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

Document based on the DA-20 Flight Manuals by

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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 operating 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

5


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


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1.5. DIMENSIONS


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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


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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


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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


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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.


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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


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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.


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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.


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



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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


(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


Powerplant instrument markings and their color code significance are shown below:

2.6. MISCELLANEOUS INSTRUMENT MARKINGS


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2.7. WEIGHT


: 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


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


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

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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


Page 4 -4


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


Page 4 -5


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.


Page 4 -6


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.


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


13. Electric Fuel Pump OFF

Page 4 -7


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


!!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


4.4.6. Before Take-Off (Engine Run-Up)


Page 4 -9


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


check pressed IN17. Circuit Breakers

18. Electric Fuel Pump ON

19. Wing Flaps T/O

release20. Parking Brake

4.4.7. Take-off


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)


!!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


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


Page 4 -11


!!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


3. Propeller Speed Control Lever 1700 - 2260 RPM

4. Carburetor Heat as required


!!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



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.


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


2. Throttle FULL


4. Wing Flaps T/O


5. Airspeed 57 kts / 66 mph / 106 km/h

4.4.13. After Landing


2. Wing Flaps UP




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


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



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


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)



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)



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


5.3.2.B Figure 5.2B: Cruising Performance DA20-100


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


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%


MPIn.Hg


RPMX100

MPIn.Hg


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


MPIn.Hg


RPMX100

MPIn.Hg


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


Configuration:

Idle, most forward center of gravity, max. weight (this is the most adverse configuration)

5.3.3. Figure 5.3: Stall Speeds


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°


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°


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


Maximum demonstrated crosswind component: 15 kts (27 km/h)

5.3.4. Figure 5.4: Wind Components


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


5.3.5.A Figure 5.5A: Take-Off Distance DA20-80


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


5.3.5.B Figure 5.5B: Take-Off Distance DA20-100


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



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



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)


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



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



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



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



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



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)


Page5 - 15



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)


Page5 - 16


a)

b)


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


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.


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)


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


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


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.


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



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


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



F5

F6


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



7.4. INSTRUMENT PANEL


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


7.4.1. Flight Instruments


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


> Radio Panel


(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


> Control Stand


(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


> Panel Switcher


(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


> Approach View


(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



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



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 :


UpDown


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


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.


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!


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


Turn OBS knob to select a VOR radial


Decrease CourseIncrease Course

To /From Indicator

Needles

Use the knob to turn the Compass Card.


Decrease HeadingIncrease Heading

Time the engine has been running.

Maximum RPM:

DA20-80: 2550

DA20-100: 2385

ADF direction pointer


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


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


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


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


16


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


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.


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


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.


Page 7 - 17

PARKINGBRAKE


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.


Open and close the canopy with the clickspots descriped in 7.4. ,or use 'SHIFT+E' on your keyboard.


7.9. POWERPLANT


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


> Propeller Pitch Control Lever

lever with blue notched knob, right of throttle

lever forward = max. RPM (fine pitch)

lever rearward = min. RPM (coarse pitch)


Choke

Small black knob below the center instrument panel (self-resetting)

knob pulled = choke ON


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


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


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



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



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.



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


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



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


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.



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


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


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.


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


7.14.2 KX 165A

Page 7 - 26


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'.


Page 7 - 27


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/ <->


7.14.3 KR 87ADF SYSTEM

Page 7 - 28


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.


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


ONSTBY

OFF

ALT

TST

KT76ABENDIX/KING

IDENT

0 0 2 1


7.14.4 KT 76A TRANSPONDER

Page 7 - 30


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


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


The KN 62A Unit is allways linked to the Nav Receiver Unit (KX165A).

Page 7 - 31


7.15. EXTERIOR MODEL AND VIRTUAL COCKPIT


Page 7 - 32



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.