Diamond Aircraft DV 20 E Flight Manual
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Diamond Aircraft DV 20 E Flight Manual

Diamond Aircraft DV 20 E Flight Manual

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Requirement
Serial Number
Registration
Doc. No.
Date of Issue
This Airplane Flight Manual has been approved by EASA under Approval No. 10056462.
DIAMOND AIRCRAFT INDUSTRIES GMBH
N.A. OTTO-STR. 5
A-2700 WIENER NEUSTADT
AUSTRIA
AIRPLANE FLIGHT MANUAL
DV 20 E
: CS-VLA
: ________
: ________
: 4.01.25-E
: 15-Dec-2015
Page 0 - 0

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  • Page 1 AIRPLANE FLIGHT MANUAL DV 20 E Requirement : CS-VLA Serial Number : ________ Registration : ________ Doc. No. : 4.01.25-E Date of Issue : 15-Dec-2015 This Airplane Flight Manual has been approved by EASA under Approval No. 10056462. DIAMOND AIRCRAFT INDUSTRIES GMBH N.A.
  • Page 2 DV 20 E AFM Introduction Intentionally left blank. Page 0 - 0a Rev. 2 22-Mar-2022 Doc. # 4.01.25-E...
  • Page 3 Before this airplane is operated for the first time, the pilot must familiarize himself with the complete contents of this Airplane Flight Manual. In the event that you have obtained your DIAMOND DV 20 E second-hand, please let us know your address, so that we can supply you with the publications necessary for the safe operation of your airplane.
  • Page 4 Introduction DV 20 E AFM 0.1 APPROVAL The content of approved chapters is approved by EASA. All other content is approved by DAI under the authority of EASA DOA No. EASA.21J.052 in accordance with Part 21. 0.2 RECORD OF REVISIONS All revisions of this manual, with the exception of - •...
  • Page 5 DV 20 E AFM Introduction Chap- Rev. Date of Approval Date Reason Page(s) Approval No. Signature Revision Date Inserted Revision 1 of the AFM Doc.No. 4.01.25-E All except 15-Dec-2016 28-Feb-2017 MÄM 20-413 is approved cover page by EASA under Approval No.
  • Page 6 Introduction DV 20 E AFM 0.3 LIST OF EFFECTIVE PAGES Page Date Page Date 15-Dec-2015 22-Mar-2022 0-0a 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 1-10 22-Mar-2022 22-Mar-2022 1-11 22-Mar-2022 22-Mar-2022 1-12...
  • Page 7 DV 20 E AFM Introduction Page Date Page Date appr. 2-1 22-Mar-2022 appr. 3-1 22-Mar-2022 appr. 2-2 22-Mar-2022 appr. 3-2 22-Mar-2022 appr. 2-3 22-Mar-2022 appr. 3-3 22-Mar-2022 appr. 2-4 22-Mar-2022 appr. 3-4 22-Mar-2022 appr. 2-5 22-Mar-2022 appr. 3-5 22-Mar-2022 appr. 2-6 22-Mar-2022 appr.
  • Page 8 Introduction DV 20 E AFM Page Date Page Date appr. 3-28 22-Mar-2022 appr. 4-1 22-Mar-2022 appr. 3-29 22-Mar-2022 appr. 4-2 22-Mar-2022 appr. 3-30 22-Mar-2022 appr. 4-3 22-Mar-2022 appr. 3-31 22-Mar-2022 appr. 4-4 22-Mar-2022 appr. 3-32 22-Mar-2022 appr. 4-5 22-Mar-2022 appr. 3-33 22-Mar-2022 appr.
  • Page 9 DV 20 E AFM Introduction Page Date Page Date 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 appr. 5-5 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 appr. 5-7 22-Mar-2022 22-Mar-2022 appr. 5-8 22-Mar-2022 22-Mar-2022 appr. 5-9 22-Mar-2022 22-Mar-2022 appr. 5-10 22-Mar-2022 6-10 22-Mar-2022 appr.
  • Page 10 Introduction DV 20 E AFM Page Date Page Date 22-Mar-2022 7-28 22-Mar-2022 7-29 22-Mar-2022 22-Mar-2022 22-Mar-2022 7-30 22-Mar-2022 7-31 22-Mar-2022 22-Mar-2022 7-32 22-Mar-2022 22-Mar-2022 22-Mar-2022 7-33 22-Mar-2022 7-34 22-Mar-2022 22-Mar-2022 7-35 22-Mar-2022 22-Mar-2022 22-Mar-2022 7-36 22-Mar-2022 7-37 22-Mar-2022 7-10 22-Mar-2022...
  • Page 11 DV 20 E AFM Introduction Page Date 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 22-Mar-2022 8-10 22-Mar-2022 8-11 22-Mar-2022 8-12 22-Mar-2022 8-13 22-Mar-2022 8-14 22-Mar-2022 Page Date 22-Mar-2022 22-Mar-2022 Doc. # 4.01.25-E Rev. 2 22-Mar-2022 Page 0 - 9...
  • Page 12 Introduction DV 20 E AFM 0.4 TABLE OF CONTENTS Chapter GENERAL (a non-approved chapter) ........1 OPERATING LIMITATIONS (an approved chapter) .

  • Page 13: Table Of Contents

    DV 20 E AFM General CHAPTER 1 GENERAL Page INTRODUCTION ........1-2 CERTIFICATION BASIS .

  • Page 14: Introduction

    General DV 20 E AFM 1.1 INTRODUCTION This Airplane Flight Manual has been prepared in order to provide pilots and instructors with all the information required for the safe and efficient operation of the airplane. The Airplane Flight Manual includes all the data which must be made available to the pilot according to the CS-VLA requirement.

  • Page 15: Certification Basis

    DV 20 E AFM General 1.2 CERTIFICATION BASIS The certification basis is CS-VLA including Amdt. 1 and additional requirements as laid down in CRI A-01 and published in the Type Certificate Data Sheet including Special Conditions for MTOM 800 kg and NVFR-Operation.

  • Page 16: Dimensions

    General DV 20 E AFM 1.4 DIMENSIONS NOTE All dimensions shown below are approximate. Overall Dimensions Span : 10.87 m 35 ft 8 in Length : 7.15 m 23 ft 5 in Height : 2.10 m 6 ft 11 in...
  • Page 17 DV 20 E AFM General Wing Flaps Area (total, left + right) : 2.16 m² 23.25 sq.ft. Horizontal Tail Area : 1.83 m 18.7 sq.ft. Elevator area : 0.50 m² 5.4 sq.ft. Angle of incidence : -4° relative to longitudinal axis of airplane...

  • Page 18: Three-View Drawing

    General DV 20 E AFM 1.5 THREE-VIEW DRAWING Page 1 - 6 Rev. 2 22-Mar-2022 Doc. No. 4.01.25-E...

  • Page 19: Definitions And Abbreviations

    DV 20 E AFM General 1.6 DEFINITIONS AND ABBREVIATIONS (a) Airspeeds CAS: Calibrated Airspeed. Indicated airspeed, corrected for installation and instrument errors. CAS equals TAS at standard atmospheric conditions (ISA) at MSL. IAS: Indicated Airspeed as shown on an airspeed indicator.
  • Page 20 General DV 20 E AFM Stalling Speed, or the minimum continuous speed at which the airplane is still controllable with flaps retracted. Best Angle-of-Climb Speed. Best Rate-of-Climb Speed. Speed at 50 ft above take-off surface. 50ft (b) Meteorological Terms ISA: International Standard Atmosphere.
  • Page 21 DV 20 E AFM General Pressure Altitude: Altitude indicated by a barometric altimeter, which is set to 1013.25 hPa (29.92 inHg). The Pressure Altitude is the Indicated Pressure Altitude corrected for installation and instrument errors. In this Airplane Flight Manual altimeter instrument errors are regarded as zero.
  • Page 22 General DV 20 E AFM (d) Mass and Balance Center of Gravity, also called 'center of mass'. Imaginary point in which the airplane mass is assumed to be concentrated for mass and balance calculations. Its distance from the Datum Plane is equal to the Center of Gravity Moment Arm.
  • Page 23 DV 20 E AFM General Unusable fuel: The quantity of fuel remaining in the tank which cannot be used for flight. Useful load: The difference between take-off mass and empty mass. (e) Engine EMS: Engine Management System ECU: Engine Control Unit...
  • Page 24 General DV 20 E AFM BACKUP Battery Backup Primary Flight Display Air Data Computer AHRS Attitude Heading Reference System PITOT Pitot Heating System MASTER CONTROL Master Control (Avionic Relay, Engine Master Relay, etc.) ALT. CONTROL: External Alternator Control ALT.: External Alternator...

  • Page 25: Units Of Measurement

    DV 20 E AFM General 1.7 UNITS OF MEASUREMENT 1.7.1 CONVERSION FACTORS Dimension SI-Units US Units Conversion Length [mm] millimeters [in] inches [mm] / 25.4 = [in] meters [ft] feet [m] / 0.3048 = [ft] [km] kilometers [NM] nautical [km] / 1.852 = [NM]...
  • Page 26 General DV 20 E AFM Dimension SI-Units US Units Conversion Intensity of ampères electric current Electric [Ah] ampère-hours charge (battery capacity) Electric volts potential Time [sec] seconds Page 1 - 14 Rev. 2 22-Mar-2022 Doc. No. 4.01.25-E...

  • Page 27: Conversion Chart Liters / Us Gallons

    DV 20 E AFM General 1.7.2 CONVERSION CHART LITERS / US GALLONS Liters US Gallons US Gallons Liters 15.1 22.7 30.3 37.9 45.4 10.6 53.0 11.9 60.6 13.2 68.1 15.9 75.7 18.5 83.3 21.1 90.9 23.8 98.4 26.4 Doc. No. 4.01.25-E Rev.

  • Page 28: Source Documentation

    General DV 20 E AFM 1.8 SOURCE DOCUMENTATION This section lists documents, manuals and other literature that were used as sources for the Airplane Flight Manual, and indicates the respective publisher. However, only the information given in the Airplane Flight Manual is valid.

  • Page 29: Propeller

    DV 20 E AFM General 1.8.2 PROPELLER Address: mt-propeller Airport Straubing Wallmühle 94348 Atting GERMANY Phone: +49-9429-9409-0 E-mail: sales@mt-propeller.com Website: www.mt-propeller.de Documents: E-124, Operation and Installation Manual Hydraulically controlled variable pitch propeller MTV -5, -6, -9, -11, -12, -14, -15, -16, -21, -22, -25 1.8.3 AVIONICS SYSTEM...
  • Page 30 General DV 20 E AFM Intentionally left blank. Page 1 - 18 Rev. 2 22-Mar-2022 Doc. No. 4.01.25-E...
  • Page 31 DV 20 E AFM Operating Limitations CHAPTER 2 OPERATING LIMITATIONS Page INTRODUCTION ........2-2 AIRSPEED .

  • Page 32: Introduction

    Operating Limitations DV 20 E AFM 2.1 INTRODUCTION Chapter 2 of this Airplane Flight Manual provides operating limitations, instrument markings and placards necessary for the safe operation of the airplane, its powerplant, standard systems and standard equipment. The limitations included in this Chapter are approved.

  • Page 33: Airspeed

    DV 20 E AFM Operating Limitations 2.2 AIRSPEED Airspeed KIAS Remarks Maneuvering speed 111 KIAS Do not make full or abrupt control surface movement above this speed. Max. flaps 78 KIAS Do not exceed these extended speed speeds with the given 100 KIAS flap setting.

  • Page 34: Airspeed Indicator Markings

    Operating Limitations DV 20 E AFM 2.3 AIRSPEED INDICATOR MARKINGS Marking KIAS Significance White arc 35-78 KIAS Operating range with flaps fully extended. Green arc 42-121 KIAS Normal operating range. Yellow arc 121-164 KIAS ‘Caution’ range - “Only in smooth air”.

  • Page 35: Power-Plant Limitations

    DV 20 E AFM Operating Limitations 2.4 POWER-PLANT LIMITATIONS a) Engine Manufacturer BRP-Powertrain GmbH & Co KG Engine designation Rotax 912 iSc3 Sport Max. take-off power 73.5 kW max. 5 min Max. continuous power 72 kW b) Propeller Manufacturer mt-Propeller...
  • Page 36 Operating Limitations DV 20 E AFM f) Ambient temperature at engine start Maximum 50 °C g) Oil temperature Minimum at engine start -20 °C Minimum 50 °C Maximum 130 °C h) Manifold air temperature Maximum 60 °C i) Coolant temperature Maximum 120 °C...
  • Page 37 DV 20 E AFM Operating Limitations Oil specification Brand Description Specification Viscosity SHELL AeroShell Sport Plus 4 API SL SAE 10W-40 Furthermore, use only motorcycle oil of a registered brand with gear additives. Use only oil with API classification ‘SG’ or higher!

  • Page 38: Engine Instrument Markings

    Operating Limitations DV 20 E AFM 2.5 ENGINE INSTRUMENT MARKINGS Engine instrument markings and their color code significance are shown in the tables below. Indi- Yellow Green Yellow cation arc/bar arc/bar arc/bar arc/bar arc/bar lower caution normal caution upper prohibited...

  • Page 39: Warning, Caution And Advisory Alerts

    DV 20 E AFM Operating Limitations 2.6 WARNING, CAUTION AND ADVISORY ALERTS Warning alerts Meaning / Cause (red) The airframe receives no electric power from the engine due VOLTAGE to generator failure. START Engine starter is engaged. CANOPY The canopy is not closed and locked.

  • Page 40: Mass (Weight)

    Operating Limitations DV 20 E AFM 2.7 MASS (WEIGHT) Mass (Weight) Value Maximum take-off mass 800 kg 1764 lb Minimum flight mass 580 kg 1279 lb Max. load in baggage compartment 20 kg 44 lb only permissible with baggage harness...

  • Page 41: Center Of Gravity

    DV 20 E AFM Operating Limitations 2.8 CENTER OF GRAVITY Datum Plane The datum plane (DP) is a plane which is normal to the airplane’s longitudinal axis and in front of the airplane as seen from the direction of flight. The airplane’s longitudinal axis is parallel with the fuselage tube.

  • Page 42: Approved Maneuvers

    Operating Limitations DV 20 E AFM 2.9 APPROVED MANEUVERS The airplane is certified in accordance with CS-VLA. Approved Maneuvers 1) All normal flight maneuvers; 2) Stalling (with the exception of dynamic stalling); and 3) Lazy Eights, Chandelles, as well as steep turns and similar maneuvers, in which an angle of bank of not more than 60°...

  • Page 43: Maneuvering Load Factors

    DV 20 E AFM Operating Limitations 2.10 MANEUVERING LOAD FACTORS NOTE The tables below show structural limitations. The load factor limits for the engine must also be observed. Refer to the corresponding Operator’s Manual for the engine. at v at v...

  • Page 44: Operating Altitude

    Operating Limitations DV 20 E AFM 2.11 OPERATING ALTITUDE The maximum operating altitude is 13,100 ft (4,000 m) pressure altitude. 2.12 FLIGHT CREW Minimum crew 1 (one person) Maximum number of occupants 2 (two persons) 2.13 KINDS OF OPERATION Provided that national operational requirements are met, the following kinds of operation are approved: •...
  • Page 45 DV 20 E AFM Operating Limitations NOTE Many of the items of minimum equipment listed in the following table are integrated in the G500. Minimum Operational Equipment (Serviceable) For daytime In addition for VFR flights night VFR flights Flight &...
  • Page 46 Operating Limitations DV 20 E AFM Minimum Operational Equipment (Serviceable) For daytime In addition for VFR flights night VFR flights Lighting • Position lights • Strobe lights (anti collision lights) • Landing light • Instrument lighting • Flashlight Other • Stall warning system •...

  • Page 47: Fuel

    DV 20 E AFM Operating Limitations 2.14 FUEL Approved fuel grades: AVGAS 100LL (ASTM D910), Super (Plus) (EN 228, maximum 5% ethanol), and blends of the above listed fuel grades. Anti knock properties: Min. RON 95 NOTE For fuels with AKI (Anti Knock Index) instead of RON specification, following AKI value has to be observed: min.

  • Page 48: Limitation Placards

    Operating Limitations DV 20 E AFM 2.15 LIMITATION PLACARDS All limitation placards are shown below. A list of all placards is included in the Airplane Maintenance Manual (Doc. No. 4.02.25), Chapter 11. The following limitation placards are in the forward view of the pilot:...
  • Page 49 DV 20 E AFM Operating Limitations Next to the Flap Selector Switch: FLAPS CRUISE FLAP SPEEDS (T/O) 100 KTS. (LDG) 78 KTS. On the Fuel Shut-off Control: FUEL PULL EASA Doc. No. 4.01.25-E Rev. 2 22-Mar-2022 Page 2 - 19...
  • Page 50 Operating Limitations DV 20 E AFM Next to the Canopy Handles (Inside) TO LIFT CANOPY TO LIFT CANOPY OPEN BOTH OPEN BOTH OPEN CLOSE SIDES CLOSE OPEN SIDES CLOSE OPEN OPEN CLOSE Next to the Canopy Handle (Outside) TO LIFT CANOPY...
  • Page 51 DV 20 E AFM Operating Limitations On the Sparbridge Between Pilot’s and Co-pilot’s Seat In the Baggage Compartment: MAX. BAGGAGE 20 kg / 44 lb In the Upper Cowling, on the Door for the Oil Filler Neck: AERO SHELL Sport Plus 4...

  • Page 52: Other Limitations

    Operating Limitations DV 20 E AFM 2.16 OTHER LIMITATIONS 2.16.1 BATTERY CHARGE Taking-off for a Night VFR flight with an empty battery is not permitted. The use of an external power supply for engine starting with an empty airplane battery is also not permitted if the subsequent flight is intended to be a Night VFR flight.

  • Page 53: Garmin G500 Avionic System

    DV 20 E AFM Operating Limitations 2.16.4 GARMIN G500 AVIONIC SYSTEM 1. The Garmin G500 Cockpit Reference Guide, Document No. 190-01102-03, latest revision must be immediately available to the flight crew. 2. The G500 must utilize the following or later approved software versions for safe...

  • Page 54: Smoking

    Operating Limitations DV 20 E AFM North of 70 degrees North latitude between longitude 85 degrees East and 114 degrees East. South of 55 degrees South latitude between longitude 120 degrees East and 165 degrees East. Loss of G500 heading and attitude may occur beyond these regions, but this will not affect the GPS track.

  • Page 55: Temperature Limits

    DV 20 E AFM Operating Limitations 2.16.7 TEMPERATURE LIMITS CAUTION For airplanes with other than white undersides, parking the airplane over a light colored or reflective surface in conditions of bright sunlight, particularly at high OAT, is not recommended. Temperature limit of the structure for the operation of the airplane: Maximum T/O temperature: 54 °C (129 °F).
  • Page 56 Operating Limitations DV 20 E AFM Intentionally left blank. EASA Page 2 - 26 Rev. 2 22-Mar-2022 Doc. No. 4.01.25-E approved...
  • Page 57 Emergency DV 20 E AFM Procedures CHAPTER 3 EMERGENCY PROCEDURES Page INTRODUCTION ........3-3 3.1.1 GENERAL .
  • Page 58 Emergency DV 20 E AFM Procedures ELECTRICAL SYSTEM FAILURE ......3-23 3.7.1 LOSS OF ELECTRICAL POWER ....3-23 3.7.2 LOW VOLTAGE WARNING LIGHT ILLUMINATED .

  • Page 59: Emergency Procedures

    Emergency DV 20 E AFM Procedures 3.1 INTRODUCTION 3.1.1 GENERAL This chapter contains checklists as well as the description of recommended procedures to be followed in the event of an emergency. Engine failure or other airplane-related emergencies are most unlikely to occur if the prescribed procedures for pre-flight checks and airplane maintenance are followed.

  • Page 60: Certain Airspeeds In Emergencies

    Emergency DV 20 E AFM Procedures 3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES Event KIAS Engine failure after take-off with flaps in T/O position Manoeuvring speed Airspeed for best glide angle Flaps CRUISE 800 kg (1762 lbs) Precautionary landing (with power and wing flaps in...

  • Page 61: Engine Failures

    Emergency DV 20 E AFM Procedures 3.2 ENGINE FAILURES 3.2.1 ENGINE FAILURE ON GROUND (a) Starter Does Not Disengage / START Warning Light ON Starter does not disengage after starting the engine (continuous whining sound audible and START warning light ON).

  • Page 62: Engine Failure During Take-Off Ground Roll

    Emergency DV 20 E AFM Procedures 3.2.2 ENGINE FAILURE DURING TAKE-OFF GROUND ROLL Abort take-off. 1. Throttle ......IDLE 2.

  • Page 63: Engine Failure In Flight

    Emergency DV 20 E AFM Procedures (b) Engine Inoperative Perform emergency landing in accordance with 3.5 - EMERGENCY LANDINGS. END OF CHECKLIST 3.2.4 ENGINE FAILURE IN FLIGHT (a) Engine Running Rough 1. Alternate air ......ON 2.
  • Page 64 Emergency DV 20 E AFM Procedures (b) Loss of Engine Power NOTE The various reasons can be lack of air, fuel, electric power etc. If no mechanical failure is expected, a restart in accordance with 3.3 - ENGINE RESTART IN FLIGHT can be attempted.
  • Page 65 Emergency DV 20 E AFM Procedures (d) Oil Pressure above Permitted Range at Low Oil Temperatures 1. Engine speed ......reduce 2.
  • Page 66 Emergency DV 20 E AFM Procedures (g) Exceeding the Maximum RPM 1. Propeller speed lever ....reduce below maximum RPM After flight: 2. Record maximum overspeed and duration in log book.

  • Page 67: Warning Flashing On The Emu Display

    Emergency DV 20 E AFM Procedures 3.2.5 WARNING FLASHING ON THE EMU DISPLAY Check which engine parameters are in the red warning range. NOTE More detailed information is available on the appropriate INFO page by pressing the INFO button on the EMU.

  • Page 68: Engine Restart In Flight

    Emergency DV 20 E AFM Procedures 3.3 ENGINE RESTART IN FLIGHT 3.3.1 RESTARTING THE ENGINE WITH WINDMILLING PROPELLER NOTE As long as the airspeed is at least 54 KIAS, the propeller will continue to windmill. 1. Airspeed ......70 KIAS 2.
  • Page 69 Emergency DV 20 E AFM Procedures 15. Starter button ......PRESS until 1500 RPM is reached (max 10s) START...

  • Page 70: Restarting The Engine With Stationary Propeller

    Emergency DV 20 E AFM Procedures 3.3.2 RESTARTING THE ENGINE WITH STATIONARY PROPELLER 1. AVIONIC MASTER ....OFF 2. Propeller speed lever ....full forward (max RPM) 3.
  • Page 71 Emergency DV 20 E AFM Procedures 13. AVIONIC MASTER ..... ON if required 14. Oil temperature ......check If the LANE A/B FAIL lights are not illuminated or flashing: 15.

  • Page 72: Gliding

    Emergency DV 20 E AFM Procedures 3.4 GLIDING 1. Wing flaps ......CRUISE 2. Airspeed at 800 kg (1764 lb) ... . . 73 KIAS NOTE The glide ratio is 11:1;...

  • Page 73: Emergency Landings

    Emergency DV 20 E AFM Procedures 3.5 EMERGENCY LANDINGS 3.5.1 EMERGENCY LANDING WITH ENGINE OFF Approach: 1. Wing flaps ......as required 2.

  • Page 74: Precautionary Landing With Engine Power Available

    Emergency DV 20 E AFM Procedures 3.5.2 PRECAUTIONARY LANDING WITH ENGINE POWER AVAILABLE NOTE A precautionary landing would be required if continuing of the flight would endanger the airplane or its occupants. Such circumstances could include mechanical defects, low fuel quantity or deteriorating weather conditions.
  • Page 75 Emergency DV 20 E AFM Procedures After Touch-down: 13. Brake ......as required 14.

  • Page 76: Engine Management System Failures

    Emergency DV 20 E AFM Procedures 3.6 ENGINE MANAGEMENT SYSTEM FAILURES 3.6.1 ERRONEOUS INDICATION OR FAILURE OF ENGINE DISPLAYS NOTE Loss of an engine parameter on the engine instrument is indicated by a white “---” instead of values in the data field.

  • Page 77: Ecu Malfunctions

    Emergency DV 20 E AFM Procedures 3.6.2 ECU MALFUNCTIONS (a) LANE A/B FAIL Light Illuminated or Flashing Inflight: - Land on the next suitable airfield. NOTE If a LANE A/B FAIL light is illuminated the engine is operated in power-mode with increased fuel consumption (up to 26.1 liter/h).
  • Page 78 Emergency DV 20 E AFM Procedures 3.6.3 EMU CAUTION LIGHT ILLUMINATED On Ground: 1. Propeller Speed Lever ..... . . increase above 1500 RPM 2.

  • Page 79: Electrical System Failure

    Emergency DV 20 E AFM Procedures 3.7 ELECTRICAL SYSTEM FAILURE 3.7.1 LOSS OF ELECTRICAL POWER 1. Battery circuit breaker ....check, if tripped reset 2.
  • Page 80 Emergency DV 20 E AFM Procedures (b) Low VOLTAGE Indication During Flight 1. GEN circuit breaker ....check, if tripped reset 2.

  • Page 81: Generator Failure

    Emergency DV 20 E AFM Procedures 3.7.3 GENERATOR FAILURE NOTE A generator failure can be detected by: - Illumination of low VOLTAGE warning light - negative Ammeter current. 1. All non-flight essential electrical consumers (especially lights and pitot heat) ..OFF 2.

  • Page 82: Smoke And Fire

    Emergency DV 20 E AFM Procedures 3.8 SMOKE AND FIRE 3.8.1 SMOKE AND FIRE ON GROUND (a) Engine Fire When Starting on the Ground 1. Fuel Shut-off Valve ....CLOSED 2.

  • Page 83: Smoke And Fire During Take-Off

    Emergency DV 20 E AFM Procedures 3.8.2 SMOKE AND FIRE DURING TAKE-OFF (a) Sufficient Runway Available for Straight-Ahead Landing 1. Throttle ......IDLE 2.

  • Page 84: Smoke And Fire In Flight

    Emergency DV 20 E AFM Procedures 3.8.3 SMOKE AND FIRE IN FLIGHT (a) Engine Fire in Flight 1. Fuel shut-off valve ..... CLOSED 2.
  • Page 85 Emergency DV 20 E AFM Procedures (b) Electrical Fire Including Smoke in Flight 1. ELECTRIC MASTER ....OFF 2. Cabin air ......OPEN 3.
  • Page 86 Emergency DV 20 E AFM Procedures (c) Cabin Fire in Flight 1. ELECTRIC MASTER ....OFF 2. Cabin air ......OPEN 3.

  • Page 87: Avionic System Failures

    Emergency DV 20 E AFM Procedures 3.9 AVIONIC SYSTEM FAILURES 3.9.1 AVIONICS SYSTEM FAILURE (a) Total Avionic Failure: 1. Avionic Master circuit breaker ... . check; reset if necessary and...

  • Page 88: G500 Failures

    Emergency DV 20 E AFM Procedures (c) Radio System Operative, Transmitting Not Possible: 1. Selected Frequency ....check if correct 2. Microphone ......check, if available use different...
  • Page 89 Emergency DV 20 E AFM Procedures (c) Airspeed Fail The display system is not receiving airspeed input AIRSPEED FAIL from the air data computer; accompanied by a red X through the airspeed display. Revert to the standby airspeed indicator. (d) Altitude Fail...

  • Page 90: Recovery From Unintentional Spin

    Emergency DV 20 E AFM Procedures 3.10 RECOVERY FROM UNINTENTIONAL SPIN 1. Throttle ......IDLE 2.

  • Page 91: Other Emergencies

    Emergency DV 20 E AFM Procedures 3.11 OTHER EMERGENCIES 3.11.1 UNINTENTIONAL FLIGHT INTO ICING CONDITION 1. Leave the icing area (by changing altitude or turning back). 2. Continue to move control surfaces to maintain their moveability. 3. Alternate air ......ON 4.
  • Page 92 Emergency DV 20 E AFM Procedures 3.11.2 FLAP SYSTEM FAILURE (a) Flap Position Indicator Failure Check flap position visually. Keep airspeed in white sector, if flap extended. Re-check all positions of the flap switch. Modified Approach Procedure Depending on the Available Flap Setting only CRUISE available: Approach airspeed .
  • Page 93 Emergency DV 20 E AFM Procedures 3.11.3 TRIM SYSTEM FAILURE (a) Stuck Trim 1. Circuit breaker ..... . . check, reset if necessary 2.

  • Page 94: Emergency Fuel Pump

    Emergency DV 20 E AFM Procedures 3.11.4 LANDING GEAR SYSTEM FAILURES (a) Landing with Defective Brakes Consider the longer rolling distance. 1. Safety harness ..... . . check fastened and tightened...
  • Page 95 Emergency DV 20 E AFM Procedures 3.11.5 SUSPICION OF CARBON MONOXIDE CONTAMINATION IN THE CABIN Carbon monoxide (CO) is a gas which is developed during the combustion process. It is poisonous and without smell. Increased concentration of carbon monoxide gas can be fatal.
  • Page 96 Emergency DV 20 E AFM Procedures 3.11.7 CANOPY LIGHT ILLUMINATED WARNING Do not try to open any canopy latch in flight. This can result in inadvertent opening of the canopy and subsequent loss of control. 1. Canopy latches LH, RH ....Both pushed forward If the CANOPY light is still illuminated: 1.
  • Page 97 Normal Operating DV 20 E AFM Procedures CHAPTER 4 NORMAL OPERATING PROCEDURES Page INTRODUCTION ........4-2 AIRSPEEDS FOR NORMAL OPERATING PROCEDURES .

  • Page 98: Flaps

    Normal Operating DV 20 E AFM Procedures INTRODUCTION Chapter 4 contains checklists and describes procedures for the normal operation of the airplane. AIRSPEEDS FOR NORMAL OPERATING PROCEDURES FLAPS Speed KIAS Climb speed during normal take-off for 50 ft (15 m)

  • Page 99: Electric Master

    Normal Operating DV 20 E AFM Procedures CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4.3.1 DAILY CHECK Before the first flight of a day it must be ensured that the following checks are performed: 1. Check of the canopy for cracks and major scratches.
  • Page 100 Normal Operating DV 20 E AFM Procedures 10. Turn the propeller slowly by hand in the direction of rotation for several times. NOTE Look especially for signs of abnormal sounds, excessive resistance or lack of compression. CAUTION Do not turn the propeller against the direction of rotation.
  • Page 101 Normal Operating DV 20 E AFM Procedures 4.3.2 PRE-FLIGHT INSPECTION I. Cabin Check 1. Structural temperature indicator (if OAT exceeds 38 °C (100 °F)) ..check that structural temperature does not exceed 54 °C (129 °F), a red ‘55' indicates a temperature...
  • Page 102 Normal Operating DV 20 E AFM Procedures 19. Wing flaps (indicator- and flap actuation) . . . check, extend and retract fully 20. Trim and flap indicator lights ... . . operational and dimmable 21.
  • Page 103 Normal Operating DV 20 E AFM Procedures II. Walk-around Check, Visual Inspection 5d-f 7b-j 3b, c, e 2c,e 2g,h 2d,f EASA Doc. No. 4.01.25-E Rev. 2 22-Mar-2022 Page 4 - 7 approved...
  • Page 104 Normal Operating DV 20 E AFM Procedures 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.
  • Page 105 Normal Operating DV 20 E AFM Procedures 3. Fuselage a) Skin ......visual inspection b) Tank vent .
  • Page 106 Normal Operating DV 20 E AFM Procedures 6. Right Main Landing Gear a) Landing gear strut ....visual inspection b) Wheel fairing ..... . . visual inspection c) Tire, wheel, brake .
  • Page 107 Normal Operating DV 20 E AFM Procedures a) Fluid levels - Oil ......check level, use dip-stick.
  • Page 108 Normal Operating DV 20 E AFM Procedures 4.3.3 BEFORE STARTING ENGINE CAUTION Before starting the engine, the canopy must be closed and latched. The red handles must be moved fully forward. After starting the engine, the canopy must stay in the closed and latched position until the engine is shut down.

  • Page 109: Starting Engine

    Normal Operating DV 20 E AFM Procedures 4.3.4 STARTING ENGINE NOTE At low temperatures preheat the engine prior to engine start. NOTE When the engine has been shut down, a restart of the engine is only possible after switching the ELECTRIC MASTER OFF.
  • Page 110 Normal Operating DV 20 E AFM Procedures NOTE Activate starter for max. 10 sec. only, followed by a cooling period of 2 min. 15. START warning light ....check OFF 16.

  • Page 111: Before Taxiing

    Normal Operating DV 20 E AFM Procedures 4.3.5 BEFORE TAXIING 1. AVIONIC MASTER ....ON 2. Flight instruments and avionics ..set 3.

  • Page 112: Before Take-Off

    Normal Operating DV 20 E AFM Procedures 4.3.7 BEFORE TAKE-OFF 1. Toe brakes ......hold 2.
  • Page 113 Normal Operating DV 20 E AFM Procedures 17. LANE SELECTOR switch ....LANE B, LANE A FAIL light ON (Max. RPM drop: 180 RPM) 18. LANE SELECTOR switch ....AUTO 19.

  • Page 114: Take-Off

    Normal Operating DV 20 E AFM Procedures 4.3.8 TAKE-OFF 1. LANE SELECTOR switch ....check AUTO 2. Emergency fuel pump ....check ON 3.

  • Page 115: Climb

    Normal Operating DV 20 E AFM Procedures 4.3.9 CLIMB 1. Propeller speed lever ....5500 RPM 2. Throttle ......FULL 3.

  • Page 116: Descent

    Normal Operating DV 20 E AFM Procedures 4.3.11 DESCENT 1. Flight instruments and avionics ... adjust 2. Throttle ......as required 3.

  • Page 117: Approach & Landing

    Normal Operating DV 20 E AFM Procedures 4.3.12 APPROACH & LANDING 1. Seat belts ......fastened 2.

  • Page 118: Go Around

    Normal Operating DV 20 E AFM Procedures 4.3.13 GO AROUND 1. Propeller speed lever ....max. RPM 2. Throttle ......FULL 3.

  • Page 119: Shut-Down

    Normal Operating DV 20 E AFM Procedures 4.3.15 SHUT-DOWN 1. Throttle ......IDLE 2.

  • Page 120: Caution Flashing On The Emu Display

    Normal Operating DV 20 E AFM Procedures 4.3.17 CAUTION FLASHING ON THE EMU DISPLAY 1. Check which engine parameters are in the amber caution range. NOTE More detailed information is available on appropriate INFO page by pressing the INFO button on the EMU.
  • Page 121 DV 20 E AFM Performance CHAPTER 5 PERFORMANCE Page INTRODUCTION ........5-2 USE OF THE PERFORMANCE TABLES AND DIAGRAMS .

  • Page 122: Introduction

    Performance DV 20 E AFM 5.1 INTRODUCTION The performance tables and diagrams on the following pages are presented so that, on the one hand, you can see what performance you can expect from your airplane, while on the other hand they allow comprehensive and sufficiently accurate flight planning. The...

  • Page 123: Performance Tables And Diagrams

    DV 20 E AFM Performance 5.3 PERFORMANCE TABLES AND DIAGRAMS 5.3.1 AIRSPEED CALIBRATION Airspeed Indicator Calibration Calibrated Airspeed [KCAS] Indicated Flaps CRUISE Flaps T/O Flaps LDG Airspeed [KIAS] Doc. No. 4.01.25-E Rev. 2 22-Mar-2022 Page 5 - 3...

  • Page 124: International Standard Atmosphere

    Performance DV 20 E AFM 5.3.2 INTERNATIONAL STANDARD ATMOSPHERE Page 5 - 4 Rev. 2 22-Mar-2022 Doc. No. 4.01.25-E...

  • Page 125: Stalling Speeds

    DV 20 E AFM Performance 5.3.3 STALLING SPEEDS Stalling Speeds at Various Flight Masses Airspeeds, most forward CG, power off: Bank Angle 0° 30° 45° 60° KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS CRUISE NOTE KIAS values may not be accurate at stall.

  • Page 126: Wind Components

    Performance DV 20 E AFM 5.3.4 WIND COMPONENTS Flight Direction 32° 0° 10° 20° 30° 40° 50° 60° 70° 80° 90° 100° 110° 180° 160° 130° 120° Crosswind Component [kts] Example: Flight direction 360° Wind 32°/30 kts Result: Crosswind component 16 kts Max.
  • Page 127 DV 20 E AFM Performance 5.3.5 TAKE-OFF DISTANCE Conditions: - Throttle ......MAX - Propeller speed lever .
  • Page 128 Performance DV 20 E AFM WARNING Poor maintenance condition of the airplane, deviation from the given procedures, uneven runway, as well as unfavorable external factors ( rain, unfavorable wind conditions, including cross-wind) will increase the take-off distance. EASA Page 5 - 8 Rev.
  • Page 129 DV 20 E AFM Performance Take-Off Distance - Normal Procedure - 800 kg / 1764 lb Weight: 800 kg / 1764 lb Flaps: Throttle: MAX : 49 KIAS Propeller: HIGH : 60 KIAS Runway: dry, paved, level 50ft Outside Air Temperature - [°C] / [°F] Press.
  • Page 130 Performance DV 20 E AFM Take-Off Distance - Normal Procedure - 700 kg / 1543 lb Weight: 700 kg / 1543 lb Flaps: Throttle: MAX : 49 KIAS Propeller: HIGH : 60 KIAS Runway: dry, paved, level 50ft Outside Air Temperature - [°C] / [°F] Press.
  • Page 131 DV 20 E AFM Performance Take-Off Distance - Normal Procedure - 600 kg / 1323 lb Weight: 600 kg / 1323 lb Flaps: Throttle: MAX : 49 KIAS Propeller: HIGH : 60 KIAS Runway: dry, paved, level 50ft Outside Air Temperature - [°C] / [°F] Press.

  • Page 132: Climb Performance - Take-Off Climb

    Performance DV 20 E AFM 5.3.6 CLIMB PERFORMANCE - TAKE-OFF CLIMB Conditions: - Throttle ......MAX - Propeller speed lever .
  • Page 133 DV 20 E AFM Performance Take-Off Climb - Flaps T/O Flaps: T/O Throttle: 66 KIAS Propeller: 5500 RPM Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C] / [°F] Alt. Alt. [ft] 2000 4000 1219 6000 1829...
  • Page 134 Performance DV 20 E AFM Take-Off Climb - Flaps T/O Flaps: T/O Throttle: 66 KIAS Propeller: 5500 RPM Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C] / [°F] Alt. Alt. [ft] 1310 1250 1180 1120 1070...
  • Page 135 DV 20 E AFM Performance 5.3.7 CLIMB PERFORMANCE - CRUISE CLIMB Conditions: - Throttle ......MAX - Propeller speed lever .
  • Page 136 Performance DV 20 E AFM Cruise Climb Flaps: CRUISE Throttle: 75 KIAS Propeller: 5500 RPM Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C] / [°F] Alt. Alt. [ft] 2000 1219 4000 1829 6000 2438 8000 3048...
  • Page 137 DV 20 E AFM Performance Cruise Climb Flaps: CRUISE Throttle: 75 KIAS Propeller: 5500 RPM Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C] / [°F] Alt. Alt. [ft] 1460 1380 1300 1230 1160 1090 1020 1193...
  • Page 138 Performance DV 20 E AFM 5.3.8 CRUISE PERFORMANCE Conditions: - Flaps ......CRUISE - Weight .
  • Page 139 DV 20 E AFM Performance Cruise Performance Outside Air Temperature - [°C] Press. ISA-10 ISA+10 ISA+20 ISA+30 Alt. [ft] [l/h] [l/h] [l/h] [l/h] [l/h] [kt] [kt] [kt] [kt] [kt] inHg] inHg] inHg] inHg] inHg] 5500 WOT 26,1 121 WOT 26,1 122 WOT 26,1 122 WOT 26,1 121 WOT 26,1 120...
  • Page 140 Performance DV 20 E AFM 5.3.9 LANDING DISTANCES Conditions: - Throttle ......IDLE - Propeller speed lever .
  • Page 141 DV 20 E AFM Performance Landing Distance - Flaps LDG - 800 kg / 1764 lb Weight: 800 kg / 1764 lb Flaps: Throttle: IDLE : 56 KIAS Propeller: HIGH Runway: dry, paved, level Outside Air Temperature - [°C] / [°F] Press.
  • Page 142 Performance DV 20 E AFM Landing Distance - Flaps LDG - 700 kg / 1543 lb Weight: 700 kg / 1543 lb Flaps: Throttle: IDLE : 56 KIAS Propeller: HIGH Runway: dry, paved, level Outside Air Temperature - [°C] / [°F] Press.
  • Page 143 DV 20 E AFM Performance Landing Distance - Flaps LDG - 600 kg / 1323 lb Weight: 600 kg / 1323 lb Flaps: Throttle: IDLE : 56 KIAS Propeller: HIGH Runway: dry, paved, level Outside Air Temperature - [°C] / [°F] Press.
  • Page 144 Performance DV 20 E AFM 5.3.10 GO-AROUND CLIMB PERFORMANCE Conditions: - Throttle ......MAX - Propeller speed lever .
  • Page 145 DV 20 E AFM Performance Go-Around Climb Performance Flaps: LDG Trottle: 56 KIAS Propeller: HIGH Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C] / [°F] Alt. Alt. [ft] 2000 1219 4000 6000 1829 8000 2438 3048...
  • Page 146 Performance DV 20 E AFM 5.3.11 APPROVED NOISE DATA Max. Flight Mass 800 kg (1764 lb) ICAO Annex 16 Chapter X, App.6 ... . 71.4 dB(A) 5.3.12 COOLING PERFORMANCE Cooling performance in accordance with CS-VLA 1041 to 1047 has been demonstrated up to 47 °C (117 °F).
  • Page 147 DV 20 E AFM Mass and Balance CHAPTER 6 MASS AND BALANCE Page INTRODUCTION ........6-2 DATUM PLANE .

  • Page 148: Introduction

    Mass and Balance DV 20 E AFM 6.1 INTRODUCTION In order to achieve the performance and flight characteristics described in this Airplane Flight Manual and for safe flight operation, the airplane must be operated within the permissible mass and balance envelope.

  • Page 149: Datum Plane

    DV 20 E AFM Mass and Balance NOTE Refer to Section 1.6 - UNITS OF MEASUREMENT for conversion of SI units to US units and vice versa. 6.2 DATUM PLANE The Datum Plane (DP) is a plane which is normal to the airplane’s longitudinal axis and in front of the airplane as seen from the direction of flight.

  • Page 150: Mass And Balance Report

    Mass and Balance DV 20 E AFM 6.3 MASS AND BALANCE REPORT The empty mass and the corresponding CG position established before delivery are the first entries in the Mass and Balance Report. Every change in permanently installed equipment, and every repair to the airplane which affects the empty mass or the empty mass CG must be recorded in the Mass and Balance Report.
  • Page 151 DV 20 E AFM Mass and Balance MASS AND BALANCE REPORT Doc. No. 4.01.25-E Rev. 2 22-Mar-2022 Page 6 - 5...

  • Page 152: Flight Mass And Center Of Gravity

    DV 20 E AFM 6.4 FLIGHT MASS AND CENTER OF GRAVITY The following information enables you to operate your DV 20 E within the permissible mass and balance limits. For the calculation of the flight mass and the corresponding CG position the following tables and diagrams are required: 6.4.1 - MOMENT ARMS...
  • Page 153 DV 20 E AFM Mass and Balance 3. Multiply the individual masses by the moment arms quoted to obtain the moment for every item of loading and enter these moments in the appropriate boxes in Table 6.4.3 - CALCULATION OF LOADING CONDITION.

  • Page 154: Moment Arms

    Mass and Balance DV 20 E AFM 6.4.1 MOMENT ARMS The most important lever arms aft of the Datum Plane: Lever Arm Item [in] Pilot / Co-pilot 0.14 Fuel / Baggage 0.82 32.4 Page 6 - 8 Rev. 2 22-Mar-2022...

  • Page 155: Loading Diagram

    DV 20 E AFM Mass and Balance 6.4.2 LOADING DIAGRAM Doc. No. 4.01.25-E Rev. 2 22-Mar-2022 Page 6 - 9...
  • Page 156 Mass and Balance DV 20 E AFM 6.4.3 CALCULATION OF LOADING CONDITION 1. Complete the form on the next page. 2. Divide the total moments from rows 4 and 6 by the related total mass to obtain the CG positions.

  • Page 157: Calculation Of Loading Condition

    DV 20 E AFM Mass and Balance DV 20 E Your DV 20 E (Example) CALCULATION OF Mass Moment Mass Moment LOADING CONDITION [kg] [kgm] [kg] [kgm] [lb] [in.lb] [lb] [in.lb] 1. Empty mass (from Mass and 144.7 Balance Report)

  • Page 158: Permissible Center Of Gravity Range

    Mass and Balance DV 20 E AFM 6.4.4 PERMISSIBLE CENTER OF GRAVITY RANGE Center of Gravity Positio n [in] 0.22 0.24 0.26 0.28 0.30 0.32 0.34 0.36 0.38 Center of Gravity Positio n [m] The flight CG position must be within the following limits: Most forward flight CG: 0.240 m (9.45 in) aft of datum plane...

  • Page 159: Equipment List And Equipment Inventory

    DV 20 E AFM Mass and Balance 6.5 EQUIPMENT LIST AND EQUIPMENT INVENTORY All equipment that is approved for installation in the DV 20 E is shown in the Equipment List below. NOTE The equipment listed below cannot be installed in any arbitrary combination.
  • Page 160 DV 20 E AFM Mass and Balance Airplane Serial No.: Registration: Date: Mass Lever Arm Description Type Part No. Manufacturer installed ELECTRICAL POWER Main battery BC100-1 B & C Speciality 22.500 10.200 -29.5 -0.75 Low Voltage Monitor D20-2401-11-00 Diamond Aircraft 0.132...
  • Page 161 DV 20 E AFM Mass and Balance Airplane Serial No.: Registration: Date: Mass Lever Arm Description Type Part No. Manufacturer installed INDICATING / REC. SYSTEM Display unit (PFD/MFD) GDU 620 011-01264-50 Garmin 6.380 2.900 -20.5 -0.52 Flight timer 85094-12 Hobbs 0.500...
  • Page 162 DV 20 E AFM Mass and Balance Airplane Serial No.: Registration: Date: Mass Lever Arm Description Type Part No. Manufacturer installed Magnetometer GMU 44 011-00870-10 Garmin 0.350 0.160 110.2 ENGINE Engine Rotax 912 iSc3 Sport BRP-Powertrain Engine control unit 881252 BRP-Powertrain 2.535...
  • Page 163 DV 20 E AFM Mass and Balance Airplane Serial No.: Registration: Date: Mass Lever Arm Description Type Part No. Manufacturer installed FUEL TANK SYSTEM Fuel probe 22-2840-02-00 Diamond Aircraft 0.350 0.160 32.3 0.820 AIRPLANE FLIGHT MANUAL Doc. No. 4.01.25-E Diamond Aircraft...
  • Page 164 DV 20 E AFM Mass and Balance Intentionally left blank. Doc. No. 4.01.25-E Rev. 2 22-Mar-2022 Page 6 - 18...
  • Page 165 DV 20 E AFM Airplane Description CHAPTER 7 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS Page INTRODUCTION ........7-3 AIRFRAME .
  • Page 166 DV 20 E AFM Airplane Description 7.12.1 GENERAL ........7-48 7.12.2 GDU 620 DISPLAY .

  • Page 167: Introduction

    DV 20 E AFM Airplane Description 7.1 INTRODUCTION Chapter 7 contains a description of the airplane and its systems, together with operating instructions. For details about optional equipment see Chapter 9. Doc. No. 4.01.15-E Rev. 2 22-Mar-2022 Page 7 - 3...

  • Page 168: Airframe

    DV 20 E AFM Airplane Description 7.2 AIRFRAME 7.2.1 GENERAL Fuselage The GFRP fuselage is of semi monocoque molded construction. The main spar is made from CFRP. The fire protection on the firewall is of a special fire-resistant matting, which is covered on the engine side by stainless steel cladding.

  • Page 169: Structural Temperature Indicator

    DV 20 E AFM Airplane Description 7.2.2 STRUCTURAL TEMPERATURE INDICATOR A structural temperature indicator, installed on the spar bridge, indicates when the structural temperature limitation is exceeded (Refer to 2.16.7 - TEMPERATURE LIMITS). Airplanes with other than white undersides have an additional structural temperature indicator installed adjacent to the fuel drains.

  • Page 170: Flight Controls

    DV 20 E AFM Airplane Description 7.3 FLIGHT CONTROLS The ailerons, elevator and wing flaps are operated through control rods, while the rudder is controlled by cables. The flaps are electrically operated. Elevator forces can be balanced using the electric trim system. Rudder forces can be balanced by a trim tab on the rudder, which is also operated by a Bowden cable.
  • Page 171 DV 20 E AFM Airplane Description Flaps Construction: GFRP/CFRP composite sandwich. Hinges: There are 4 hinges at each flap. The flaps are attached to the wing with a bolt and an aluminium bracket. Operation: Each part is connected with a flap control horn to the push rods of the flap control system.
  • Page 172 DV 20 E AFM Airplane Description The flaps are operated by means of a 3-position flap selector switch on the instrument panel. The positions of the switch correspond to the positions of the flaps, the Cruise position of the switch being at the top. If the switch is moved to another position, the flaps continue to travel automatically until they have reached the position selected on the switch.
  • Page 173 DV 20 E AFM Airplane Description Elevator Construction: GFRP sandwich. Hinges: 5 hinges. Operation: Steel pushrods; Two of the bellcrank bearings are accessible for visual inspection next to the lower hinge of the rudder. The elevator horn and its bearing, as well as the connection to the pushrod, can be visually inspected at the upper end of the rudder.
  • Page 174 DV 20 E AFM Airplane Description Elevator Trim The rocker switch is located on top of the control stick. The digital trim indicator is located in the upper instrument panel. The switch controls an electrical actuator beside the vertical push rod in the vertical stabilizer.
  • Page 175 DV 20 E AFM Airplane Description Flight Control Lock A flight control lock is provided with each airplane and should be installed whenever the airplane is parked. See Figure 7.3 - Installation and Removal of the Control Lock. CAUTION Failure to install the flight control lock whenever the airplane is parked may result in control system damage, due to gusts or turbulence.
  • Page 176 DV 20 E AFM Airplane Description Trim the airplane to neutral. Pull the left rudder pedals fully aft and check that they are locked in position. Hook the control lock's forks over the rudder pedal tubes as shown above. Push down the control stick's leather boot to expose the control stick tube, and push the control stick forward against the control lock.

  • Page 177: Instrument Panel

    DV 20 E AFM Airplane Description 7.4 INSTRUMENT PANEL Figure 7.4 - Instrument Panel NOTE The figure above shows the typical installation position for the equipment. The actual installation may vary due to the approved equipment version. Doc. No. 4.01.15-E Rev.
  • Page 178 DV 20 E AFM Airplane Description Figure 7.5 - Circuit Breaker Panel Page 7 - 14 Rev. 2 22-Mar-2022 Doc. No. 4.01.25-E...
  • Page 179 DV 20 E AFM Airplane Description Figure 7.6 - Circuit Breaker Panel (if OÄM 20-245/b is installed) Doc. No. 4.01.15-E Rev. 2 22-Mar-2022 Page 7 - 15...
  • Page 180 DV 20 E AFM Airplane Description Major Instruments and Controls GDU 620 Display 16 COM #2 Trim Indicator 17 Flap controller Warning / Caution Lights 18 Transponder Backup artificial horizon 19 BATTERY BACKUP Switch Backup airspeed indicator 20 Fuel Pump Test button...

  • Page 181: Landing Gear

    DV 20 E AFM Airplane Description 7.5 LANDING GEAR The landing gear system consists of the two main landing gear wheels mounted to aluminum spring struts and a 60° castering nose wheel. The suspension of the nose wheel is provided by an elastomer spring.
  • Page 182 DV 20 E AFM Airplane Description Figure 7.7 - Brake System Schematic Diagram Page 7 - 18 Rev. 2 22-Mar-2022 Doc. No. 4.01.25-E...
  • Page 183 DV 20 E AFM Airplane Description 7.6 SEATS AND SAFETY HARNESSES To increase passive safety, the seats are constructed using a carbon fiber/Kevlar hybrid material and GFRP. The seats are removable to allow maintenance and inspection of the underlying controls. Covers on the control sticks prevent loose objects from falling into the area of the controls.
  • Page 184 DV 20 E AFM Airplane Description 7.7 CANOPY AND CABIN INTERIOR CAUTION Before starting the engine, the canopy must be closed and latched. The red handles must be moved fully forward. After starting the engine, the canopy must stay in the closed and latched position until the engine is shut down.
  • Page 185 DV 20 E AFM Airplane Description Closing the Canopy from Outside Move both the LH and RH external latching handles in the aft - up direction to the CLOSE position. Opening the Canopy from Outside Move both the LH and RH external latching handles in the Fwd - Down direction to the OPEN position and lift the canopy.
  • Page 186 DV 20 E AFM Airplane Description Heating and Ventilation The cabin heat and defrost system, directs ram air through the coolant radiator and the exhaust heat shroud into the cabin heat valve. The warm air is then directed to the window defrosting vents and to the cabin floor as selected by the Floor/Defrost lever.

  • Page 187: Power Plant

    DV 20 E AFM Airplane Description 7.8 POWER PLANT 7.8.1 ENGINES, GENERAL The DV 20 E has a Rotax 912 iSc3 Sport engine installed, which has the following specifications: - Four cylinder, four-stroke engine with dry sump forced lubrication. - Horizontally opposed construction.

  • Page 188: Propeller

    DV 20 E AFM Airplane Description In case of failure of any generator, the engine provides no more electric power to the airframe. Failure of a generator is indicated by the low voltage light and negative current on the ammeter.

  • Page 189: Operating Controls

    DV 20 E AFM Airplane Description Ground Operation CAUTION Operation on the ground at high RPM should be avoided as far as possible, as the blades could suffer stone damage. For this reason a suitable site for engine runs should be selected, where there are no loose stones or similar items.
  • Page 190 DV 20 E AFM Airplane Description The propeller governor is flanged into the front of the engine. It regulates the supply of engine oil to the propeller. The propeller governor oil circulation is an integral part of the engine oil circulation system. Following a defect in governor or oil system, the blades go to the finest possible pitch (maximum RPM), thus allowing continuation of flight.

  • Page 191: Engine Instruments

    DV 20 E AFM Airplane Description START Button Pressing the START button starts the engine. LANE SELECTOR Switch There is a LANE SELECTOR switch. For normal operation the switch is set to AUTO. The engine is controlled by either LANE A or LANE B. In case of a failure of the active lane the engine controls are switched over to the other lane automatically.
  • Page 192 DV 20 E AFM Airplane Description After successful completion of the internal test procedure the lights are extinguished. In case of an internal fault detected by ECU internal mechanisms the LANE A/B FAIL light is flashing or permanently illuminated depending on the nature of the fault.
  • Page 193 DV 20 E AFM Airplane Description Engine Instrument EMU 912 iS evo Figure 7.9 - EMU Display - Main Page The EMU displays all flight relevant engine parameters on the MAIN page. Engine parameters with operating limitations and caution ranges that are displayed as alphanumeric values are color-coded with green, amber and red.
  • Page 194 DV 20 E AFM Airplane Description Designation Indication Unit Engine RPM 1/min Manifold pressure inHG Oil pressure Oil temperature °C Exhaust gas temperature °C Coolant temperature °C Fuel pressure FUEL Fuel consumption rate ECU voltage Manifold air temperature °C MODE...
  • Page 195 DV 20 E AFM Airplane Description Figure 7.10 - EMU Display - INFO Page Return to main page Page down Page Up ZERO Reset drag indicators Doc. No. 4.01.15-E Rev. 2 22-Mar-2022 Page 7 - 31...

  • Page 196: Fuel System

    DV 20 E AFM Airplane Description 7.8.5 FUEL SYSTEM General Fuel is stored in the fuel tank which is located below the baggage compartment. The fuel is injected with high pressure into the cylinders. The injection nozzles (one per cylinder) are supplied with fuel by the fuel rail. Pressure inside the fuel rail is generated by two independent electric fuel pumps.
  • Page 197 DV 20 E AFM Airplane Description Gascolator Fuel is gravity fed to a gascolator below the tank and then to the electric fuel pump unit. The gascolator acts as a trap for sediment and water that has entered the fuel line from the tank.
  • Page 198 DV 20 E AFM Airplane Description Fuel Shut-Off Valve Closing the fuel shut-off valve located on the aft side of the firewall will cause the engine to stop within a few seconds. CAUTION The fuel shut-off valve should only be closed for emergencies or fuel system maintenance.
  • Page 199 DV 20 E AFM Airplane Description Fuel Quantity Indication A fuel probe measures the fuel quantity in the tank. The indication is provided by the fuel quantity gauge. Information about fuel consumption can be found in Chapter 5 - PERFORMANCE.

  • Page 200: Cooling System

    DV 20 E AFM Airplane Description 7.8.6 COOLING SYSTEM The Rotax 912 iSc3 Sport features liquid cooling of the cylinder heads and ram air cooling of the cylinders. The cooling system of the cylinder heads is a closed circuit with a dispatcher vessel (expansion tank) on top of the engine and an equalizing reservoir (overflow bottle).
  • Page 201 DV 20 E AFM Airplane Description Figure 7.13 - Overflow Bottle Doc. No. 4.01.15-E Rev. 2 22-Mar-2022 Page 7 - 37...

  • Page 202: Oil System

    DV 20 E AFM Airplane Description 7.8.7 OIL SYSTEM The Rotax 912 iSc3 Sport has a dry sump lubrication system. The camshaft driven oil pump has an integrated oil pressure regulator and oil pressure sensor. The oil pump transports the oil from the oil tank through a radiator and the oil filter to the lubrication points of the engine (see Figure 7.14).

  • Page 203: Electrical System

    DV 20 E AFM Airplane Description 7.9 ELECTRICAL SYSTEM Figure 7.15 - Electric System Schematic Doc. No. 4.01.15-E Rev. 2 22-Mar-2022 Page 7 - 39...
  • Page 204 DV 20 E AFM Airplane Description Figure 7.16 - Electrical System Schematic (if OÄM 20-245/b is installed) Page 7 - 40 Rev. 2 22-Mar-2022 Doc. No. 4.01.25-E...

  • Page 205: General

    DV 20 E AFM Airplane Description 7.9.1 GENERAL The DV 20 E has a 14 Volt DC system, which can be sub-divided into: - Power generation - Storage - Distribution - Consumers Consumers The individual consumers (e.g. radio, position lights, etc.) are connected to the appropriate bus via automatic circuit breakers.
  • Page 206 DV 20 E AFM Airplane Description Instrument Lighting With a rotary button (INSTRUMENT) in the LH section of the instrument panel the internal lighting of the instruments is switched on and its brightness is adjusted. Pitot Heating The Pitot probe, which provides measurement for the Pitot-static system, is electrically heated.
  • Page 207 DV 20 E AFM Airplane Description 7.9.2 ENGINE MANAGEMENT SYSTEM / EMS EMS Overview The ROTAX 912 iSc Sport is equipped with an electronic guided dual ignition unit with integrated generator. The ignition unit is easy to maintain and needs (except for start the engine) no external power supply.
  • Page 208 DV 20 E AFM Airplane Description EMS Power Supply The EMS power supply primarily comprises 2 alternators with permanent magnets. It also comprises an external rectifier, voltage stabilizer and overvoltage protection, which are integrated in the FUSE BOX. The two 3-phase A/C current generators (alternators) are physically separated in the engine integrated power supply units.
  • Page 209 DV 20 E AFM Airplane Description Other main functions of the ECU include: Ignition control Fuel injection control Indication of faults and values that are outside operating limits Storing faults Power supply monitoring Additional Power Supply (if OÄM 20-245/b is installed): In addition to the two in the engine integrated alternators, there is an external alternator that supplies power to the aircraft system.
  • Page 210 DV 20 E AFM Airplane Description The Pitot static pressure probe should be protected whenever the airplane is parked to prevent contamination and subsequent malfunction of the airplane systems relying on its proper functioning. NOTE Use only the factory supplied pitot static probe cover with the “Remove before Flight”...
  • Page 211 DV 20 E AFM Airplane Description 7.11 STALL WARNING SYSTEM A stall warning horn, located in the left instrument panel, will operate at a minimum airspeed of 5 kts before a stall. The horn grows louder as the speed approaches the stall speed.
  • Page 212 DV 20 E AFM Airplane Description 7.12 GARMIN G500 INTEGRATED AVIONICS SYSTEM 7.12.1 GENERAL The G500 system consists of: - Garmin Display Unit (GDU) 620 (PFD/MFD). - Garmin Data Computer (GDC) 74A [Air Data Computer (ADC)]. - Garmin Reference System (GRS) 77 [Attitude and Heading Reference System (AHRS)].
  • Page 213 DV 20 E AFM Airplane Description 7.12.3 GRS 77 AHRS The GRS 77 is an attitude and heading reference unit that provides aircraft attitude and flight characteristics information to the GDU 620. The unit contains advanced tilt sensors, accelerometers, and rate sensors. In addition, the GRS 77 interfaces with both the GDC 74A air data computer and the GMU 44 magnetometer.
  • Page 214 DV 20 E AFM Airplane Description Intentionally left blank. Page 7 - 50 Rev. 2 22-Mar-2022 Doc. No. 4.01.25-E...
  • Page 215 Handling, Care, DV 20 E AFM Maintenance CHAPTER 8 AIRPLANE HANDLING, CARE AND MAINTENANCE Page INTRODUCTION ........8-2 AIRPLANE INSPECTION INTERVALS .

  • Page 216: Introduction

    Handling, Care, DV 20 E AFM Maintenance 8.1 INTRODUCTION Chapter 8 contains the manufacturer's recommended procedures for proper ground handling and servicing of the airplane. The Airplane Maintenance Manual (Doc. No. 4.02.25) lists certain inspection and maintenance requirements which must be followed if the airplane is to retain a new plane performance and reliability.

  • Page 217: Airplane Alterations Or Repairs

    Handling, Care, DV 20 E AFM Maintenance 8.3 AIRPLANE ALTERATIONS OR REPAIRS Alterations or repairs to the airplane may be carried out only according to the Airplane Maintenance Manual, Doc. No. 4.02.25, and only by authorized personnel. 8.4 SERVICING 8.4.1 REFUELING WARNING Do not allow fire, sparks or heat near fuel.

  • Page 218: Engine Oil Level Check

    Handling, Care, DV 20 E AFM Maintenance CAUTION Use only approved fuel types given in Chapter 2. 1. Ground the airplane and the fuel supply vehicle electrically at the exhaust tube. 2. Remove the fuel filler cap. Check cap retaining cable for damage.

  • Page 219: Ground Handling / Road Transport

    Handling, Care, DV 20 E AFM Maintenance 8.5 GROUND HANDLING / ROAD TRANSPORT 8.5.1 GROUND HANDLING Towing Forward The airplane is most easily and safely maneuvered by hand with the tow-bar attached to the nose wheel. See Figure 8.1 for installation of tow bar.
  • Page 220 Handling, Care, DV 20 E AFM Maintenance CAUTION The tow bar may only be used for moving the airplane on the ground by hand. After moving the airplane, the tow bar must be removed. NOTE When moving the airplane rearward, the tow bar must be held firmly to prevent abrupt sideward deflection of the nose wheel.

  • Page 221: Parking

    Handling, Care, DV 20 E AFM Maintenance 8.5.2 PARKING For short term parking, the airplane must be positioned into the wind, the parking brake must be engaged, the wing flaps must be in the retracted position and the wheels must be chocked.
  • Page 222 Handling, Care, DV 20 E AFM Maintenance Control Surfaces Gust Lock The primary controls can be blocked by a control surfaces gust lock. It is recommended that the control surfaces gust lock be used when parking outdoors, because otherwise the control surfaces can hit the stops in strong tail wind. This can lead to excessive wear or damage.

  • Page 223: Mooring

    Handling, Care, DV 20 E AFM Maintenance 8.5.3 MOORING Near the lower end of the tail fin of the airplane there is a hole which can be used to tie down the airplane to the ground. Also on each wing near the wing tip, an eyelet with a metric M8 thread can be installed and used as tie-down points.

  • Page 224: Jacking

    Handling, Care, DV 20 E AFM Maintenance 8.5.4 JACKING The airplane can be jacked at the two jackpoints located on the lower side of the center wing's LH and RH root ribs as well as at the tail fin. Figure 8.3 - Jacking Point Locations Page 8 - 10 Rev.

  • Page 225: Cleaning And Care

    Handling, Care, DV 20 E AFM Maintenance 8.6 CLEANING AND CARE CAUTION The airplane must be kept clean. The bright surface prevents the structure from overheating. CAUTION Excessive dirt deteriorates the flight performance. 8.6.1 PAINTED SURFACES The entire surface of the airplane is painted with a white weatherproof two component paint.

  • Page 226: Canopy

    Handling, Care, DV 20 E AFM Maintenance 8.6.2 CANOPY The canopy glass and the rear windows should be cleaned with 'Plexiklar' or any other acrylic glass detergent if available; otherwise use lukewarm water. Final cleaning should be carried out with a clean piece of chamois leather or soft cloth. Never rub or polish dry acrylic glass.
  • Page 227 Handling, Care, DV 20 E AFM Maintenance 8.7 GROUND DE-ICING 1. Remove any snow from the airplane using a soft brush. 2. Put the airplane in a heated hangar or spray deicing fluid onto ice-covered surfaces using a suitable spray bottle.
  • Page 228 Handling, Care, DV 20 E AFM Maintenance Intentionally left blank. Page 8 - 14 Rev. 2 22-Mar-2022 Doc. No. 4.01.25-E...
  • Page 229 DV 20 E AFM Supplements CHAPTER 9 SUPPLEMENTS Page INTRODUCTION ........9-2 LIST OF SUPPLEMENTS .
  • Page 230 DV 20 E AFM 9.1 INTRODUCTION Chapter 9 contains information concerning additional (optional) equipment of the DV 20 E. Unless otherwise stated, the procedures given in the Supplements must be applied in addition to the procedures given in the main part of the Airplane Flight Manual.

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