Diamond JAR-VLA Flight Manual

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Page 1

JAR-VLA

FLIGHT MANUAL

DA 20/100

Category of Airworthiness : NORMAL

Applicable Airworthiness Requirements :JAR VLA incl. Amendment VLA/92/1

Serial No. :

Registration :

Date of Issue : 20 December, 2000

Document No. : DA202-100-VLA

This manual must be carried in the aircraft at all times! Scope and revision status can be found in the List

of Effective Pages and in the Record of Revisions.

The pages identified as "DOT-appr." in the List of Effective Pages are approved by:

Signature

Authority

Date of approval 20 December, 2000

This airplane is to be operated in compliance with the information and limitations contained herein.

William Jupp

Chief, Flight test

For Director, Aircraft Certification

Transport Canada

Page 0 - 1

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DIAMOND AIRCRAFT DA 20/100 Flight Manual

PREFACE

Congratulations on your choice of the DA 20/100 KATANA.

Safe handling of an airplane increases and ensures your safety and provides you with many hours of

enjoyment. For this reason you should take the time to familiarize yourself with your KATANA airplane.

We ask that you carefully read this Flight Manual and pay special attention to the recommendations

given. A careful study of the manual will reward you with many hours of trouble-free flight operation of

your KATANA airplane.

thereof by any means without the express written permission of

DIAMOND AIRCRAFT INDUSTRIES prohibited.

 by DIAMOND AIRCRAFT INDUSTRIES,

London, Ontario

Doc # DA202-100-VLA 20 December, 2000 Page Issue 1 0 - 2

Canada

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DIAMOND AIRCRAFT DA 20/100 Flight Manual

TABLE OF CONTENTS

Chapter

GENERAL 1

OPERATING LIMITATIONS

EMERGENCY PROCEDURES

NORMAL OPERATING PROCEDURES

PERFORMANCE

WEIGHT AND BALANCE / EQUIPMENT LIST

DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS

HANDLING, PREVENTIVE AND CORRECTIVE MAINTENANCE

SUPPLEMENTS 9

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DIAMOND AIRCRAFT DA 20/100 Flight Manual

LIST OF EFFECTIVE PAGES

Chapter

0 0-1 20 Dec., 2000 3 DOT-appr 3-1 18 Nov., 2003

0-2 20 Dec., 2000 DOT-appr 3-2 09 Mar., 2001 0-3 20 Dec., 2000 DOT-appr 3-3 20 Dec., 2000 0-4 22 Aug., 2006 0-5 March 19, 2004 0-6 22 Aug., 2006 0-7 20 Dec., 2000 DOT-appr 3-7 20 Dec., 2000 0-8 20 Dec., 2000 DOT-appr 3-8 20 Dec., 2000 0-9 18 Nov., 2003 DOT-appr 3-9 20 Dec., 2000 DOT-appr 3-10 20 Dec., 2000

1 1-1 20 Dec., 2000 DOT-appr 3-11 20 Dec., 2000

1-2 20 Dec., 2000 DOT-appr 3-12 20 Dec., 2000 1-3 20 Dec., 2000 DOT-appr 3-13 09 Mar., 2001 1-4 20 Dec., 2000 DOT-appr 3-14 20 Dec., 2000 1-5 20 Dec., 2000 DOT-appr 3-15 20 Dec., 2000 1-6 20 Dec., 2000 DOT-appr 3-16 20 Dec., 2000 1-7 18 Nov., 2003 DOT-appr 3-17 20 Dec., 2000 1-8 22 Aug., 2006 1-9 09 Mar., 2001

1-14 20 Dec., 2000 DOT-appr 4-5 20 Dec., 2000 DOT-appr 4-6 20 Dec., 2000

2 DOT-appr. 2-1 20 Dec., 2000 DOT-appr 4-7 20 Dec., 2000

DOT-appr 2-2 20 Dec., 2000 DOT-appr 4-8 20 Dec., 2000 DOT-appr 2-3 20 Dec., 2000 DOT-appr 4-9 20 Dec., 2000 DOT-appr 2-4 20 Dec., 2000 DOT-appr 4-10 20 Dec., 2000 DOT-appr 2-5 18 Nov., 2003 DOT-appr 4-11 20 Dec., 2000 DOT-appr 2-6 09 Mar., 2001 DOT-appr 4-12 20 Dec., 2000 DOT-appr 2-7 18 Nov., 2003 DOT-appr 4-13 20 Dec., 2000 DOT-appr 2-8 20 Dec., 2000 DOT-appr 4-14 20 Dec., 2000 DOT-appr 2-9 20 Dec., 2000 DOT-appr 4-15 20 Dec., 2000 DOT-appr 2-10 20 Dec., 2000 DOT-appr 4-16 20 Dec., 2000 DOT-appr. 2-11 20 Dec., 2000 DOT-appr 4-17 20 Dec., 2000 DOT-appr 2-12 20 Dec., 2000 DOT-appr 4-18 20 Dec., 2000 DOT-appr 2-13 20 Dec., 2000 DOT-appr 2-14 20 Dec., 2000 DOT-appr 2-15 22 Aug., 2006 DOT-appr 2-16 20 Dec., 2000 DOT-appr 2-17 20 Dec., 2000

Page Date Chapter

1-10 20 Dec., 2000 4 DOT-appr 4-1 20 Dec., 2000 1-11 20 Dec., 2000 DOT-appr 4-2 20 Dec., 2000 1-12 20 Dec., 2000 DOT-appr 4-3 20 Dec., 2000 1-13 20 Dec., 2000 DOT-appr 4-4 20 Dec., 2000

DOT-appr 3-4 20 Dec., 2000 DOT-appr 3-5 20 Dec., 2000 DOT-appr 3-6 20 Dec., 2000

DOT-appr 3-18 20 Dec., 2000

Page Date

Doc # DA202-100-VLA Revision 4 0 - 4

22 August, 2006 Page

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DIAMOND AIRCRAFT DA 20/100 Flight Manual

Chapter Page Date Chapter Page Date

5 DOT-appr 5-1 March 19, 2004 7-17 20 Dec., 2000

5-2 20 Dec., 2000 7-18 20 Dec., 2000 DOT-appr 5-3 20 Dec., 2000 5-4 20 Dec., 2000 8 8-1 20 Dec., 2000 DOT-appr 5-5 20 Dec., 2000 8-2 20 Dec., 2000 DOT-appr 5-6 20 Dec., 2000 8-3 20 Dec., 2000 DOT-appr 5-7 March 19, 2004 8-4 20 Dec., 2000 DOT-appr 5-8 March 19, 2004 8-5 20 Dec., 2000 DOT-appr 5-9 March 19, 2004 8-6 20 Dec., 2000 DOT-appr 5-10 March 19, 2004 8-7 20 Dec., 2000 DOT-appr 5-11 March 19, 2004 DOT-appr 5-12 March 19, 2004 9 9-1 20 Dec., 2000 DOT-appr 5-13 March 19, 2004 9-2 20 Dec., 2000 DOT-appr 5-14 March 19, 2004

DOT-appr 5-15 March 19, 2004 Supp. 1 S1-1 20 Dec., 2000

S1-2 20 Dec., 2000

6 DOT-appr. 6-1 20 Dec., 2000 S1-3 20 Dec., 2000

DOT-appr 6-2 20 Dec., 2000 DOT-appr 6-3 20 Dec., 2000 DOT-appr 6-4 20 Dec., 2000 6-5 20 Dec., 2000 6-6 20 Dec., 2000 DOT-appr 6-7 20 Dec., 2000 DOT-appr 6-8 09 Mar., 2001 DOT-appr 6-9 09 Mar., 2001 DOT-appr 6-10 18 Nov., 2003 6-11 20 Dec., 2000 6-12 20 Dec., 2000 6-13 20 Dec., 2000 6-14 20 Dec., 2000 6-15 20 Dec., 2000

7 7-1 20 Dec., 2000

7-2 20 Dec., 2000 7-3 20 Dec., 2000 7-4 20 Dec., 2000 7-5 20 Dec., 2000 7-6 20 Dec., 2000 7-7 20 Dec., 2000 7-8 20 Dec., 2000 7-9 20 Dec., 2000 7-10 20 Dec., 2000 7-11 20 Dec., 2000 7-12 18 Nov., 2003 7-13 20 Dec., 2000 7-14 20 Dec., 2000 7-15 20 Dec., 2000 7-16 20 Dec., 2000

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[INTENTIONALLY LEFT BLANK]

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DIAMOND AIRCRAFT DA 20/100 Flight Manual

REVISION LOG

This log should be used for control of all revisions issued and installed in this manual. The affected

pages of any revision as well as the Record of Revisions must be inserted into the manual upon receipt.

The pages superseded by the revision must be removed and destroyed. The Revision Log should be

updated by hand. Changes are identified on those pages affected by a revision bar.

Rev. No. Date Issued: Inserted On: Inserted By:

Issue 1

20 Dec., 2000 20 Dec., 2000

Diamond Aircraft

Doc # DA202-100-VLA 20 December, 2000 Page Issue 1 0 - 8

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DIAMOND AIRCRAFT DA 20/100 Flight Manual

SUBSCRIPTION SERVICE

Diamond Aircraft Publications Revision Subscription Contacts

To ensure safe operation and maintenance of the DA20/100 Katana aircraft, it is recommended

that operators verify that their documentation is at the correct issue/revision levels. For revision

and subscription service please contact the following:

1. DA20/100 Katana related manuals and publications.

North America, Australia, South Africa: Europe, Other:

Diamond Aircraft Industries Inc. Customer Support 1560 Crumlin Sideroad London, Ontario Canada N5V 1S2 www.diamondair.com Phone:

Fax:

519-457-4041 519-457-4045

Diamond Aircraft Industries GmbH Customer Support N.A. Otto-Strasse 5 A-2700 Wiener Neustadt Austria

www.diamond-air.at Phone:

Fax:

011-43-2622-26700 011-43-2622-26780

2. Rotax 912 Engine related manuals and publications.

North America:

Rotech Research Canada LTD. 6235 Okanagan Landing Road Vernon, British Columbia Canada V1H 1M5 www.rotec.com Phone:

Fax:

OR Contact your authorized Rotax Engine distributor as listed in the back of the 912 Operators Manual.

3. Hoffmann Propeller Model HO-V352 related manuals and publications.

North America, Australia, South Africa: Europe, Other:

Diamond Aircraft Industries Inc. Customer Support 1560 Crumlin Sideroad London, Ontario Canada N5V 1S2 www.diamondair.com Phone:

Fax:

250-260-6299 250-260-6269

519-457-4041 519-457-4045

HB- FLUGTECHNIK GES.M.B.H. Dr. Adolf Scharf Str. 44 A-4053HAID

www.rotax.bombardier.com Phone:

Fax:

Hoffmann Propeller GmbH. & Co. Customer Support Kupferlingstr. 9 D-83022 Rosenheim Germany

Phone:

Fax:

07229 / 79104/79117 07229 / 79104 15

011-49-8031-1878-0 011-49-8031-1878-78

Doc # DA202-100-VLA November 18, 2003 Page Revision 2 0 - 9

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DIAMOND AIRCRAFT DA 20/100 Flight Manual General

CHAPTER 1

GENERAL

1.1. INTRODUCTION 1- 1

1.2. CERTIFICATION BASIS 1- 2

1.3. WARNINGS, CAUTIONS, AND NOTES 1- 2

1.4. THREE-VIEW-DRAWING OF AIRPLANE 1- 3

1.5. DIMENSIONS 1- 4

1.6. ENGINE 1- 5

1.7. PROPELLER 1- 5

1.8. FUEL 1- 6

1.9. LUBRICANT AND COOLANT 1- 7

1.10. WEIGHT 1- 9

1.11. LIST OF DEFINITIONS AND ABBREVIATIONS 1-10

1.12. CONVERSION FACTORS 1-14

1.1. INTRODUCTION

The Airplane Flight Manual has been prepared to provide pilots and instructors with information for the

safe and efficient operation of this airplane.

This Manual includes the material required by JAR-VLA including amendment VLA/92/1. It also contains

supplemental data supplied by the airplane manufacturer that can be useful to the pilot.

The Flight Manual conforms to a standard equipped DA 20/100 KATANA. Any optional equipment

installed on request of the customer (COMM, NAV, etc.) is not considered.

For the operation of optional equipment the Operation Manual of the respective vendor must be used.

For permissible accessories refer to the equipment list, Section 6.5.

Doc # DA202-100-VLA 9 March, 2001 Page Revision 1 1 - 1

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DIAMOND AIRCRAFT DA 20/100 Flight Manual General

1.2. CERTIFICATION BASIS

The DA 20/100 has been approved by Transport Canada as meeting the requirements of JAR-VLA and

amendment VLA/92/1. The Type Certificate No. A-191, originally issued on July 29th, 1994, has been

revised to include the DA20/100.

Category of Airworthiness: NORMAL

Noise Certification Basis: a) Canadian Airworthiness Manual Chapter 516

b) FAA Part 36

c) LBA: LSL Chapter X of 1.01.1991

For others, refer to the national type certificate data sheets, as applicable.

1.3. WARNINGS, CAUTIONS, AND NOTES

The following definitions apply to warnings, cautions, and notes used in the Flight Manual:

WARNING

means that the non-observation of the corresponding procedure leads to an

immediate or important degradation of the flight safety.

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 but

which is important or unusual.

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DIAMOND AIRCRAFT DA 20/100 Flight Manual General

1.4. THREE-VIEW-DRAWING OF AIRPLANE

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DIAMOND AIRCRAFT DA 20/100 Flight Manual General

1.5. DIMENSIONS

1.5.1 Overall Dimensions

Span: 35 ft 7 in (10.84 m)

Length: 23 ft 6.0 in ( 7.17 m)

Height: 6 ft 11.0 in ( 2.10m)

1.5.2 Wing

Airfoil: Wortmann FX 63-137/20 HOAC

Wing Area: 125 sq.ft. (11.6 m

Mean Aerodynamic

3 ft 6.9 in ( 1.09 m)

)

Chord (MAC):

Aspect Ratio: 10.0

Dihedral: +4° nominal

Sweep of Leading Edge: +1° nominal

1.5.3 Horizontal Stabilizer

Angle of Incidence : -2.5° ±0.5°

Span: 8 ft 8 in (2.65 m)

1.5.4 Landing Gear

Track: 6 ft 3 in (1.90 m)

Wheel Base: 5 ft 9 in (1.75 m)

Tire Size:

Nose:

4.00-4 (TOST)

Tire Pressure:

Main:*

Nose:

Main:

* Main tires must be same brand, model and size.

Doc # DA202-100-VLA 9 March, 2001 Page Revision 1 1 - 4

5.00-4 (GOODYEAR)

15 x 6.00-5 (GOODYEAR) or

5.00 x 5, 6 Ply (TSO C62)

26 psi (1.8 bar)

33 psi (2.3 bar)

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DIAMOND AIRCRAFT DA 20/100 Flight Manual General

1.6. ENGINE

Rotax 912S, 4 Cylinder, 4 Stroke-Engine, horizontally opposed, liquid cooled cylinder heads, air-cooled

cylinders.

Propeller drive via integrated reduction gear.

Reduction Ratio: 2.43 : 1

Displacement: 82.5 cu.in. (1.352 liters)

Output Power: 100 hp (73.5 kW)

at 2385 RPM

1.7. PROPELLER

Two-bladed variable pitch propeller, manufactured by HOFFMANN,

Constant speed, hydraulic pitch control

Range of Pitch Angle:

Diameter: 5 ft 6.9 in (1.70 m)

model HO-V352F/170FQ OR

model HO-V352F/C170FQ

10° - 35°

Doc # DA202-100-VLA 9 March, 2001 Page Revision 1 1 - 5

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DIAMOND AIRCRAFT DA 20/100 Flight Manual General

1.8. FUEL

Approved Fuel Grades: AVGAS 100LL

Automotive Gasoline, Unleaded, Minimum

95 RON or 91 AKI

RON = Research Octane Number

MON = Motor Octane Number

AKI = Anti Knock Index =

Total Fuel Capacity:

Usable Fuel: 19.5 US gal. (74 liters)

Unusable Fuel: 0.6 US gal. ( 2 liters)

Specifications: Europe - EN 228

USA - ASTM D4814

Canada –

20.1 US gal. (76 liters)

(or more current issue)

MON + RON 2

CAN/CGSB-3.5-94

CAUTION

Use of automotive gasoline containing alcohol (e.g.: methanol or

ethanol) other than specified in the above listed specifications, is not

permitted.

Petroleum suppliers provide automotive gasoline of varying volatilities, depending on the season and climatic zone. Fuels with higher volatility (“cold weather” grade fuels) are more susceptible to fuel vapour formation than fuels with lower volatility (“hot weather” grade fuels), at equal temperatures. Use of fuels dispensed in winter or in colder climatic zones, under high ambient temperature conditions, increases the risk of vapor formation and subsequent possible engine malfunction.

Doc # DA202-100-VLA 9 March, 2001 Page Revision 1 1 - 6

NOTE

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DIAMOND AIRCRAFT DA 20/100 Flight Manual General

1.9. LUBRICANT AND COOLANT

1.9.1. Lubricant

Use only motor oil with API classification SF or SG or higher.

Due to high stresses in the reduction gears, a 4 stroke motorcycle oil of a registered brand with gear additives

that meets API classification SF or SG are highly recommended.

The viscosity should be selected according to the various climatic conditions using the following table.

When operating with AVGAS100LL fuel do not

Oil Capacity: Minimum : 3.0 liters (3.2 US qt.)

Maximum : 3.4 liters (3.6 US qt.)

Doc # DA202-100-VLA November 18, 2003 Page Revision 2 1 - 7

CAUTION

Do not use aviation lubricant!

use synthetic oil.

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DIAMOND AIRCRAFT DA 20/100 Flight Manual

General

1.9.2. Coolant

EVANS NPG+ waterless coolant or a comparable coolant must be used without water or other

additives.

WARNING

Water or water-containing coolant must not be added in any case to the cooling system.

CAUTION

The coolant manufacturer’s data for change/replacement, usage, and operation are to be

observed.

(a) Coolant Capacity:

Minimum

Maximum : 2.6 US qt. (2.5 liters)

(b) Reservoir Capacity:

Minimum

Maximum : 0.21 US qt. (0.2 liters)

: 2.5 US qt. (2.4 liters)

: 0.11 US qt. (0.1 liters)

NOTE

The level in the reservoir can be checked using the coolant dipstick. Excessive overfilling

of the reservoir can result in overflow during operation. In the event of a completely empty

reservoir, the coolant level in the dispatcher vessel on top of the engine must also be

checked.

Doc # DA202-100-VLA August 22, 2006 Page Revision 4 1 - 8

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DIAMOND AIRCRAFT DA 20/100 Flight Manual General

1.10. WEIGHT

Maximum Take-off Weight : 750 kg (1653 lbs)

Maximum Landing Weight : 750 kg (1653 lbs)

Empty Weight : See Chapter 6

Maximum Weight in Baggage Compartment

: 20 kg (44 lbs)

only if restraining devices available

Wing Loading

At Maximum Take-off Weight

: 64.61 kg/m

(13.23 lbs/sq.ft.)

Performance Load at Max. Take-off Weight : 7.50 kg/hp (16.53 lbs/hp.)

Doc # DA202-100-VLA 9 March, 2001 Page Revision 1 1 - 9

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DIAMOND AIRCRAFT DA 20/100 Flight Manual General

1.11. LIST OF DEFINITIONS AND ABBREVIATIONS

1.11.1. Speed

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.

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 and

temperature errors.

: Maneuvering speed. Maximum speed at which the airplane is not overstressed at full

deflection of control surfaces.

: Maximum speed with flaps extended.

: Speed which must never be exceeded in any operation.

: Maximum structural cruising speed which should only be exceeded in calm air, and then

only with caution.

: The power-off stall speed with the airplane in its standard configuration.

: The power-off stall speed with the airplane in landing configuration.

: Best angle-of-climb speed.

: Best rate-of-climb speed.

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DIAMOND AIRCRAFT DA 20/100 Flight Manual General

1.11.2. Meteorological Terms

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.

1.11.3. Powerplant

Take-off Power:

Maximum engine power for take-off.

Maximum Continuous Power:

Maximum permissible continuous engine output power during flight.

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DIAMOND AIRCRAFT DA 20/100 Flight Manual General

1.11.4. Flight Performance and Flight Planning

Demonstrated Crosswind Component:

The maximum speed of the crosswind component at which the maneuvrability 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 0.5 m/s (100 ft/min.).

1.11.5. Weight and Balance

Reference Datum (RD):

An imaginary vertical plane from which all horizontal distances for the center 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.

Lever Arm:

The horizontal distance from the reference datum to the center of gravity (of a component).

Moment:

The weight of a component multiplied by its lever arm.

Center 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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DIAMOND AIRCRAFT DA 20/100 Flight Manual General

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.

1.11.6. Equipment

ACL: Anti collision light

1.11.7 Miscellaneous

GFRP - Glass Fibre Reinforced Plastic

CFRP - Carbon Fibre Reinforced Plastic

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DIAMOND AIRCRAFT DA 20/100 Flight Manual General

1.12. CONVERSION FACTORS

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/m

1 [in. Hg] = 33.865 [hPa]

1 [psi] = 68.97 [mbar]

] = 1 [mbar]

1.12.4 Weight

1 [lbs] = 0.454 [kg]

1.12.5 Volume

1 [US gallon] = 3.785 [liters]

1 [Imperial gallon] = 4.546 [liters]

Doc # DA202-100-VLA 20 December, 2000 Page Issue 1 1 - 14

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations

CHAPTER 2

OPERATING LIMITATIONS

2.1 INTRODUCTION 2-1

2.2 AIRSPEED LIMITATIONS 2-2

2.3 AIRSPEED INDICATOR MARKINGS 2-2

2.4 POWERPLANT LIMITATIONS 2-3

2.5 POWERPLANT INSTRUMENT MARKINGS 2-5

2.6 MISCELLANEOUS INSTRUMENT MARKINGS 2-5

2.7 WEIGHT 2-6

2.8 CENTER OF GRAVITY 2-6

2.9 APPROVED MANEUVERS 2-7

2.10 MANEUVERING LOAD FACTORS 2-7

2.11 MAXIMUM PASSENGER SEATING 2-8

2.12 FLIGHT CREW 2-8

2.13 KINDS OF OPERATION 2-8

2.14 FUEL 2-9

2.15 PLACARDS 2-9

2.16 DEMONSTRATED CROSSWIND COMPONENT 2-17

2.17 TEMPERATURE LIMITS 2-17

2.1. INTRODUCTION

Chapter 2 of this Flight Manual comprises 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.

The operating limitations in this Chapter and Chapter 9 have been approved by the Department of

Transport (DOT), and must be complied with for all operations.

These limitations must be complied with for all operations.

Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 2 - 1

WARNING

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations

2.2. AIRSPEED LIMITATIONS

IAS

Speed kts mph km/h Remarks

104 120 193 Do not make full or abrupt control

Maneuvering Speed

81 93 150 Do not exceed this speed with flaps

Maximum Flap Extended Speed

118 135 218 Do not exceed this speed except in

Maximum Structural Cruising Speed

161 185 298 Do not exceed this speed in any operation

Never Exceed Speed

2.3. AIRSPEED INDICATOR MARKINGS

IAS

movement above this speed, because under certain conditions the airplane may be overstressed by full control movement.

extended

smooth air, and then only with caution

Marking kts mph km/h Explanation

White Arc 37-81 43-93 69-150 Operating range with extended flaps

Green Arc 41-118 47-135 76-218 Normal operating range

Yellow Arc 118-161 135-185 218-298 Maneuvers must be conducted with

caution and only in smooth air.

Red Line 161 185 298 Maximum permissible speed for all

operating modes

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations

2.4. POWER PLANT LIMITATIONS

2.4.1. Engine

(a) Engine Manufacturer

(b) Engine Type Designation

: Bombardier Rotax, Gunskirchen/Austria

: 912 S3

NOTE

The propeller is driven by the engine via a reduction gear with a ratio of 2.43:1. The RPM indicator indicates the propeller speed. For that reason, all speed references within this manual - contrary to the engine manual - are propeller speeds.

Max. T/O Power (5 min.) : 100 hp / 73.5 kW

Max. Permissible T/O RPM : 2385 RPM

Max. Continuous Power : 93 hp / 69 kW

Max. Permissible Continuous RPM : 2260 RPM

(d) Oil Pressure

Minimum

Normal

Max. in case of Cold-start (short-term) : 102 psi (7.0 bar)

(e) Fuel Pressure

Minimum : 2.2 psi (0.15 bar)

Maximum : 5.8 psi (0.40 bar)

(f) Oil Temperature

Minimum : 122°F ( 50°C)

Maximum : 266°F (130°C)

: 12 psi (.8 bar) Below 1440 RPM

: 29 psi – 73 psi (2.0-5.0 bar) Above 1440 RPM

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations

(g) Cylinder Head Temperature

Maximum : 275°F (135°C)

(h) Fuel Specifications

Approved Fuel Grades : AVGAS 100LL

(i) Oil Grades

2.4.2. Propeller

(a) Propeller Manufacturer

(b) Propeller Type

HO-V352F/C170FQ

Unleaded Automotive Fuel 95 RON /91 AKI

(refer also to page 1-6)

: 4 stroke motorcycle oil of a registered brand with gear additives that meets or exceedes API classification SF or SG are highly recommended.

(also see Page 1-7 for additional information on the selection of suitable lubricants)

: Hoffmann Propeller, Rosenheim/Germany

: HO-V352F/170FQ OR

: 5 ft 6.9 in (1.70 m)

(d) Propeller Pitch (at 3/4 radius)

(e) Propeller Speed Limitations

: 10° - 35°

Max. T/O RPM (max. 5 min.) : 2385 RPM

Max. Continuous RPM : 2260 RPM

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations

2.5. POWERPLANT INSTRUMENT MARKINGS

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

Instrument Red Line

= Lower Limit

Tachometer -

Oil Temperature

Indicator

Cylinder Head

Temperature

Indicator

Oil Pressure

Indicator

* Recommended nominal idle speed = 950 RPM

122° F

50° C

- - - 275° F

12 psi

0.8 bar

Green Arc

= Normal

Operating Range

*600 - 2260 RPM

122- 266° F

50 - 130° C

29 - 73 psi

2 - 5 bar

ABOVE 1440

RPM

Yellow Arc

= Caution Range

2260 - 2385 RPM

12 – 29 psi

0.8 – 2 bar

BELOW 1440

RPM

73 - 102 psi

5 - 7 bar

2.6. MISCELLANEOUS INSTRUMENT MARKINGS

Red Line

= Upper Limit

2385 RPM

- 266° F

130° C

135° C

102 psi

7 bar

Instrument Red Line

= Lower Limit

Voltmeter 8-11 Volts 12.5 - 16 Volts 11 - 12.5 Volts 16.1 Volts

Green Arc

= Normal

Operating Range

Yellow Arc

= Caution Range

Red Line

= Upper Limit

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations

2.7. WEIGHT

Maximum permissible weight : 750 kg (1653 lbs)

Maximum permissible weight in the baggage compartment

: 20 kg (44 lbs) only permissible with baggage harness

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. Procedures for horizontal

alignment, as well as particulars with regard to the empty weight center of gravity, refer to Chapter 6.

Most forward CG (all weights) : 250 mm (9.84 in) aft of RD

Most rearward CG (all weights) : 390 mm (15.35 in) aft of RD

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.

Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 2 - 6

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations

2.9. APPROVED MANEUVRES

This airplane is certified in the NORMAL Category in accordance with JAR-VLA.

Permissible Normal Category Maneuvres:

a) All normal flight maneuvres

b) Stalls (except WHIP 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:

Positive + 4.4 + 4.4 + 2.0

Negative - 2.2 - 2.2 0

at vA: at vNE: with fully

extended flaps

WARNING

Exceeding the maximum load factors will result in overstressing of the airplane.

Simultaneous full deflection of more than one control surface can result in overstressing

of the structure, even at speeds below the maneuvering speed.

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations

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 Indicator

Altimeter

Magnetic Compass

Minimum Equipment, Powerplant Instruments:

Fuel Quantity Indicator

Oil Pressure Indicator

Oil Temperature Indicator

Manifold Pressure Indicator

Cylinder Head Temperature Indicator

Tachometer

Fuel Pressure Warning Light

Voltmeter

Ammeter

Generator 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.

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations

2.14. FUEL

Fuel Capacity

Total Fuel Quantity: : 20.1 US gal. (76 liters)

Usable Fuel: : 19.5 US gal. (74 liters )

Unusable Fuel: : 0.53 US gal. ( 2 liters)

2.15. PLACARDS

The following placards must be installed:

1. On the instrument panel next to airspeed indicator

Effective for all aircraft operated strictly under JAR-VLA regulations

This airplane is classified as a very light airplane approved for day VFR only, in non-icing conditions. All aerobatic maneuvres, including intentional spinning, are prohibited. See Flight Manual for other limitations.

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations

2. On the instrument panel under the airspeed

3. Next to the switches

4. On the flap control

5. On the dimming switch for trim display, flap control and GPS (if installed)

6. Next to dimming potentiometer for cabin and fuel shut-off valve light

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations

7. On the instrument panel next to the individual circuit breakers



Depending on aircraft specific avionic

equipment configuration.

Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 2 - 11



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DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations

8. On top of the instrument panel under the compass

10. On top the instrument panel within pilot’s direct line of vision

11. On DME channeling switch on the RH

side of the radio stack (optional)

9. Around Trim Display on top of the instrument panel

12. Above RH air vent on the instrument panel (optional)

13. Above the OAT indicator 14. Below Microphone jack on LH side of the instrument panel

15. On the fuel quantity gauge 16. Next to GPS (if installed)

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations

17. Under the instrument panel next to the individual knobs

18. On the centre console between throttle and propeller levers

19. On the side of the throttle quadrant next to tension adjustment knob

20. Next to trim switch on the centre console

21. Next to instrument and map light switches on the centre console

22. Next to fuel shut-off valve in correct position

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations

23. Next to canopy release handles

Inside Left (partially coloured red) Inside Right (partially coloured red)

Outside Left Outside Right

24. Next to ELT (if installed) to indicate switch position

for EBC 102A ELT model for EBC 502 ELT model

25. Next to Headset Jacks on the Back Rest

Pilot side (LH) Co-pilot side (RH)

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations

26. On the LH side of baggage compartment 27. On the brake fluid reservoirs (rudder pedals)

Hydraulic Fluid

MIL-H-5606

28. On inside of oil filler door (coloured red)

29. On oil filler cap

30. On coolant equalizing reservoir

31. On coolant dispatcher vessel

32. Next to fuel filler cap

DO NOT

ADD WATER

TO THIS SYSTEM

STOP!

EVANS NPG+

WATERLESS

COOLANT ONLY

Doc # 202-100-VLA Revision 4 2 - 15

22 August, 2006 Page

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations

33. On fuselage upper skin behind cockpit (only if ELT is installed), coloured yellow

34. On fuselage underside (belly), by left wing

35. Under each wing and tail skid plate

36. Around Stall Warning Hole in left wing

37. On Nose Landing Gear Strut 38. On Main Landing Gear Strut

Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 2 - 16

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations

2.16. DEMONSTRATED CROSSWIND COMPONENT

The maximum demonstrated crosswind component is 15 kts. (27 km/h).

2.17. TEMPERATURE LIMITS

Limits for outside air temperature and temperature of the structure for the operation of the airplane:

Maximum T/O Temperature :

Structural Temperature limit

For Indicator see pg.4-3

131°F (55°C)

Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 2 - 17

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures

CHAPTER 3

EMERGENCY PROCEDURES

3.1. INTRODUCTION 3- 2

3.2. AIRSPEEDS DURING EMERGENCY PROCEDURES 3- 2

3.3. EMERGENCY PROCEDURES - CHECKLISTS

3.3.1. Engine Failures (a) Engine Failure during Take-off Run 3- 3 (b) Engine Failure after Take-off

I. Insufficient Engine Power 3- 3 II. Engine Inoperative 3- 4 (c) Engine Failure during Flight I. Engine Running Roughly 3- 4 II. Loss of Oil Pressure 3- 4 III. Loss of Fuel Pressure 3- 4 IV. Restarting the Engine with Propeller Windmilling 3- 5 V. Restarting the Engine with Propeller at Full Stop 3- 6

3.3.2. Emergency Landing (a) Emergency Landing with Engine Off 3- 7

(b) Precautionary Landing with Engine Power Available 3- 7

3.3.3. Fire (a) Engine Fire during Start on the Ground 3- 9 (b) Engine Fire during Flight 3- 9 (c) Electrical Fire including Smoke during Flight 3- 9 (d) Electrical Fire including Smoke on the Ground 3-10 (e) Cabin Fire during Flight 3-10

3.3.4. Icing Unintentional Flight into Icing Area 3-11

3.3.5. Recovery from Unintentional Spin 3-11

3.3.6. Landing with Defective Tire on Main Landing Gear 3-12

3.3.7. [Intentionally left blank] 3-12

3.3.8. Gliding 3-13

3.3.9. Electrical Power Failure 3-13

3.3.10. Flap System Failure 3-15

3.3.11. Starter Failure 3-15

3.3.12. Avionics System Failure 3-16

3.3.13. Trim System Failure 3-17

3.3.14. Instrument Panel Lighting Failure 3-18

3.3.15. Tachometer failure 3-18

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures

3.1. INTRODUCTION

The following chapter contains check-lists as well as descriptions of the recommended procedures in

case of an emergency. Since it is impossible to present in the Flight Manual all emergency situations

which may occur, knowledge of the airplane and experience of the pilot are essential in rectifying such

problems.

3.2. AIRSPEEDS DURING EMERGENCY PROCEDURES

kts mph km/h

Engine failure after take-off with flaps in T/O position 60 68 110

Manoeuvring Speed 104 120 193

Airspeed for best glide angle

Wing Flaps in T/O Position 1653 lbs (750 kg)

Wing Flaps in T/O-Position 1322 lbs (600 kg) 66 76 121

Precautionary Landing (with power and Wing Flaps in landing position) 57 66 106

Emergency landing with engine off (Wing Flaps in T/O or LDG position) 57 66 106

Emergency landing with engine off (Wing Flaps UP) 65 75 120

IAS

84 135

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures

3.3. EMERGENCY PROCEDURES - CHECKLISTS

3.3.1. Engine Failures

(a) Engine Failure during Take-off Run

1. Throttle IDLE

2. Brakes as required

(b) Engine Failure after Take-Off

I. INSUFFICIENT ENGINE POWER

1. Airspeed (v

2. Throttle FULL

3. Carburetor Heat ON

4. Choke OFF

5. Fuel Shut-off Valve OPEN

6. Ignition Switch BOTH

7. Electric Fuel Pump ON

8. Propeller Speed Control Lever max. RPM

) 60 kts / 68 mph / 110 km/h

IAS

WARNING

If adequate engine performance cannot be restored immediately, prepare for an

emergency landing. If possible, land straight ahead, avoiding obstacles.

Shortly before landing:

9. Fuel Shut-off Valve CLOSED

10. Ignition Switch OFF

11. Master Switch (Battery) OFF

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures

II. ENGINE INOPERATIVE

Perform emergency landing according to paragraph 3.3.2.

I. ENGINE RUNNING ROUGHLY

1. Carburetor Heat ON

2. Electric Fuel Pump ON

3. Choke check OFF

4. Fuel Shut-off Valve check OPEN

5. Ignition Switch cycle L - BOTH - R - BOTH

6. Throttle at present position

7. No Improvement reduce throttle to minimum

required power, land as soon

as possible.

II. LOSS OF OIL PRESSURE

1. Oil Temperature check

2. If Oil Pressure drops below Green Arc

land at nearest airfield

but Oil Temperature is normal

If Oil Pressure drops below Green Arc

and Oil Temperature is rising

reduce throttle to minimum required

power;

land as soon as possible. Be prepared

for engine failure and emergency

landing

III. LOSS OF FUEL PRESSURE

1. Electric Fuel Pump ON, and land at nearest suitable airport

If Fuel Pressure Warning Light

does not extinguish

Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 4

Land at nearest suitable airport. Be

prepared for engine failure and

emergency landing.

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures

IV. RESTARTING THE ENGINE WITH PROPELLER WINDMILLING

As long as the airspeed (v

) is at least 54 kts / 62 mph / 100 km/h, the propeller will

IAS

continue to windmill.

1. Airspeed (v

) 70 kts / 81 mph / 130 km/h

IAS

2. Wing Flaps T/O Position

3. Propeller Speed Control Lever max. RPM

4. Fuel Shut-off Valve OPEN

5. Ignition Switch BOTH

6. Electric Fuel Pump ON

7. Throttle 3/4 in (2 cm) forward

If the engine does not start within 10 seconds: Cold Start

8. Throttle IDLE

9. Choke ON (Pulled)

10. Ignition Switch START

Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 5

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures

V. RESTARTING THE ENGINE WITH PROPELLER AT FULL STOP

1. Electrically Powered Equipment OFF

2. Master Switch (Battery) ON

3. Propeller Speed Control Lever max. RPM

4. Fuel shut off valve OPEN

5. Electric Fuel Pump ON

6. Throttle Cold Start:

Warm Start:

7. Choke Cold Start:

Warm Start:

IDLE

3/4 in (2 cm) forward

ON (pulled)

OFF

8. Ignition Switch START

NOTE

The engine may also be re-started by increasing the airspeed by pushing the airplane

into a descent and accelerating to approx. (v

1000 ft / 300 m altitude must be taken into account.

After successful re-start:

9. Oil Pressure check

10. Choke OFF

11. Electrically Powered Equipment ON if required

) 120 kts / 138 mph / 222 km/h. A loss of

IAS

12. Oil Temperature check

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures

3.3.2. Emergency Landing

(a) Emergency Landing Approach with Engine off

1. Airspeed (v

Airspeed (v

2. Fuel Shut-off Valve CLOSED

3. Ignition Switch OFF

4. Safety Belts secured

5. Radio Transmit, giving location and intentions

6. Master Switch (Battery) OFF

(b) Precautionary Landing with Engine Power Available

) (Flaps in T/O and LDG position) 57 kts / 66 mph / 106 km/h

IAS

) (Flaps UP) 65 kts / 75 mph / 120 km/h

IAS

NOTE

A precautionary landing would be required if continuing the flight would endanger the

aircraft or its occupants. Such circumstances could include mechanical defects, low fuel

quantity or deteriorating weather conditions.

1. Search for a suitable place to land. Special

attention must be given to wind direction and

obstacles in the approach path

2. Safety Belts secured

3. Initiate Descent

4. Throttle as required

5. Trim as required

Wing Flaps

(observe permissible speed)

Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 7

as required

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures

7. Overfly selected landing area (not below 500 ft / 150 m above

ground) to confirm suitability and that approach route is free of

obstacles

8. Climb up to 1000 ft AGL (if possible)

9. Low pass over flight (around 100 feet) to observe any possible

obstacles, such as cables, fences, ditches

10. Climb up to 1000 ft AGL (if possible)

11. Radio Transmit, giving location and

12. Final Approach

Throttle as required

Propeller Speed Control Lever max. RPM

Carburetor Heat ON

Electric Fuel Pump ON

Wing Flaps LDG

Airspeed (v

13. Touch-down is to be made with minimum airspeed, nose wheel

) 57 kts / 66 mph / 106 km/h

IAS

intentions

should be kept above ground as long as possible

14. After Touch-down:

Brake as required

Fuel Shut-off Valve CLOSED

Ignition Switch OFF

Master Switch (Battery) OFF

NOTE

If no suitable level landing area can be found, an up-hill landing should be performed, if

possible.

Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 8

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures

3.3.3. Fire

(a) Engine Fire during Engine-Start-Up on the Ground

1. Fuel Shut-off Valve CLOSED

2. Throttle FULL

3. Master Switch (Battery) OFF

4. Ignition Switch OFF

5. Evacuate Airplane immediately

(b) Engine Fire during Flight

1. Fuel Shut-off Valve CLOSED

2. Airspeed (v

3. Flaps T/O

4. Throttle FULL

5. Electric Fuel Pump OFF

6. Cabin Heat CLOSED

7. Perform emergency landing with engine

off according to paragraph 3.3.2

1. Master Switch (Battery) OFF

2. Cabin Air OPEN

3. Fire Extinguisher use only if smoke development

) 70 kts / 81 mph / 130 km/h

IAS

continues.

CAUTION

If fire extinguisher is used, the cabin must be aerated.

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures

In case the fire is extinguished and electric power is required for continuation of the flight:

4. Avionics Master Switch OFF

5. Electrically Powered Equipment OFF

6. Master Switch (Battery) ON

7. Avionics Master Switch ON

8. Radio ON

9. Land as soon as possible.

(d) Electrical Fire including Smoke on the Ground

1. Master Switch (Battery) OFF

If engine running:

2. Throttle IDLE

3. Fuel Shut-off Valve CLOSED

4. Ignition Switch OFF

5. Canopy open

6. Fire Extinguisher deploy as required

(e) Cabin Fire during Flight

1. Master Switch (Battery) OFF

2. Cabin Air OPEN

3. Cabin Heat CLOSED

4. Fire Extinguisher deploy as required

5. Land as soon as possible

If fire extinguisher is used, the cabin must be aerated.

Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 10

CAUTION

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures

3.3.4. Icing

Unintentional Flight into Icing Area

1. Leave icing area (through change of altitude or change of flight direction to reach area with higher outside air temp.).

2. Continue to move control surfaces to maintain their moveability.

3. Carburetor Heat ON

4. Increase RPM to avoid icing of propeller blades (observe maximum RPM)

5. Cabin Heat OPEN

CAUTION

In case of icing on the leading edge of the wing, the stall speed will increase.

CAUTION

In case of icing on wing leading edge, erroneous indicating of the airspeed, altimeter, rate of

climb and stall warning should be expected.

3.3.5. Recovery from Unintentional Spin

1. Throttle IDLE

2. Rudder fully applied opposite to direction of spin

3. Control Stick ease forward

4. Rudder neutral, after rotation has stopped

5. Wing Flaps UP

6. Elevator pull cautiously

Bring airplane from descent into level

flight position. Do not exceed maximum permissible speed (v

Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 11

)

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures

3.3.6. Landing with Defective Tire on Main Landing Gear

1. Final approach with wing flaps in landing position.

2. Land airplane on the side of runway opposite to the side with the defective tire to compensate for

change in direction which is to be expected during final rolling.

3. Land with wing slightly tipped in the direction of the non-defective tire. To increase the

maneuvrability during rolling, the nose-wheel should be brought to the ground as soon as

possible after touch-down.

4. To ease the load on the defective tire, the aileron should be fully applied in the direction of the

non-defective tire.

3.3.7. [Intentionally left blank]

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures

3.3.8. Gliding

1. Wing Flaps T/O

2. Airspeed at 1653 lbs (750 kg) (v

3. Glide Ratio 14, which means at

1000 ft/305m above ground, and with no

wind the distance of glide is

2.3 NM (4.25 km)

) 73 kts / 84 mph / 135 km/h

IAS

NOTE

The glide distance from 1000 ft altitude increases for each 10 kts tail wind by 1968 ft (0.6 km).

The glide distance from 1000 ft altitude decreases for each 10 kts head wind by 2296 ft (0.7 km).

3.3.9. Electrical Power Failure

a) Total Electrical Power Failure

1. Battery Circuit Breaker If tripped, reset

2. Master Switch (Generator/Battery) check ON

3. If Unsuccessful Land at nearest suitable airport

b) Generator Failure

GEN. Annunciator Illuminated

1. Master Switch (Generator) Cycle Generator Master Switch OFF - ON

2. Generator Circuit Breaker If tripped, reset

3. Generator CONTROL Circuit Breaker If tripped, reset

4. If Generator can not be brought on-line Switch OFF all non-flight essential electrical

consumers. Monitor Ammeter and Voltmeter. Land

at nearest suitable airport.

NOTE

There are 30 minutes of battery life remaining at a discharge load of 20 amperes.

Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 13

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures

c) Low Voltage Indication (needle in yellow Arc)

I. LOW VOLTAGE INDICATION (NEEDLE IN YELLOW ARC) WHILE AIRPLANE ON

GROUND

1. Propeller RPM Increase RPM until needle is in the Green Arc.

This should occur before exceeding 1350 RPM.

2. Non-flight essential electrical consumers Switch OFF consumers until needle is in the

Green Arc.

3. If needle remains in the yellow arc and the

ammeter is indicating to the left of centre

(discharge)

II. LOW VOLTAGE INDICATION (NEEDLE IN YELLOW ARC) DURING FLIGHT

1. All non-flight essential electrical

consumers

2. If needle is remaining in the yellow arc

and the ammeter is indicating to the left of

centre (discharge):

III. LOW VOLTAGE INDICATION (NEEDLE IN YELLOW ARC) DURING LANDING:

1. After landing proceed in accordance with paragraph 3.3.9 (c).

Discontinue any planned flight activity

Switch OFF

Generator Failure: Refer to paragraph 3.3.9 (b)

If at any time the Voltmeter needle indicates in the red arc, you should land at the nearest

suitable airfield and service the aircraft accordingly before continuing the flight.

Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 14

WARNING

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures

3.3.10. Flap System Failure

Flap Position Indicator Failure

- visual check of the flap position

- select airspeed within the range of the white arc marked on the airspeed indicator

- check all positions of the flap toggle switch (flap stops are fail-safe)

- modify approach and landing as follows:

• only UP available: - raise approach speed by 5 kts

- throttle as required

- flat approach angle

• only T/O available: - normal approach speed

- throttle as required

- flat approach angle

• only LDG available: - normal landing

3.3.11. Starter Failure

Starter does not disengage after starting the engine (continuous whining sound audible).

1. Throttle IDLE

2. Ignition Switch OFF

discontinue any planned flight

Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 15

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures

3.3.12 Avionics System Failure

Total Avionic Failure:

1. Check Avionic Master Circuit Breaker If tripped, re-engage and monitor status, If it trips

again, land at nearest suitable airport

2. Check Avionic Master Switch Toggle avionic master switch, if avionic system

remains off-line, pull avionic master control circuit

breaker and land at nearest suitable airport

Radio System Operative, no reception:

1. Microphone Key check for stuck Microphone Key on transceiver display

2. Headphones check, deactivate SQUELCH for a few moments, if

SQUELCH not heard, check headset connection

Radio System Operative, transmitting not possible:

1. Selected Frequency check if correct

2. Microphone check, if available use different one (headset)

Problem cannot be resolved: switch transponder (if available) to "COMM FAILURE" code if required by

the situation and permitted by applicable national regulations.

Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 16

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures

3.3.13 Trim System Failure

Stuck Trim:

1. Circuit breaker check, reset if breaker is tripped

2. Rocker switch depress in both directions, wait

5 minutes, try again

NOTE

Full range of travel is available for elevator, but expect forces up to 20 lbs. on control stick.

3. Land at nearest suitable airport

Runaway of Trim:

1. Control Stick Grip stick and maintain control of airplane

2. Trim motor circuit breaker Pull circuit breaker

3. Rocker Switch Check if depressed

If reason for runaway condition is obvious and has been resolved, push in (engage) circuit breaker.

NOTE

Full travel of the elevator trim system will take approximately 10 seconds.

Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 17

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures

3.3.14 Instrument Panel Lighting Failure

1. Rocker Switch, map light ON

2. Rocker Switch, I-panel lighting Cycle Rocker Switch OFF - ON

3. Dimming Control Turn fully clockwise

4. Internal Lighting Circuit Breaker. If tripped, reset

5. If NOT Successful

Expect electrical power failure.

3.3.15 Tachometer failure

Operation at T/O (5 minute) power:

1. Airspeed Do not exceed 110 KIAS

Operation at maximum continuous power:

1. Propeller Speed Control Lever Ensure lever is at least ½ inch (10mm)

Use Flashlight

Ref. 3.3.9

(measured at slot) aft of full forward position. Engine will now be operating at, or below, maximum continuous power.

NOTE

With propeller speed control lever at least ½ inch (10mm) aft of full forward position, the Max. Permissible Continuous RPM (2260 RPM) cannot be exceeded at any throttle setting and airspeed. However, maximum engine power may not be available.

Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 18

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DIAMOND AIRCRAFT DA 20/100 Flight

Manual

Normal Operating Procedures

CHAPTER 4

NORMAL OPERATING PROCEDURES

4.1. INTRODUCTION 4- 2

4.2. AIRSPEEDS FOR NORMAL FLIGHT OPERATION 4- 2

4.3. STRUCTURAL TEMPERATURE INDICATOR 4- 3

4.4. NORMAL OPERATION CHECKLIST 4- 5

4.4.1. Preflight Inspection I. In-Cabin Check 4- 5 II. Walk-Around Check 4- 6

4.4.2. Before Starting Engine 4- 9

4.4.3. Starting Engine 4-10

4.4.4. Before Taxiing 4-11

4.4.5. Taxiing 4-11

4.4.6. Before Take-off (Engine Run-up) 4-12

4.4.7. Take-off 4-13

4.4.8. Climb 4-14

4.4.9. Cruise 4-14

4.4.10. Descent 4-15

4.4.11. Landing Approach 4-15

4.4.12. Balked Landing 4-16

4.4.13. After Landing 4-16

4.4.14. Engine Shut-down 4-16

4.4.15. Flight in Rain 4-17

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Normal Operating Procedures

Manual

4.1. INTRODUCTION

Chapter 4 provides checklist and amplified procedures for the normal operation. For normal procedures and supplementary information associated with optional systems refer to Chapter 9.

4.2. AIRSPEEDS FOR NORMAL FLIGHT OPERATION

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.

IAS

TAKE-OFF

kts mph km/h

Climb Speed during normal take-off for 15 m (50 ft) obstacle 57 66 106 Best Rate-of-Climb speed at sea level vy (Wing Flaps T/O) 65 75 120 Best Angle-of-Climb speed at sea level vx (Wing Flaps T/O) 57 66 106

LANDING

kts mph km/h Approach speed for normal landing. Wing Flaps in landing position 57 66 106 Balked landing climb speed, Wing Flaps in landing position 57 66 106 Maximum demonstrated crosswind speed during take-off and landing 15 17 27

CRUISE

Maximum permissible speed in rough air v

Maximum permissible speed with full control surface deflections v Maximum permissible speed with Wing Flaps extended v

kts mph km/h

118 135 218 104 120 193

81 93 150

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Normal Operating Procedures

4.3 STRUCTURAL TEMPERATURE INDICATOR

A structural temperature indicator, installed on the spar bridge, indicates when the structural temperature limitation is exceeded (ref. section 2.17). The indicator need only be checked if the OAT exceeds 38° C (100° F). The indicator is accessed by lifting the flap between the two seatback cushions. The indicator is visible through the cut out in the seat shell backs (ref. fig. 2). At temperatures below the 55° C (131° F) limit, the indicator appears all red with a faint indication of “55” (° C). At temperatures exceeding the 55° C (131° F) limit, the indicator displays a clearly contrasting red “55” (° C) on a black background (ref. fig.1).

NOTE

At temperatures approaching the limit, the background will progressively darken

prior to turning black; this indicates acceptable temperatures.

Red “55” on black background indicates that structural temperature limit is exceeded. Flight is prohibited.

All red indicates that structural temperature is below limit. Flight is permitted.

Figure 1

Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 4 - 3

Figure 2

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[ INTENTIONALLY LEFT BLANK ]

Normal Operating Procedures

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4.4. NORMAL OPERATION CHECKLIST

4.4.1. Preflight Inspection

I. In-Cabin Check

Normal Operating Procedures

1. Structural Temperature Indicator (if OAT exceeds 38°C (100° F))

2. Airplane Documents check

3. Flight Control Lock removed

4. Flight Controls check for proper direction of

5. Ignition Key pulled out

6. Carburetor Heat free, OFF

7. Cabin Heat free

8. Choke free, self-resetting

9. Parking Brake free

10. Throttle free, IDLE

11. Propeller Speed Control Lever free, max. RPM

12. Master Switch (Battery) ON

13. Warning Lights (Gen., Fuel Press., and Canopy) illuminated

14. Fuel Quantity sufficient

15. Engine Gauges, Ammeter and Voltmeter check

16. Circuit Breakers pressed in

17. Map Light operational

18. Instrument Lights operational and dimmable

19. Trim NEUTRAL

20. Wing Flaps (Indicator- and Flap Actuation) check, extend and retract fully

21. Trim and Flap Indicator Lights operational and dimmable

22. Exterior Lights operational as required

23. Master Switch (Battery) OFF

24. Foreign Object Inspection done

25. Emergency Locator Transmitter (ELT): EBC Model 502 - ARM EBC Model 102A - OFF

26. Fire Extinguisher check

27. Baggage stowed, baggage net attached

28. Canopy clean, undamaged

check that Structural Temperature does not exceed 55° C (131° F)

movement

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II. Walk Around Check and Visual Inspection

Normal Operating Procedures

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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 visual inspection b) Wheel Fairing visual inspection c) Tire Pressure (33 psi / 2.3 bar) check d) Tire, Wheel, Brake visual inspection

Normal Operating Procedures

e) Wheel Chocks remove

2. Left Wing

a) Entire Wing visual inspection b) Stall Warning 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

3. Fuselage

a) Skin visual inspection b) Tank Vent check c) Tank Drain drain water d) Fuel Quantity visual inspection (use fuel pipette) e) Antennas visual inspection

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4. Empennage

a) Stabilizers and Control Surfaces visual inspection b) Tie down remove c) Trim Tabs visual inspection

5. Right Wing

a) Entire Wing visual inspection b) Wing Flap including Inspection Panel 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 visual inspection b) Wheel Fairing visual inspection c) Tire Pressure (33 psi / 2.3 bar) check d) Tire, Wheel, Brake visual inspection e) Wheel Chocks remove

Normal Operating Procedures

7. Nose

a) - Oil check level by using dip-stick.

min / max range is indicated by flat area of stick

- Coolant Level must be between dip-stick markings, refill if required.

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, towbar removed h) Wheel Fairing visual inspection

i) Tire Pressure (26 psi / 1.8 bar) check j) Tire and Wheel visual inspection

k) Wheel Chocks remove

Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 4 - 8

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Normal Operating Procedures

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.

Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 4 - 9

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Normal Operating Procedures

4.4.3. Starting Engine

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.

1. Electric Fuel Pump ON (noise of pump audible)

2. Fuel Pressure Warning Light OFF

3. Throttle- Cold Start

- Warm Engine

4. Choke - Cold Start

- Warm Engine

5. Toe Brakes Hold

6. Propeller Area Clear

IDLE approximately 3/4 in (2 cm) forward ON, fully pulled and hold OFF

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 maximum of 10 seconds

CAUTION

If Oil Pressure is below 12 psi (0.8 bar) shut down engine immediately (max. 10 seconds delay).

NOTE

Oil Pressure may advance to the yellow arc until Oil Temp. reaches normal operating temperatures.

NOTE

Activate starter for max. 10 sec. only, followed by a cooling period of 2 min.

11. Generator Warning Light OFF

12. Exterior Lights as required

13. Electric Fuel Pump OFF

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Normal Operating Procedures

4.4.4. Before Taxiing

1. Avionics Master Switch ON

2. Flight Instruments and Avionics set

3. Engine Gauges check

4. Voltmeter check, ensure needle is in the

green arc. Increase RPM to achieve or turn OFF non-flight essential electrical consumers

5. Warning Lights (Gen., Fuel Press., Canopy) push to test

6. Parking Brake release

CAUTION

Warm-up engine to a minimum Oil Temperature of 122° F (50° C) at 1100 to 1500 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.

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Normal Operating Procedures

4.4.6. Before Take-off (Engine Run-up)

NOTE

For OAT’s less than -5º F (-20º C) turn cabin heat on for at least 10 minutes prior to take-off.

1. Toe Brakes hold

2. Safety Belts fastened

3. Canopy closed and locked

4. Fuel Pressure Warning Light OFF (If light illuminates,

maintenance action is required and flight should not be initiated )

5. Fuel Shut-off Valve check OPEN

6. Fuel Quantity Indicator check

7. Engine Gauges within green range

8. Trim NEUTRAL

9. Controls free

10. Throttle 1700-1800 RPM

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, but RPM drop must be noticeable)

13. Throttle 1500 RPM

14. Carburetor Heat ON

RPM drop: max. 50 RPM;

15. Throttle IDLE

16. Carburetor Heat OFF

17. Circuit Breakers check pressed IN

18. Electric Fuel Pump ON

19. Wing Flaps T/O

20. Parking Brake release

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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

Normal Operating Procedures

7. Throttle Check RPM

8. Elevator - at beginning of rolling NEUTRAL

9. Directional Control maintain with rudder

FULL 2260 RPM to 2385 RPM

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 (v

11. Climb Speed (v

) 51 kts / 59 mph / 95 km/h

IAS

) 57 kts / 66 mph / 106 km/h

IAS

CAUTION

For the shortest possible take-off distance to clear a 15 m (50 ft) obstacle:

Lift-off Speed (v Climb Speed (v

) 54 kts / 62 mph / 100 km/h

IAS

) 57 kts / 66 mph / 106 km/h

IAS

12. Propeller Speed Control Lever 2260 RPM

13. Electric Fuel Pump OFF

In order to avoid excessive noise, the propeller speed should be reduced to 2260 RPM as

Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 4 - 13

(after reaching safe height)

NOTE

soon as a safe flight altitude has been reached.

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Normal Operating Procedures

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

NOTE

The best rate of climb speed decreases with increasing altitude.

NOTE

Electric fuel pump ON above 13000 ft.

Speeds [ v

Altitude flaps T/O flaps UP

feet kts mph km/h kts mph km/h

0 - 4000 65 75 120 69 79 128

4000 - 7000 63 73 117 65 75 120

7000 -10000 62 71 115

above 10000 59 68 110

]

IAS

     

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

3. Wing Flaps UP

4. Trim as required

5. Engine Gauges check Doc # 202-100-VLA 20 December, 2000 Page

DOT Approved 4 - 14

Electric fuel pump ON above 13000 ft.

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Normal Operating Procedures

4.4.10. Descent

1. Flight Instruments and Avionics adjust

2. Throttle as required

3. Propeller Speed Control Lever 1700 - 2260 RPM

4. Carburetor Heat as required

NOTE

To achieve a fast descent: Propeller Speed Control Lever 2260 RPM Throttle IDLE Carburetor Heat ON

NOTE

If RPM drops and then rises, suspect carburetor icing and leave Carb Heat ON.

Otherwise turn Carb Heat OFF.

Wing Flaps UP Airspeed 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

NOTE

If RPM drops and then rises, suspect carburetor icing and leave Carb Heat ON.

Otherwise turn Carb Heat OFF.

7. Throttle as required

8. Airspeed max. 81 kts / 93 mph / 150 km/h

9. Wing Flaps T/O

10. Trim as required Doc # 202-100-VLA 20 December, 2000 Page

DOT Approved 4 - 15

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11. Propeller Speed Control Lever max. RPM

12. Wing Flaps LDG

13. Approach Speed 57 kts / 66 mph / 106 km/h

Normal Operating Procedures

CAUTION

For strong headwind, crosswind, danger of wind-shear or turbulence, a higher approach

speed should be selected.

4.4.12. Balked Landing

1. Propeller Speed Control Lever max. RPM

2. Throttle FULL

3. Carburetor Heat OFF

4. Wing Flaps T/O

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

4.4.13. After Landing

1. Throttle as required

2. Wing Flaps UP

3. Carburetor Heat OFF

4. Exterior Lights as required

5. Electric Fuel Pump OFF

4.4.14. Engine Shut-down

1. Throttle IDLE

2. Parking Brake set

3. ELT Check (by listening to

121.5 MHZ for signal)

4. Avionics Master Switch OFF

5. Electric Consumers OFF

6. Ignition Switch OFF

7. Instrument Panel Lighting OFF

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8. Master Switch (Battery) OFF

9. Tie Downs and Wheel Chocks as required

Normal Operating Procedures

NOTE

In case of post ignition due to hot weather conditions, the ignition should be switched on, choke pulled and after approximately 3 seconds, ignition should 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

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance

CHAPTER 5

PERFORMANCE

5.1 INTRODUCTION 5- 2

5.2 USE OF PERFORMANCE TABLES AND DIAGRAMS 5- 2

5.3 PERFORMANCE TABLES AND DIAGRAMS 5- 3

5.3.1 Figure 5.1: Airspeed Calibration 5- 3

5.3.2 Figure 5.2: Cruising Performance 5- 4

5.3.3 Figure 5.3: Stall Speeds 5- 5

5.3.4 Figure 5.4: Wind Data 5- 6

5.3.5 Figure 5.5: Take-Off Distances 5- 7

5.3.6 Figure 5.6: Climb Performance / Service Ceiling 5- 9

5.3.7 [INTENTIONALLY LEFT BLANK] 5-10

5.3.8 Figure 5.8: Cruising Speed (True Airspeed) 5-11

5.3.9 Figure 5.9: Maximum Flight Duration 5-12

5.3.10 Figure 5.10: Climb Performance during Balked Landing 5-13

5.3.11 Landing Distances 5-14

5.4

NOISE DATA 5-15

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DIAMOND AIRCRAFT DA 20/100 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 [59° F (15° C)

and 29.92 in. Hg (1013.25 mbar) 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 given in %.

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.

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[

]

5.3. PERFORMANCE TABLE AND DIAGRAMS

5.3.1. Figure 5.1: Airspeed System Calibration

Assumes zero indicator error

160

150

140

130

120

[kts

CAS

110

100

T/O, LDG

40 50 60 70 80 90 100 110 120 130 140 150 160

kts

IAS

Example: v

Doc # 202-100-VLA 20 December, 2000 Page DOT-Approved 5 - 3

= 93 kts equals v

IAS

= 95 kts.

CAS

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance

5.3.2. Figure 5.2: Cruising Performance

Pressure

altitude

Ft. M

0 0 15 59 19 24.7 13.6 3.6 20 25.7 15.6 4.1 2000 600 11 52 19 24.0 14.4 3.8 20 24.7 16.0 4.2 4000 1200 7 45 19 23.3 15.6 4.1 21 23.3 16.8 4.4 6000 1800 3 38 20 22.0 16.8 4.4 22 22.7 19.6 5.2 8000 2400 -1 31 21 21.0 18.0 4.8 22 21.7 21.2 5.6

10000 3000 -5 24 22 19.7 19.2 5.1 22.6 20.3* 22.4* 5.9* 12000 3600 -8 17 22.6 18.0* 20.4* 5.4*

13000 4000 -11 12 22.6 17.0* 21.5* 5.7*

Standard

Temp.

°C °F

Engine power in % of maximum continuous power

55% 65%

Rpm

X100

In.Hg

Fuel Flow Fuel Flow

L/hr

Gal/hr

Rpm

X100

In.Hg

L/hr

Gal/hr

Pressure

altitude

Ft. M

0 0 15 59 21 27.0 18.0 4.8 22.6 27.7 22.0 5.8

2000 600 11 52 22 25.7 18.4 4.9 22.6 26.7 22.4 5.9 4000 1200 7 45 22.6 24.3 19.6 5.2 22.6 25.7* 25.2* 6.7* 6000 1800 3 38 22.6 23.3 23.2 6.1 8000 2400 -1 31 22.6 22.0* 23.6* 6.2*

Standard

Temp.

°C °F

Rpm

X100

75% 85%

In.Hg

Fuel Flow Fuel Flow

L/hr

Gal/hr

Rpm

X100

In.Hg

L/hr

Gal/hr

Pressure

altitude

Ft. M

0 0 15 59 22.6 28.3 26.0 6.9 23.8 29.7* 30.0 7.9* 2000 600 11 52 22.6 27.7* 26.8* 7.1*

4000 1200 7 45 22.6 25.7* 25.2* 6.7* 6000 1800 3 38

Standard

Temp.

°C °F

Maximum Continuous

Power

Rpm

X100

In.Hg

Fuel Flow Fuel Flow

L/hr

Gal/hr

Maximum Take-Off Power

Rpm

X100

In.Hg

L/hr

Gal/hr

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)

To keep engine wear to a minimum, engine operation below 1900 RPM is not recommended.

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NOTE

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance

5.3.3. Figure 5.3: Stall Speeds

Configuration:

Idle, most forward center of gravity, max. weight

(this is the most adverse configuration)

Stall speeds in kts

Bank Angle

Flaps 0° 30° 45° 60°

IAS CAS IAS CAS IAS CAS IAS CAS

UP 41 50 46 53 55 59 69 70

T/O 39 46 44 49 51 54 63 65

LDG 37 44 41 47 49 52 59 62

Stall speeds in mph

Bank Angle

Flaps 0° 30° 45° 60°

IAS CAS IAS CAS IAS CAS IAS CAS

UP 47 57 53 62 63 68 79 81

T/O 45 52 51 56 59 62 72 75

LDG 43 50 47 54 56 60 68 72

Stall speeds in km/h

Bank Angle

Flaps 0° 30° 45° 60°

IAS CAS IAS CAS IAS CAS IAS CAS

UP 76 93 85 99 101 109 127 130

T/O 72 84 81 91 94 100 117 120

LDG 69 81 76 87 91 96 109 115

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance

5.3.4. Figure 5.4: Wind Components

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

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)

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance

5.3.5. Figure 5.5: Take-off Distance

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)

-4 14 32 50 68 86 104

S t

Ouside Air Temperature (°F)

-20-100 10203040 Ouside Air Temperature (°C)

Airc ra ft W e ig h t (lb s.)

1653 1598 1543 1488 1433 1378 1323

Aircraft Weight (kg)

600625650675700725750

0 5 10 15 20

Headwind Component (knot)

Ob s ta c le He ig h t (f e e t)

0163349

0 5 10 15

Obstacle Height (m )

(feet )

3500

3300

3100

2900

2700

2500

2300

2100

1900

1700

1500

1300

1100

900

700

500

(m )

1052

952

852

752

652

552

Takeoff Distance

452

352

252

152

(m )(feet )

Example: - Pressure altitude: 3000 ft

- Outside temperature: 15° C (59° F)

- Weight : 1598 lbs (725 kg)

-Headwind: 10 kts

Result: - Take-off roll distance: 1025ft (312.4 m)

- Take-off distance to clear a 15 m (50 ft) obstacle: 1425 ft (434.3 m)

NOTE

Poor maintenance condition of the airplane, deviation from the given procedures as well as unfavourable outside conditions (high temperature, rain, unfavourable wind conditions, including cross-wind) could increase the take-off distance considerably.

For take-off from dry, short-cut grass covered runways, the following corrections must be taken into account, compared to paved runways:

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance

• Grass up to 5cm (2in) deep: 10% increase in take-off roll distance;

• Grass 5 to 10cm (2 to 4in) deep: 15% increase in take-off roll distance;

• Grass deeper than 10cm (4in): 25% increase in take-off roll distance.

On wet soft grass covered runways with grass deeper than 10cm (4in), the take-off roll distance might be increased by as much as 40%.

This information is provided for guidance purposes only and has not been demonstrated. The dashed lines in the above diagram (wind component) represent tailwind.

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance

5.3.6. Figure 5.6 : Climb Performance / Service Ceiling

Service Ceiling (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

TEMPERA TURE (°F)

-4 5 142332415059687786

18000

16000

Standard Temperature

14000

12000

10000

8000

6000

PRESSURE ALTITUDE (FEET)

4000

2000

-2000

-20-15-10-5 0 5 1015202530

TEMPERA TURE (°C)

0.5 1.0 1.5 2.0 2.5 3.0 3.6 4.1 4.6 5.1

16000

14000

12000

10000

8000

6000

4000

2000

100 200 300 400 500 600 700 800 900 1000

m/sec

1433 lbs / 650 kg

1543 lbs / 700 kg

1609 lbs / 730 kg

1653 lbs / 750 kg

RO C (ft/min)

Example: Pressure Altitude: 5000 ft (1524 m) OAT: 46° F (8° C) Weight : 1477 lbs (670 kg) Result: Climb performance: 554 ft/min (2.82 m/s)

In case of operation without wheel fairings the climb performance is reduced by approximately 3%.

Doc # DA202-100-VLA March 19, 2004 Page Revision 3 5 - 9

CAUTION

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance

5.3.7. [INTENTIONALLY LEFT BLANK]

[ INTENTIONALLY LEFT BLANK ]

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance

5.3.8. Figure 5.8: Cruising Speed (True Airspeed)

Diagram for true airspeed (TAS) calculation at selected power level. Flight mass 750 kg (1653 lbs) and Flaps UP.

Temperature (°F)

Temperature (°C)

Example: Pressure altitude: 9500 ft Temperature: 57° F (14° C) power setting: 55 %

Result: True airspeed (TAS): 116 kts (215 km/h)

True Airspeed (knots)

CAUTION

In case of operation without wheel fairings the maximum cruising speed is reduced by approximately 5%.

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance

5.3.9. Figure 5.9: Maximum Flight Duration

Diagram for calculation of the maximum flight duration depending on fuel availability.

Flight Time (hour), 45 minute reserve

- 3/4 1/4 1 1/4 2 1/4 3 1/4 4 1/4 5 1/4

75 %

55 %

95 %

/ 6

Fuel Quantity (litres)

0123456

Flight Time (hour), no reserve

Example: Fuel quantity: 13.2 US gal (50 liters)

Pressure Altitude 6000 ft Power Setting: 75%

Fuel Quantity (US Gal)

Result: Possible flight time Possible flight time

Doc # DA202-100-VLA March 19, 2004 Page Revision 3 5 - 12

without reserve: 2:11 h:min with reserve of 45 mins: 1:26 h:min

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance

)

5.3.10. Figure 5.10: Climb Performance during Balked Landing

Conditions: Speed = 57 kts / 66 mph / 106 km/h Wing Flaps in Landing Position (LDG) Weight 750 kg (1653 lbs) most forward center of gravity max take-off power

800

4.06

700

3.56

600

500

3.05

2.54

400

ROC (ft/min)

300

200

2.03

ROC ( m/sec)

1.52

1.02

100

0.51

0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000

0.00

Hp (ft)

Hp (m

Example: Pressure altitude: 2250 ft (685 m) Outside temperature: 59° F (15° C)

Result: Climb performance during balked landing: 320 ft/min. (1.63 m/sec)

In case of operation without wheel fairings the climb performance is reduced by approximately 3%.

Doc # DA202-100-VLA March 19, 2004 Page Revision 3 5 - 13

CAUTION

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance

5.3.11. Landing Distance

Conditions: - Throttle: Idle

- Maximum T/O Weight

- Propeller Speed Control Lever: max RPM

- Approach Speed 57 kts / 66 mph / 106 km/h

- Level Runway, paved

- Wing Flaps in Landing position (LDG)

- Standard Setting, MSL

Landing distance over a 15 m (50 ft) obstacle: approx. 1532 ft (467 m) Landing roll distance: approx. 790 ft (241 m)

Figure 5.11: Landing and Rolling Distances for Heights Above MSL

Height above MSL ft.

(m)

(0)

1000

(305)

2000 (610)

3000

(914)

4000

(1219)

5000

(1524)

Landing Distance

Landing Roll Distance ft.

ft.

(m)

1532

(467)

790

(241)

1593

(486)

813

(248)

1653 (504)

837

(255)

1714 (522)

862

(263)

1775

(541)

889

(271)

1836

(560)

916

(279)

NOTE

For landings on dry, short-cut grass covered runways, the following corrections must be taken into account, compared to paved runways:

• Grass up to 5cm (2in) deep: 5% increase in landing roll distance;

• Grass 5 to 10cm (2 to 4in) deep: 15% increase in landing roll distance;

• Grass deeper than 10cm (4in): 25% increase in landing roll distance.

On wet soft grass covered runways with grass deeper than 10cm (4in), the landing roll distance might be increased by as much as 40%.

This information is provided for guidance purposes only and has not been demonstrated.

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance

5.4 NOISE DATA

a) Noise limit according to FAR 36, Appendix G: 75.0 dB (A) Noise value measured: 63.8 dB (A)

b) Noise limit according to ICAO Annex 16, Chapter 10: 79.1 dB (A) Noise value measured: 71.7 dB (A)

Doc # DA202-100-VLA March 19, 2004 Page Revision 3 5 - 15

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance

CHAPTER 6

WEIGHT AND BALANCE / EQUIPMENT LIST

6.1 INTRODUCTION 6-2

6.2 AIRPLANE WEIGHING 6-3

- Figure 6.1 Weighing Report 6-4

6.3 WEIGHT AND BALANCE REPORT 6-5

- Figure 6.2 Weight & Balance Report 6-6

6.4 FLIGHT-WEIGHT AND CENTER OF GRAVITY 6-7

- Figure 6.3 Weight & Balance Diagram 6-8

- Figure 6.4 Calculation of Loading Condition 6-9

- Figure 6.5 Permissible Center of Gravity Range and permissible Flight Weight-Moment

6.5 EQUIPMENT LIST 6-11

6-10

AIRCRAFT SPECIFIC WEIGHT AND BALANCE DOCUMENTS

(ENCLOSED AT THE END OF THIS CHAPTER)

Doc # 202-100-VLA 20 December, 2000 Page DOT-Approved 6 - 1

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance

1. 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 as described in Chapter 2.

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 procedure for weighing the airplane and calculating the empty weight CG position are given in this

Chapter.

The aircraft is weighed when new and should be reweighed in accordance with applicable air regulations.

Empty weight and the center of gravity are recorded in a Weighing Report and Weight and Balance

Report as illustrated in the samples in figure 6.1 and 6.2. The actual report for the aircraft is at the end of

this chapter.

In case of equipment changes, the new weight and empty weight CG position must be determined by

calculation or by weighing and must be entered in the Weight & Balance Report. The following pages are

sample forms which can be used for airplane weighing, calculation of the empty weight CG position, and

for the determination of the useful load.

NOTE

After every repair, painting or change of equipment the new empty weight must be

determined as required by applicable air regulations. Weight, empty weight CG position

and useful load must be entered in the Weight & Balance Report by an authorized

person.

Doc # 202-100-VLA 20 December, 2000 Page DOT-Approved 6 - 2

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance

6.2. AIRPLANE WEIGHING

Pre-weighing conditions:

- equipment must be in accordance with the airplane equipment list

- brake fluid, lubricant (3.17 US qt / 3 liters), coolant (2.64 US qt / 2,5 liters) and

unusable fuel (0.53 US gal./ 2 liters), included

To determine the empty weight and the empty weight CG position, the airplane is to be positioned in the

above mentioned pre-weighing condition, with the nose gear and each main gear on a scale. Ensure the

aircraft is level longitudinally as illustrated on the weighing report (see figure 6.1).

With the airplane correctly positioned, a plumb line is dropped from the leading edge of each wing at the

root rib to the floor, join these two points to determine the reference datum (RD). From this line use a

suspended plumb line aligned with each landing gear to measure the distances D

main gear) and D

(right main gear).

(nose gear), DL (left

The following formulas apply:

Empty Weight: W

Empty Weight Moment: M = W

Empty Weight CG position : =

= WN + WL + WR lbs [kg]

x DN + WL x DL + WR x DR in⋅lbs [m⋅kg]

Empty Weight Moment

Empty Weight

= in [m]

CAUTION

Items ahead of RD are considered to have a negative lever arm.

Items aft of RD are considered to have a positive lever arm.

Record the data in the Weighing Report included at the end of this chapter. The following

Sample Weighing Report figure 6.1 is for reference only.

Doc # 202-100-VLA 20 December, 2000 Page DOT-Approved 6 - 3

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance

Figure 6.1: Sample Weighing Report (Aircraft Specific report at the end of this chapter.)

Model:

DA 20/100

Data in accordance with TCDS and Flight Manual Reason for Weighing:

Reference Datum: Leading edge of wing at root rib

Horizontal reference line: 24” Spirit Level placed on Fuselage Canopy Rail (L or R), supported at front by a

2 1/4” spacer as shown below

Weighing Conditions: including brake fluid, lubricant, coolant and unusable fuel (3.31 lbs/1.5 kg)

Equipment List dated:

S/N: Registration:

Support Gross

[lbs] ([kg])

Tare

[lbs] ([kg])

Net Weight

[lbs] ([kg])

Lever Arm

[in] ([m])

Nose WN = DN =

Main Left WL = DL =

Main Right WR = DR =

Empty Weight WT = WN + WL + WR = lbs (kg)

Empty Weight Moment M = WN x DN + WL x DL + WR x D

Empty Weight CG Position

Empty Weight Moment

Empty Weight

(Positive results indicate, that CG is located aft of RD)

= _________________

Maximum Permissible Useful Load: Maximum Weight [lbs] ([kg]) Empty Weight [lbs] ([kg])

−

in lbs [m kg]

in [m]

Max useful Load [lbs] ([kg]) =

Data to be entered into the Flight Manual: see page 6-6

Empty Weight [lbs] ([kg])

Empty- Weight-Moment [in⋅lbs] ([kg⋅m])

Place / Date

Inspector’s Stamp Inspector’s Signature

Doc # 202-100-VLA 20 December, 2000 Page DOT-Approved 6 - 4

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance

6.3. WEIGHT AND BALANCE REPORT

The empty weight and Empty Weight CG position data determined prior to delivery of the airplane is the

first entry in the Weight and Balance Report. Each change of the installed equipment as well as each

repair affecting the empty weight, the CG position of the empty weight or the empty weight moment must

be entered in the Weight and Balance Report at the end of this chapter. The following Sample Weight

and Balance Report figure 6.2. is for reference only.

Ensure that you are using the latest weight and balance information when performing a weight and

balance calculation

Doc # 202-100-VLA 20 December, 2000 Page Issue 1 6 - 5

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance

figure 6.2: Sample Weight and Balance Report (Aircraft specific report at the end of this chapter)

Model: DA20-A1/100 KATANA

Aircraft Specific Weight and Balance Report

Date Description Changes of W eight Actual Signature

IN OU

of Part or Addition (+) Subtraction (-) Empty Weight

Modification Weight Arm Moment W eight Arm Moment Weight Arm Moment

Original

lbs in in.lbs lbs in in .lbs lbs in in.lbs

(kg) (m ) (kg.m) (kg) (m) (kg.m) (kg) (m) (kg.m)

ircraft Serial No.:

Registration:

Issue Date:

Doc # 202-100-VLA 20 December, 2000 Page Issue 1 6 - 6

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DIAMOND AIRCRAFT DA 20/100 Flight Manual 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 Diagram

Figure 6.4 Calculation of Loading Condition

Figure 6.5 Permissible Center of Gravity Range

and permissible Flight-

are to be used for calculations of the flight-weight and the center of gravity as follows:

1. 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".

2. 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.

3. 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.

Weight-Moment

Doc # 202-100-VLA 20 December, 2000 Page DOT approved 6 - 7

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance

Figure 6.3: Weight & Balance Diagram

Example: Pilot and Passenger: 380 lbs. (172 kg)

Fuel 19.5 US gal. / 74 liters: 117 lbs. ( 53 kg)

(6.01 lbs. per US gal./0.72 kg per liter)

Baggage 11lbs. (5 kg)

Result: Moment of Pilot and Passenger: 2139 in.lbs. (24.60 kgm)

Moment of Fuel: 3796 in.lbs. (43.76 kgm)

Moment of Baggage 357 in.lbs. (4.12 kgm)

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance

Figure 6.4: Calculation of Loading Condition

Calculation of the

Load Limits

(Weight [kg]) ([kgm]) (Weight [kg]) ([kgm])

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: 0.143 m (5.63 in)

3. Baggage:

Lever Arm: 0.824 m (32.44 in)

DA 20 (Example) Your DA 20

Weight [lbs] Moment

[in.lbs]

1145

(520)

380

(172)

(5)

12880

(148.40)

2139

(24.60)

357

(4.12)

Weight [lbs] Moment

[in.lbs]

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 liter)

Lever Arm (32.44 in) (0.824 m)

6. Total Weight and Total Moment, taking fuel into account

(sum of 4. and 5.)

7. Find the values for the total weight (1536 lbs. and 1653 lbs.) and the total moment (15376 in lbs. and 19172 in.lbs.) in the center of gravity diagram. Since they are within the limitation range, the loading is permissible.

1536

(697)

117

(53)

1653

(750)

15376

(177.12)

3796

(43.76)

19172

(220.88)

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DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance

Figure 6.5: Permissible Center of Gravity Range and permissible Flight-Weight-Moment

1653 --

1635

1585

1535

1485

1435

1385

Flight Weight [lbs.]

1335

1285

Permissible Center of Gravity Range [mm/in]

)

(

)

(

)

(

)

(

)

(

)

(

)

--750

)

(

735

710

685

660

635

Flight Weight [kg.]

610

585

1235

12100 13428 14756 16084 17412 18740 20068 21396 22724 24052 25380

Permissable Flight-Weight-Moment

DA 20 (Example of page 6-9)

Changes during flight (due to fuel consumption)

560

(in*lbs)

(Kg*m)

Doc # 202-100-VLA November 18, 2003 Page Revision 2 6 - 10

Diamond JAR-VLA Flight Manual

Specifications and Main Features

Frequently Asked Questions

User Manual