (5365 m)
Best Rate-of-Climb Speed with Wing Flaps in Take-Off Position (T/O): 65 kts / 75 mph / 120 km/h
Example: Pressure Altitude: 5000 ft (1524 m)OAT: 8° C (46° F)Weight : 670 kg (1477 lbs)
Result: Climb performance: 554 ft/min (2.82 m/s)
! CAUTION: In case of operation without wheel fairings the climb performance is reduced by approximately 3%.
m/Sec0.5 1.0 1.5 2.0 2.5 3.0 3.6 4.1 5.1
100 200 300 400 500 600 700 800
ft/Min
1433lbs/650kg
1543lbs/700kg
1609lbs/730kg
Temperature [°C]-20 -10 0 +10 +20 +30
Pre
ssur
e A
ltitu
de [f
t]
0
-2000
2000
4000
6000
8000
10000
12000
14000
16000
18000-4 +14 +32 +50 +68 +86
Temperature [°F]
Standard Temperature
4.6
900 1000
1653lbs/750kg
Page5 - 10
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual < Performance
5.3.8.A Figure 5.8A: Cruising Speed (True Airspeed)DA20-80
Diagram for true airspeed (TAS) calculation at selected power level.
Example: Pressure altitude: 9500 ft Temperature: 14° C (57° F) Power setting: 60 % Result: True airspeed (TAS): 104.2 kts (193 km/h)
Temperature [°C]-20 -10 0 +10 +20 +30
Pre
ssu
re A
ltitu
de
[ft]
0
-2000
2000
4000
6000
8000
10000
12000
14000
16000
18000
-4 +14 +32 +50 +68 +86
Temperature [°F]
TEMER
E
STAN
DA
RD
P
ATU
R
80 90 100 110 120
140 150 160 170 180 190 200 210 220True Airspeed [km/h]
True Airspeed [knots]
55%
60%
%65
75%
85%
%95
Flight Mass 1609 lbs (730 kg), foremost CG,Flaps UP, Aircraft in good condition.
! CAUTION: In case of operation without wheel fairings the maximum cruising speed is reduced by proximately 5%.
Page5 - 11
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual < Performance
5.3.8.B Figure 5.8B: Cruising Speed (True Airspeed)DA20-100
Diagram for true airspeed (TAS) calculation at selected power level.
Example: Pressure altitude: 9500 ft Temperature: 14° C (57° F) Power setting: 55 % Result: True airspeed (TAS): 116 kts (215 km/h)
Temperature [°C]-20 -10 0 +10 +20 +30
Pre
ssu
re A
ltitu
de
[ft]
0
-2000
2000
4000
6000
8000
10000
12000
14000
-4 +14 +32 +50 +68 +86
Temperature [°F]
95
170 180 190 200 210 220 230 240 250True Airspeed [km/h]
True Airspeed [knots]
55%
65%
7%5
85%
Flight Mass 1609 lbs (730 kg), foremost CG,Flaps UP, Aircraft in good condition.
! CAUTION: In case of operation without wheel fairings the maximum cruising speed is reduced by proximately 5%.
100 105 110 115 120 125 130 135
59%
STAR
EE
TUE
ND
AD
TM
PR
AR
Page5 - 12
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual < Performance
5.3.9.A Figure 5.9A: Maximum Flight Duration DA20-80
Diagram for calculation of the maximum flight duration depending on fuel availability.
80
70
60
50
40
30
20
10
01 2 3 4 5 6
0
4
8
12
16
20
hrs.
59%
8%5 75%
65%55%
Max. usable fuel 19.5 US gal [74 liters]
Fu
el q
ua
ntit
y in
litr
es
Fu
el q
ua
ntit
y in
US
ga
llon
s
Flight time, no reserve
Example: Fuel quantity: 50 litres(13.2 US gal) Power Setting: 65%
Result: Possible flight time without reserve: 3:28 h:min Possible flight time with reserve of 45 mins: 2:43 h:min
Page5 - 13
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual < Performance
5.3.9.B Figure 5.9B: Maximum Flight Duration DA20-100
Diagram for calculation of the maximum flight duration depending on fuel availability.
Example: Fuel quantity: 50 litres(13.2 US gal) Pressure Altitude 6000 ft Power Setting: 75%
Result: Possible flight time without reserve: 2:11 h:min Possible flight time with reserve of 45 mins: 1:26 h:min
80
70
60
50
40
30
20
10
01 2 3 4 5 6
0
4
8
12
16
20
600m
/ 2
000f
t
Fu
el q
ua
ntity
in
litre
s
Flight time (hour), no reserve
0
1800
m / 6
00f
t
0m 4
00
t
120
/0
f
600m /
2000ft
1800m /
600ft0
20m
/ 4000f
10
t
6
/
00m 2000ft
95% 75% 55%
Fu
el q
ua
ntity
in
US
Ga
l
Flight time (hour), 45 minute reserve
1/4 1 1/4 2 1/4 3 1/4 4 1/4 5 1/4
Page5 - 14
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual < Performance
5.3.10.AFigure 5.10A: Climb Performance during Balked Landing DA20-80
Conditions: Speed = 57 kts / 67 mph / 108 km/h Wing Flaps in Landing Position (LDG) Weight 730 kg (1609 lbs) most forward center of gravity max take-off power
200010000 3000 4000 5000 6000 7000 8000 9000 10000 PRESSURE ALTITUDEHp [ft]
0 500 1000 1500 2000 2500 3000 PRESSURE ALTITUDEHp [m]
3.0
2.0
1.0
0.0
ROCm/s ROC
ft/min
600
700
500
400
300
200
100
0
OA 15°
T -COAT 0°C
OAT +1°C
5
OAT +30°C
Example: Pressure altitude: 3000 ft Outside temperature: 15° C(59° F)
Result: Climb performance during balked landing: 270 ft/min. (1.3 m/s)
! CAUTION: In case of operation without wheel fairings the climb performance is reduced by approximately 3%.
Page5 - 15
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual < Performance
5.3.10.B Figure 5.10B: Climb Performance during Balked Landing DA20-100
Conditions: Speed = 57 kts / 67 mph / 108 km/h Wing Flaps in Landing Position (LDG) Weight 730 kg (1609 lbs) most forward center of gravity max take-off power
200010000 3000 4000 5000 6000 7000 8000 9000 10000 PRESSURE ALTITUDEHp [ft]
0 500 1000 1500 2000 2500 3000 PRESSURE ALTITUDEHp [m]
3.0
2.0
1.0
0.0
ROCm/s ROC
ft/min
600
700
500
400
300
200
100
0
T-1
°
OA
5COA
0°C
T
T
OA +1
°C5O
T +3C
A
0°
Example: Pressure altitude: 2500 ft Outside temperature: 15° C(59° F)
Result: Climb performance during balked landing: 330 ft/min. (1.67 m/s)
! CAUTION: In case of operation without wheel fairings the climb performance is reduced by approximately 3%.
Page5 - 16
Document based on the DA-20 Flight Manuals by
a)
b)
DA 20 Flight Manual < Performance
5.3.11. Landing Distance
Conditions: - Throttle: Idle- Maximum T/O Weight- Propeller Speed Control Lever: max RPM- Approach Speed 57 kts / 66 mph / 106 km/h- Level Runway, paved- Wing Flaps in Landing position (LDG)- Standard Setting, MSL
Landing distance over a 15 m (50 ft) obstacle: approx. 454 m (1490 ft) Landing roll distance: approx. 228 m (748 ft)
Figure 5.11: Landing and Rolling Distances for Heights Above MSL
Height above MSL
Landing Distance
Landing Roll Distance
ft.(m)
0(0)
1000(305)
2000(610)
3000(915)
4000(1220)
5000(1524)
ft.(m)
1490(454)
1550(472)
1609(491)
1669(509)
1728(527)
1788(545)
ft.(m)
748(228)
770(235)
793(242)
817(249)
842(257)
868(265)
! NOTE: Poor maintenance condition of the airplane, deviation from the given procedures as well as unfavorable outside conditions (i. e. high temperature, rain, unfavorable wind conditions, slippery runway) could increase the landing distance considerably.
5.4. NOISE DATA
Noise limit according to FAR 36, Appendix G: 76.8 dB (A)Noise value measured: 65.2 dB (A)
Noise limit according to ICAO Annex 16, Chapter 10: 71.9 dB (A)Noise value measured: 63.6 dB (A)
a)
b)
Noise limit according to FAR 36, Appendix G: 74.7 dB (A)Noise value measured: 63.8 dB (A)
Noise limit according to ICAO Annex 16, Chapter 10: 78.8 dB (A)Noise value measured: 71.7 dB (A)
DA20-80
DA20-100
Page5 - 17
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual < Weight & Balance
Introduction
To obtain the performance, flight characteristics and safe operation described in this Flight Manual, the airplane must be operated within the permissible weight and balance envelope. It is the pilot's responsibility to adhere to the weight and balance limitations and to take into consideration the change of the CG position due to fuel consumption.
The following pages are sample forms which can be used for the determination of the useful load.
Page6 - 1
6.1. Introduction
CHAPTER 6
WEIGHT & BALANCE
6.4. FLIGHT WEIGHT AND CENTER OF GRAVITY
The following data enables the pilot to operate the DA 20/100 within the required weight and center of gravity limitations. The following diagrams,
Figure 6.3 Weight & Balance DiagramFigure 6.4 Calculation of Loading ConditionFigure 6.5 Permissible Center of Gravity Range and permissible Flight-Weight-Moment
are to be used for calculations of the flight-weight and the center of gravity as follows:
The empty weight and the empty-weight-moment of the airplane should be taken from the weighing report or from the weight & balance report and entered into the form "Calculation of Loading Condition" (figure 6.4) in the columns identified with "Your DA 20".
Using the Weight & Balance Diagram (see figure 6.3) determine the moment for each part to be loaded, and enter it in the respective column in figure 6.4.
Add the weights and the moments of each column (point 4 and point 6 in figure 6.4) and enter the sum in figure 6.5 "Permissible CG Range and Permissible Flight-Weight-Moment" to check if the values are within the permissible limits of the loading range.
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual
5.3.1. Figure 5.1: Airspeed System Calibration
Page6 - 2
< Weight & Balance
Figure 6.3: Weight & Balance Diagram
1000 2000 3000 4000 5000
10 20 30 40 50 60
100
200
300
400
500
600
Load Moment [kg.m]
Load Moment [in.lbs]
Lo
ad
[lb
s]
Lo
ad
[kg
]
50
100
150
200
250
Max. Usable Fuel 19.5 US gal (74 litres)
Max. Baggage 44 lbs [20 kg]2
l
(6.01 lbs per US gal/ 0.7 kg per iter)
ag
B gga e
Pi
t
-
lo &
Co
Pilo
t
Example:
Pilot and Passenger: 380 lbs. (172 kg)Fuel 14.0 US gal. / 52.9 litres: 84 lbs. ( 38 kg)(6.01 lbs. per US gal./0.72 kg per liter)
Result:
Moment of Pilot and Passenger: 2139 in.lbs. (24.6 kgm)Moment of Fuel: 2725 in.lbs. (31.3 kgm)
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual
Page6 - 3
< Weight & Balance
DA 20 (Example)
1.Empty Weight (use the data for your airplane recorded in the equipment list, including unusable fuel, lubricant and coolant).
2. Pilot and Passenger:
Lever Arm: 0.143m (5.63 in)
3. Baggage:
Lever Arm: 0.824m (32.44 in)
4. Total Weight and Total Moment with empty fuel tank (sum of 1. -> 3.)
5. Usable Fuel Load(6.01 lbs. per US gal. / 0.72 kg per litre)Lever Arm: 0.824m (32.44 in)
6. Total Weight and Total Moment taking fuel into account (sum of 4. and 5.)
7. Find the values for the total weight (1525 lbs. and 1609 lbs.) and the total moment (15019 in.lbs. and 17744 in.lbs.) in the center of gravity diagram. Since they are within the limitation range, the loading is permissible.
Your DA 20
Weight [lbs]
Weight [kg]
Moment [in.lbs][kgm]
Weight [lbs]
Weight [kg]
Moment [in.lbs][kgm]
1145
(520)
12880
(148.404)
380
(172)
2139
(24.596)
--
(--)
--
(--)
1525
(692)
15019
(172.000)
84
(38)
2725
(31.312)
1609
(730)
17744
(204.312)
Calculation of theLoad Limits
Figure 6.4: Calculation of Loading Condition
Document based on the DA-20 Flight Manuals by
Page6 - 4
(lbs)(kg)
560
600
650
700
730 1609
1500
1400
1300
1235
12151 15000 17500 20000 22500 24735
140 160 180 200 220 240 260 280
Permissible Flight - Weight - Moment
(in*lbs)
(Kg+m)
9.8
" (2
50
mm
)
10
.6"
(27
0m
m)
11.4
" (2
90
mm
)
12
.2"
(31
0m
m)
13
.0"
(33
0m
m)
13
.8"
(35
0m
m)
14
.5"
(37
0m
m)
15
.35
" (3
90
mm
)
Permissible Center of Gravity Range
1
DA 20 Flight Manual < Weight & Balance
Figure 6.5: Permissible Center of Gravity Range and permissible Flight-Weight-Moment
1) Changes during flight due fuel consumption
>>In Flight Simulator:
We recommend to use the Loadeditor which has been installed with DA20 "Katana" for changing weight and loading. Manipulate the fuel quantity as usual in the flight simulator aircraft menu.
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual < AIRPLANE & SYSTEMS
Introduction
This Chapter provides description and operation of the airplane and its systems.
The GFRP-fuselage is of semi-monocoque construction. The fire protection cover on the fire wall is made from a special fire retarding fleece, that is covered by a stainless steel plate on the engine side. The main bulkhead is of CFRP/GFRP construction.The metal instrument panel permits the installation of instruments up to a maximum weight of 25 kg (55 lbs.).
7.1. Introduction
CHAPTER 7
DESCRIPTION OF THE AIRPLANEAND ITS SYSTEMS
7.2. AIRFRAME
7.2.1. Fuselage
The GFRP-wings are of semi-monocoque sandwich construction, and contain a CFRP-spar. The ailerons and flaps are made from CFRP and are attached to the wings using aluminum hinges. The wing-fuselage connection is made with three bolts each. The so-called A- and B- bolts are fixed to the fuselage's root rib. The A-bolt is placed in front of the spar tunnel, the B-bolt lies near the trailing edge. The two main bolts are placed in the middle of the spar tunnel (main bulkhead). They are accessible between the backrests and can be inserted from the front side. A spring loaded hook locks both bolt handles, thereby securing them.
7.2.2. Wings
The rudder and elevator units are of semi-monocoque sandwich construction. The vertical stabilizer contains a folded-top antenna for the radio equipment, the horizontal stabilizer contains an antenna for the NAV equipment (VOR).
7.2.2. Wings
Page 7 - 1
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual < AIRPLANE & SYSTEMS
The ailerons and elevator are actuated via push rods, and the rudder is controlled using control cables. The flaps have three positions (up [UP], take-off [T/O], and landing [LDG]) and are electrically operated. The switch is located on the instrument panel. In addition the flap control circuit is provided with a manually triggerable circuit breaker.Elevator forces may be balanced using the electric trim system.
7.3. FLIGHT CONTROLS
The Rocker switch is located on center console behind engine control unit.
The switch controls an electrical actuator beside the vertical push rod in the vertical stabilizer. The actuator applies via compression springs a load on the elevator controls. Its circuit breaker is located in the circuit breaker panel and can also be triggered manually. Pushing the switch forward will trim the aircraft nose down.
The digital trim indicator is located in the middle of the instrument panel.
7.3.1. Trim System
>>In Flight Simulator:
Trim your aircraft via Numpad '7' and '1' on your keyboard, or control the switches in the 2d panel 'control stand' and the virtual cockpit view with the mouse.
Nose down7Pos1
1End
Keyboard:
Nose up
Mouse:
NOSEDOWN
NOSEUP
TRIM
Left click: Nose down
Left click: Nose up
Page 7 - 2
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual < AIRPLANE & SYSTEMS
F5
F6
>>In Flight Simulator:
Use your keyboard to set flaps, or extend and retract the flaps by switching the lever in the 2d panel and virtual cockpit with your mouse.
Retract flaps fully
Retract flaps one notch
Extend flaps one notch
Extend flaps fully
The flaps are driven by an electric motor. The flaps are controlled by a three position flap operating switch on the instrument panel. The three positions of the switch correspond to the position of the flaps, where the top position of the switch is used during cruise flight. When the switch is moved to a different position, the flaps move automatically until the selected position is reached. The up (fully retracted) and landing (fully extended) positions are additionally equipped with a limit switch to prevent overtraveling.
The electric flap actuator is protected by an automatic circuit breaker (3.5 A), located in the circuit breaker panel, which can also be triggered manually.
7.3.2. Flaps
The current flap position is indicated by three control lights beside the flap operating switch.
7.3.3. Flaps Position Indicator
When two lights are illuminated at the same time, the flaps are between these two positions. This is the case while the flaps are in motion.
Wing Flap Position Light Degree
CRUISE
T/O
LDG
green
yellowyellow
0°
15°40°
F7
F8
Flaps
2d Panel:Use right mouse click to extend, left click to extract the flaps one notch.
VCP:Click and hold the lever, drag the mouse up to retract and down to extend the flaps.
The mouse wheel can be used in both views.
Keyboard: Mouse:
Page 7 - 3
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual < AIRPLANE & SYSTEMS
7.4. INSTRUMENT PANEL
>>In Flight Simulator:
Our Katana uses the two methods offered by the Flight Simulator to display the cockpit:
2d Panels: This is the FS standard view, and we hardly recommend to load the Katana in this view. First, you will be sitting in front of the main panel. Many further panels can be opened and closed via clickspots in the panel, the 'panel switcher' or 'SHIFT+#'.
Virtual Cockpit:
The virtual Cockpit is a 3d recreation of the DA-20 cockpit. You can turn your head with the cooliehat of your joystick, and interact with the gauges, levers and switches with the mouse.
Page 7 - 4
Document based on the DA-20 Flight Manuals by
7.4.1. Flight Instruments
DA 20 Flight Manual < AIRPLANE & SYSTEMS
The flight instruments are installed on the pilot's side of the instrument panel.
7.4.1.1 The 2d Panel and Subpanels
21 3 4
65 7 8
15 16 17 18 19 20 21 22
23
10
11 12 13 14
24
25
26
27
28
9
F
G DE C A
B
A
1.2.3.4.5.6.7.8.9.
10.11.12.13.14.15.
Airspeed IndicatorArtificial Horizon Ind.AltimeterTachometerTurn and Bank Ind.Directional GyroVertical Speed Ind.CDIADF Pointer Outside Air Temp. Ind.Clock / TimerCompassTrim Ind. DimmerTrim Position Ind.Fuel Pump Switch
16.17.18.19.20.21.22.23.24.25.26.27.28.
Strobe Light SwitchLanding Light SwitchTaxi Light SwitchNav Lights SwitchAvionic Master SwitchMaster SwitchIgnition SwitchFlap ControlKMA 28 Audio Ampl.KX165A NAV/COMMKR87 ADFKT76A TransponderKN62A DME
ABCDEFG
Engine PanelRadiosControl StandFuel SwitchOpen CanopyOpen WindowPanel Switcher
Clickspots
> Main Panel
There are 3 methods to open / close the different subpanels : The most common way to manage the panels is to press 'SHIFT' and one of the number keys on your keyboard. Additionally you can also use the clickspots on the panels, those orange colored areas you will see on the next sides, or the 'panel switcher'.
Page 7 - 5
Document based on the DA-20 Flight Manuals by
> Radio Panel
DA 20 Flight Manual < AIRPLANE & SYSTEMS
(SHIFT+2)
A
A
1
2
3
4
5
6 7
1.2.3.4.5.6.7.
KMA 28 Audio Ampl.KX165A NAV/COMMKR87 ADFKT76A TransponderKN62A DMEADF PointerCDI
A Close Radio Panel
Clickspots
> GPS (SHIFT+3)
A
For GPS Manual see FS9 Documentation. A Close GPS Window
Clickspots
> Engine Panel (SHIFT+4)
A
A
1
2
3
4
5
6
7
8
9
1.2.3.4.5.6.7.8.9.
Manifold PressureOil PressureVoltmeterAmmeterHobbsOil Temp. Ind.Cylinder Head Temp.Fuel IndicatorCircuit Breakers
A Close Engine Panel
Clickspots
Page 7 - 6
Document based on the DA-20 Flight Manuals by
> Control Stand
DA 20 Flight Manual < AIRPLANE & SYSTEMS
(SHIFT+5)
A
3 4
5 6
1 2
8 9
7
1.2.3.4.5.6.7.8.9.
Power LeverPropeller RPM LeverCarb Heat KnobCabin Heat KnobChoke KnobParking Brake KnobTrim SwitchI-Panel Light SwitchMap Light Switch
A Close Control Stand
Clickspots
> Fuel Switch (SHIFT+6)
A
1
1. Fuel SwitchA Close Fuel Switch
Window
Clickspots
> VOR 2 Panel (SHIFT+7)
1
1.2.
KX165A #2CDI #2 A Close VOR 2
Clickspots
2 A
Page 7 - 7
Document based on the DA-20 Flight Manuals by
> Panel Switcher
DA 20 Flight Manual < AIRPLANE & SYSTEMS
(SHIFT+8)
4
5
6 7
1 2
3
9
8
A
1.2.3.4.5.6.7.8.9.
MainpanelRadiosEngine PanelVOR 2GPSKneeboardFuel SwitchControl StandSwitch Passenger View
A Close Panel Switcher
Clickspots
> Passenger View (Num2, Coolie-Hat backward)
3 4
5 6
7 8 918
13
14
15
16
17
1 2 10 11 12
19 23
20 24
21 25
22 26
27
1.2.3.4.5.6.7.8.9.
10.11.12.13.14.15.
Clock / TimerCompassAltimeterTachometerVertical Speed Ind.CDIMaster SwitchIgnition SwitchFlap ControlTrim IndicatorAnnunciatior LightCanopy Warning LightKMA 28 Audio Ampl.KX165A NAV/COMMKR87 ADF
16.17.18.19.20.21.22.23.24.25.26.27.
KT76A TransponderKN62A DMEADF IndicatorManifold PressureOil PressureVoltmeterAmmeterHobbsOil Temp. Ind.Cylinder Head Temp.Fuel IndicatorCircuit Breakers
Page 7 - 8
Document based on the DA-20 Flight Manuals by
> Approach View
DA 20 Flight Manual < AIRPLANE & SYSTEMS
(Num5+Num8, Coolie-Hat forward)
For the description of the instruments, switches etc. please refer to the main panel section
7.4.1.2 The Virtual Cockpit
ABCD
Open / Close WindowOpen / Close CanopyKneeboardMap View
Clickspots
B
A
C
D
C E
G
F
EFG
Open / Close GPS WindowOpen / Close Radio PanelOpen / Close Engine Panel
Page 7 - 9
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual < AIRPLANE & SYSTEMS
1
10
1.2.3.4.5.6.7.8.9.
10.11.12.13.14.15.16.17.18.19.20.21.22.23.24.25.
Airspeed IndicatorArtificial Horizon Ind.AltimeterTachometerTurn and Bank Ind.Directional GyroVertical Speed Ind.CDIADF Pointer Outside Air Temp. Ind.Clock / TimerCompassTrim Ind. DimmerTrim Position Ind.Fuel Pump SwitchStrobe Light SwitchLanding Light SwitchTaxi Light SwitchNav Lights SwitchAvionic Master SwitchMaster SwitchIgnition SwitchFlap ControlKMA 28 Audio Ampl.KX165A NAV/COMM
26.27.28.29.30.31.32.33.34.35.36.37.38.39.40.41.42.43.44.45.46.47.48.
49.
KR87 ADFKT76A TransponderKN62A DMEPower LeverPropeller RPM LeverCarb Heat KnobCabin Heat KnobChoke KnobParking Brake KnobTrim SwitchI-Panel Light SwitchMap Light SwitchAnnunciatior LightCanopy Warning LightManifold PressureOil PressureVoltmeterAmmeterHobbsOil Temp. Ind.Cylinder Head Temp.Fuel IndicatorCircuit Breakers(not operational in VCP)Fuel Shut-Off Valve
2 3 4
5 6 7 8
9
15 16 17 18 19 20 21
22 23
31 32
33 34
29
30
35
36 37
49
1311 12
38 39
4440
41
42
43 47
46
45
48
53
5352
51
50
14
24
25
26
27
28
50.51.52.53.
I-Panel ReostatStall Warning HornMicrophone JackAir Vent
Page 7 - 10
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual < AIRPLANE & SYSTEMS
7.4.1.3 Instruments
40
60
80100
120
140
1600
AIRSPEED
KNOTS
> Airspeed Indicator (ASI)
Cage the Artificial Horizon Indicator with either left or right mouse button.
> Artificial Horizon Indicator (ATTI)
ULLPTOCAGE
29.9
29.8
01
2
34
56
7
8
9
ALTIMETER
010 FEET
> Altimeter (ALT)
Page 7 - 11
IAS
Marking kts mph km/h Explanation
White Arc 37-81 43-93 69-150 Operation rangewith ext. flaps
Green Arc 41-118 47-135 76-218 Normal operationrange
Yellow Arc 118-161 135-185 218-298 Maneuvers must beconducted with caution and only in smooth air.
Red Line 161 185 298 Max. permissible speed for all operating modes.
iiTip:
Options > Settings > International > Units of measure:
Metric - altitude calibration in 'millibar' U.S. System - altitude calibration in 'in.HG'
Kohlsman setting knob to calibrate the altitude:
Left mouseclick:Right mouseclick:
DecreaseIncrease
Adjust vertical position of the needle :
Left mouseclick:Right mouseclick:
UpDown
Document based on the DA-20 Flight Manuals by
2 MIN.NO PITCH
INFORMATION
D.C.ELEC
TURN COORDINATOR
N3330
27W
21
18S
12
E6
3
510 15
0 20
510 15
UP
DOWN
VERTICAL SPEED100 FEET PER MINUTE
> TURN AND BANK INDICATOR
> DIRECTIONAL GYRO
> VERTICAL SPEED INDICATOR (VSI)
Page 7 - 12
DA 20 Flight Manual < AIRPLANE & SYSTEMS
When wingtip of the airplane symbol aligns with this marking, the aircraft flies a 360° turn in 2 minutes, which means the plane turns at 3° per second.
The heading indicator is based on a gyro, therefore it drifts with the time, and needs to be aligned before takeoff and also during the flight
Use this knob to calibrate the heading indicator.
Left mouseclick:Right mouseclick:
Decrease HeadingIncrease Heading
iiTip:
Whenever the static port is blocked, the ASI, ALT and VSI won't work anymore. By destroying the glass cover of the VSI due clicking it with the right mouse button, the instruments will do their duty again.
But take care: The VSI will point up while sinking and down will climbing!
Document based on the DA-20 Flight Manuals by
3
RPMx100
5
10
15 2025
30
350 1 3 8 8
HOURS
03330
272
421
1815
12
96
3
SO
B
N3303
27W
21
18S
12
E6
3
> Tachometer
> Course Deviation Indicator (CDI)
> ADF
Page 7 - 13
DA 20 Flight Manual < AIRPLANE & SYSTEMS
Turn OBS knob to select a VOR radial
Left mouseclick:Right mouseclick:
Decrease CourseIncrease Course
To /From Indicator
Needles
Use the knob to turn the Compass Card.
Left mouseclick:Right mouseclick:
Decrease HeadingIncrease Heading
Time the engine has been running.
Maximum RPM:
DA20-80: 2550
DA20-100: 2385
ADF direction pointer
Document based on the DA-20 Flight Manuals by
GMT LT
SELECT CONTROL
VOLTS
1112:53:11
E
NOSE UP
NEUTRAL
NOSE DOWN
TRIM
OAT
+12
> Clock / Timer
> Magnetic Compass
> Trim Indicator
> Outside Air Temperature Display
DIM
BRT
> Annunciator Lights / Canopy Locking Warning Light
Page 7 - 14
DA 20 Flight Manual < AIRPLANE & SYSTEMS
GEN
FUEL
CANOPY
Press to display the voltage.
Start, stop and reset the timer.
Switch between the clock and timer mode.
The indicator shows the current position of the trim tab. For takeoff, set trim to neutral.
The display brightness can be changed with the switch left of the indicator.
iiTip:
Options>Settings>International>Units of measure
Metric - Temperature in °C U.S. System - Temperature in °F
Document based on the DA-20 Flight Manuals by
MANIFOLDPRESSURE
20
in. hg
25
15 30
10 35
Oil
30
ÖLDRUCK
lbs./hg. inch
0 15090
60
VOLT
108
12 1416
AMPS
60-
060+
VDO
Page 7 - 15
DA 20 Flight Manual < AIRPLANE & SYSTEMS
Oil
EM ERAÖLT P TUR
°F
120180
210 250
300
0 1 3 8 80 , h
CHT120
ZY INDERKOPFLTEMPERATUR
180210 250
300
FUEL
01/4 1/2 3/4
1/1
gAusflie bare LUsabl 74
> Engine Gauges
> Manifold Pressure in in.Hg
> Oil Pressure in lbs/ in.Hg
> Voltmeter
> Ammeter
> Hobbsmeter
> Oil Temperature in °F
> Cylinder Head Temperature in °F
> Fuel Quantity
Document based on the DA-20 Flight Manuals by
Page 7 - 16
DA 20 Flight Manual < AIRPLANE & SYSTEMS
7.4.2. Cabin Heat
The cabin heat and defrost system, directs ram air through the coolant radiator and the heat shroud (located around the muffler) into the heat valve. The warm air is then directed to both the window defrosting vents and to the cabin floor. The cabin heat knob, located in front of the center console, is used to regulate the flow of heated air.
knob pulled = cabin heat ON
CABIN HEAT
>>In Flight Simulator:
The Cabin Heat knob only works in the 2d panel. It can not be operated in the virtual cockpit.
7.4.3. Cabin Air
The cabin aeration is controlled by two adjustable air-vent nozzles. The two sliding windows in the canopy can be opened for additional ventilation.
7.5. LANDING GEAR SYSTEM
The landing gear system consists of the two main landing gear wheels mounted to a self-spring steel strut and a free castering nose wheel. The suspension of the nose wheel is handled by an elastomer package. The landing gear wheel fairings are removable. During flight operations without wheel fairings, partially reduced flight performance must be taken into account (see Chapter 5).
7.4.3. Wheel Brakes
Hydraulically operated disc brakes act on the wheels of the main landing gear. The wheel brakes are operated individually using the toe-brake pedals either on the pilot's or on the co-pilot's side. If either the left or right wheel brake system on the pilot’s side fail, the co-pilot’s brakes fail too. The same applies to a failure on the co-pilot’s side, in this case, also the pilot’s brakes fail.
>>In Flight Simulator:
The Katana doesn't have a nose wheel steering. Use differential braking to control the movement on the ground. If you use a 4-axis joystick, try to press the brake button together with moving the rudder. Otherwise useyour keyboard:
F11 F12Left Brake Right Brake
Document based on the DA-20 Flight Manuals by
7.5.2. Parking Brake
The knob is located on the center console in front of the throttle quadrant, and is pushed in when the brakes are to be released. To set the parking brake, pull the knob to the stop. Repeated pushing of the toe-brake pedals will build up the required brake pressure which will remain in effect until the parking brake is released.
knob pulled = parking brake is set
The baggage compartment is located behind the seat above the fuel tank. The baggage should be distributed evenly in the baggage compartment. The baggage net must be secured.
DA 20 Flight Manual < AIRPLANE & SYSTEMS
Page 7 - 17
PARKINGBRAKE
>>In Flight Simulator:
You won't need to apply brake pressure with the pedals. Just use theknob, or press 'CTRL+.'
7.8. CANOPY
7.7. BAGGAGE COMPARTMENT
!!CAUTION:
Ensure that baggage compartment limitations (20 kg max. / 44 lbs) and aircraft weight and balance limitations are not exceeded.
The canopy is closed by pulling down on the forward handles on the canopy frame. Locking the canopy is accomplished by pushing forward on the two locking handles on the left and right side of the frame.
!!CAUTION:
Before starting the engine, the canopy must be closed and locked.
!!NOTE:
The Master Switch must be ON for the Canopy Locking Warning Light to be operational.
>>In Flight Simulator:
Open and close the canopy with the clickspots descriped in 7.4. ,or use 'SHIFT+E' on your keyboard.
Document based on the DA-20 Flight Manuals by
7.9. POWERPLANT
DA 20 Flight Manual < AIRPLANE & SYSTEMS
7.9.1. Engine
Rotax 912, 4 cylinder, 4 stroke engine, horizontally opposed, liquid cooled cylinder heads, air cooled cylinders.
Propeller drive via integrated reduction gear (crankshaft RPM in parentheses).
Displacement: 1.211 litres (73.9 cu.in.)Max. T/O Power (5 min.): 59.6 kW / 80 HP at 2550 RPM (5800 RPM)Max. Continuous Power: 58 kW / 78 HP at 2420 RPM (5500 RPM)
Displacement: 1.352 litres (82.5 cu.in.)Max. T/O Power (5 min.): 100 HP / 73.5 kW at 2385 RPM (5800 RPM)Max. Continuous Power: 94 HP / 69 kW at 2260 RPM (5500 RPM)
Additional information can be found in the Engine Operating Manual.The powerplant instruments are located on the instrument panel on the co-pilot's side. The ignition switch is present in form of a key switch. The ignition is turned on by turning the key to position BOTH. The starter is operated by further turning against spring load to the right (position START). The engine is shut off by the ignition switch. Due to the backlash in the reduction gear, the propeller can be easily turned approximately 30° by hand. Sudden throttle movements should be avoided to prevent impact load in the gearbox.
DA20-80:
DA20-100:
7.9.1. Carburetor Heat, Throttle, Propeller Pitch Control Lever
The Throttle and Propeller Pitch Control levers are grouped together (throttle quadrant) on the center console. The carburetor heat knob is located in the front of the center console.
> Carburetor Heat
square knob, in front of throttle in center console
During normal operation the Carburetor heat is OFF (knob pushed IN)
knob pulled = ON
CARB HEAT
>Throttle
large lever with black conical knobs
lever full forward = FULL throttle
lever full rearward = IDLE
Page 7 - 18
Document based on the DA-20 Flight Manuals by
> Propeller Pitch Control Lever
lever with blue notched knob, right of throttle
lever forward = max. RPM (fine pitch)
lever rearward = min. RPM (coarse pitch)
DA 20 Flight Manual < AIRPLANE & SYSTEMS
Choke
Small black knob below the center instrument panel (self-resetting)
knob pulled = choke ON
>>In Flight Simulator:
FS doesn't support a 'Choke', so this system had to be faked. You can use the switch, but it will have no effect.
7.9.3.
CHOKE
Propeller7.9.4.
The HO-V352F Hoffmann Propeller is used on the DA 20/100 KATANA. The infinitely variable pitch is hydraulically controlled by a Woodward Governor. When the desired propeller RPM is preselected, the governor automatically maintains this RPM, regardless of manifold pressure and airspeed.
Propeller Governor7.9.5.
Woodward A 210786
Propeller Pitch Adjustment7.9.5.
Propeller pitch adjustments are made with the propeller pitch control lever located on the center console (throttle quadrant) to the right of the throttle. Pulling the lever backwards causes a reduction in RPM. The governor keeps the selected RPM constant regardless of airspeed or throttle setting. If the engine power level selected with the throttle is insufficient to keep the selected RPM constant, the propeller blades will move to the smallest possible pitch.The propeller governor is mounted on the engine. It is driven directly by the engine. The propeller governor oil circuit is part of the engine oil circulation system. A defect in the governor or oil system will cause the blades to run to the minimum pitch position. The pitch of the blades can be rotated through its pitch angle by hand.
Page 7 - 19
Document based on the DA-20 Flight Manuals by
ENGINE COMPARTMENT CABIN FUEL COMPARTMENT
Fuel QuanityIndicator
Return Line
Fuel PressureWarning Light
PressureSensor
Oriface
Carburetor
Fuel DistributionManifold
Mechanical Fuel Pump
Carburetor
Supply Line Fuel Shut-OffValve
Vent Line
Ball Valve
Electric Fuel Pump
FillerSignal Line
Fuel Drain Valve
Fuel Drain Tube
7.10. FUEL SYSTEM
DA 20 Flight Manual < AIRPLANE & SYSTEMS
The tank, made from aluminum, is located behind the seats, below the baggage compartment. It holds 76 liters (20.1 US gal.), of which 74 liters (19.5 US gal.) are usable. The tank filler on the left side of the fuselage behind the canopy is connected to the tank with a rubber hose. The tank vent line runs from the filler connection piece through the fuselage bottom skin to the exterior of the airplane .A finger filter is installed at the bottom of the tank. From there, the fuel is fed to the electric fuel pump, and from there, through the middle tunnel to the fuel shut-off valve. From the fuel shut-off valve it is fed to the firewall breach, and further to the mechanical fuel pump. From there, the fuel reaches the distribution manifold and finally the float chambers of both carburetors. A return line runs from the distribution manifold to the tank. Incorporated in the return line is an orifice.
A fuel pressure sensor is installed at the distribution manifold. As soon as the fuel pressure drops below 0.1 bar (1.5 psi), the fuel pressure warning light will illuminate.
Page 7 - 20
GEN
FUEL
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual < AIRPLANE & SYSTEMS
Page 7 - 21
7.10.1. Fuel Shut-Off Valve
!!WARNING:
The fuel shut-off valve should only be closed during engine fire or fuel system maintenance. After reopening, the locking detent should be checked to ensure it performs the proper safety function. Otherwise the danger of operating the airplane with the fuel shut-off valve closed (engine failure) is possible!
F Vuel alveOPEN
Fuel ValveOPEN
Fuel ValveSCLO ED
u V lF el a veO DCL SE
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual < AIRPLANE & SYSTEMS
Page 7 - 22
7.11. ELECTRICAL SYSTEM
GeneratorFailure
2
50
2
GeneratorMaster
Over voltageSensor
Generator
B+
LG
Over voltageRelay
D5
50
2
D4
D5
StarterRelay
BatteryRelay
BatteryMaster
StartSwitch
Battery
Ele
ctrica
l Bu
s
A 12 V battery is connected to the master bus via the master circuit breaker (50 Amps). The 40 amp. generator is attached to the engine near the propeller hub, recharges the battery via the generator circuit breaker (50 Amps).Both circuit breakers can be t r iggered manual ly. The generator warning light is activated by the voltage regulator monitoring circuit and illuminates when the generator is not charging the battery.
7.11.1. Power Supply
The engine is provided with two independent ignition systems. The two magne tos a re independent from the power supply system, and are in operation as soon as the propeller RPM is greater than 100. This ensures safe engine operation even in case of an electrical power failure.
7.11.2. Ignition System
!!WARNING:
If the ignition key is turned to L, R or BOTH, the respective magneto is "hot". If the propeller is moved during this time the engine may fire and cause serious or fatal injury to personnel.
Document based on the DA-20 Flight Manuals by
>>In Flight Simulator:
Turn the ignition key clockwise with the right mouse button.Counter clockwise with the left mouse button.
OF
F
RL OTH
B
SA
RT
T
DA 20 Flight Manual < AIRPLANE & SYSTEMS
Page 7 - 23
7.11.3. Electrical Powered Equipment
The individual consumers (e.g. Radio, Fuel Pump, Position Lights, etc.) are connected in series with their respective circuit breakers. Equipment that does not have switches installed, and requires a switch, is controlled by rocker switches in the lower left side of the instrument panel. Refer to Section 7.4 for an illustration of the instrument panel.
7.11.4. Voltmeter
The voltmeter indicates the status of the electrical bus. It consists of a dial that is marked numerically from 8 - 16 volts in divisions of 2. The scale is divided into three colored arcs to indicate the seriousness of the bus condition. These arcs are:
Red for 8.0 - 11.0 volts,Yellow for 11.0 - 12.5 volts,Green for 12.5 - 16.0 volts,Redline at 16.1 volts.
VOLT
108
12 1416
7.11.5. Ammeter
The ammeter indicates the charging (+) and discharging (-) of the battery. It consists of a dial which is marked numerically from -60 to 60 amps.AMPS
60-
060+
VDO
7.11.6. Generator Warning Light
The generator warning light (red) illuminates during:
- Generator failure, no output from the generator
The only remaining power source is the battery (20 amps. for 30 minutes)
GEN
FUEL
7.11.7. Fuel Pressure Indicator
As soon as the fuel pressure drops below 1.45 psi (0.1 bar), the fuel pressure switch closes, and the fuel pressure warning light illuminates.GEN
FUEL
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual < AIRPLANE & SYSTEMS
Page 7 - 24
7.11.8. Instruments
The instruments for temperatures, oil pressure, and fuel quantity are connected in series with the respective sensors. The electrical resistance of a sensor changes with the measurable variable, which causes the power to the instrument and consequently the needle deflection to change. Oil pressure indicator, cylinder head temperature indicator and fuel pressure warning light are supplied with power through one circuit breaker. Oil temperature indicator and fuel quantity indicator are also protected together by one circuit breaker.
7.11.9. Internal Lighting
The internal lighting of the DA 20/100 KATANA is provided by a lighting module located aft of the Pilot’s head and on the center line of the aircraft. Included in this module are two
panel illumination lights and one map light. The switches for the lights are located on the center console aft of the Trim control switch. There is a dimming control located on the left side of the instrument panel for adjusting the intensity of the panel lighting. As well there is a toggle switch located on the top center of the instrument panel that controls the intensity of the Wing Flap and Trim annunciator. A red LED mounted underneath the instrument panel, on the pilot’s side, is used to illuminate the Fuel Shut Off Valve.
ON
OFF
INSTRUMENTPANEL LIGHT
MAP LIGHT
>>In Flight Simulator:
You may find the map light in the virtual cockpit too bright. It is intended to lighten the cockpit when it is too much shaded by the flight simulator.
7.12. PITOT AND STATIC PRESSURE SYSTEMS
The pitot pressure is measured on the leading edge of a calibrated probe below the left wing. The static pressure is measured by the same probe using two holes in the lower edge and rear edge of the probe. For protection against water and humidity, water sumps are installed within the line. These water sumps are accessible beneath the left seat shell.The error of the static pressure system is small enough to be neglected for the measuring of the altitude. For the error of the airspeed indicating system refer to Chapter 5.The pitot static pressure probe should be protected whenever the aircraft is parked to prevent contamination and subsequent malfunction of the aircraft systems relying on its proper functioning.
7.13. STALL WARNING SYSTEM
When the airspeed drops below 1.1 times the stall speed, a horn sounds in the left instrument panel. The horn grows louder as the speed approaches the stall speed. The horn is activated by suction on a hose that leads from a hole in the leading edge of the left wing to the horn. The hole is marked by a red circle.The stall warning hole should be plugged whenever the aircraft is parked to prevent contamination and subsequent malfunction of the stall warning system.
Document based on the DA-20 Flight Manuals by
DA 20 Flight Manual < AIRPLANE & SYSTEMS
7.14. AVIONICS
The center of the instrument panel contains the radio and navigation equipment. The microphone key for the radio is installed in the control stick. There are two connectors for headsets on the backrest of the seat.
Page 7 - 25
Document based on the DA-20 Flight Manuals by
Com1
Com2
Nav1
Nav2
MKR
ICS
ADF
AUX
DME
SPRCOM3
COM2
COM1 COM1/2
COM2/1
TEL
TRANSMIT SWAP
KMA 28 TSOBENDIX/KING
HILOTM
ISOALL
CREWPUSHOFF/EMG
VOL
O M I
7.14.1 KMA 28 Audio Amplifier/Intercom/Marker Beacon Receiver
Marker BeaconIndicator Lamps
Receive Audio Selectors Mic Selector
Intercom Volume
Use this knob to turn on / off the KMA 28 unit by a click with the left mouse button.
Intercom Volume
Manage the sources you want to hear. Click the Nav1/2, MKR, ADF or DME pushbuttons to turn on or off the receivers. Every switch has an integrated green LED, if it illuminated, the receiver is audible. Com1/2 are no pushbuttons, use the Mic Selector Switch to control the transceivers.
Receive Audio Selectors
Above the Intercom Volume Switch you'll find the visual indicators for the Marker Beacon Receiver. Audio can be turned on and off with the 'MKR' pushbutton.
Marker Beacon
>>In Flight Simulator:
Some functions of the KMA 28 don't make sense in a flight simulator, or are even not possible to simulate, for example 'COM3' or 'TEL'. We had to leave those buttons and switches without a function.
DA 20 Flight Manual < AIRPLANE & SYSTEMS
7.14. AVIONICS
The center of the instrument panel contains the radio and navigation equipment. The microphone key for the radio is installed in the control stick. There are two connectors for headsets on the backrest of the seat.
7.14.1 KMA 28 Audio Amplifier/Intercom/Marker Beacon Receiver
Marker BeaconIndicator Lamps
Receive Audio Selectors Mic Selector
DA 20 Flight Manual < AIRPLANE & SYSTEMS
7.14.2 KX 165A
Page 7 - 26
Document based on the DA-20 Flight Manuals by
BENDIX/KING KX 165A TSO
CHAN MODE
TIMER
NAVPULLTEST
PULL 25K PULL OBS
STBYSTBY
COMM
PULL
TESTOFF
121.30 119.55 114.20 109.00
Active CommFrequency
On/Off CommVolume Knob
Standby CommFrequency
Active NavFrequency
Standby NavFrequency
Comm Frequency Transfer Button
Channel Button
Comm FrequencySelect Knob
Nav AudioVolumeControl Comm Frequency
Transfer Button
Nav Mode Button
Nav FrequencySelect Knob
Left-click on the On/Off Comm Volume Knob turns the KX 165A unit on and off.
Clickspots
COMM
PULL
TESTOFF
BENDIX/KING KX 165A TSO
CHAN MODE
TIMER
NAVPULLTEST
PULL 25K PULL OBS
STBYSTBY
121.30 119.55 114.20 109.00
COMM
PULL
TESTOFF
1
2 7
3
4
5 6 10
9
8
1)2)3)4)5)6)7)8)9)
10)
Left-click : Turn the KX 165A unit on / offTune the Standby Comm Frequency. Right click = increase, left click = decrease.Toggle the active / standby frequenciesPress to activate / deactivate the Channel ModeSwitch the channels. Right click = next channel, left click = last channel.Pull to hear ident by a left click.Tune the Standby Nav Frequency. Right click = increase, left click = decrease.Toggle the active / standby frequencies.Toggle the different display modesTune the Standby Nav Frequency or OBS. Right click = increase, left click = decrease.
ACTIVE / CDI MODE
The standby frequency is replaced by the OBS, which can be changed with the 'Nav Frequency Select Knob'. The vertical 'needle' behaves just like the one of a
mechanical CDI,when it is centered, your aircraft is centered on the selected OBS course. When no signal is received, or the signal is to weak,' FLAG' will appear at the left side of the display.
COMM Transceiver
Switch the KX 165A unit on or off with the 'Comm Volume Knob'.
Enter the desired standby frequency. Do not use the knob, click on the frequency in the display instead. Use the 'Comm Frequency Transfer Button' to swap the active and the standby frequency.
The KX 165A can manage up to 32 frequencies saved to channels.
To program a channel, press the 'Channel Button' for longer than 2 seconds. You'll notice 'PG' and a channel number to be displayed. Select the channel you want to program with the 'Comm Frequency Select Knob' and press the 'Comm Frequency Transfer Button'. Now the standby frequency is flashing, and can be altered. To save the frequency to the channel, press the 'Channel Button' once more.
To select a channel, push the 'Channel Button' momentarily, and choose the desired channel with the 'Comm Frequency Select Knob'.
DA 20 Flight Manual < AIRPLANE & SYSTEMS
Page 7 - 27
Document based on the DA-20 Flight Manuals by
NAV Receiver
As long as the standby frequency is displayed, it may be changed via the 'Nav Frequency Select Knob' or by clicking the frequency on the display.
The Nav Receiver is equipped with different modes. They can be switched by the 'Nav Mode Button'.
114.20 072OBS
- -- -- -- -- -- -- -- -- -I
114.20 295 TOBEARING TO/ RADIALFROM
Pushing the 'Nav Mode Button' will switch from the 'CDI Mode' to the 'Bearing To Mode'. The direct course to the station is displayed followed by a 'TO'. Pressing the
button again switches to the 'Radial From Mode'. 'TO' is replaced by 'FR'.
114.20 1:16ET
ELAPSED TIMER
The elapsed timer appears on the right half of the display. A right click on the 'Nav Frequency Select Knob' will start/stop/reset the timer.
OFFBENDIX/KING
VOL
STBY/TIMER
ADF KR 87 TSO
ADF BFO SET/ RST
FLT/ ET
FRQ/ <->
DA 20 Flight Manual < AIRPLANE & SYSTEMS
7.14.3 KR 87ADF SYSTEM
Page 7 - 28
Document based on the DA-20 Flight Manuals by
ANT/ADFMode Annunciation
IN USEFrequency
BFOAnnunciation
ANTADF 323 231BFO
FRQFLTET
IN USEFrequency
STANDBYFrequencyAnnunciation
STANDBY FrequencyFLIGHT TIME orELAPSED TIME
Flight timer andElapsed timermode annunciation
FrequencySelect Knob
ON / OFF / VOLControl Switch
Select ANT mode(out position)Select ADF mode(in position)
SelectBFOButton
FrequencyTransferButton
Select FLIGHTTIMER orELAPSED TIMER
Set and ResetELAPSED TIMER
A right click increases the frequency, a left click decreases the frequency.
Frequency Select Knob
Use this knob to turn on the KR 87 unit by turning it clockwise with the right mouse button -turn it off by turning the button with the left mouse button.
ON / OFF / VOL Control Switch
100 KHz
1 KHz
10 KHz
100 Hz
The active frequency is shown on the left side of the display. A standby frequency is displayed on the right, as long as 'FRQ' is annunciated. While in the FLT (Flight Time) or ET (Elapsed Time) mode, the standby frequency is placed in 'blind memory'.
When 'FRQ' is annunciated, the Frequency Select Knob manipulates the stanby frequency. By pressing the 'Frequency Transfer Button, standby and active frequency get exchanged.
DA 20 Flight Manual < AIRPLANE & SYSTEMS
Antenna (ANT) :
- Select/deselect this mode with the 'ADF' button. - Better audio reception from the station for identification.- Bearing pointer in the ADF instrument will be deactivated and turn to 90° relative position.
ADF :
- Select/deselect this mode with the 'ADF' button.- Bearing pointer shows direction to the tuned station.
BFO:
- Some stations outside the United States are unmodulated. In the BFO mode, the carrier wave and the associated morse code identifier may be heared.
Flight Timer (FLT):
- Selected by pressing 'FLT/ET'. All further activation of the button switches between Flight Timer and Elapsed Timer.- The Flight Timer will reset everytime the power is turned off.- To call back Standby Frequency, press 'FRQ' button.
Elapsed Timer (ET):
- Selected by pressing 'FLT/ET' two times.- Timer is started by pressing 'SET/RST' button. - Pressing 'SET/RST' a second time will stop the timer.- Pressing a third time will reset the timer.- To call back Standby Frequency, press 'FRQ' button.
Operating Modes
ANT 323 21:38 FLT
ANT 323 ET00:01:38
Page 7 - 29
Document based on the DA-20 Flight Manuals by
ONSTBY
OFF
ALT
TST
KT76ABENDIX/KING
IDENT
0 0 2 1
DA 20 Flight Manual < AIRPLANE & SYSTEMS
7.14.4 KT 76A TRANSPONDER
Page 7 - 30
Document based on the DA-20 Flight Manuals by
Function SelectorKnob
Ident Button
Ident Light
Set transponder code:
Right clickLeft click
= =
increasedecrease
OFF: KT 76 is unpowered.
STBY: The unit energized, but does not reply to any interrogation.
ON: The transponder is able to respond to Mode A and C interoggations.
ALT: The transponder is able to respond to Mode A and C interoggations, altitude reporting capability.
TST: Initializing self test routine.
Operating Modes
DA 20 Flight Manual < AIRPLANE & SYSTEMS
Turn the KN 62A Unit on/off with a left mouse click on the corresponding switch.
7.14.5 KN 62A Digital DME
ON / OFF Switch
RMT FREQ GS/T
OFF
KN62A DME
BENDIX/KING
3-Position Function Switch:
NM RMT MHZ26.6 113.00
Remote (RMT) TimingFrequency (FREQ) Groundspeed/Time-to-Station (GS/T)
RMT FREQ GS/T
NM MHZ92.4 112.30
RMT FREQ GS/T
NM MHZ26.6 113.00
RMT FREQ GS/T
NM KT MIN26.6 83 18
Switch between the different modes with the 3-Position Function Switch. A left click moves the switch to the left, a right click to the right.
DISTANCE FREQUENCY
DISTANCE FREQUENCY
DISTANCE GROUND- SPEED
TIME TOSTATION
FREQUENCY MODE
REMOTE MODE
GROUND SPEED /TIME-TO-STATION MODE
>>In Flight Simulator:
The KN 62A Unit is allways linked to the Nav Receiver Unit (KX165A).
Page 7 - 31
Document based on the DA-20 Flight Manuals by
7.15. EXTERIOR MODEL AND VIRTUAL COCKPIT
DA 20 Flight Manual < AIRPLANE & SYSTEMS
Page 7 - 32
Document based on the DA-20 Flight Manuals by
>>In Flight Simulator:
Special features:
Apply and remove tie downs and wheel chocks: wing fold
Open and close fuel cap: tailhook
Remove engine cowling: # (spoilers, airbrake)
Note: Maybe you haven't assigned a key to the functions 'wing fold' and 'tailhook'. You'll find them under Options>Controls>Assignments: Event: 'Tail hook up/down' and 'Wing fold/unfold'
The exterior model has been created with the recently released software development kit, so expect the newest FS9 features to be included in this addon, as they are dynamic shine, usable switches and levers in the virtual cockpit, rain dropping on the canopy and much more.
The Katana features 5 levels of detail (LOD) to obtain good framerates, even if you meet another one during a mulitplayer session.