Даймонд да 40 руководство по летной эксплуатации

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• Page 2: Sep-2004 1

  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 STAR 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 3
  DA 40 AFM Introduction 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 — C Temporary Revisions, C updates of the modification level (Section 1.1),…
• Page 4
  Introduction DA 40 AFM Rev. Chapte Date of Date of Reason Page(s) Approval Date Inserted Signature Revision Approval [approved by Ing. Andreas corrections 26-Sep-2000 09-Oct-2000 Winkler for ACG] 0-2, 0-4 thru 0-7 OÄM 40-060 1-16 (White Wire 2-1, 2-7 thru 2-9,…
• Page 5
  DA 40 AFM Introduction Rev. Chapte Date of Date of Reason Page(s) Approval Date Inserted Signature Revision Approval OÄM 40-067 [approved by (IFR) Ing. Andreas 09 Apr 2001 02 Jul 2001 Winkler for corrections ACG] OÄM 40-061 0-1 thru 0-8…
• Page 6
  Introduction DA 40 AFM Rev. Date of EASA Approv- Date Reason Chapter Page(s) Signature Revision al No. Compliance Inserted [Ing. Andreas type certifi- 0-0, 0-5, 0-6 15 Sep 2004 2004-12326 Winkler for cation in China ACG] MÄM-40- -047, -069, -075, -078,…
• Page 7
  DA 40 AFM Introduction Rev. Date of EASA Approv- Date Reason Chapter Page(s) Signature Revision al No. Compliance Inserted MÄM-40- -176, -227/a, -313, -344, -360/a, -378, -401, -415, Revision No. 8 -428, -446; of the AFM Doc. No. OÄM-40- 6.01.01-E is…
• Page 8
  Introduction DA 40 AFM 0.3 LIST OF EFFECTIVE PAGES Page Date Page Date 15-Sep-2004 01-Dec-2010 0-0a 15-Sep-2004 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 1-10 01-Dec-2010 01-Dec-2010 1-11 01-Dec-2010 0-10 01-Dec-2010…
• Page 9
  DA 40 AFM Introduction Page Date Page Date appr. 2-1 01-Dec-2010 appr. 2-28 01-Dec-2010 appr. 2-29 01-Dec-2010 appr. 2-2 01-Dec-2010 appr. 2-30 01-Dec-2010 appr. 2-3 01-Dec-2010 appr. 2-31 01-Dec-2010 appr. 2-4 01-Dec-2010 appr. 2-32 01-Dec-2010 appr. 2-5 01-Dec-2010 appr. 2-33 01-Dec-2010 appr.
• Page 10
  Introduction DA 40 AFM Page Date Page Date 01-Dec-2010 3-29 01-Dec-2010 3-30 01-Dec-2010 01-Dec-2010 3-31 01-Dec-2010 01-Dec-2010 3-32 01-Dec-2010 01-Dec-2010 3-33 01-Dec-2010 01-Dec-2010 3-34 01-Dec-2010 01-Dec-2010 3-35 01-Dec-2010 01-Dec-2010 3-36 01-Dec-2010 01-Dec-2010 3-37 01-Dec-2010 01-Dec-2010 3-38 01-Dec-2010 3-10 01-Dec-2010 3-39…
• Page 11
  DA 40 AFM Introduction Page Date Page Date 4A-1 01-Dec-2010 4A-28 01-Dec-2010 4A-29 01-Dec-2010 4A-2 01-Dec-2010 4A-30 01-Dec-2010 4A-3 01-Dec-2010 4A-31 01-Dec-2010 4A-4 01-Dec-2010 4A-32 01-Dec-2010 4A-5 01-Dec-2010 4A-33 01-Dec-2010 4A-6 01-Dec-2010 4A-34 01-Dec-2010 4A-7 01-Dec-2010 4A-35 01-Dec-2010 4A-8 01-Dec-2010…
• Page 12
  Introduction DA 40 AFM Page Date Page Date 4B-1 01-Dec-2010 01-Dec-2010 4B-2 01-Dec-2010 01-Dec-2010 4B-3 01-Dec-2010 01-Dec-2010 4B-4 01-Dec-2010 01-Dec-2010 4B-5 01-Dec-2010 01-Dec-2010 4B-6 01-Dec-2010 01-Dec-2010 4B-7 01-Dec-2010 01-Dec-2010 4B-8 01-Dec-2010 01-Dec-2010 4B-9 01-Dec-2010 01-Dec-2010 4B-10 01-Dec-2010 5-10 01-Dec-2010 4B-11…
• Page 13
  DA 40 AFM Introduction Page Date Page Date 01-Dec-2010 6-28 01-Dec-2010 6-29 01-Dec-2010 01-Dec-2010 6-30 01-Dec-2010 01-Dec-2010 6-31 01-Dec-2010 01-Dec-2010 6-32 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 6-10 01-Dec-2010 6-11 01-Dec-2010 6-12 01-Dec-2010 6-13 01-Dec-2010 6-14 01-Dec-2010 6-15 01-Dec-2010 6-16…
• Page 14
  Introduction DA 40 AFM Page Date Page Date 01-Dec-2010 7-28 01-Dec-2010 7-29 01-Dec-2010 01-Dec-2010 7-30 01-Dec-2010 01-Dec-2010 7-31 01-Dec-2010 01-Dec-2010 7-32 01-Dec-2010 01-Dec-2010 7-33 01-Dec-2010 01-Dec-2010 7-34 01-Dec-2010 01-Dec-2010 7-35 01-Dec-2010 01-Dec-2010 7-36 01-Dec-2010 01-Dec-2010 7-37 01-Dec-2010 7-10 01-Dec-2010 7-38…
• Page 15
  DA 40 AFM Introduction Page Date Page Date 7-55 01-Dec-2010 01-Dec-2010 7-56 01-Dec-2010 01-Dec-2010 7-57 01-Dec-2010 01-Dec-2010 7-58 01-Dec-2010 01-Dec-2010 01-Dec-2010 Page Date 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 01-Dec-2010 8-10 01-Dec-2010 8-11 01-Dec-2010 8-12 01-Dec-2010 Doc. # 6.01.01-E Rev.
• Page 16
  Introduction DA 40 AFM 0.4 TABLE OF CONTENTS Chapter GENERAL (a non-approved chapter) ……..1 OPERATING LIMITATIONS (an approved chapter) .

• Page 17: Table Of Contents

  DA 40 AFM General CHAPTER 1 GENERAL Page INTRODUCTION ……..1-2 CERTIFICATION BASIS .

• Page 18: Introduction

  General DA 40 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 JAR-23 requirement.

• Page 19
  DA 40 AFM General Modification Source Installed 9 yes 9 no Door Locking System OÄM 40-081 9 yes 9 no NLG Speedkit OÄM 40-105 9 yes 9 no MLG Speedkit OÄM 40-106 9 yes 9 no Essential Tie Relay Bypass OÄM 40-126…
• Page 20
  General DA 40 AFM CAUTION The DA 40 is a single engine airplane. When the operating limitations and maintenance requirements are complied with, it has the high degree of reliability which is required by the certification basis. Nevertheless, an engine failure is not completely impossible.

• Page 21: Certification Basis

  DA 40 AFM General 1.2 CERTIFICATION BASIS This airplane has been type certified in accordance with the JAA JC/VP procedure. The certification basis is JAR-23, published on 11-Mar-1994. 1.3 WARNINGS, CAUTIONS AND NOTES Special statements in the Airplane Flight Manual concerning the safety or operation of…

• Page 22: Dimensions

  General DA 40 AFM 1.4 DIMENSIONS Overall Dimensions Span appr. 11.94 m appr. 39 ft 2 in Length appr. 8.01 m appr. 26 ft 3 in Height appr. 1.97 m appr. 6 ft 6 in Wing Airfoil Wortmann FX 63-137/20 — W4 Wing Area appr.

• Page 23
  DA 40 AFM General Vertical Tail Area appr. 1.60 m² appr. 17.2 sq.ft. Rudder area appr. 0.47 m² appr. 5.1 sq.ft. Landing Gear Track appr. 2.97 m appr. 9 ft 9 in Wheelbase appr. 1.68 m appr. 5 ft 6 in Nose wheel 5.00-5;…

• Page 24: Definitions And Abbreviations

  General DA 40 AFM 1.5 DEFINITIONS AND ABBREVIATIONS (a) Airspeeds CAS: Calibrated Airspeed. Indicated airspeed, corrected for installation and instrument errors. CAS equals TAS at standard atmospheric conditions at MSL. IAS: Indicated Airspeed as shown on an airspeed indicator. KCAS: CAS in knots.

• Page 25
  DA 40 AFM General (b) Meteorological Terms ISA: International Standard Atmosphere. Conditions at which air is identified as an ideal dry gas. The temperature at mean sea level is 15 EC (59 °F), air pressure at MSL is 1013.25 hPa (29.92 inHg); the temperature gradient up to the altitude at which the temperature reaches -56.5 EC (-69.7 °F) is -0.0065 EC/m (-0.00357 °F/ft), and…
• Page 26
  General DA 40 AFM (c) Flight Performance and Flight Planning Demonstrated Crosswind Component: The speed of the crosswind component at which adequate maneuverability for take-off and landing has been demonstrated during type certification. MET: Weather, weather advice. NAV: Navigation, route planning.

• Page 27: Doc. # 6.01.01-E Rev. 8 01-Dec

  DA 40 AFM General Usable Fuel: The quantity of fuel available for flight planning. Unusable Fuel: The quantity of fuel remaining in the tank which cannot be used for flight. Empty Mass: The mass of the airplane including unusable fuel, all operating consumables and the maximum quantity of oil.

• Page 28
  General DA 40 AFM (f) Designation of the Circuit Breakers on the Instrument Panel Asymmetric Instrument Panel (Circuit Breakers Right Hand) AVIONICS: Automatic Direction Finder AUDIO Audio Panel / Intercom AUTOPILOT Autopilot AVIONIC BUS Avionic Bus Distance Measuring Equipment ESSENTIAL AVIONIC Essential Avionic Bus…
• Page 29
  DA 40 AFM General LIGHTING: FLOOD Flood Light INST. Instrument Lights LANDING Landing Light POSITION Position Lights STROBE Strobe Light (=Anti Collision Light = ACL) TAXI/MAP Taxi Light/Map Light SYSTEMS: ANNUN. Annunciator Panel Directional Gyro FAN/OAT Fan/Outside Air Temperature Indicator…
• Page 30
  General DA 40 AFM Symmetric Instrument Panel (Circuit Breakers Bottom Side) MAIN BUS: ALT. Alternator ALT. CONT. Alternator Control ALT. PROT. Alternator Protection AV. BUS Avionic Bus Directional Gyro FAN/OAT Fan/Outside Air Temperature Indicator FUEL PUMP Fuel Pump IGNITION Ignition INST.
• Page 31
  DA 40 AFM General MAIN AV. BUS (Main Avionic Bus): Automatic Direction Finder AUDIO Audio Panel / Intercom AUTO PILOT Autopilot COM2 Communication #2 COM/NAV2 Communication / Navigation #2 Distance Measuring Equipment GPS2 Global Positioning System #2 GPS/NAV2 Global Positioning System/Navigation #2…
• Page 32
  General DA 40 AFM ESSENTIAL BUS: ANNUN. Annunciator Panel BATT. Battery ESS. AV. Essential Avionic-Bus ESS TIE Bus Interconnection FLAPS Flaps FLOOD Flood Light HORIZON Artificial Horizon (Attitude Gyro) INST. 1 Engine Instrument VM 1000 LANDING Landing Light MASTER CONTROL…
• Page 33
  DA 40 AFM General (g) Equipment ELT: Emergency Locator Transmitter. (h) Design Change Advisories MÄM: Mandatory Design Change Advisory. OÄM: Optional Design Change Advisory. (i) Miscellaneous ACG: Austro Control GmbH (formerly BAZ, Federal Office of Civil Aviation). ATC: Air Traffic Control.

• Page 34: Units Of Measurement

  General DA 40 AFM 1.6 UNITS OF MEASUREMENT 1.6.1 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 35
  DA 40 AFM General Dimension SI-Units US Units Conversion Intensity of ampères electric current Electric [Ah] ampère-hours charge (battery capacity) Electric volts potential Time [sec] seconds Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 1 — 19…

• Page 36: Conversion Chart Liters / Us Gallons

  General DA 40 AFM 1.6.2 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 26.4 106.0 29.1 113.6 31.7…

• Page 37: Three-View Drawing

  DA 40 AFM General 1.7 THREE-VIEW DRAWING Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 1 — 21…

• Page 38: Source Documentation

  General DA 40 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 39: Propeller

  DA 40 AFM General 1.8.2 PROPELLER Address: mt-Propeller Airport Straubing Wallmühle D-94348 ATTING GERMANY Phone: +49-9429-9409-0 E-mail: sales@mt-propeller.com Webpage: 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 ENGINE INSTRUMENTS…

• Page 40: Ignition Control Unit

  General DA 40 AFM 1.8.4 IGNITION CONTROL UNIT The electronic ignition control unit LASAR is optional equipment. Address: UNISON Industries 7575 Baymeadows Way JACKSONVILLE, FL 32256 Phone: +1-904-739-4066 Webpage: www.unisonindustries.com Documents: L-1502 LASAR Installation, Operation, and Troubleshooting Manual Page 1 — 24 Rev.

• Page 41: Operating Limitations

  Operating DA 40 AFM Limitations CHAPTER 2 OPERATING LIMITATIONS Page INTRODUCTION ……..2-2 AIRSPEED .

• Page 42: Introduction

  Operating DA 40 AFM Limitations 2.1 INTRODUCTION Chapter 2 of this Airplane Flight Manual includes operating limitations, instrument markings, and placards necessary for safe operation of the airplane, its power-plant, standard systems and standard equipment. The limitations included in this Chapter are approved.

• Page 43: Airspeed

  Operating DA 40 AFM Limitations 2.2 AIRSPEED Airspeed Remarks Maneuvering 108 KIAS Do not make full or abrupt speed control surface movement (above 980 kg / 2161 lb above this speed. up to 1150 kg / 2535 lb) 94 KIAS…

• Page 44: Airspeed Indicator Markings

  Operating DA 40 AFM Limitations 2.3 AIRSPEED INDICATOR MARKINGS Marking Significance White arc 49 KIAS — 91 KIAS Operating range with flaps fully extended. Green arc 52 KIAS — 129 KIAS Normal operating range. Yellow arc 129 KIAS — 178 KIAS ‘Caution’…

• Page 45: Power-Plant Limitations

  Operating DA 40 AFM Limitations 2.4 POWER-PLANT LIMITATIONS a) Engine manufacturer : Textron Lycoming b) Engine designation : IO-360 M1-A c) RPM limitations Max. take-off RPM : 2700 RPM Max. continuous RPM : 2400 RPM d) Manifold pressure limitations Maximum…

• Page 46
  Operating DA 40 AFM Limitations k) Propeller designation : MTV-12-B/180-17 or MTV-12-B/180-17f l) Propeller diameter : 1.80 m (+ 0 mm, — 50 mm) 5 ft 10.9 in (+ 0.0 in, — 2.0 in) m) Propeller pitch angle (0.75 R) : 10.5° to 30°…

• Page 47: Engine Instrument Markings

  Operating DA 40 AFM Limitations 2.5 ENGINE INSTRUMENT MARKINGS Engine instrument markings and their color code significance are shown in the table below: NOTE When an indication lies in the upper or lower prohibited range, the numerical indication will begin flashing as well.

• Page 48
  Operating DA 40 AFM Limitations Green Yellow Yellow arc/bar arc/bar arc/bar arc/bar arc/bar Indi- cation lower normal upper caution caution prohibited operating prohibited range range range range range Fuel 0 — 15 US gal quantity, 0 US gal Standard 0 — 17 US gal…

• Page 49: Warning, Caution And Status Lights

  Operating DA 40 AFM Limitations 2.6 WARNING, CAUTION AND STATUS LIGHTS The following tables show the color and significance of the warning, caution and status lights on the annunciator panel. There are two variants of the annunciator panel, ‘DAI’ and ‘White Wire’ (see Section 7.11).

• Page 50
  Operating DA 40 AFM Limitations Color and Significance of the Caution Lights (Amber) Caution Lights (Amber) Cause Variant Variant Meaning ‘DAI’ ‘White Wire’ Fuel quantity Fuel quantity in the left tank L FUEL left tank less than 3 US gal (±1 US gal)

• Page 51: Mass (Weight)

  Operating DA 40 AFM Limitations 2.7 MASS (WEIGHT) Maximum take-off mass (Normal Category) : 1150 kg 2535 lb if MÄM 40-227 is carried out : 1200 kg 2646 lb Maximum take-off mass (Utility Category) : 980 kg 2161 lb Maximum landing mass…

• Page 52
  Operating DA 40 AFM Limitations NOTE In some countries the beginning of a flight is defined by starting the engine. In those countries a maximum ramp mass 4 kg (9 lb) above the maximum take-off mass is approved. At the time of lift-off the maximum permitted take-off mass must not be exceeded.

• Page 53: Center Of Gravity

  Operating DA 40 AFM 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 upper surface of a 600:31 wedge which is placed on top of the rear fuselage in front of the vertical stabilizer.

• Page 54: Approved Maneuvers

  Operating DA 40 AFM Limitations 2.9 APPROVED MANEUVERS The airplane is certified in the Normal Category and in the Utility Category in accordance with JAR-23. Approved Maneuvers a) Normal Category: All normal flight maneuvers; Stalling (with the exception of dynamic stalling); and Lazy Eights, Chandelles, as well as steep turns and similar maneuvers, in which an angle of bank of not more than 60°…

• Page 55
  Operating DA 40 AFM Limitations b) Utility Category: All normal flight maneuvers; Stalling (with the exception of dynamic stalling); and Lazy Eights, Chandelles, as well as steep turns and similar maneuvers, in which an angle of bank of not more than 90° is attained.

• Page 56: Maneuvering Load Factors

  Operating DA 40 AFM Limitations 2.10 MANEUVERING LOAD FACTORS Table of maximum structural load factors: Normal Category With Flaps in T/O at v at v or LDG Position Positive Negative -1.52 Utility Category With Flaps in T/O at v at v…

• Page 57: Operating Altitude

  Operating DA 40 AFM Limitations 2.11 OPERATING ALTITUDE The maximum demonstrated operating altitude is 16,400 ft (5,000 m). The maximum approved operating altitude for US registered airplanes is 14,000 ft MSL unless an approved supplemental oxygen system is installed. 2.12 FLIGHT CREW…

• Page 58: Kinds Of Operation

  Operating DA 40 AFM Limitations 2.13 KINDS OF OPERATION Provided that national operational requirements are met, the following kinds of operation are approved: Daytime flights according to Visual Flight Rules (VFR). With the appropriate equipment: night flights according to Visual Flight Rules (NVFR).

• Page 59
  Operating DA 40 AFM Limitations Minimum Operational Equipment (Serviceable) For Daytime In Addition In addition VFR Flights for Night VFR Flights for IFR Flights Flight and * Airspeed * Vertical speed indicator (VSI) * Second VHF Naviga- indicator radio (COM)
• Page 60
  Operating DA 40 AFM Limitations Minimum Operational Equipment (Serviceable) For Daytime In Addition In addition VFR Flights for Night VFR Flights for IFR Flights Lighting * Position lights * Strobe lights (anti collision lights) * Landing light * Instrument lighting…
• Page 61
  Operating DA 40 AFM Limitations NOTE A list of approved equipment can be found in Chapter 6. NOTE For the upgrade of an airplane for Night VFR or IFR operation it is not sufficient to install the required equipment. The retrofit…

• Page 62: Fuel

  Operating DA 40 AFM Limitations 2.14 FUEL Fuel Grade AVGAS 100LL Fuel Quantity a) Standard Tank: Total fuel quantity : 2 x 20.6 US gal (app. 2 x 78 liter) Unusable fuel : 2 x 0.5 US gal (app. 2 x 2 liter) Max.

• Page 63
  Operating DA 40 AFM Limitations b) Long Range Tank (if installed): Total fuel quantity : 2 x 25.5 US gal (app. 2 x 96.5 liter) Unusable fuel : 2 x 0.5 US gal (app. 2 x 2 liter) Max. indicated fuel quantity : 16 US gal (app.

• Page 64: Limitation Placards

  Operating DA 40 AFM Limitations 2.15 LIMITATION PLACARDS All limitation placards are shown below. A list of all placards is included in the Airplane Maintenance Manual (Doc. No. 6.02.01), Chapter 11. On the Instrument Panel: If MÄM 40-227 is not carried out:…

• Page 65
  Operating DA 40 AFM Limitations If MÄM 40-227 is carried out: Maneuvering Speed: = 111 KIAS (above 1036 up to 1200 kg, above 2284 up to 2646 lb) = 94 KIAS (780 to 1036 kg, 1720 to 2284 lb) The airplane may only be operated in accordance with the Airplane Flight Manual.
• Page 66
  Operating DA 40 AFM Limitations Next to the Fuel Quantity Indication: a) Standard Tank: Up to serial number 40.054: max. indicated fuel quantity: 15 US gal left and right tank max. 10 US gal difference For use of max. tank capacity see AFM Serial number 40.055 and subsequent:…
• Page 67
  Operating DA 40 AFM Limitations On the Fuel Tank Selector: a) Standard Tank: b) Long Range Tank (if installed): 25 US gal. 25 US gal. 94 l 94 l EASA Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 2 — 27…
• Page 68
  Operating DA 40 AFM Limitations In the Cowling, on the Door for the Oil Filler Neck: 1 qt = 0.95 liters SAE 15W50 ashless dispersant aviation grade oil (SAE Standard J-1899) or see AFM Chapter 2 VFR Min./Max.: 4/8 qts IFR Min./Max.: 6/8 qts…

• Page 69: Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page

  Operating DA 40 AFM Limitations In the Cockpit, on the Left Fuselage Sidewall: (if alternate static valve is installed): Next to the Baggage Compartment: a) Standard Baggage Compartment: max. 30 kg / 66 lbs EASA Doc. # 6.01.01-E Rev. 8…

• Page 70
  Operating DA 40 AFM Limitations b) Extended Baggage Compartment (OÄM 40-163, if installed): FORWARD BAGGAGE AFT BAGGAGE COMPARTMENT COMPARTMENT MAX. 45 kg [100 lb] MAX. 18 kg [40 lb] ARM: 3.89 m [153.1″] ARM: 4.54 m [178.7″] MAX. BAGGAGE TOTAL 45 kg [100 lb] MAX.
• Page 71
  Operating DA 40 AFM Limitations Beside the Door Locking Device (OÄM 40-081, if installed): EMERGENCY EXIT: The keylock must be unlocked during flight! Above the NAV #2 CDI (OÄM 40-206, if installed): NAV No. 2 not approved for precision approaches EASA Doc.

• Page 72: Other Limitations

  Operating DA 40 AFM Limitations 2.16 OTHER LIMITATIONS 2.16.1 TEMPERATURE The airplane may only be operated when its temperature prior to operation is not less than -40 °C (-40 °F) and not higher than 54 °C (129 °F). CAUTION For cold weather starting of the engine refer to the latest instructions given by the engine manufacturer.

• Page 73: Door Locking Device

  Operating DA 40 AFM Limitations for the attitude gyro (artificial horizon) and flood light for another 1.5 hours when the emergency power pack (if installed) is used. 2.16.5 DOOR LOCKING DEVICE The canopy and the passenger door must not be blocked by the door locking device during operation of the airplane.

• Page 74
  Operating DA 40 AFM Limitations Intentionally left blank. EASA Page 2 — 34 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E approved…

• Page 75: Emergency Procedures

  Emergency DA 40 AFM Procedures CHAPTER 3 EMERGENCY PROCEDURES Page INTRODUCTION ……..3-3 3.1.1 GENERAL .

• Page 76
  Emergency DA 40 AFM Procedures OTHER EMERGENCIES ……. 3-34 3.7.1 ICING ……… 3-34 3.7.2 FAILURES IN THE ELECTRICAL SYSTEM .

• Page 77: Introduction

  Emergency DA 40 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 78: Certain Airspeeds In Emergencies

  Emergency DA 40 AFM Procedures 3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES Flight Mass 850 kg 1000 kg 1150 kg 1200 kg 2646 lb Event 1874 lb 2205 lb 2535 lb Engine failure after take-off 59 KIAS 66 KIAS 72 KIAS 74 KIAS…

• Page 79: Engine Problems

  Emergency DA 40 AFM Procedures 3.2 ENGINE PROBLEMS 3.2.1 ENGINE PROBLEMS ON THE GROUND 1. Throttle ……IDLE 2.

• Page 80: Engine Problems During Take-Off

  Emergency DA 40 AFM Procedures 3.2.2 ENGINE PROBLEMS DURING TAKE-OFF (a) Take-Off Can Still Be Aborted (Sufficient Runway Length Available) Land Straight Ahead: 1. Throttle ……IDLE On the Ground: 2.

• Page 81
  Emergency DA 40 AFM Procedures (b) Take-Off Can No Longer Be Aborted 1. Airspeed ……74 KIAS (1200 kg, 2646 lb)

• Page 82: Engine Problems In Flight

  Emergency DA 40 AFM Procedures 3.2.3 ENGINE PROBLEMS IN FLIGHT (a) Engine Running Roughly WARNING An engine which is running very roughly can lead to the loss of the propeller. If the engine is running roughly operation should only be continued if there is no other alternative.

• Page 83
  Emergency DA 40 AFM Procedures 11. Ignition circuit breaker (IGN) … . pull (only if the electronic ignition control unit is installed); if rough running is cleared by doing this, the…
• Page 84
  Emergency DA 40 AFM Procedures (b) Loss of Oil Pressure 1. Check oil pressure warning light and oil pressure indicator. 2. Check oil temperature. If the oil pressure indication drops below the green sector and the oil temperature is normal (oil pressure warning light does not illuminate or flash): * Monitor the oil pressure warning light: it is probable that the oil pressure indication is defective.
• Page 85
  Emergency DA 40 AFM Procedures (c) High Oil Pressure Check oil temperature. * If the oil temperature is normal, it is probable that the fault lies in the oil pressure indication, which should thus be ignored (the airplane should be serviced).
• Page 86
  Emergency DA 40 AFM Procedures (e) High Cylinder Head Temperature Cylinder head temperature in yellow sector or above: 1. Check mixture setting, enrich mixture if necessary. 2. Check oil temperature. * If the oil temperature is also high: Check oil pressure. If the oil pressure is low, proceed as in 3.2.3 (b) — LOSS OF OIL PRESSURE.
• Page 87
  Emergency DA 40 AFM Procedures (f) High RPM RPM moves on its own into the yellow sector, or is in the red sector: 1. Check friction adjuster for throttle quadrant. 2. Check oil pressure: Following a loss of oil or oil pressure, the propeller governor sets a high RPM.
• Page 88
  Emergency DA 40 AFM Procedures (g) Loss of RPM 1. Electrical fuel pump ….check ON 2. Fuel tank selector ….check 3.
• Page 89
  Emergency DA 40 AFM Procedures (h) High Fuel Flow Fuel flow in the red sector: 1. Electrical fuel pump ….ON 2. Fuel pressure ….. . . check after 10 — 15 sec: * If the fuel pressure is low, refer to 3.2.3 (i) — LOW FUEL PRESSURE WITH…
• Page 90
  Emergency DA 40 AFM Procedures (i) Low Fuel Pressure with the Electrical Fuel Pump Set to ON Fuel pressure warning light illuminates, or fuel pressure indication below the green sector: 1. Fuel flow ……check: * If the fuel flow is high, there is possibly a leak (between the injection system and the injectors).

• Page 91: Restarting The Engine With Windmilling Propeller

  Emergency DA 40 AFM Procedures 3.2.4 RESTARTING THE ENGINE WITH WINDMILLING PROPELLER NOTE Restarting the engine is possible at all airspeeds above 70 KIAS up to v and up to the maximum demonstrated operating altitude. NOTE As long as an airspeed of at least 65 KIAS is maintained, and there is no major engine failure, the propeller will continue to windmill.

• Page 92: Defective Engine Controls

  Emergency DA 40 AFM Procedures 3.2.5 DEFECTIVE ENGINE CONTROLS Defective Mixture Control Cable (a) Flight and Landing: 1. Maintain altitude to the nearest airfield. 2. During descent, test the reaction of the engine to a higher power setting. A lean mixture can lead to engine roughness and a loss of power. The landing approach must be planned accordingly.

• Page 93
  Emergency DA 40 AFM Procedures Defective Throttle Control Cable (a) Sufficient Engine Power Available to Continue Flight: 1. Approach nearest airfield, control engine power with RPM lever. 2. Perform landing with shut-down engine. (b) No Sufficient Engine Power Available to Continue Flight: 1.

• Page 94: Restarting The Engine With Stationary Propeller

  Emergency DA 40 AFM Procedures 3.2.6 RESTARTING THE ENGINE WITH STATIONARY PROPELLER NOTE Restarting the engine is possible at all airspeeds above 80 KIAS up to v and up to the maximum demonstrated operating altitude. 1. Airspeed ……80 KIAS 2.

• Page 95
  Emergency DA 40 AFM Procedures CAUTION Engine restart following an engine fire should only be attempted if it is unlikely that a safe emergency landing can be made. It must be expected that engine restart is impossible after an engine fire.

• Page 96: Smoke And Fire

  Emergency DA 40 AFM Procedures 3.3 SMOKE AND FIRE 3.3.1 SMOKE AND FIRE ON THE GROUND (a) Engine Fire When Starting on the Ground 1. Fuel tank selector ….OFF 2.

• Page 97
  Emergency DA 40 AFM Procedures (b) Electrical Fire with Smoke on the Ground 1. Master switch (ALT/BAT) ….OFF If the Engine is Running: 2. Throttle ……IDLE 3.

• Page 98: Smoke And Fire On The Ground

  Emergency DA 40 AFM Procedures 3.3.2 SMOKE AND FIRE DURING TAKE-OFF (a) If Take-Off Can Still Be Aborted 1. Throttle ……IDLE 2.

• Page 99
  Emergency DA 40 AFM Procedures After Climbing to a Height From Which the Selected Landing Area Can Be Reached Safely: 4. Fuel tank selector ….OFF 5.

• Page 100: Smoke And Fire In Flight

  Emergency DA 40 AFM Procedures 3.3.3 SMOKE AND FIRE IN FLIGHT CAUTION In the event of smoke or fire, prepare to land the airplane without delay while completing fire suppression and/or smoke evacuation procedures. If it cannot be visually verified that…

• Page 101
  Emergency DA 40 AFM Procedures (b) Electrical Fire with Smoke in Flight 1. Emergency switch ….ON if installed 2. Master switch (ALT/BAT) ….OFF 3.

• Page 102: Gliding

  Emergency DA 40 AFM Procedures 3.4 GLIDING 1. Flaps ……UP 2.

• Page 103: Emergency Landings

  Emergency DA 40 AFM Procedures 3.5 EMERGENCY LANDINGS 3.5.1 EMERGENCY LANDING WITH ENGINE OFF 1. Select suitable landing area. If no level landing area is available, a landing on an upward slope should be sought. 2. Consider wind. 3. Approach: If possible, fly along a short-cut rectangular circuit.

• Page 104
  Emergency DA 40 AFM Procedures CAUTION If sufficient time is remaining, the risk of fire in the event of a collision with obstacles can be reduced as follows: — Ignition switch ….OFF — Master switch (ALT/BAT) .

• Page 105: Landing With A Defective Tire On The Main Landing

  Emergency DA 40 AFM Procedures 3.5.2 LANDING WITH A DEFECTIVE TIRE ON THE MAIN LANDING GEAR CAUTION A defective (e.g. burst) tire is not usually easy to detect. The damage normally occurs during take-off or landing, and is hardly noticeable during fast taxiing. It is only during the roll-out after landing or at lower taxiing speeds that a tendency to swerve occurs.

• Page 106: Landing With Defective Brakes

  Emergency DA 40 AFM Procedures 3.5.3 LANDING WITH DEFECTIVE BRAKES In general, a landing on grass is recommended in order to reduce the landing run by virtue of the greater rolling resistance. CAUTION If sufficient time is remaining, the risk of fire in the event of a collision can be reduced as follows: — Fuel tank selector .

• Page 107: Recovery From An Unintentional Spin

  Emergency DA 40 AFM Procedures 3.6 RECOVERY FROM AN UNINTENTIONAL SPIN CAUTION Steps 1 to 4 must be carried out immediately and simultaneously. 1. Throttle ……IDLE 2.

• Page 108: Other Emergencies

  Emergency DA 40 AFM Procedures 3.7 OTHER EMERGENCIES 3.7.1 ICING Unintentional Flight Into Icing Conditions 1. Leave the icing area (by changing altitude or turning back, in order to reach zones with a higher ambient temperature). 2. Pitot heating ……ON 3.

• Page 109: Failures In The Electrical System

  Emergency DA 40 AFM Procedures 3.7.2 FAILURES IN THE ELECTRICAL SYSTEM (a) Complete Failure of the Electrical System Due to the strong mechanical design as well as due to the required check of the system during scheduled inspections, a total failure of the electrical system is extremely unlikely.

• Page 110
  Emergency DA 40 AFM Procedures (b) Alternator Failure An alternator failure is indicated by an illuminated or flashing alternator warning light (ALT or ALTERNATOR) on the annunciator panel and a flashing ammeter on the Vision Microsystems VM 1000 engine instrument.
• Page 111
  Emergency DA 40 AFM Procedures These items of equipment can be supplied with power by the battery for at least 30 minutes. Economical use, in particular of the Pitot heating, and switching off equipment that is not needed extends the time during which the other equipment remains available.
• Page 112
  Emergency DA 40 AFM Procedures (c) Starter Malfunction If the starter does not disengage from the engine after starting (starter warning light (START) on the annunciator panel remains illuminated or flashing after the engine has started): 1. Throttle ……IDLE 2.
• Page 113
  The DA 40 may be equipped with a CO detector (optional equipment, OÄM 40-253). If the visual alert annunciator illuminates in flight, press the TEST/RESET button. If the alert…

• Page 114: Door’-Warning Light On

  Emergency DA 40 AFM Procedures 3.7.4 ‘DOOR’-WARNING LIGHT ON 1. Airspeed ……reduce immediately 2.

• Page 115: Emergency Exit

  Emergency DA 40 AFM Procedures 3.7.5 EMERGENCY EXIT In case of a roll-over of the airplane on ground, it can be evacuated through the rear door. For this purpose release the front hinge of the rear door. The function is displayed on a placard next to the hinge.

• Page 116
  Emergency DA 40 AFM Procedures Intentionally left blank. Page 3 — 42 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E…
• Page 117
  Normal Operating DA 40 AFM Procedures CHAPTER 4A NORMAL OPERATING PROCEDURES Page 4A.1 INTRODUCTION ……..4A-2 4A.2 AIRSPEEDS FOR NORMAL OPERATING PROCEDURES .

• Page 118: Introduction

  Normal Operating DA 40 AFM Procedures 4A.1 INTRODUCTION Chapter 4A contains checklists and describes extended procedures for the normal operation of the airplane. 4A.2 AIRSPEEDS FOR NORMAL OPERATING PROCEDURES 850 kg 1000 kg 1150 kg Flight Mass 1200 kg Event…

• Page 119: Checklists For Normal Operating Procedures

  Normal Operating DA 40 AFM Procedures 4A.3 CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4A.3.1 PRE-FLIGHT INSPECTION I. Cabin Check a) MET, NAV, mass & CG ….flight planning completed b) Airplane documents .

• Page 120
  Normal Operating DA 40 AFM Procedures NOTE Standard Tank: Depending on the type of fuel probes installed, the indicator can read a maximum of 15 US gal or 17 US gal (refer to Section 7.10 for details). When the fuel quantity indicator…
• Page 121
  Normal Operating DA 40 AFM Procedures n) Position lights, strobe lights (ACLs) ..check o) Master switch (BAT) ….OFF p) Check for loose items .
• Page 122
  Normal Operating DA 40 AFM Procedures 1. Left Main Landing Gear: a) Landing gear strut ….. visual inspection b) Strut fairing (if installed) ….visual inspection c) Wheel fairing .
• Page 123
  Normal Operating DA 40 AFM Procedures i) 2 stall strips on wing ….visual inspection j) Pitot probe ……clean, orifices open k) Landing/taxi light .
• Page 124
  Normal Operating DA 40 AFM Procedures 5. Fuselage, Right Side: a) Fuselage skin ……visual inspection b) Window ……visual inspection c) Canopy, right side .
• Page 125
  Normal Operating DA 40 AFM Procedures 7. Right Main Landing Gear: a) Landing gear strut ….. visual inspection b) Strut fairing (if installed) ….visual inspection c) Wheel fairing .
• Page 126
  Normal Operating DA 40 AFM Procedures f) Nose landing gear ….. visual inspection g) Tire and wheel ……visual inspection h) Slip marks .

• Page 127: 3.1 Pre-Flight Inspection

  Normal Operating DA 40 AFM Procedures 4A.3.2 BEFORE STARTING ENGINE 1. Pre-flight inspection ….complete 2. Rudder pedals ….. . . adjusted 3.

• Page 128
  Normal Operating DA 40 AFM Procedures 17. Alternate air ……CLOSED 18. Alternate static valve ….CLOSED, if installed 19.

• Page 129: 3.3 Starting Engine

  Normal Operating DA 40 AFM Procedures 4A.3.3 STARTING ENGINE (a) Cold Engine 1. Strobe light (ACL) ….ON 2. Electrical fuel pump ….ON, note pump noise (= functional check of pump) 3.

• Page 130
  Normal Operating DA 40 AFM Procedures CAUTION The use of an external pre-heater and external power source is recommended whenever possible, in particular at ambient temperatures below 0 °C (32 °F), to reduce wear and abuse to the engine and electrical system. Refer to Section 4B.8 — STARTING THE ENGINE WITH EXTERNAL POWER.
• Page 131
  Normal Operating DA 40 AFM Procedures (b) Warm Engine 1. Strobe light (ACL) ….ON 2. Electrical fuel pump ….ON, note pump noise and fuel pressure increase 3.
• Page 132
  Normal Operating DA 40 AFM Procedures When Engine Fires: 6. Mixture control lever ….rapidly move to RICH 7. Oil pressure ……green sector within 15 sec…
• Page 133
  Normal Operating DA 40 AFM Procedures (c) Engine Will Not Start After Injection (“Flooded Engine”) 1. Strobe light (ACL) ….ON 2.
• Page 134
  Normal Operating DA 40 AFM Procedures When Engine Fires: 7. Mixture control lever ….rapidly move to RICH 8. Oil pressure ……green sector within 15 sec…

• Page 135: 3.4 Before Taxiing

  Normal Operating DA 40 AFM Procedures 4A.3.4 BEFORE TAXIING 1. Avionics Master switch ….ON 2. Electrical equipment ….ON as required 3.

• Page 136: 3.5 Taxiing

  Normal Operating DA 40 AFM Procedures 4A.3.5 TAXIING 1. Parking brake ……release 2. Brakes ……test on moving off 3.

• Page 137
  Normal Operating DA 40 AFM Procedures Remedy: For about 1 to 2 minutes, or until the engine settles, run at a speed of 1800 to 2000 RPM. Oil and cylinder head temperatures must stay within limits. Pull throttle back to IDLE to confirm smooth running.

• Page 138: 3.6 Before Take-Off

  Normal Operating DA 40 AFM Procedures 4A.3.6 BEFORE TAKE-OFF CAUTION Before take-off, the engine must run on each tank for at least 1 minute at 1500 RPM. 1. Position airplane into wind if possible 2. Parking brake ……set 3.

• Page 139
  Normal Operating DA 40 AFM Procedures 10. Fuel pressure indicator ….check (approx. 14 — 35 PSI) 11. Electrical fuel pump ….ON 12.
• Page 140
  Normal Operating DA 40 AFM Procedures CAUTION The lack of an RPM drop suggests a faulty grounding or incorrect ignition timing. In case of doubt the magneto check can be repeated with a leaner mixture, in order to confirm a problem.

• Page 141: 3.7 Take-Off

  Normal Operating DA 40 AFM Procedures 4A.3.7 TAKE-OFF Normal Take-Off Procedure 1. Transponder ……ON/ALT 2. RPM lever ……check HIGH RPM 3.

• Page 142
  Normal Operating DA 40 AFM Procedures 7. Airspeed ……67 KIAS (1200 kg, 2646 lb)

• Page 143: 3.8 Climb

  Normal Operating DA 40 AFM Procedures 4A.3.8 CLIMB Procedure for Best Rate of Climb 1. Flaps ……T/O 2.

• Page 144
  Normal Operating DA 40 AFM Procedures Cruise Climb 1. Flaps ……UP 2.

• Page 145: 3.9 Cruise

  Normal Operating DA 40 AFM Procedures 4A.3.9 CRUISE 1. Flaps ……UP 2.

• Page 146
  Normal Operating DA 40 AFM Procedures 5. Trim ……. as required 6.
• Page 147
  Normal Operating DA 40 AFM Procedures 4A.3.10 MIXTURE ADJUSTMENT CAUTION The maximum permissible cylinder head temperature (500 °F (260 °C)) must never be exceeded. The mixture control lever should always be moved slowly. Before selecting a higher power setting the mixture control lever should, on each occasion, be moved slowly to fully RICH.
• Page 148
  Normal Operating DA 40 AFM Procedures Best Power Mixture The mixture can be set for maximum performance at all power settings. The mixture should first be set as for ‘best economy’. The mixture should then be enriched until the exhaust gas temperature is approximately 100 °F (55 °C) lower.

• Page 149: 3.11 Descent

  Normal Operating DA 40 AFM Procedures 4A.3.11 DESCENT 1. Mixture control lever ….adjust as required for the altitude, operate slowly 2. RPM lever ……1800 — 2400 RPM 3.

• Page 150: 3.12 Landing Approach

  Normal Operating DA 40 AFM Procedures 4A.3.12 LANDING APPROACH 1. Fuel selector ……fullest tank 2. Electrical fuel pump ….ON 3.

• Page 151
  Normal Operating DA 40 AFM Procedures NOTE In case of airplanes with a maximum landing mass less than the maximum permitted flight mass, a landing with a higher mass constitutes an abnormal operating procedure. Refer to Sections 2.7 — MASS (WEIGHT) and 4B.7 — LANDING WITH HIGH LANDING MASS.

• Page 152: 3.13 Go-Around

  Normal Operating DA 40 AFM Procedures 4A.3.13 GO-AROUND 1. Throttle ……MAX PWR 2.

• Page 153: 3.14 After Landing

  Normal Operating DA 40 AFM Procedures 4A.3.14 AFTER LANDING 1. Throttle ……IDLE 2.

• Page 154: 3.15 Engine Shut-Down

  Normal Operating DA 40 AFM Procedures 4A.3.15 ENGINE SHUT-DOWN 1. Parking brake ……set 2. Engine instruments ….check 3.

• Page 155: 3.16 Post-Flight Inspection

  Normal Operating DA 40 AFM Procedures 4A.3.16 POST-FLIGHT INSPECTION 1. Ignition switch ….. . . OFF, remove key 2. Master switch (BAT) ….ON 3.

• Page 156: 3.17 Flight In Rain

  Normal Operating DA 40 AFM Procedures 4A.3.17 FLIGHT IN RAIN NOTE Performance deteriorates in rain; this applies particularly to the take-off distance and to the maximum horizontal speed. The effect on the flight characteristics is minimal. Flight through very heavy rain should be avoided because of the associated visibility problems.

• Page 157
  Abnormal Operating DA 40 AFM Procedures CHAPTER 4B ABNORMAL OPERATING PROCEDURES Page 4B.1 PRECAUTIONARY LANDING ……4B-2 4B.2 INSTRUMENT INDICATIONS OUTSIDE OF GREEN RANGE .

• Page 158: Precautionary Landing

  Abnormal Operating DA 40 AFM Procedures 4B.1 PRECAUTIONARY LANDING NOTE A landing of this type is only necessary when there is a reasonable suspicion that due to fuel shortage, weather conditions, or at nightfall the possibility of endangering the airplane and its occupants by continuing the flight cannot be excluded.

• Page 159
  Abnormal Operating DA 40 AFM Procedures On Final Approach: 6. Flaps ……LDG 7.

• Page 160: Instrument Indications Outside Of Green Range

  Abnormal Operating DA 40 AFM Procedures 4B.2 INSTRUMENT INDICATIONS OUTSIDE OF GREEN RANGE (a) High Oil Pressure When Starting in Low Ambient Temperatures Reduce RPM and re-check oil pressure at a higher oil temperature. If on reducing the RPM the indicated oil pressure does not change, it is probable that the fault lies in the oil pressure indication.

• Page 161: Failures In The Electrical System

  Abnormal Operating DA 40 AFM Procedures 4B.3 FAILURES IN THE ELECTRICAL SYSTEM (a) ‘Low Voltage’ Caution (VOLT or LOW VOLTS) This caution is indicated when the normal on-board voltage (28 V) drops below 24 V. Possible reasons are: — A fault in the power supply.

• Page 162
  Abnormal Operating DA 40 AFM Procedures (b) Electronic Ignition Control Unit If the electronic ignition control unit is installed but inoperative, the white status light for the ignition (IGN or IGNITION) will be illuminated, and the conventional magneto ignition will take over the ignition control.

• Page 163: Take-Off From A Short Grass Strip

  Abnormal Operating DA 40 AFM Procedures 4B.4 TAKE-OFF FROM A SHORT GRASS STRIP 1. Brakes ……apply 2.

• Page 164
  Abnormal Operating DA 40 AFM Procedures 10. Flaps ……UP, above safe altitude 11.

• Page 165: Failures In Flap Operating System

  Abnormal Operating DA 40 AFM Procedures 4B.5 FAILURES IN FLAP OPERATING SYSTEM Failure in Position Indication or Function Check flap position visually. Keep airspeed in white sector. Re-check all positions of the flap switch. Modified Approach Procedure Depending on the Available Flap Setting (a) Only UP or T/O Available: Airspeed .

• Page 166: Failures In Electrical Rudder Pedal Adjustment . 4B-10

  Abnormal Operating DA 40 AFM Procedures 4B.6 FAILURES IN ELECTRICAL RUDDER PEDAL ADJUSTMENT Runaway of Electrical Rudder Pedal Adjustment (Optional Equipment, OÄM 40-251) NOTE The circuit breaker for the rudder pedal adjustment is located below the related switch, on the rear wall of the leg room.

• Page 167: Landing With High Landing Mass

  Abnormal Operating DA 40 AFM Procedures 4B.7 LANDING WITH HIGH LANDING MASS NOTE This Section only applies to airplanes with a maximum landing mass less than the maximum flight mass. All landings with a current flight mass not exceeding the maximum permissible landing mass constitutes a normal operating procedure.

• Page 168: Starting The Engine With External Power

  Abnormal Operating DA 40 AFM Procedures 4B.8 STARTING THE ENGINE WITH EXTERNAL POWER WARNING The use of an external power supply for engine starting with an empty airplane battery is not permitted if the subsequent flight is intended to be an IFR flight. In this case the airplane battery must be charged first.

• Page 169
  Abnormal Operating DA 40 AFM Procedures CAUTION When operating the canopy, ensure that there are no obstructions between the canopy and the mating frame, for example seat belts, clothing, etc. When operating the locking handle do NOT apply undue force.
• Page 170
  Abnormal Operating DA 40 AFM Procedures 21. External power ….. . . connect 22. Master switch (BAT) ….ON 23.
• Page 171
  DA 40 AFM Performance CHAPTER 5 PERFORMANCE Page INTRODUCTION ……..5-2 USE OF THE PERFORMANCE TABLES AND DIAGRAMS .

• Page 172: Introduction

  The installation of the optional fairings on the main landing gear struts and/or nose landing gear strut has only minor effects on the flight performance of the DA 40. Therefore, no change applies to the performance tables and diagrams.

• Page 173: Performance Tables And Diagrams

  DA 40 AFM Performance 5.3 PERFORMANCE TABLES AND DIAGRAMS 5.3.1 AIRSPEED CALIBRATION Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 5 — 3…

• Page 174
  Performance DA 40 AFM 5.3.2 TABLE FOR SETTING ENGINE PERFORMANCE NOTE If the Long Range Tank is installed: Auxiliary fuel below 3 US gal cannot be indicated by the system. If a fuel indicator shows 16 US gal and the auxiliary…
• Page 175
  DA 40 AFM Performance Engine Power as % of Max. Take-Off Power 45 % 55 % 1800 2000 2200 2400 2000 2200 2400 Fuel Flow Best Economy [US gal/h] Best Power [°C] [°F] Manifold Pressure (MP) [inHg] 22.7 21.3 20.2 19.0…
• Page 176
  Performance DA 40 AFM Engine Power as % of Max. Take-Off Power 65 % 75 % 2000 2200 2400 2200 2400 Fuel Flow Best Economy [US gal/h] Best Power 10.7 [°C] [°F] Manifold Pressure (MP) [inHg] 26.8 23.4 25.8 24.9 27.3…

• Page 177: Pressure Altitude — Density Altitude

  DA 40 AFM Performance 5.3.3 PRESSURE ALTITUDE — DENSITY ALTITUDE Conversion from pressure altitude to density altitude. 14000 4000 12000 3500 10000 3000 14000 4000 2500 12000 8000 8000 3500 10000 2000 3000 6000 2500 8000 1500 4000 2000 6000…

• Page 178: Stalling Speeds

  Performance DA 40 AFM 5.3.4 STALLING SPEEDS Airspeeds in KIAS Mass: 980 kg (2161 lb) Bank Angle 980 kg 0° 30° 45° 60° Flaps Mass: 1150 kg (2535 lb) Bank Angle 1150 kg 0° 30° 45° 60° Flaps Mass: 1200 kg (2646 lb) (if MÄM 40-227 is carried out)

• Page 179: Wind Components

  DA 40 AFM Performance 5.3.5 WIND COMPONENTS Example: Flight direction 360° Wind 32°/30 kts Result: Crosswind component 16 kts Max. demonstrated crosswind component 20 kts Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 5 — 9…

• Page 180: Take-Off Distance

  Performance DA 40 AFM 5.3.6 TAKE-OFF DISTANCE Conditions: — Throttle ….MAX PWR — RPM lever ….2700 RPM — Flaps .

• Page 181
  DA 40 AFM Performance CAUTION The figures in the following NOTE are typical values. On wet ground or wet soft grass covered runways the take-off roll may become significantly longer than stated below. In any case the pilot must allow for the condition of the runway to ensure a safe take-off.
• Page 182
  Performance DA 40 AFM Page 5 — 12 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E…

• Page 183: Climb Performance — Take-Off Climb

  DA 40 AFM Performance 5.3.7 CLIMB PERFORMANCE — TAKE-OFF CLIMB Conditions: — Throttle ….MAX PWR — RPM lever ….2400 RPM — Flaps .

• Page 184
  Performance DA 40 AFM Page 5 — 14 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E…

• Page 185: Climb Performance — Cruise Climb

  DA 40 AFM Performance 5.3.8 CLIMB PERFORMANCE — CRUISE CLIMB Conditions: — Throttle ….MAX PWR — RPM lever ….2400 RPM — Flaps .

• Page 186
  Performance DA 40 AFM Page 5 — 16 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E…

• Page 187: Cruising (True Airspeed Tas)

  DA 40 AFM Performance 5.3.9 CRUISING (TRUE AIRSPEED TAS) Diagram to establish true airspeed (TAS) at a given power setting. Example: Pressure altitude … . . 5000 ft Temperature ….15 EC (59 °F) Power setting .

• Page 188: Landing Distance — Flaps Ldg

  Performance DA 40 AFM 5.3.10 LANDING DISTANCE — FLAPS LDG Conditions: — Throttle ….IDLE — RPM lever ….HIGH RPM — Flaps .

• Page 189
  DA 40 AFM Performance CAUTION For a safe landing the landing distance available (LDA) should be at least equal to the landing distance over a 50 ft (15 m) obstacle. CAUTION The figures in the following NOTE are typical values. On wet ground or wet soft grass covered runways the landing distance may become significantly longer than stated below.
• Page 190
  Performance DA 40 AFM Page 5 — 20 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E…

• Page 191: Landing Distance — Flaps Up

  DA 40 AFM Performance 5.3.11 LANDING DISTANCE — FLAPS UP Conditions: — Throttle ….IDLE — RPM lever ….HIGH RPM — Flaps .

• Page 192
  Performance DA 40 AFM CAUTION For a safe landing the landing distance available (LDA) should be at least equal to the landing distance over a 50 ft (15 m) obstacle. CAUTION The figures in the following NOTE are typical values. On wet ground or wet soft grass covered runways the landing distance may become significantly longer than stated below.
• Page 193
  DA 40 AFM Performance Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 5 — 23…
• Page 194
  5.3.12 GRADIENT OF CLIMB ON GO-AROUND The DA 40 reaches a constant gradient of climb of 7.0 % in the following condition: — Mass ……max. flight mass (1150 kg, 2535 lb) — Power setting .
• Page 195
  DA 40 AFM Mass & Balance CHAPTER 6 MASS AND BALANCE Page INTRODUCTION ……..6-2 DATUM PLANE .

• Page 196: Introduction

  Mass & Balance DA 40 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 197: Datum Plane

  DA 40 AFM Mass & 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 198
  Mass & Balance DA 40 AFM MASS AND BALANCE REPORT (Continuous report on structural or equipment changes) Page 6 — 4 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E…

• Page 199: Flight Mass And Center Of Gravity

  Mass & Balance 6.4 FLIGHT MASS AND CENTER OF GRAVITY The following information enables you to operate your DA 40 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 200
  Mass & Balance DA 40 AFM Baggage The DA 40 may be equipped with one of the following baggage compartment variants: (a) Standard baggage compartment. (b) Standard baggage compartment with ‘baggage tube’. (c) Extended baggage compartment (OÄM 40-163). It consists of a forward and an aft part.
• Page 201
  DA 40 AFM Mass & Balance b) Long Range Tank: Read the fuel quantity indicated on the fuel quantity indicators. NOTE At an indication of 16 US gal the amount of auxiliary fuel can be determined by switching the AUX FUEL QTY switch to the respective position (LH or RH).

• Page 202: Calculation Of Loading Condition

  Mass & Balance DA 40 AFM Moments 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 203
  DA 40 AFM Mass & Balance 6.4.1 MOMENT ARMS The most important lever arms aft of the Datum Plane: 1.00 m 39.4 in Front seats 2.30 m 90.6 in Rear seats 3.25 m 128.0 in Wing tanks (Standard & Long Range) 2.63 m…
• Page 204
  Mass & Balance DA 40 AFM 6.4.2 LOADING DIAGRAM Page 6 — 10 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E…
• Page 205
  DA 40 AFM Mass & Balance 6.4.3 CALCULATION OF LOADING CONDITION CAUTION For airplanes equipped with the optional Long Range Tank, a restricted range of permitted CG positions applies. NOTE For the mass (weight) of the fuel, a density of 0.72 kg/liter (6.01 lb/US gal) is assumed.
• Page 206
  Mass & Balance DA 40 AFM DA 40 (Example) Your DA 40 Mass Moment Mass Moment [kg] [kg m] [kg] [kg m] [lb] [in lb] [lb] [in lb] Empty mass (from Mass 1760 1620 152,762 and Balance Report) Oil not added -1.7…

• Page 207: Permissible Center Of Gravity Range

  DA 40 AFM Mass & Balance 6.4.4 PERMISSIBLE CENTER OF GRAVITY RANGE CG pos. [in] 2700 1200 1200 kg / 2646 lb MÄM 40-227 carried out 1150 2500 1150 kg / 2535 lb 1100 Normal 1050 2300 980 kg / 2161 lb…

• Page 208
  Mass & Balance DA 40 AFM Rearward Flight CG Limit: 2.59 m (102.0 in) aft of Datum Plane (Standard Tank) 2.55 m (100.4 in) aft of Datum Plane (with Long Range Tank installed) Page 6 — 14 Rev. 8 01-Dec-2010…

• Page 209: Permissible Moment Range

  DA 40 AFM Mass & Balance 6.4.5 PERMISSIBLE MOMENT RANGE 3108 3060 2486 Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 6 — 15…

• Page 210: Equipment List And Equipment Inventory

  DA 40 AFM 6.5 EQUIPMENT LIST AND EQUIPMENT INVENTORY All equipment that is approved for installation in the DA 40 is shown in the Equipment List below. The items of equipment installed in your particular airplane are indicated in the appropriate column.

• Page 227
  Airplane DA 40 AFM Description CHAPTER 7 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS Page INTRODUCTION ……..7-3 AIRFRAME .
• Page 228
  Airplane DA 40 AFM Description 7.15 CO-MONITOR (IF INSTALLED) ……7-55 7.15.1 SELF TEST SEQUENCE ……7-55 7.15.2 IN-FLIGHT CO ALARM .
• Page 229
  Airplane DA 40 AFM 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. 7.2 AIRFRAME Fuselage The GFRP fuselage is of semi monocoque molded construction. 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 230: Flight Controls

  Airplane DA 40 AFM Description 7.3 FLIGHT CONTROLS The ailerons, elevator and wing flaps are operated through control rods, while the rudder is controlled by cable. The flaps are electrically operated. Elevator forces can be balanced by a trim tab on the elevator, which is operated by a Bowden cable.

• Page 231
  Airplane DA 40 AFM Description Flaps Construction: GFRP/CFRP composite sandwich Hinges: There are 6 hinges, which are hinge pins mounted in an aluminum bracket. They are secured in position by a roll pin. The absence of this roll pin can lead to the loss of the hinge pin and a consequent loss of flight safety.
• Page 232
  Airplane DA 40 AFM 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 233
  Airplane DA 40 AFM Description Elevator Construction: GFRP sandwich Hinges: 5 hinges Operation Steel push-rods; Two of the bellcrank bearings are accessible to visual inspection next to the lower hinge of the rudder. The elevator horn and its bearing, as well as the connection to the push-rod, can be visually inspected at the upper end of the rudder.
• Page 234
  Airplane DA 40 AFM Description Elevator Trim The trim control is a black wheel in the center console to the rear of the engine controls. To guard against over-rotating, the trim wheel incorporates a friction device. A mark on the wheel shows the take-off (T/O) position.
• Page 235
  Airplane DA 40 AFM Description Electrical Pedal Adjustment (Optional Equipment, OÄM 40-251) NOTE The pedals may only be adjusted on the ground! The pedals are adjusted using a rocker switch, located on the rear wall of the leg room. The related circuit breaker is located below the switch.

• Page 236: Instrument Panel

  7.4 INSTRUMENT PANEL Instrument Panel Variants The DA 40 can be equipped with one of numerous instrument panel variants. Therefore only two example variants (VFR and IFR) are described in this section. The equipment that is actually installed in a particular airplane is listed in the Equipment Inventory in Section 6.5.

• Page 237
  Airplane DA 40 AFM Description VFR instrument panel (example) IFR instrument panel (example) Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 7 — 11…
• Page 238
  Airplane DA 40 AFM Description Major Instruments and Controls 1 Electrical switches, ignition switch 18 ADF indicator 2 Circuit breakers* 19 Course deviation indicator (CDI) 3 Emergency switch 20 Audio amplifier / intercom / marker beacon receiver 4 Rotary buttons for instrument…

• Page 239: Landing Gear

  Airplane DA 40 AFM Description 7.5 LANDING GEAR The landing gear consists of a main landing gear of sprung steel struts, and a free-castering nose wheel which is sprung by an elastomer package. The wheel fairings are removable. When flying without wheel fairings, it should be noted that there is a reduction in some areas of performance (see Chapter 5).

• Page 240
  Airplane DA 40 AFM Description Hydraulic System Schematic brake pedals, brake pedals, pilot co-pilot parking brake valve brake cylinder, LH brake cylinder, RH Page 7 — 14 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E…
• Page 241
  Airplane DA 40 AFM 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 facilitate the maintenance and inspection of the underlying controls. Covers on the control sticks prevent loose objects from falling into the area of the controls.

• Page 242: Baggage Compartment

  DA 40 AFM Description 7.7 BAGGAGE COMPARTMENT The DA 40 may be equipped with one of the following baggage compartment variants: (a) Standard baggage compartment. (b) Standard baggage compartment with ‘baggage tube’. (c) Extended baggage compartment (OÄM 40-163). It consists of a forward and an aft part.

• Page 243
  Airplane DA 40 AFM Description 7.8 CANOPY, REAR DOOR, AND CABIN INTERIOR Front Canopy The front canopy is closed by pulling down on the canopy frame, following which it is locked by means of a handle on the left hand side of the frame. On locking, steel bolts lock into mating holes in polyethylene blocks.
• Page 244
  Airplane DA 40 AFM Description Rear Door The rear door is closed in the same way, by pulling down on the frame or on the handle (if installed) and locking it with the handle. A gas pressure damper prevents the door from dropping;…
• Page 245
  Airplane DA 40 AFM Description Emergency Axe If OÄM 40-326 is incorporated an emergency axe is installed on the floor panel under the pilot’s seat (see Figure below). If the canopy can not be opened in case of an emergency use the emergency axe to break through the canopy.
• Page 246
  Airplane DA 40 AFM Description 7.9 POWER PLANT 7.9.1 ENGINE, GENERAL Lycoming IO-360-M1A: Air-cooled four-cylinder four-stroke engine. Horizontally-opposed direct-drive engine with fuel injection and underslung exhaust. Displacement: 5916 cm (361 in Max. power: 180 HP (134.2 kW) at 2700 RPM at sea level and ISA.
• Page 247
  Airplane DA 40 AFM Description 7.9.2 OPERATING CONTROLS The engine performance is controlled by means of three levers: throttle, RPM lever and mixture control lever, situated together as a group on the large center console (also referred to as the throttle quadrant). Front and rear are defined in relation to the direction of flight.
• Page 248
  Airplane DA 40 AFM Description The propeller governor is flanged onto 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 the finest possible pitch (maximum RPM), thus allowing continuation of the flight.
• Page 249
  Airplane DA 40 AFM Description In cruise, the mixture should be made leaner in order to reach the appropriate fuel-air mixture. The leaning procedure is given in Chapter 4. To shut off the engine the mixture control lever is pulled to the rear stop. Air without fuel is thus drawn into the cylinders and the engine dies.
• Page 250
  Airplane DA 40 AFM Description 7.9.3 PROPELLER A mt-Propeller MTV-12-B/180-17 type or MTV-12-B/180-17f type, hydraulically-regulated 3-bladed constant speed propeller is installed. It has wood-composite blades with fiber- reinforced plastic coating and stainless steel edge cladding; in the region of the propeller hub the leading edge is coated with adhesive PU foil.
• Page 251
  Airplane DA 40 AFM Description 7.9.4 ENGINE INSTRUMENTS Button 1: Lean mode Button 2: Digital exhaust gas / cylinder head temperature mode Button 3: Switch in autotrack Button 4: Fuel computer mode Button 5: Engine data recorder Button 3 has an additional function on switch-on: Display mode Doc.
• Page 252
  Airplane DA 40 AFM Description Sweep Mode or Pointer Mode If the switch-on button 3 is kept pressed until the display transfers from activating all bars/pointers to indicating the actual values, the type of presentation can be selected. In one case the circular instruments show the values with a pointer as in conventional analog instruments, whilst in the other case the circular instruments fill with pointers/bars up to the current value.
• Page 253
  Airplane DA 40 AFM Description Button 1 — Lean Mode Upon powering up the unit the Normal mode is shown. Between the colored sector markings the cylinder head temperatures of the individual cylinders are shown by bars. Above those are bars showing the exhaust gas temperatures of the individual cylinders.
• Page 254
  Airplane DA 40 AFM Description Button 2: Digital Exhaust Gas / Cylinder Head Temperature Mode Using this button, the numerical indication for exhaust gas and cylinder head temperature underneath the graphical representation of these figures is set. Following each sequential operation of the button the exhaust gas and cylinder head temperatures of an individual cylinder are displayed.
• Page 255
  Airplane DA 40 AFM Description HRS: This mode shows the remaining flight time (in hours) on the basis of the current fuel flow. The steps in this indication are tenths of hours. This mode is also only available if the ADD mode — add up fuel — has previously been activated.
• Page 256
  Airplane DA 40 AFM Description Button 5 — Engine Data Recorder Operating button 5 will activate the engine data recorder. The digital values shown are the minimum values recorded by the engine instrument unit during operation, such as lowest voltage, lowest fuel pressure, etc. The numerical RPM indicator will indicate the total operating hours.
• Page 257
  Airplane DA 40 AFM Description 7.10 FUEL SYSTEM a) Standard Tank: Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 7 — 31…
• Page 258
  Airplane DA 40 AFM Description b) Long Range Tank: Page 7 — 32 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E…
• Page 259
  Airplane DA 40 AFM Description Fuel Pumps The fuel system is equipped with a mechanical and an electrical fuel pump. The mechanical pump provides for the normal fuel supply. The electrical fuel pump is provided as an auxiliary and emergency pump, which does not operate under normal circumstances.
• Page 260
  Airplane DA 40 AFM Description b) Long Range Tank Fuel Tanks Each of the two wing tanks consists of two (standard tank) or three (long range tank) aluminum chambers which are joined by a piece of flexible hose and two independent vent hoses.
• Page 261
  Airplane DA 40 AFM Description A coarse filter (finger filter) is fitted before the outlet. To allow draining of the tank, there is an outlet valve at its lowest point. A gascolator sits at the lowest point in the fuel system.
• Page 262
  Airplane DA 40 AFM Description b) Long Range Tank For ascertaining fuel quantity in the enlarged tanks an additional capacitive probe is used on each side (LH/RH). When the fuel quantity indicator reads zero, only the unusable fuel remains in the tank. The usable capacity of each tank is 25 US gal (approximately 94 liter).
• Page 263
  Airplane DA 40 AFM Description The actual fuel quantity in the respective tank (LH/RH) is the sum of the central indication and the corresponding indication on the left or right side. CAUTION The correct indication of the fuel quantity takes 2 minutes after actuation of the AUX FUEL QTY switch.
• Page 264
  Airplane DA 40 AFM Description Fuel Quantity Measuring Device The fuel quantity measuring device allows the fuel quantity in the tank to be determined during the pre-flight inspection. It functions according to the principle of communicating containers. The fuel quantity measuring device has a recess which fits the airfoil of the wing.
• Page 265
  Airplane DA 40 AFM Description unuseable unuseable fuel fuel a) Standard Tank b) Long Range Tank Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 7 — 39…
• Page 266
  Airplane DA 40 AFM Description 7.11 ELECTRICAL SYSTEM Page 7 — 40 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E…
• Page 267
  Airplane DA 40 AFM Description Doc. # 6.01.01-E Rev. 8 01-Dec-2010 Page 7 — 41…
• Page 268
  Airplane DA 40 AFM Description 7.11.1 GENERAL The DA 40 has 28 Volt DC system, which can be sub-divided into: — Power generation — Storage — Distribution — Consumers Power Generation The 70 Ampère alternator (generator) is mounted on the front of the engine. It is driven by a V-belt, and charges the battery.
• Page 269
  Section 1.5 — DEFINITIONS AND ABBREVIATIONS. Ignition The basic version of the DA 40 is equipped with the electric start boost system SlickSTART. This system improves the start characteristics by delivering more spark energy during the engine start sequence. After engine starting the ignition is controlled by the conventional retard breaker magneto system.
• Page 270
  Airplane DA 40 AFM Description Voltmeter The voltmeter displays the potential on the main bus. If the alternator is operating, the alternator voltage is shown, otherwise it is that provided by the battery. Ammeter The ammeter displays the current with which the alternator is being loaded.
• Page 271
  Airplane DA 40 AFM Description Pitot Heating The Pitot probe, which provides measurement for the Pitot-static system, is electrically heated. The heating is activated with a switch (PITOT) on the row of switches on the instrument panel. The temperature is automatically kept constant by means of a thermal switch on the Pitot probe, and as an additional safety measure a thermal fuse is built in.
• Page 272
  Airplane DA 40 AFM Description 7.11.2 DAI ANNUNCIATOR PANEL (WARNING, CAUTION AND STATUS LIGHTS) There are two variants of the annunciator panel (‘DAI’ and ‘White Wire’). The ‘DAI’ variant, which is described below, can be identified by the lights in the shape of a square.
• Page 273
  Airplane DA 40 AFM Description Fuel Pressure Warning Light (FUEL PR) The fuel pressure warning light illuminates when the fuel pressure drops below 14 PSI. The color is red. Low Fuel Caution Lights (L FUEL and R FUEL) Each tank has its own caution light. It starts to flash when the fuel quantity becomes low, and illuminates permanently when the quantity of usable fuel in the respective tank drops below 3 US gal (±1 US gal).
• Page 274
  Airplane DA 40 AFM Description Status Light for the Ignition (IGN) This light is only used when the electronic ignition control unit is installed. The status light for the ignition illuminates when the electronic ignition control is not operating. In this case the conventional magneto ignition will be in use. The color is white.
• Page 275
  Airplane DA 40 AFM Description 7.11.3 WHITE WIRE ANNUNCIATOR PANEL (WARNING, CAUTION AND STATUS LIGHTS) There are two variants of the annunciator panel (‘DAI’ and ‘White Wire’). The ‘White Wire’ variant, which is described below, can be identified by the flat front panel and the ‘White Wire’ logo on the display in the upper left corner.
• Page 276
  Airplane DA 40 AFM Description Caution Messages A caution is indicated by a momentary aural alert (sounded in the airplane’s intercom system), flashing of the amber CAUTION light, and flashing of the amber caution light associated with the affected system.
• Page 277
  Airplane DA 40 AFM Description Fuel Pressure Warning Message (FUEL PRESS) The fuel pressure warning message is displayed when the fuel pressure drops below 14 PSI. Low Fuel Caution Message (LOW FUEL) As soon as the amount of usable fuel in one tank is less than 3 US gal (±1 US gal), a caution message is displayed in the usual manner (momentary aural alert, flashing CAUTION light, flashing LOW FUEL caution light).
• Page 278
  Airplane DA 40 AFM Description Door Warning Message (DOORS) The door warning message is displayed when the front canopy and/or the rear door is not closed and locked. The procedure to be followed upon door warning is given in 3.7.4 — DOOR-WARNING LIGHT ON.
• Page 279
  The White Wire annunciator panel is prepared for the installation of an autopilot in the DA 40. When the autopilot is installed and ready for operation, this warning message indicates a failure of the automatic trim system of the autopilot. For further details, refer to the Supplement to the AFM for the autopilot (if installed).
• Page 280
  Airplane DA 40 AFM Description 7.12 PITOT-STATIC SYSTEM Total pressure is measured at the leading edge of a Pitot probe under the left wing. Static pressure is measured at two orifices at lower and rear edges of the same probe. To protect against dirt and condensation there are filters in the system, which are accessible from the wing root.
• Page 281
  Airplane DA 40 AFM Description 7.15 CO-MONITOR (IF INSTALLED) The airplane may be equipped with a CO detector (OÄM 40-253). 7.15.1 SELF TEST SEQUENCE When power is applied to the CO detector, a self-test routine begins. The test checks for functionality of the critical components such as the CO sensor, temperature sensor, and the integrity of the total CO detector system.
• Page 282
  Airplane DA 40 AFM Description 7.15.3 UNIT FAILURE INDICATION A failure of the CO sensor, temperature sensor, or the micro-controller will result in the following failure indications: The remote light will flash at an approximately rate of one flash each four seconds until the failure is cleared or power is removed from the unit.
• Page 283
  DA 40 AFM Handling CHAPTER 8 AIRPLANE HANDLING, CARE AND MAINTENANCE Page INTRODUCTION ……..8-2 AIRPLANE INSPECTION INTERVALS .

• Page 284: Introduction

  Handling DA 40 AFM 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. 6.02.01) lists certain inspection and maintenance requirements which must be followed if the airplane is to retain a new plane performance and reliability.

• Page 285: Airplane Alterations Or Repairs

  DA 40 AFM Handling 8.3 AIRPLANE ALTERATIONS OR REPAIRS Alterations or repairs of the airplane may be carried out only according to the Airplane Maintenance Manual, Doc. No. 6.02.01, and only by authorized personnel. 8.4 GROUND HANDLING / ROAD TRANSPORT 8.4.1 GROUND HANDLING WITHOUT TOW BAR…

• Page 286
  Handling DA 40 AFM NOTE When moving the airplane rearward, the tow bar must be held firmly to prevent abrupt sideward deflection of the nose wheel. Page 8 — 4 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E…

• Page 287: Parking

  DA 40 AFM Handling 8.4.3 PARKING For short term parking, the airplane must be positioned into the wind, the parking brake must be engaged and the wing flaps must be in the retracted position. For extended and unattended parking, as well as in unpredictable wind conditions, the airplane must be anchored to the ground or placed in a hangar.

• Page 288
  Handling DA 40 AFM Page 8 — 6 Rev. 8 01-Dec-2010 Doc. # 6.01.01-E…

• Page 289: Mooring

  8.4.5 JACKING The DA 40 can be jacked at the two jackpoints located on the lower side of the fuselage’s LH and RH root ribs as well as at the tail fin. 8.4.6 ALIGNMENT For alignment push down on the tail section at the fuselage/vertical tail junction until the nose wheel is clear of the ground.

• Page 290: Road Transport

  Handling DA 40 AFM 8.4.7 ROAD TRANSPORT For transporting the airplane on the road it is recommended that an open trailer be used. All airplane components must be stored on a cushioned surface and secured to avoid any movement during transportation.

• Page 291: Cleaning And Care

  DA 40 AFM Handling 8.5 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. 8.5.1 PAINTED SURFACES The entire surface of the airplane is painted with a white weatherproof two component paint.

• Page 292: Canopy And Rear Door

  Handling DA 40 AFM 8.5.2 CANOPY AND REAR DOOR The canopy and rear door should be cleaned with ‘Plexiklar’ or any other acrylic glass detergent if available; otherwise use lukewarm water. Final cleaning should be done with a clean piece of chamois-leather or soft cloth. Never rub or polish dry acrylic glass.

• Page 293: Interior Surfaces

  DA 40 AFM Handling 8.5.5 INTERIOR SURFACES The interior should be cleaned using a vacuum cleaner. All loose items (pens, bags etc.) should be removed or properly stored and secured. All instruments can be cleaned using a soft dry cloth, plastic surfaces should be wiped clean using a damp cloth without any cleaning agents.

• Page 294
  General DA 40 AFM 8.6 DE-ICING ON THE GROUND Approved De-Icing Fluids Manufacturer Product Kilfrost TKS 80 Aeroshell Compound 07 Any source AL-5 (DTD 406B) De-Icing Procedure 1. Remove any snow from the airplane using a soft brush. 2. Spray de-icing fluid onto ice-covered surfaces using a suitable spray bottle.
• Page 295
  DA 40 AFM Supplements CHAPTER 9 SUPPLEMENTS Page INTRODUCTION ……..9-2 LIST OF SUPPLEMENTS .
• Page 296
  DA 40 AFM 9.1 INTRODUCTION Chapter 9 contains information concerning additional (optional) equipment of the DA 40. 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.
• Page 297
  DA 40 AFM Supplements 9.2 LIST OF SUPPLEMENTS Airplane S/N: Registration: Date: applicable Sup. Rev. Title Date COMM/NAV, KX 125 20-Apr-2001 Bendix/King Intercom System, Model PM 1000 II 15-Mar-2005 PS Engineering, Inc. Transponder, KT 76A 20-Apr-2001 Bendix/King GPS, KLN 89B…
• Page 298
  Supplements DA 40 AFM Airplane S/N: Registration: Date: applicable Sup. Rev. Title Date Automatic Direction Finder, KR 87 17-Feb-2003 Bendix/King Distance Measuring Equipment, KN 62A 17-Feb-2003 Bendix/King Compass System, KCS 55A 15-Mar-2005 Bendix/King Transponder, KT 76C 15-Mar-2005 Bendix/King Autopilot System, KAP 140…
• Page 299
  DA 40 AFM Supplements Airplane S/N: Registration: Date: applicable Sup. Rev. Title Date Course Devation Indicator, 15-Mar-2005 GI 106A, Garmin COM / NAV / GPS, 15-Mar-2002 GNS 530, Garmin Strike Finder, 10-Oct-2001 SF 2000, Insight GPS Annunciation Unit, 20-Dec-2002 MD 41-1488/1484, MID Continent…
• Page 300
  AIM 1100-28LK(0F) DIA 15-Mar-2005 BF Goodrich Digital Chronometer, 15-Mar-2005 Model 803, Davtron Ventilation Inlet Baffle 27-Apr-2005 Use of the DA 40 as Tow-Plane 28-Nov-2001 Operation of the DA 40 26-Nov-2001 with Winter Kit Emergency Locator Transmitter, 15-Mar-2005 Model E-01, ACK…

Quick Links

Chapters

• Page 2
  DA 40 NG AFM Introduction Intentionally left blank. Page 0 — 0a Rev. 3 01-Jul-2014 Doc. # 6.01.15-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 DA 40 NG 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 DA 40 NG 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
  DA 40 NG AFM Introduction Rev. Chap- Date of Approval Date Date Reason Page(s) Signature Revision Note of Approval Inserted MÄM 40-415, 40-432, 40-440, 40-448, 40-460, 40-466, 40-447, 40-514, Revision 1 of the AFM Doc. No. OÄM 6.01.15-E is all, except…
• Page 6
  Introduction DA 40 NG AFM Rev. Chap- Date of Approval Date Date Reason Page(s) Signature Revision Note of Approval Inserted MÄM 40-777/a, 40-766, 40-765, 40-754, 40-751, 40-742, 40-731, 40-710/a, 40-674, 40-672, 40-662, 40-638, 40-631, 40-632, 40-618/a & OÄM 40-321/b, 40-574,…
• Page 7
  DA 40 NG AFM Introduction 0.3 LIST OF EFFECTIVE PAGES Page Date Page Date 15-Jun-2011 01-Jul-2014 0-0a 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 1-10 01-Jul-2014 01-Jul-2014 1-11 01-Jul-2014 0-10…
• Page 8
  Introduction DA 40 NG AFM Page Date Page Date appr. 2-28 01-Jul-2014 appr. 2-1 01-Jul-2014 appr. 2-29 01-Jul-2014 appr. 2-2 01-Jul-2014 appr. 2-30 01-Jul-2014 appr. 2-3 01-Jul-2014 appr. 2-31 01-Jul-2014 appr. 2-4 01-Jul-2014 appr. 2-32 01-Jul-2014 appr. 2-5 01-Jul-2014 appr. 2-33 01-Jul-2014 appr.
• Page 9
  DA 40 NG AFM Introduction Page Date Page Date 3-29 01-Jul-2014 01-Jul-2014 3-30 01-Jul-2014 01-Jul-2014 3-31 01-Jul-2014 01-Jul-2014 3-32 01-Jul-2014 01-Jul-2014 3-33 01-Jul-2014 01-Jul-2014 3-34 01-Jul-2014 01-Jul-2014 3-35 01-Jul-2014 01-Jul-2014 3-36 01-Jul-2014 01-Jul-2014 3-37 01-Jul-2014 01-Jul-2014 3-38 01-Jul-2014 3-10 01-Jul-2014…
• Page 10
  Introduction DA 40 NG AFM Page Date Page Date 4A-28 01-Jul-2014 4A-1 01-Jul-2014 4A-29 01-Jul-2014 4A-2 01-Jul-2014 4A-30 01-Jul-2014 4A-3 01-Jul-2014 4A-31 01-Jul-2014 4A-4 01-Jul-2014 4A-32 01-Jul-2014 4A-5 01-Jul-2014 4A-33 01-Jul-2014 4A-6 01-Jul-2014 4A-34 01-Jul-2014 4A-7 01-Jul-2014 4A-35 01-Jul-2014 4A-8…
• Page 11
  DA 40 NG AFM Introduction Page Date Page Date 4B-28 01-Jul-2014 4B-1 01-Jul-2014 4B-29 01-Jul-2014 4B-2 01-Jul-2014 4B-30 01-Jul-2014 4B-3 01-Jul-2014 4B-4 01-Jul-2014 4B-5 01-Jul-2014 4B-6 01-Jul-2014 4B-7 01-Jul-2014 4B-8 01-Jul-2014 4B-9 01-Jul-2014 4B-10 01-Jul-2014 4B-11 01-Jul-2014 4B-12 01-Jul-2014 4B-13…
• Page 12
  Introduction DA 40 NG AFM Page Date Page Date 5-28 01-Jul-2014 01-Jul-2014 5-29 01-Jul-2014 01-Jul-2014 5-30 01-Jul-2014 01-Jul-2014 5-31 01-Jul-2014 01-Jul-2014 5-32 01-Jul-2014 01-Jul-2014 5-33 01-Jul-2014 01-Jul-2014 5-34 01-Jul-2014 01-Jul-2014 5-35 01-Jul-2014 01-Jul-2014 5-36 01-Jul-2014 01-Jul-2014 5-37 01-Jul-2014 5-10 01-Jul-2014…
• Page 13
  DA 40 NG AFM Introduction Page Date 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 6-10 01-Jul-2014 6-11 01-Jul-2014 6-12 01-Jul-2014 6-13 01-Jul-2014 6-14 01-Jul-2014 6-15 01-Jul-2014 6-16 01-Jul-2014 6-17 01-Jul-2014 6-18 01-Jul-2014 6-19 01-Jul-2014 6-20 01-Jul-2014 6-21 01-Jul-2014…
• Page 14
  Introduction DA 40 NG AFM Page Date Page Date 7-28 01-Jul-2014 01-Jul-2014 7-29 01-Jul-2014 01-Jul-2014 7-30 01-Jul-2014 01-Jul-2014 7-31 01-Jul-2014 01-Jul-2014 7-32 01-Jul-2014 01-Jul-2014 7-33 01-Jul-2014 01-Jul-2014 7-34 01-Jul-2014 01-Jul-2014 7-35 01-Jul-2014 01-Jul-2014 7-36 01-Jul-2014 01-Jul-2014 7-37 01-Jul-2014 7-10 01-Jul-2014…
• Page 15
  DA 40 NG AFM Introduction Page Date Page Date 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 01-Jul-2014 8-10 01-Jul-2014 8-11 01-Jul-2014 8-12 01-Jul-2014 8-13 01-Jul-2014 8-14 01-Jul-2014 Page 0 — 13 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E…
• Page 16
  Introduction DA 40 NG AFM 0.4 TABLE OF CONTENTS Chapter GENERAL (a non-approved chapter) ……..1 OPERATING LIMITATIONS (an approved chapter) .

• Page 17: Table Of Contents

  DA 40 NG AFM General CHAPTER 1 GENERAL Page INTRODUCTION ……..1-2 CERTIFICATION BASIS .

• Page 18: Introduction

  General DA 40 NG 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 JAR-23 requirement.

• Page 19
  This Airplane Flight Manual must be kept on board the airplane at all times. Its designated place is the side bag of the forward left seat. CAUTION The DA 40 NG is a single engine airplane. When the operating limitations and maintenance requirements are complied with, it has the high degree of reliability which is required by the certification basis.

• Page 20: Certification Basis

  General DA 40 NG AFM 1.2 CERTIFICATION BASIS This airplane has been type certified in accordance with the procedures established by EASA. The certification basis is JAR-23, published on 11-Mar-1994 and additional requirements as laid down in CRI A-01. 1.3 WARNINGS, CAUTIONS AND NOTES…

• Page 21: Dimensions

  DA 40 NG AFM General 1.4 DIMENSIONS NOTE All dimensions shown below are approximate. Overall Dimensions Span 11.63 m 38 ft 2 in Length 8.06 m 26 ft 5 in Height 1.97 m 6 ft 6 in Wing Airfoil Wortmann FX 63-137/20 — W4 Wing area 13.244 m²…

• Page 22
  General DA 40 NG AFM Horizontal Tail Area 2.34 m 25.2 sq.ft. Elevator area 0.665 m 7.2 sq.ft. Angle of incidence : -3.0° relative to longitudinal axis of airplane Vertical Tail Area 1.60 m² 17.2 sq.ft. Rudder area 0.47 m²…

• Page 23: Definitions And Abbreviations

  DA 40 NG AFM General 1.5 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 24
  General DA 40 NG AFM Stalling Speed, or the minimum continuous speed at which the airplane is still controllable in the given configuration. Stalling Speed, or the minimum continuous speed at which the airplane is still controllable in the landing configuration.
• Page 25
  DA 40 NG AFM General Pressure Altitude: Altitude above MSL, indicated by a barometric altimeter which is set to 1,013.25 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 26
  General DA 40 NG 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 27
  DA 40 NG AFM General Moment Arm: The horizontal distance from the Datum Plane to the Center of Gravity of a component. Moment: The mass of a component multiplied by its moment arm. Usable Fuel: The quantity of fuel available for flight planning.
• Page 28
  General DA 40 NG AFM (f) Designation of the Circuit Breakers on the Instrument Panel ADC: Air Data Computer. ADF: Automatic Direction Finder. AHRS: Attitude and Heading Reference System. ANNUN: Annunciator Panel. AV/CDU FAN: Avionic-, CDU-Cooling Fans. AV. BUS: Avionic Bus.
• Page 29
  DA 40 NG AFM General INST.1: Engine Instrument. INST. LT: Instrument Lights. LANDING: Landing Light. MAIN TIE: Bus Interconnection. MASTER CONTROL: Master Control (Avionics Relay). MFD: Multi Function Display. NAV: NAV Receiver. PFD: Primary Flight Display. PITOT: Pitot Heating System.
• Page 30
  General DA 40 NG AFM (i) Miscellaneous ACG: Austro Control GmbH (formerly BAZ, Federal Office of Civil Aviation). ATC: Air Traffic Control. CFRP: Carbon Fiber Reinforced Plastic. EASA: European Aviation Safety Agency. GFRP: Glass Fiber Reinforced Plastic. GIA: Garmin Integrated Avionics.

• Page 31: Units Of Measurement

  DA 40 NG AFM General 1.6 UNITS OF MEASUREMENT 1.6.1 CONVERSION FACTORS Dimension SI-Units US Units Conversion Length [mm] millimeter [in] inch [mm] / 25.4 = [in] meter [ft] feet [m] / 0.3048 = [ft] [km] kilometer [NM] nautical mile [km] / 1.852 = [NM]…

• Page 32
  General DA 40 NG AFM Dimension SI-Units US Units Conversion Intensity of ampère electric current Electric [Ah] ampère-hour charge (battery capacity) Electric volt potential Time [sec] second Page 1 — 16 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E…

• Page 33: Conversion Chart Liter / Us Gallon

  DA 40 NG AFM General 1.6.2 CONVERSION CHART LITER / US GALLON Liter US Gallon US Gallon Liter 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 26.4 106.0 29.1 113.6…

• Page 34: Three-View Drawing

  General DA 40 NG AFM 1.7 THREE-VIEW DRAWING Page 1 — 18 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E…

• Page 35: Source Documentation

  DA 40 NG AFM General 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 36: Propeller

  General DA 40 NG AFM 1.8.2 PROPELLER Address: mt-propeller Airport Straubing Wallmühle D-94348 ATTING GERMANY Phone: +49-9429-9409-0 E-mail: sales@mt-propeller.com Internet: 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 Page 1 — 20 Rev.

• Page 37
  Operating DA 40 NG AFM Limitations CHAPTER 2 OPERATING LIMITATIONS Page INTRODUCTION ……..2-2 AIRSPEED .

• Page 38: Introduction

  Operating DA 40 NG AFM Limitations 2.1 INTRODUCTION Chapter 2 of this Airplane Flight Manual includes operating limitations, instrument markings, and placards necessary for the safe operation of the airplane, its power-plant, standard systems and standard equipment. The limitations included in this Chapter are approved.

• Page 39: Airspeed

  Operating DA 40 NG AFM Limitations 2.2 AIRSPEED Airspeed KIAS Remarks up to 1080 kg 101 KIAS (2381 lb) Do not make full or Operating above 1080 kg abrupt control surface maneuvering (2381 lb) to 108 KIAS movement above this…

• Page 40: Airspeed Indicator Markings

  Operating DA 40 NG AFM Limitations 2.3 AIRSPEED INDICATOR MARKINGS Marking Significance White arc 60 KIAS — 98 KIAS Operating range with flaps fully extended. Green arc 66 KIAS — 130 KIAS Normal operating range. Yellow arc 130 KIAS — 172 KIAS ‘Caution’ range — “Only in smooth air”.

• Page 41: Power-Plant Limitations

  Operating DA 40 NG AFM Limitations 2.4 POWER-PLANT LIMITATIONS a) Engine manufacturer Austro Engine b) Engine designation E4-A c) RPM limitations (shown as propeller RPM) Maximum take-off (RPM) 2300 RPM max. 5 min Max. continuous power (RPM) : 2100 RPM Max.

• Page 42
  Operating DA 40 NG AFM Limitations Minimum — 30 °C Maximum 140 °C Normal range 50 °C — 135 °C h) Gearbox temperature Minimum — 30 °C Minimum (full load) 35 °C Maximum 120 °C NOTE A cautionary (yellow) gearbox temperature range is not imposed by the engine manufacturer.
• Page 43
  Operating DA 40 NG AFM Limitations k) Fuel pressure (absolute pressure) Minimum 4 bar NOTE The fuel pressure is not indicated; a fuel pressure warning will illuminate on the PFD (if G1000 is installed) or SED (if installed) if the pressure is below the limit.
• Page 44
  Operating DA 40 NG AFM Limitations r) Governor mt-Propeller P-853-16 electrical governor s) Oil specification Approved Engine Oil Types SAE Grade SHELL HELIX ULTRA 5W-30 ADDINOL SUPER POWER MV 0537 5W-30 BP Visco 5000 5W-30 5W-30 REPSOL ELITE Common Rail 5W30…
• Page 45
  Operating DA 40 NG AFM Limitations CASTROL Edge 0W-40 A3/B4 0W-40 CASTROL Edge Professional A3 0W-40 SHELL HELIX Ultra 0W-40 CAUTION Only engine oils conforming to MB 229.5 specification are approved by Austro Engine GmbH to be used for operation.
• Page 46
  Operating DA 40 NG AFM Limitations v) Maximum restart altitude 16,400 ft pressure altitude for immediate restarts 10,000 ft pressure altitude for restarts within 2 minutes EASA Page 2 — 10 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E approved…

• Page 47: Engine Instrument Markings

  Operating DA 40 NG AFM Limitations 2.5 ENGINE INSTRUMENT MARKINGS Engine instrument markings and their color code significance are shown in the table below: Indi- Yellow Green Yellow cation arc/bar arc/bar arc/bar arc/bar arc/bar lower caution normal caution upper prohibited…

• Page 48: Warning, Caution And Status Lights

  Operating DA 40 NG AFM Limitations 2.6 WARNING, CAUTION AND STATUS LIGHTS The following tables show the color and significance of the warning, caution and advisory alert lights. There are two variants: G1000 annunciation or SED, MED and ‘White Wire’ annunciator panel.

• Page 49
  Operating DA 40 NG AFM Limitations Warning Alerts (Red) SED, MED, G1000 Meaning / Cause White Wire installed installed Canopy and/or rear door are/is not closed and DOOR OPEN DOORS locked. Display system is not receiving attitude ATTITUDE reference information from the AHRS;…
• Page 50
  Operating DA 40 NG AFM Limitations Color and Significance of the Caution Lights (Amber) Caution Alerts (Amber) SED, MED, G1000 Meaning / Cause White Wire installed installed CAUTION CAUTION One of the cautions below is being indicated. A fault has occurred in the engine ECU A…
• Page 51
  Operating DA 40 NG AFM Limitations Color and Significance of the Status Lights (White) Advisory Alerts (White) SED, MED, G1000 Meaning / Cause White Wire installed installed GLOW ON GLOW Engine glow plug active. Fuel transfer from auxiliary to main tank is in…

• Page 52: Mass (Weight)

  Operating DA 40 NG AFM Limitations 2.7 MASS (WEIGHT) Mass (Weight) Value Maximum take-off mass 1280 kg 2822 lb Maximum take-off mass (if MÄM 40-662 is installed) 1310 kg 2888 lb Maximum landing mass 1216 kg 2681 lb if MÄM 40-574 is installed…

• Page 53
  Operating DA 40 NG AFM Limitations NOTE In some countries the beginning of a flight is defined by starting the engine. In those countries a maximum ramp mass 4 kg (9 lb) above the maximum take-off mass is approved. At the time of lift-off the maximum permitted take-off mass must not be exceeded.

• Page 54: Center Of Gravity

  Operating DA 40 NG AFM 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 upper surface of a 600:31 wedge which is placed on top of the rear fuselage in front of the vertical stabilizer.

• Page 55: Approved Maneuvers

  Operating DA 40 NG AFM Limitations 2.9 APPROVED MANEUVERS The airplane is to be operated in the Normal Category in accordance with JAR 23. 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 56: Maneuvering Load Factors

  Operating DA 40 NG AFM Limitations 2.10 MANEUVERING LOAD FACTORS WARNING The table below shows structural limitations. Exceeding the maximum load factors will lead to an overstressing of the airplane. CAUTION Intentional negative g-maneuvers are not permitted. at v at v…

• Page 57: Operating Altitude

  Operating DA 40 NG AFM Limitations 2.11 OPERATING ALTITUDE The maximum operating altitude is 16,400 ft (5,000 m) pressure altitude. 2.12 FLIGHT CREW Minimum crew 1 (one person) Maximum number of occupants : 4 (four persons) EASA Doc. # 6.01.15-E Rev.

• Page 58: Kinds Of Operation

  Operating DA 40 NG AFM Limitations 2.13 KINDS OF OPERATION Provided that national operational requirements are met, the following kinds of operation are approved: • Daytime flights according to Visual Flight Rules (VFR) • With the appropriate equipment: night flights according to Visual Flight Rules (NVFR) •…

• Page 59
  Operating DA 40 NG AFM Limitations For daytime VFR In addition In addition flights for night VFR flights for IFR flights Flight & • Airspeed indicator • Vertical speed • Second airspeed naviga- • Altimeter indicator (VSI) indicator (on PFD tion •…
• Page 60
  Operating DA 40 NG AFM Limitations For daytime VFR In addition In addition flights for night VFR flights for IFR flights Engine • Fuel qty. • Ammeter instru- • Oil press. • Voltmeter ments • Oil temp. • Coolant temp.
• Page 61
  Operating DA 40 NG AFM Limitations For daytime VFR In addition In addition flights for night VFR flights for IFR flights Lighting • Position lights • Strobe lights (anti collision lights) • Landing light • Instrument lighting • Flood light •…

• Page 62: Fuel

  Operating DA 40 NG AFM Limitations 2.14 FUEL Approved fuel grades: JET A, JET A-1 (ASTM D 1655) TS-1(Russia, GOST 10227-86) TS-1 (Ukraine, GSTU 320.00149943.011-99) RT (Russia, GOST 10227-86) RT (Ukraine, GSTU 320.00149943.007-97) No. 3 Jet Fuel (China, GB 6537-2006) JP-8 (F34) (USA, MIL-DTL-83133G-2010) and blends of the above listed fuel grades.

• Page 63
  Operating DA 40 NG AFM Limitations CAUTION In case of an unknown or an over dosage of the fuel additives the fuel system must be purged until the dosage is within the permitted limits. NOTE The specified additives are qualified for the operation with the certified fuel grades.
• Page 64
  Operating DA 40 NG AFM Limitations Standard Tank Configuration: Total fuel quantity 2 x 15.0 US gal (2 x 56.8 liter) Usable fuel 2 x 14.0 US gal (2 x 53.0 liter) Long Range Tank (if installed) Configuration: Total fuel quantity 2 x 20.5 US gal (2 x 77.6 liter)

• Page 65: Limitation Placards

  DA 40 NG AFM Limitations 2.15 LIMITATION PLACARDS All limitation placards relevant for the base DA 40 NG airplane are shown below. A list of all placards is included in the Airplane Maintenance Manual (Doc. No. 6.02.15), Chapter 11. On the Instrument Panel: THIS AIRPLANE MAY ONLY BE OPERATED IN ACCORDANCE WITH THE AIRPLANE FLIGHT MANUAL IN THE «NORMAL»…

• Page 66
  Operating DA 40 NG AFM Limitations Next to Each of the Two Fuel Filler Necks: WARNING APPROVED FUEL JET-A1 or see Airplane Flight Manual Next to the Essential Bus Switch: Ess. Bus NOT for normal operation. See AFM. EASA Page 2 — 30 Rev.
• Page 67
  Operating DA 40 NG AFM Limitations In the Cowling, on the Door for the Oil Filler Neck: SHELL HELIX ULTRA 5W30 or see Airplane Flight Manual Next to the Flap Selector Switch: max. 110 KIAS max. 98 KIAS On the Fuel Valve:…
• Page 68
  Operating DA 40 NG AFM Limitations Next to the Baggage Compartment: Max. 30 kg/ 66 lb Baggage Tube Compartment: Max. 5 kg/ 11 lb Baggage Tray (if OÄM 40-164 installed, extended baggage compartment): EASA Page 2 — 32 Rev. 3 01-Jul-2014 Doc.
• Page 69
  Operating DA 40 NG AFM Limitations COCKPIT BAGGAGE BAGGAGE COMPARTMENT EXTENSION MAX. 45 kg [100 lb] MAX. 18 kg [40 lb] ARM: 3.89 m [153.1”] ARM: 4.54 m [178.7”] MAX. BAGGAGE TOTAL (COCKPIT BAGGAGE COMPARTMENT & EXTENSION): 45 kg [100 lb]…
• Page 70
  Operating DA 40 NG AFM Limitations On the Left Sidewall, Next to the Instrument Panel: Alternate Static OPEN CLOSED If Alternate Static is open Emergency Window and Cockpit Vent must be closed Beside the Door Locking Device: EMERGENCY EXIT: The keylock must be…

• Page 71: Other Limitations

  Operating DA 40 NG AFM Limitations 2.16 OTHER LIMITATIONS 2.16.1 TEMPERATURE The airplane may only be operated when its temperature prior to operation is not less than -40 °C (-40 °F). With the airplane cold soaked and its temperature below -20 °C (-4 °F) the use of an external pre-heater for the engine and pilot compartment prior to operation is mandatory.

• Page 72: Door Locking Device

  Operating DA 40 NG AFM Limitations 2.16.4 DOOR LOCKING DEVICE The canopy and the passenger door must not be key locked during operation of the airplane. 2.16.5 ELECTRONIC EQUIPMENT The use and switching on of electronic equipment other than that which is part of the equipment of the airplane is not permitted, as it could lead to interference with the airplane’s avionics.

• Page 73
  Emergency DA 40 NG AFM Procedures CHAPTER 3 EMERGENCY PROCEDURES Page INTRODUCTION ……..3-3 3.1.1 GENERAL .
• Page 74
  Emergency DA 40 NG AFM Procedures SMOKE AND FIRE ……..3-33 3.5.1 SMOKE AND FIRE ON GROUND .

• Page 75: Introduction

  Emergency DA 40 NG 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 76: Certain Airspeeds In Emergencies

  Emergency DA 40 NG AFM Procedures 3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES Event KIAS Airspeed for best glide angle (Flaps UP) 88 KIAS Flaps UP 83 KIAS Airspeed for emergency Flaps T/O 78 KIAS landing with engine off Flaps LDG 77 KIAS Page 3 — 4 Rev.

• Page 77: Instrument Indications In Prohibited (Red) Range

  Emergency DA 40 NG AFM Procedures 3.2 INSTRUMENT INDICATIONS IN PROHIBITED (RED) RANGE 3.2.1 ENGINE TEMPERATURE Engine coolant temperature is in the upper red range (too high / above 105 °C). Coolant temperatures above the limit value of 105 °C can lead to a total loss of power due to engine failure.

• Page 78
  Emergency DA 40 NG AFM Procedures During cruise: — Reduce power, or — Increase airspeed, if necessary by initiating a descent. — Check coolant temperature in green range. CAUTION If high coolant temperature is indicated and the COOL LVL (if G1000 is installed) or WATERLEV (if SED is installed)

• Page 79: Oil Temperature

  Emergency DA 40 NG AFM Procedures 3.2.2 OIL TEMPERATURE Engine oil temperature is in the upper red range (too high / above 140 °C). Oil temperatures above the limit value of 140 °C can lead to a total loss of power due to engine failure.

• Page 80
  Emergency DA 40 NG AFM Procedures CAUTION If high oil temperature is announced and the oil pressure indication is within the green range, it can be assumed that there is no technical defect in the engine oil system and that the above mentioned procedure can decrease the temperature(s).

• Page 81: Oil Pressure

  Emergency DA 40 NG AFM Procedures 3.2.3 OIL PRESSURE Engine oil pressure is in the lower red range (too low / below 0.9 bar). Oil pressures below the limit value of 0.9 bar can lead to a total loss of power due to engine failure.

• Page 82: Gearbox Temperature

  Emergency DA 40 NG AFM Procedures 3.2.4 GEARBOX TEMPERATURE Engine gearbox temperature is in the upper red range (too high / above 120 °C). Gearbox temperatures above the limit value of 120 °C can lead to a total loss of power due to engine failure.

• Page 83: L/R Fuel Temperature

  Emergency DA 40 NG AFM Procedures 3.2.5 L/R FUEL TEMPERATURE Fuel temperature is in the upper red range (too high / above 60 °C). Fuel temperatures above the limit value of 60 °C can lead to a noticeable reduction of the high pressure pump efficiency.

• Page 84: Fuel Pressure

  Emergency DA 40 NG AFM Procedures 3.2.6 FUEL PRESSURE Engine fuel pressure is low. 1. Fuel quantity ……check 2.

• Page 85: Alternator Amps

  Emergency DA 40 NG AFM Procedures 3.2.7 ALTERNATOR AMPS Engine alternator output is in the upper red range (too high / above 70 A). This warning is indicated when the consumption of electrical power is too high. Possible reasons are: A fault in wiring or equipment.

• Page 86: Alternator Fail

  Emergency DA 40 NG AFM Procedures 3.2.8 ALTERNATOR FAIL Engine alternator has failed. The batteries are the last remaining source of electrical power for about 30 minutes. 1. Circuit breakers ….. . check 2.

• Page 87: Engine Problems

  Emergency DA 40 NG AFM Procedures 3.3 ENGINE PROBLEMS 3.3.1 ENGINE PROBLEMS ON GROUND 1. POWER lever ……IDLE 2.

• Page 88: Engine Problems During Take-Off

  Emergency DA 40 NG AFM Procedures 3.3.2 ENGINE PROBLEMS DURING TAKE-OFF (a) Take-Off Can Still Be Aborted (Sufficient Runway Length Available) Land Straight Ahead: 1. POWER lever ……IDLE On the Ground: 2.

• Page 89
  Emergency DA 40 NG AFM Procedures (b) Take-Off Can No Longer Be Aborted 1. Airspeed ……immediate pitch down to avoid…

• Page 90: Engine Troubleshooting In Flight

  Emergency DA 40 NG AFM Procedures 3.3.3 ENGINE TROUBLESHOOTING IN FLIGHT WARNING Control over the flight attitude has priority over attempts to solve the current problem («first fly the airplane»). 1. Airspeed ……88 KIAS 2.

• Page 91
  Emergency DA 40 NG AFM Procedures WARNING Do not increase the POWER lever past the propeller speed of 1975 RPM or the setting determined in step 6. An increase of engine power beyond this setting leads into another power loss.
• Page 92
  Emergency DA 40 NG AFM Procedures Otherwise: 5. VOTER switch ….. . . switch back to AUTO to retain ECU redundancy If normal engine operation is restored continue flight and land as soon as possible.

• Page 93: Engine Failure In Flight

  Emergency DA 40 NG AFM Procedures 3.3.4 ENGINE FAILURE IN FLIGHT WARNING Control over the flight attitude has priority over attempts to solve the current problem («first fly the airplane»). NOTE As long as there is no major mechanical engine defect, the propeller will continue to windmill.

• Page 94: Restarting The Engine In Flight

  Emergency DA 40 NG AFM Procedures 3.3.5 RESTARTING THE ENGINE IN FLIGHT NOTE With a failed engine the propeller continues to windmill. A stopped propeller indicates a major mechanical engine defect. Starter assisted restart shall not be considered. Maximum restart altitude: 16,400 ft pressure altitude .

• Page 95
  Emergency DA 40 NG AFM Procedures If Engine Does Not Start: 10. Fuel valve ……EMERGENCY If Engine Does Not Start Adopt Glide Configuration: 11.

• Page 96: Defective Rpm Regulating System

  Emergency DA 40 NG AFM Procedures 3.3.6 DEFECTIVE RPM REGULATING SYSTEM WARNING In case of defective RPM regulating system, reduced engine performance should be anticipated. CAUTION Following a failure of the governor the RPM should be adjusted with the POWER lever.

• Page 97
  Emergency DA 40 NG AFM Procedures (b) Propeller Overspeed CAUTION Climb performance will be reduced. NOTE The propeller now works like a fixed pitch propeller. RPM is controlled by the engine power setting. Flight to the nearest airfield can be continued with a lower power setting and at a lower airspeed.
• Page 98
  Emergency DA 40 NG AFM Procedures If the Problem Does Not Clear: 7. Land on the nearest suitable airfield. If an Increased Climb Rate is Required: 8. Flaps ……. T/O position 9.
• Page 99
  Emergency DA 40 NG AFM Procedures (c) Propeller Underspeed 1. POWER lever ……as required If the Problem Does Not Clear 2.

• Page 100: Fuel Transfer Pump Failure

  Emergency DA 40 NG AFM Procedures 3.3.7 FUEL TRANSFER PUMP FAILURE 1. Fuel quantity ……check If Main Tank Fuel Quantity Low: 2.

• Page 101
  Emergency DA 40 NG AFM Procedures NOTE AUX tank quantity must not be less than 1 US gal and MAIN tank quantity must not be more than 14 US gal. 6. Fuel valve ……NORMAL 7.

• Page 102: Failures In The Electrical System

  Emergency DA 40 NG AFM Procedures 3.4 FAILURES IN THE ELECTRICAL SYSTEM 3.4.1 COMPLETE FAILURE OF THE ELECTRICAL SYSTEM 1. Circuit breakers ….. . check IN 2.

• Page 103: High Current

  Emergency DA 40 NG AFM Procedures 3.4.2 HIGH CURRENT If HIGH CURRENT (> 70 A) is indicated on the G1000 (if installed) or SED (if installed): 1. ESSENTIAL BUS ….. ON 2.

• Page 104: Starter Malfunction

  Emergency DA 40 NG AFM Procedures 3.4.3 STARTER MALFUNCTION If the starter does not disengage from the engine after starting (Starter engaged warning (STARTER) on the G1000 (if installed) or START on the White Wire annunciator (if installed) illuminates after the engine has started): On Ground: 1.

• Page 105: Smoke And Fire

  Emergency DA 40 NG AFM Procedures 3.5 SMOKE AND FIRE 3.5.1 SMOKE AND FIRE ON GROUND (a) Engine Fire When Starting on the Ground 1. Fuel valve ……OFF 2.

• Page 106
  Emergency DA 40 NG AFM Procedures (b) Electrical Fire with Smoke on the Ground 1. ELECTRIC MASTER ….OFF If the Engine Is Running: 2.

• Page 107: Smoke And Fire During Take-Off

  Emergency DA 40 NG AFM Procedures 3.5.2 SMOKE AND FIRE DURING TAKE-OFF (a) If Take-Off Can Still Be Aborted 1. POWER lever ……IDLE 2.

• Page 108
  Emergency DA 40 NG AFM Procedures (b) If Take-Off Cannot Be Aborted 1. Cabin heat ……OFF 2.
• Page 109
  Emergency DA 40 NG AFM Procedures CAUTION In case of extreme smoke development, the front canopy may be unlatched during flight. This allows it to partially open, in order to improve ventilation. The canopy will remain open in this position. Flight characteristics will not be affected significantly.

• Page 110: Smoke And Fire In Flight

  Emergency DA 40 NG AFM Procedures 3.5.3 SMOKE AND FIRE IN FLIGHT WARNING In the event of smoke or fire, prepare to land the airplane without delay while completing fire suppression and/or smoke evacuation procedures. If it cannot be visually verified that the fire has been completely extinguished, whether the smoke has cleared or not, land immediately.

• Page 111
  Emergency DA 40 NG AFM Procedures (b) Electrical Fire with Smoke in Flight 1. EMERGENCY switch (if installed) ..ON 2. AVIONIC MASTER ….OFF 3.

• Page 112: Gliding

  Emergency DA 40 NG AFM Procedures 3.6 GLIDING 1. Flaps ……. UP 2.

• Page 113: Emergency Landings

  Emergency DA 40 NG AFM Procedures 3.7 EMERGENCY LANDINGS NOTE For all airspeed tables in the following sections apply linear variations between weights. 3.7.1 EMERGENCY LANDING WITH ENGINE OFF CAUTION For emergency landing the adjustable backrests (if installed) must be fixed in the upright position.

• Page 114
  Emergency DA 40 NG AFM Procedures 9. Approach speed ….. . see table below: up to 940 kg 1000 kg…

• Page 115: Gear

  Emergency DA 40 NG AFM Procedures 3.7.2 LANDING WITH A DEFECTIVE TIRE ON THE MAIN LANDING GEAR CAUTION A defective (e.g. burst) tire is not usually easy to detect. The damage normally occurs during take-off or landing, and is hardly noticeable during fast taxiing. It is only during the roll-out after landing or at lower taxiing speeds that a tendency to swerve occurs.

• Page 116: Landing With Defective Brakes

  Emergency DA 40 NG AFM Procedures 3.7.3 LANDING WITH DEFECTIVE BRAKES In general, a landing on grass is recommended in order to reduce the landing run due to the greater rolling resistance. WARNING If sufficient time is remaining, the risk of fire in the event of a collision can be reduced as follows after a safe touch-down: — Fuel valve .

• Page 117: Recovery From An Unintentional Spin

  Emergency DA 40 NG AFM Procedures 3.8 RECOVERY FROM AN UNINTENTIONAL SPIN CAUTION Steps 1 to 4 must be carried out immediately and simultaneously. 1. POWER lever ……IDLE 2.

• Page 118: Other Emergencies

  Emergency DA 40 NG AFM Procedures 3.9 OTHER EMERGENCIES 3.9.1 ICING Unintentional Flight Into Icing Conditions 1. Leave the icing area (by changing altitude or turning back, in order to reach zones with a higher ambient temperature). 2. Pitot heating ……ON 3.

• Page 119
  Emergency DA 40 NG AFM Procedures 3.9.2 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. Since it occurs however usually together with flue gases, it can be detected.
• Page 120
  Emergency DA 40 NG AFM Procedures 3.9.3 UNLOCKED DOORS 1. Airspeed ……reduce immediately 2.
• Page 121
  Normal Operating DA 40 NG AFM Procedures CHAPTER 4A NORMAL OPERATING PROCEDURES Page 4A.1 INTRODUCTION ……..4A-2 4A.2 AIRSPEEDS FOR NORMAL OPERATING PROCEDURES .

• Page 122: Introduction

  Normal Operating DA 40 NG AFM Procedures 4A.1 INTRODUCTION Chapter 4A contains checklists and describes procedures for the normal operation of the airplane. 4A.2 AIRSPEEDS FOR NORMAL OPERATING PROCEDURES NOTE For all airspeed tables in the following Sections apply linear variations between weights.

• Page 123: Flight Characteristics

  (Flaps T/O) 4A.3 FLIGHT CHARACTERISTICS The DA 40 NG is to be flown with «the feet on the pedals“, meaning that coordinated flight in all phases and configurations shall be supported by dedicated use of the rudder and ailerons together.

• Page 124: Checklists For Normal Operating Procedures

  Normal Operating DA 40 NG AFM Procedures 4A.5 CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4A.5.1 PRE-FLIGHT INSPECTION I. Cabin Check a) MET, NAV, Mass & CG ….flight planning completed b) Airplane documents .

• Page 125
  Normal Operating DA 40 NG AFM Procedures n) Position lights, strobe lights (ACL) ..check OFF o) Taxi lights, landing lights ….check OFF p) ELECTRIC MASTER .
• Page 126
  Normal Operating DA 40 NG AFM Procedures II. Walk-Around Check, Visual Inspection CAUTION A visual inspection means: examination for damage, cracks, delamination, excessive play, load transmission, correct attachment and general condition. In addition control surfaces should be checked for freedom of movement.
• Page 127
  Normal Operating DA 40 NG AFM Procedures 2. Left Wing: a) Entire wing surface ….visual inspection b) Step ……. . visual inspection c) Air intake on lower wing surface .
• Page 128
  Normal Operating DA 40 NG AFM Procedures r) Foreign objects in aileron paddle ..visual inspection s) Trim tab ……visual inspection t) Flap and linkage .
• Page 129
  Normal Operating DA 40 NG AFM Procedures 5. Fuselage, Right Side: a) Fuselage skin ……visual inspection b) Static source .
• Page 130
  Normal Operating DA 40 NG AFM Procedures 7. Right Main Landing Gear: a) Landing gear strut or fairing (if installed) ..visual inspection b) Wear, tread depth of tires ….check c) Tire, wheel, brake .
• Page 131
  Normal Operating DA 40 NG AFM Procedures l) Wear, tread depth of tire ….check m) Wheel fairing (if installed) ….visual inspection n) Tow bar .

• Page 132: 5.2 Before Starting Engine

  Normal Operating DA 40 NG AFM Procedures 4A.5.2 BEFORE STARTING ENGINE CAUTION For take off the adjustable backrests (if installed) must be fixed in the upright position. NOTE The pilot must ensure that a passenger sitting on a front seat is instructed in the operation of the adjustable backrest (if installed).

• Page 133
  Normal Operating DA 40 NG AFM Procedures NOTE A slight downward pressure on the canopy may be required to ease the handle operation. 10. Parking brake ……set 11.

• Page 134: 5.3 Starting Engine

  Normal Operating DA 40 NG AFM Procedures 4A.5.3 STARTING ENGINE CAUTION Before starting the engine and until the engine is shut down, the canopy must be closed and latched in position 1 or 2 (‘cooling gap’) and the door must be closed and latched.

• Page 135
  Normal Operating DA 40 NG AFM Procedures 1. Strobe lights (ACL) ….ON 2. ENGINE MASTER ….ON 3.
• Page 136
  Normal Operating DA 40 NG AFM Procedures 7. Annunciations / STARTER (if G1000 is installed) or START (if White Wire annunciator panel is installed) . . check OFF 8. Annunciations / Oil pressure … . . check OK 9.
• Page 137
  Normal Operating DA 40 NG AFM Procedures 4A.5.4 BEFORE TAXIING 1. AVIONIC MASTER ….ON 2. Power lever ……as required, max. 50% if engine temperature below green range 3.
• Page 138
  Normal Operating DA 40 NG AFM Procedures NOTE If the G1000 avionics system and the autopilot GFC 700 are installed, the AFCS automatically conducts a preflight self-test upon initial power application. The preflight test is indicated by a white boxed PFT on the PFD. Upon successful…
• Page 139
  Normal Operating DA 40 NG AFM Procedures 4A.5.5 TAXIING 1. Parking brake ……release 2. Brakes ……test 3.
• Page 140
  Normal Operating DA 40 NG AFM Procedures 4A.5.6 BEFORE TAKE-OFF CAUTION For take-off the adjustable backrests (if installed) must be fixed in the upright position. 1. Position airplane into wind if possible. 2. Parking brake ……set 3.
• Page 141
  Normal Operating DA 40 NG AFM Procedures 11. Fuel valve ……check NORMAL 12.
• Page 142
  Normal Operating DA 40 NG AFM Procedures NOTE The engine oil / gearbox temperature has to be in the green range before starting the test sequence. Efficient engine warm up may require higher power settings (max. 50% engine power). Releasing the ECU TEST BUTTON or manipulating the POWER lever before the test sequence is completed will abort the test sequence.
• Page 143
  Normal Operating DA 40 NG AFM Procedures 8. ECU A/B FAIL (if G1000 is installed) or ECU A/B (if White Wire annunciator panel is installed) lights ….verify both OFF Test sequence completed.
• Page 144
  Normal Operating DA 40 NG AFM Procedures Available Power Check: 1. POWER lever ……MAX for 10 seconds 2.
• Page 145
  Normal Operating DA 40 NG AFM Procedures 4A.5.7 TAKE-OFF Normal Take-Off Procedure 1. Transponder ……as required 2.
• Page 146
  Normal Operating DA 40 NG AFM Procedures NOTE A spurious activation of the stall warning during take-off in crosswind conditions, operation on unpaved surfaces and gusty conditions may occur. 6. Airspeed for initial climb ….see table below:…
• Page 147
  Normal Operating DA 40 NG AFM Procedures 4A.5.8 CLIMB Procedure for Take-Off Climb 1. Flaps ……T/O 2.
• Page 148
  Normal Operating DA 40 NG AFM Procedures 4A.5.9 CRUISE 1. Flaps ……UP 2.
• Page 149
  Normal Operating DA 40 NG AFM Procedures 4A.5.10 FUEL TRANSFER CAUTION During normal operation fuel is taken from the main tank only. Therefore fuel must be transferred from the auxiliary tank to the main tank by activating the fuel transfer pump. The transfer rate is approximately 60 US gal/h (227 liter/h).
• Page 150
  Normal Operating DA 40 NG AFM Procedures 4A.5.11 DESCENT 1. POWER lever ……as required 2. Airspeed ……as required 3.
• Page 151
  Normal Operating DA 40 NG AFM Procedures 4A.5.12 APPROACH & LANDING Approach: NOTE If MÄM 40-574 is NOT carried out, a landing with a mass between 1216 kg (2681 lb) and 1280 kg (2822 lb) constitutes an abnormal operating procedure. Refer to Section 4B.7 — LANDING WITH HIGH LANDING MASS.
• Page 152
  Normal Operating DA 40 NG AFM Procedures Before Landing: 8. Airspeed ……see table below:…
• Page 153
  Normal Operating DA 40 NG AFM Procedures 4A.5.13 GO-AROUND 1. POWER lever ……MAX 2. Airspeed ……72 KIAS 3.
• Page 154
  Normal Operating DA 40 NG AFM Procedures 4A.5.14 AFTER LANDING 1. POWER lever ……IDLE 2. Brakes ……as required 3.
• Page 155
  Normal Operating DA 40 NG AFM Procedures 4A.5.15 ENGINE SHUT-DOWN 1. Parking brake ……set 2. POWER lever ……up to 10 % load for 1 minute 3.
• Page 156
  Normal Operating DA 40 NG AFM Procedures 4A.5.16 POST FLIGHT INSPECTION 1. Record any problem found in flight and during the post-flight check in the log book. 2. Park the airplane. 3. If necessary, moor the airplane. END OF CHECKLIST 4A.5.17 PARKING…
• Page 157
  Normal Operating DA 40 NG AFM Procedures 4A.5.18 FLIGHT IN RAIN NOTE Performance deteriorates in rain; this applies particularly to the take-off distance and to the maximum horizontal speed. The effect on the flight characteristics is minimal. Flight through very heavy rain should be avoided because of the associated visibility problems.
• Page 158
  Normal Operating DA 40 NG AFM Procedures Anti-microbial life fuel additives may be manually batch-blended into the fuel tanks. In this case introduce the additive while filling the tank after approximately the half tank is filled. Anti-icing fuel additives should not be batch-blended into the fuel tank. The fuel additive should be injected into a stream of fuel.
• Page 159
  Normal Operating DA 40 NG AFM Procedures (c) PRIST Hi-Flash Fuel Quantity Fuel Additive *, ** PRIST Hi-Flash (1500 ppm) Liter US gal 13.2 40.2 88.68 58.9 1.99 26.4 80.4 177.37 117.9 3.99 39.6 120.6 266.05 176.8 5.98 * Densities used for calculation: Fuel: 0.804 kg/l, PRIST Hi-Flash: 1.05 kg/l ** Do not batch blend 4A.5.20 FLIGHT AT HIGH ALTITUDE…
• Page 160
  Normal Operating DA 40 NG AFM Procedures Intentionally left blank. Page 4A — 40 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E…
• Page 161
  Abnormal Operating DA 40 NG AFM Procedures CHAPTER 4B ABNORMAL OPERATING PROCEDURES Page 4B.1 PRECAUTIONARY LANDING ……4B-2 4B.2 INSTRUMENT INDICATIONS OUTSIDE OF GREEN RANGE .

• Page 162: Precautionary Landing

  Abnormal Operating DA 40 NG AFM Procedures 4B.1 PRECAUTIONARY LANDING NOTE A landing of this type is only necessary when there is a reasonable suspicion that due to operational factors such as fuel shortage, weather conditions, etc. the possibility of endangering the airplane and its occupants by continuing the flight cannot be excluded.

• Page 163
  Abnormal Operating DA 40 NG AFM Procedures CAUTION If sufficient time is remaining, the risk of fire in the event of a collision with obstacles can be reduced as follows after a safe touch-down: 6. ENGINE MASTER ….OFF 7.

• Page 164: Instrument Indications Outside Of Green Range

  Abnormal Operating DA 40 NG AFM Procedures 4B.2 INSTRUMENT INDICATIONS OUTSIDE OF GREEN RANGE 4B.2.1 RPM High RPM 1. Reduce power. 2. Keep RPM within the green range using the POWER lever. NOTE An RPM in the yellow range is permissible for up to 5 minutes if required, e.g.

• Page 165: 2.2 Coolant Temperature

  Abnormal Operating DA 40 NG AFM Procedures 4B.2.2 COOLANT TEMPERATURE (a) High Coolant Temperature Proceed according to: Section 3.2.1 — ENGINE TEMPERATURE. (b) Low Coolant Temperature — Check for COOL LVL (if G1000 is installed) or WATERLEV (if SED is installed) caution message (low coolant level).

• Page 166: 2.3 Oil Temperature

  Abnormal Operating DA 40 NG AFM Procedures 4B.2.3 OIL TEMPERATURE a) High Oil Temperature Proceed according to: Section 3.2.2 — OIL TEMPERATURE. (b) Low Oil Temperature NOTE During an extended descent from high altitudes with a low power setting oil temperature may decrease. In this case an increase in power can help.

• Page 167: 2.4 Oil Pressure

  Abnormal Operating DA 40 NG AFM Procedures 4B.2.4 OIL PRESSURE High Oil Pressure — Check oil temperature. — Check coolant temperature. If the temperature is within the green range: — Expect false oil pressure indication. Keep monitoring temperatures. If the temperature is outside of the green range: — Reduce power on engine.

• Page 168: 2.5 Gearbox Temperature

  Abnormal Operating DA 40 NG AFM Procedures 4B.2.5 GEARBOX TEMPERATURE High Gearbox Temperature Proceed according to: Section 3.2.4 — GEARBOX TEMPERATURE. NOTE A cautionary (yellow) gearbox temperature range is not imposed by the engine manufacturer. However, there is a delay between power changes and gearbox temperature.

• Page 169: 2.6 Fuel Temperature

  Abnormal Operating DA 40 NG AFM Procedures 4B.2.6 FUEL TEMPERATURE (a) High Fuel Temperature Proceed according to: Section 3.2.5 — L/R FUEL TEMPERATURE. (b) Low Fuel Temperature — Increase power. — Reduce airspeed. CAUTION At low ambient temperature conditions and/or at high…

• Page 170: 2.7 Voltage

  Abnormal Operating DA 40 NG AFM Procedures 4B.2.7 VOLTAGE (a) Low Voltage Indication on the Ground with Engine Running — Terminate flight preparation. (b) Low Voltage During Flight 1. Circuit breakers ….. . check 2.

• Page 171: 2.8 Current

  Abnormal Operating DA 40 NG AFM Procedures 4B.2.8 CURRENT This caution is indicated when the consumption of electric power exceeds 60 A. 1. Electrical equipment ….switch OFF as necessary and…

• Page 172
  Abnormal Operating DA 40 NG AFM Procedures 4B.3 CAUTION-ALERTS 4B.3.1 ECU A FAILURE * Engine ECU A has failed or * is being tested during FADEC test procedure before take-off check. Depending on the type of failure, the ECU failure cautions are either ‘non latched’, i.e.
• Page 173
  Abnormal Operating DA 40 NG AFM Procedures 1. ALTERNATE AIR ….OPEN 2. Fuel pump ……ON 3.
• Page 174
  Abnormal Operating DA 40 NG AFM Procedures 4B.3.2 ECU B FAILURE * Engine ECU B has failed or * is being tested during FADEC test procedure before take-off check. Depending on the type of failure, the ECU failure cautions are either ‘non latched’, i.e.
• Page 175
  Abnormal Operating DA 40 NG AFM Procedures 1. ALTERNATE AIR ….OPEN 2. Fuel pump ……ON 3.
• Page 176
  Abnormal Operating DA 40 NG AFM Procedures 4B.3.3 FUEL QUANTITY LOW Left fuel quantity is low. 1. Fuel transfer pump ….ON 2.
• Page 177
  Abnormal Operating DA 40 NG AFM Procedures If the Caution Does Not Extinguish: — Be prepared for an emergency landing. — Proceed in accordance with Section 3.7.1 — EMERGENCY LANDING WITH ENGINE OFF. WARNING If air enters the high pressure fuel pump (e.g. empty fuel tank), an inspection of the pump is necessary prior to next flight.
• Page 178
  Abnormal Operating DA 40 NG AFM Procedures 4B.3.4 COOLANT LEVEL Engine coolant level is low. A low coolant caution alert may indicate a loss of coolant. This will subsequently lead to decreased engine cooling capability/loss of engine power due to engine failure.
• Page 179
  Abnormal Operating DA 40 NG AFM Procedures 4B.3.5 PITOT HEATING FAILURE Pitot heating system has failed. If in Icing Conditions: 1. Expect loss of airspeed indication. 2. Leave icing zone / refer to Section 3.9.1 — ICING. END OF CHECKLIST 4B.3.6 ENGINE CAUTION (IF WHITE WIRE ANNUNCIATOR PANEL IS INSTALLED)
• Page 180
  Abnormal Operating DA 40 NG AFM Procedures 4B.4 CANOPY IN COOLING GAP POSITION CAUTION If take-off was inadvertently done with the canopy in the cooling gap position, do not attempt to close the canopy in flight. Land the airplane and close the canopy on ground.
• Page 181
  Abnormal Operating DA 40 NG AFM Procedures 4B.5 FAILURES IN FLAP OPERATING SYSTEM Failure in Position Indication or Function 1. FLAPS position ….. . . check visually 2.
• Page 182
  Abnormal Operating DA 40 NG AFM Procedures (b) Only T/O Available: Airspeed ……see table below:…
• Page 183
  Abnormal Operating DA 40 NG AFM Procedures 4B.6 LIGHTNING STRIKE 1. Airspeed ……as low as practicable, do not exceed v (refer to Section 2.2)
• Page 184
  Abnormal Operating DA 40 NG AFM Procedures 4B.7 LANDING WITH MASS ABOVE MAXIMUM LANDING MASS NOTE Refer to Section 4A.5.12 — APPROACH AND LANDING for landings with a mass up to 1216 kg (2681 lb), and if MÄM 40- 574 is carried out for landings with a mass up to 1280 kg (2822 lb).
• Page 185
  Abnormal Operating DA 40 NG AFM Procedures 4B.8 STARTING ENGINE WITH EXTERNAL POWER 4B.8.1 BEFORE STARTING ENGINE 1. Pre-flight inspection ….complete 2.
• Page 186
  Abnormal Operating DA 40 NG AFM Procedures 13. Friction device on POWER lever ..adjusted 14. Alternate air ……check CLOSED 15.
• Page 187
  Abnormal Operating DA 40 NG AFM Procedures 4B.8.2 STARTING ENGINE CAUTION Do not operate the engine starter motor for more than 10 seconds, because of possible overheating of the starter motor. If the STARTER annunciation on the G1000 (if installed) or…
• Page 188
  Abnormal Operating DA 40 NG AFM Procedures Annunciations / GLOW ON (if G1000 is installed) or GLOW (if White Wire annunciator panel is installed) … . check ON NOTE GLOW ON (if G1000 is installed) or GLOW (if White Wire annunciator panel is installed) is indicated only when the engine is cold.
• Page 189
  Abnormal Operating DA 40 NG AFM Procedures 8. Annunciations / Oil pressure … . . check OK 9. Circuit breakers ….. . . check all IN 10.
• Page 190
  Abnormal Operating DA 40 NG AFM Procedures Intentionally left blank. Page 4B — 30 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E…
• Page 191
  DA 40 NG AFM Performance CHAPTER 5 PERFORMANCE Page INTRODUCTION ……..5-2 USE OF THE PERFORMANCE TABLES AND DIAGRAMS .

• Page 192: Introduction

  Performance DA 40 NG 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 they allow comprehensive and sufficiently accurate flight planning. The values…

• Page 193
  DA 40 NG AFM Performance For operation at outside air temperatures lower than provided in these tables, use data for lowest temperature shown. Use extreme caution for operation at outside air temperatures higher than provided in the tables (areas are indicated with a diagonal line).

• Page 194: Performance Tables And Diagrams

  Performance DA 40 NG AFM 5.3 PERFORMANCE TABLES AND DIAGRAMS 5.3.1 AIRSPEED CALIBRATION Airspeed Indicator Calibration Indicated Calibrated Airspeed [KCAS] Airspeed [KIAS] at Various Flap Settings Not applicable % % % % % % Not applicable % % % % % % Page 5 — 4 Rev.

• Page 195: Fuel Flow

  DA 40 NG AFM Performance 5.3.2 FUEL FLOW NOTE The fuel calculations on the FUEL CALC portion of the G1000 MFD do not use the airplane’s fuel quantity indicators. The values shown are numbers which are calculated from the last fuel quantity update done by the pilot and actual fuel flow data.

• Page 196: Pressure Altitude — Density Altitude

  Performance DA 40 NG AFM 5.3.3 PRESSURE ALTITUDE — DENSITY ALTITUDE Conversion from pressure altitude to density altitude. 14000 4000 12000 3500 10000 3000 14000 4000 2500 12000 8000 8000 3500 10000 2000 3000 6000 2500 8000 1500 4000 2000…

• Page 197: International Standard Atmosphere

  DA 40 NG AFM Performance 5.3.4 INTERNATIONAL STANDARD ATMOSPHERE Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 5 — 7…

• Page 198
  Performance DA 40 NG AFM 5.3.5 STALLING SPEEDS Stalling Speeds at Various Flight Masses Indicated airspeed may not be accurate at stall. Airspeeds, most forward CG, power off: Bank Angle 1000 kg (2205 lb) 0° 30° 45° 60° Flaps KIAS…
• Page 199
  DA 40 NG AFM Performance Bank Angle 1310 kg (2888 lb) 0° 30° 45° 60° Flaps KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 5 — 9…

• Page 200: Wind Components

  Performance DA 40 NG AFM 5.3.6 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 kt Result: Crosswind component 16 kt Max.

• Page 201: Take-Off Distance

  DA 40 NG AFM Performance 5.3.7 TAKE-OFF DISTANCE Conditions: — POWER lever ….. . MAX — Flaps ……T/O — Runway .

• Page 202
  Performance DA 40 NG AFM If brakes are not held while applying power, distances apply where full power setting is complete. WARNING For a safe take-off the available runway length must be at least equal to the take-off distance over a 50 ft (15 m) obstacle.
• Page 203
  DA 40 NG AFM Performance Take-Off Distance — Normal Procedure — 1310 kg / 2888 lb Weight: 1310 kg / 2888 lb Flaps: 67 KIAS Power: 72 KIAS Runway: dry, paved, level Press. Outside Air Temperature — [°C] / [°F] Distance Alt.
• Page 204
  Performance DA 40 NG AFM Take-Off Distance — Normal Procedure — 1280 kg / 2822 lb Weight: 1280 kg / 2822 lb Flaps: 67 KIAS Power: 72 KIAS Runway: dry, paved, level Press. Outside Air Temperature — [°C] / [°F] Distance Alt.
• Page 205
  DA 40 NG AFM Performance Take-Off Distance — Normal Procedure — 1200 kg / 2645 lb Weight: 1200 kg / 2645 lb Flaps: 65 KIAS Power: 70 KIAS Runway: dry, paved, level Press. Outside Air Temperature — [°C] / [°F] Distance Alt.
• Page 206
  Performance DA 40 NG AFM Take-Off Distance — Normal Procedure — 1100 kg / 2425 lb Weight: 1100 kg / 2425 lb Flaps: 61 KIAS Power: 67 KIAS Runway: dry, paved, level Press. Outside Air Temperature — [°C] / [°F] Distance Alt.

• Page 207: Climb Performance — Take-Off Climb

  DA 40 NG AFM Performance 5.3.8 CLIMB PERFORMANCE — TAKE-OFF CLIMB Conditions: — POWER lever ….92% or max. 2100 RPM — Flaps ….T/O — Airspeed .

• Page 208
  Performance DA 40 NG AFM Take — Off Climb — Flaps T/O Power: 92% or max. Flaps: T/O 2100 RPM : 72 KIAS Rate of Climb — [ft/min] Press. Press. Outside Air Temperature — [°C] / [°F] Alt. Alt. [ft]…
• Page 209
  DA 40 NG AFM Performance Take — Off Climb — Flaps T/O Power: 92% or max. Flaps: T/O 2100 RPM : 72 KIAS Rate of Climb — [ft/min] Press. Press. Outside Air Temperature — [°C] / [°F] Alt. Alt. [ft]…

• Page 210: Climb Performance — Cruise Climb

  Performance DA 40 NG AFM 5.3.9 CLIMB PERFORMANCE — CRUISE CLIMB Conditions: — POWER lever ….92% or max. 2100 RPM — Flaps ….UP — Airspeed .

• Page 211
  DA 40 NG AFM Performance Cruise Climb — Flaps UP Power: 92% or max. Flaps: UP 2100 RPM : 88 KIAS Rate of Climb — [ft/min] Press. Press. Outside Air Temperature — [°C] / [°F] Alt. Alt. [ft] 2000 4000…
• Page 212
  Performance DA 40 NG AFM Cruise Climb — Flaps UP Power: 92% or max. Flaps: UP 2100 RPM : 88 KIAS Rate of Climb — [ft/min] Press. Press. Outside Air Temperature — [°C] / [°F] Alt. Alt. [ft] 2000 4000…

• Page 213: Time, Fuel And Distance To Climb

  DA 40 NG AFM Performance 5.3.10 TIME, FUEL AND DISTANCE TO CLIMB Conditions: — Power lever ……92% or max. 2100 RPM — Flaps .

• Page 214
  Performance DA 40 NG AFM Time, Fuel and Distance to Climb Power: 92% or max. 2100 Flaps: UP 88 KIAS Press. Press. Dist- Alt. Alt. Time Fuel ance [ft] [°C] [°F] [kt] [ft/min] [m/s] [min] [NM] gal] 2000 4000 1219…
• Page 215
  DA 40 NG AFM Performance Time, Fuel and Distance to Climb Power: 92% or max. 2100 Flaps: UP 88 KIAS Press. Press. Dist- Alt. Alt. Time Fuel ance [ft] [°C] [°F] [kt] [ft/min] [m/s] [min] [NM] gal] 2000 4000 1219…
• Page 216
  Performance DA 40 NG AFM 5.3.11 CRUISE PERFORMANCE NOTE For operation without wheel fairings a performance reduction of 4% TAS at all power settings must be expected. Conditions: — Flaps ……UP — Landing gear .

• Page 217: Cruise Performance

  DA 40 NG AFM Performance Cruise Performance Outside Air Temperature — [°C] ISA-10 ISA+10 ISA+20 ISA+30 Press. Alt. [ft] / [m] [kt] [kt] [kt] [kt] [kt] gal/h] gal/h] gal/h] gal/h] gal/h] 2000 4000 1219 6000 1829 8000 2438 10000 3048…

• Page 218: Landing Distances

  Performance DA 40 NG AFM 5.3.12 LANDING DISTANCES Conditions: — Power lever ……IDLE — Flaps ……LDG, T/O or UP — Runway .

• Page 219
  DA 40 NG AFM Performance 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 landing distance. CAUTION The factors in the above corrections are typical values. On wet ground or wet soft grass covered runways the landing distance may become significantly longer than stated above.
• Page 220
  Performance DA 40 NG AFM Landing Distance — Flaps LDG — 1310 kg / 2888 lb Weight: 1310 kg / 2888 lb Flaps: 77 KIAS Power: IDLE % % % Runway: dry, paved, level Outside Air Temperature — [°C] / [°F] Press.
• Page 221
  DA 40 NG AFM Performance Landing Distance — Flaps LDG — 1280 kg / 2822 lb Weight: 1280 kg / 2822 lb Flaps: 77 KIAS Power: IDLE % % % Runway: dry, paved, level Outside Air Temperature — [°C] / [°F] Press.
• Page 222
  Performance DA 40 NG AFM Landing Distance — Flaps LDG — 1200 kg / 2645 lb Weight: 1200 kg / 2645 lb Flaps: 76 KIAS Power: IDLE % % % Runway: dry, paved, level Outside Air Temperature — [°C] / [°F] Press.
• Page 223
  DA 40 NG AFM Performance Landing Distance — Flaps LDG — 1100 kg / 2425 lb Weight: 1100 kg / 2425 lb Flaps: 72 KIAS Power: IDLE % % % Runway: dry, paved, level Outside Air Temperature — [°C] / [°F] Press.
• Page 224
  Performance DA 40 NG AFM 5.3.13 LANDING DISTANCE — ABNORMAL FLAP POSITION Landing Distance — Abnormal Flap Position — 1310 kg / 2888 lb Weight: 1310 kg / 2888 lb Flaps: T/O or UP 78 KIAS (Flaps T/O) Power: IDLE…
• Page 225
  DA 40 NG AFM Performance Landing Distance — Abnormal Flap Position — 1280 kg / 2822 lb Weight: 1280 kg / 2822 lb Flaps: T/O or UP 78 KIAS (Flaps T/O) Power: IDLE % % % 83 KIAS (Flaps UP) Runway: dry, paved, level Outside Air Temperature — [°C] / [°F]…
• Page 226
  Performance DA 40 NG AFM Landing Distance — Abnormal Flap Position 1200 kg / 2645 lb Weight: 1200 kg / 2645 lb Flaps: T/O or UP 78KIAS (Flaps T/O) Power: IDLE % % % 82 KIAS (Flaps UP) Runway: dry, paved, level Outside Air Temperature — [°C] / [°F]…
• Page 227
  DA 40 NG AFM Performance Landing Distance — Abnormal Flap Position 1100 kg / 2425 lb Weight: 1100 kg / 2425 lb Flaps: T/O or UP 74 KIAS (Flaps T/O) Power: IDLE % % % 78 KIAS (Flaps UP) Runway: dry, paved, level Outside Air Temperature — [°C] / [°F]…
• Page 228
  Performance DA 40 NG AFM 5.3.14 GO-AROUND CLIMB PERFORMANCE Conditions: — Power lever ……MAX — Flaps ……LDG — Airspeed .
• Page 229
  DA 40 NG AFM Performance Go-Around Climb Performance % % % % % % % Flaps: LDG Power: MAX 77 KIAS at 1280 kg (2822 lb) and 1310 kg (2888 lb) 76 KIAS at 1200 kg (2645 lb) 72 KIAS at 1100 kg ( 2425 lb)
• Page 230
  Performance DA 40 NG AFM Go-Around Climb Performance % % % % % % % Flaps: LDG Power: MAX 77 KIAS at 1280 kg (2822 lb) and 1310 kg (2888 lb) 76 KIAS at 1200 kg (2645 lb) 72 KIAS at 1100 kg ( 2425 lb)
• Page 231
  DA 40 NG AFM Performance 5.3.15 GLIDE The following table shows the glide ratio and the resulting maximum horizontal distance in nautical miles per 1000 ft (305 m) of altitude loss in a glide traveled in still air. Glide ratio…
• Page 232
  Performance DA 40 NG AFM 5.3.16 APPROVED NOISE DATA Maximum Flight Mass 1280 kg (2825 lb): ICAO Annex 16 Chapter X ….74.5 dB(A) CS-36 Subpart C .
• Page 233
  DA 40 NG AFM Mass & Balance CHAPTER 6 MASS AND BALANCE / EQUIPMENT LIST Page INTRODUCTION ……..6-2 DATUM PLANE .

• Page 234: Introduction

  Mass & Balance DA 40 NG 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 235: Datum Plane

  DA 40 NG AFM Mass & 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 236
  Mass & Balance DA 40 NG AFM MASS AND BALANCE REPORT (Continuous report on structural or equipment changes) DA 40 NG Serial No.: Registration: Page No.: Changes in Mass Addition (+) Subtraction (-) Current Empty Mass Moment Moment Moment Description of Entry No.

• Page 237: Flight Mass And Center Of Gravity

  Mass & Balance 6.4 FLIGHT MASS AND CENTER OF GRAVITY The following information enables you to operate your DA 40 NG 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 238
  Mass & Balance DA 40 NG AFM 5. Graphical method: Diagram 6.4.2 — LOADING DIAGRAM is used to determine the moments. The masses and moments for the individual items of loading are added. Then Diagram 6.4.5 — PERMISSIBLE MOMENT RANGE is used to check whether the total moment associated with the total mass is in the admissible range.
• Page 239
  DA 40 NG AFM Mass & Balance 6.4.1 MOMENT ARMS The most important lever arms aft of the Datum Plane: — Front seats : 2.30 m 90.6 in — Rear seats : 3.25 m 128.0 in — Wing tank (Standard & Long Range) : 2.63 m…
• Page 240
  Mass & Balance DA 40 NG AFM 6.4.2 LOADING DIAGRAM Page 6 — 8 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E…
• Page 241
  DA 40 NG AFM Mass & Balance 6.4.3 CALCULATION OF LOADING CONDITION a) Standard Tank Configuration DA 40 NG Your DA 40 NG (Example) CALCULATION OF Mass Moment Mass Moment LOADING CONDITION [kg] [kgm] [kg] [kgm] [lb] [in.lb] [lb] [in.lb] 1.
• Page 242
  Mass & Balance DA 40 NG AFM DA 40 NG Your DA 40 NG (Example) CALCULATION OF Mass Moment Mass Moment LOADING CONDITION [kg] [kgm] [kg] [kgm] [lb] [in.lb] [lb] [in.lb] 9. Total mass and total moment 1,070 2,598.8 with empty fuel tanks (Total…
• Page 243
  DA 40 NG AFM Mass & Balance b) Long Range Tank Configuration DA 40 NG Your DA 40 NG (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 2,180.8…
• Page 244
  Mass & Balance DA 40 NG AFM DA 40 NG Your DA 40 NG (Example) CALCULATION OF Mass Moment Mass Moment LOADING CONDITION [kg] [kgm] [kg] [kgm] [lb] [in.lb] [lb] [in.lb] 9. Total mass and total moment 1,070 2,598.8 with empty fuel tanks (Total…
• Page 245
  DA 40 NG AFM Mass & Balance 6.4.4 PERMISSIBLE CENTER OF GRAVITY RANGE If MÄM 40-662 is installed: MTOM 1310 kg (2888 lb) 1310 The CG’s shown in the diagram are from the examples in Tables 6.4.3 — CALCULATION OF LOADING CONDITION a) and b), rows 9 and 11.
• Page 246
  Mass & Balance DA 40 NG AFM 6.4.5 PERMISSIBLE MOMENT RANGE Page 6 — 14 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E…

• Page 247: Equipment List And Equipment Inventory

  DA 40 NG AFM Mass & Balance 6.5 EQUIPMENT LIST AND EQUIPMENT INVENTORY All equipment approved for installation in the DA 40 NG is shown in the Equipment List below. The items of equipment installed in your particular airplane are indicated in the appropriate column.

• Page 261
  Airplane DA 40 NG AFM Description CHAPTER 7 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS Page INTRODUCTION ……..7-2 AIRFRAME .

• Page 262: Introduction

  Airplane DA 40 NG AFM 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. 7.2 AIRFRAME Fuselage The GFRP fuselage is of semi monocoque molded construction. 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 263: Flight Controls

  Airplane DA 40 NG AFM 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 by a trim tab on the elevator, which is operated by a Bowden cable.

• Page 264
  Airplane DA 40 NG AFM Description Flaps Construction: GFRP/CFRP composite sandwich. Hinges: There are 6 hinges, which are hinge pins mounted in an aluminum bracket. They are secured in position by a roll pin. The absence of this roll pin can lead to the loss of the hinge pin and a consequent loss of flight safety.
• Page 265
  Airplane DA 40 NG AFM 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 266
  Airplane DA 40 NG AFM Description Elevator Construction: GFRP sandwich. Hinges: 5 hinges. Operation: Steel push-rods; Two of the bellcrank bearings are accessible to visual inspection next to the lower hinge of the rudder. The elevator horn and its bearing, as well as the connection to the push-rod, can be visually inspected at the upper end of the rudder.
• Page 267
  Airplane DA 40 NG AFM Description Elevator Trim The trim control is a black wheel in the center console to the rear of the power lever. To guard against over-rotating, the trim wheel incorporates a friction device. A mark on the wheel shows the take-off (T/O) position.

• Page 268: Instrument Panel

  Airplane DA 40 NG AFM Description 7.4 INSTRUMENT PANEL EECU BUS FUE L FUEL EECU A EECU B EECU A EECU B PUMP A PUMP B ESSENTIAL BUS HORIZON AHRS COM1 GPS /NAV 1 MASTER CONTROL MAIN BUS AVIONICS BUS…

• Page 269
  Airplane DA 40 NG AFM Description Instrument Panel with G1000 Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 7 — 9…
• Page 270
  Airplane DA 40 NG AFM Description Instrument Panel with SED, MED and White Wire Annunciator Panel Page 7 — 10 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E…
• Page 271
  Airplane DA 40 NG AFM Description Major Instruments and Controls Electric Master key switch 21 ELT control unit Fuel Transfer switch 22 Accessory power socket Pitot Heat switch Avionics Master switch 24 Primary Flight Display (PFD) Essential Bus switch 25 Audio amplifier / Intercom /…
• Page 272
  Airplane DA 40 NG AFM Description NOTE The figures on previous pages show the typical DA 40 NG installation position for the equipment. The actual installation may vary due to the approved equipment version. Cockpit Ventilation Ventilation in the front is provided by the movable ventilation over nozzles (16) in the instrument panel.
• Page 273
  Airplane DA 40 NG AFM Description Cabin Air Control Cabin Air Exhaust NACA Air Inlet Sealed Cabin Air Control RH Cover plate Rear Cabin Air Control Cabin Air Sealed Exhaust Cabin Air Control LH Cover plate NACA Air Inlet Doc. # 6.01.15-E Rev.

• Page 274: Landing Gear

  Airplane DA 40 NG AFM Description 7.5 LANDING GEAR The landing gear consists of a main landing gear of spring steel struts, and a free-castering nose wheel which is spring-loaded by an elastomer package. The wheel fairings are removable. When flying without wheel fairings, it should be noted that there is a reduction in some areas of performance (see Chapter 5).

• Page 275
  Airplane DA 40 NG AFM Description Hydraulic System Schematic Flexible Hose Flexible Hose Vented Vented Master Master Plug Plug Cylinders Cylinders Fluid Level Brake Fluid Reservoir Pilot’s Pedals Co-Pilot’s Pedals Flexible Hose LOCK PARKING BRAKE Flexible Hose RELEASE Parking Brake Valve…

• Page 276: Seats And Safety Harnesses

  Airplane DA 40 NG AFM 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 the maintenance and inspection of the underlying controls. Covers on the control sticks prevent loose objects from falling into the area of the controls.

• Page 277
  Airplane DA 40 NG AFM Description in the upright position. If possible, set the backrest lever to the „locked“ position. The mechanism must be repaired at the next scheduled inspection. The lumbar support can be adjusted by operating the lumbar support lever mounted on the outboard side of the seat pan.

• Page 278: Baggage Compartment

  Airplane DA 40 NG AFM Description 7.7 BAGGAGE COMPARTMENT The baggage compartment is behind the seat backs of the rear seats. Without a baggage net, no baggage may be loaded. As options, a baggage tube or a baggage extension (OÄM 40-164) or a short baggage extension (OÄM 40-331) may be installed.

• Page 279
  Airplane DA 40 NG AFM Description Do not key-lock the front canopy before flight to assure emergency evacuation from outside. A window on the left and right hand side of the canopy can be opened for additional ventilation or as emergency window.
• Page 280
  Airplane DA 40 NG AFM Description Emergency Axe If OÄM 40-326 is incorporated an emergency axe is installed on the floor panel under the co-pilot’s seat (see Figure below). If the canopy can not be opened in case of an emergency use the emergency axe to break through the canopy.

• Page 281: Power Plant

  Airplane DA 40 NG AFM Description 7.9 POWER PLANT 7.9.1 ENGINE, GENERAL The installed Austro Engine E4-A engine has the following specifications: Liquid-cooled four-cylinder four-stroke engine with wet sump lubrication Inline construction Common rail direct injection Propeller speed reducing gear 1:1.69…

• Page 282: Operating Controls

  Airplane DA 40 NG AFM Description 7.9.2 OPERATING CONTROLS POWER lever The engine performance is controlled by the power lever, situated on the large center console. ‘Front’ and ‘rear’ are defined in relation to the direction of flight. This lever is used to set the desired engine power LOAD (%)

• Page 283
  Airplane DA 40 NG AFM Description ELECTRIC MASTER The key can be switched into three positions: Disconnecting battery power. Connecting battery power to the power distribution system. START Starting the engine. ENGINE MASTER The engine can only be cranked with the ENGINE MASTER switched to ON. To shut down the engine the ENGINE MASTER is switched to OFF.
• Page 284
  Airplane DA 40 NG AFM Description ECU TEST POWER lever at IDLE: By pushing and holding the button until the end of the procedure, the self-test of each engine control unit is started. The procedure is possible on the ground only. Otherwise the test will not start.

• Page 285: Propeller

  Airplane DA 40 NG AFM Description 7.9.3 PROPELLER An mt-Propeller MTV-6-R/190-69 hydraulically regulated 3-bladed constant speed propeller is installed. The propeller has wood-composite blades with fiber-reinforced plastic coating and metal leading edge protection; in the region of the propeller hub the leading edge is coated with adhesive PU tape.

• Page 286
  Airplane DA 40 NG AFM 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 287: Fuel System

  Airplane DA 40 NG AFM Description 7.9.4 FUEL SYSTEM Standard Tank Schematic Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 7 — 27…

• Page 288
  Airplane DA 40 NG AFM Description Long Range Tank Schematic Page 7 — 28 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E…
• Page 289
  Airplane DA 40 NG AFM Description Normal Fuel Supply & Engine Fuel Valve Normal Fuel Transfer Normal Emergency Fuel Filter Fuel Pumps Main Tank Auxiliary Tank Fuel Supply Transfer Pump Fuel Return Fuel Transfer Emergency Fuel Supply & Engine Fuel Valve…
• Page 290
  Airplane DA 40 NG AFM Description Fuel is stored in the fuel tanks which are located in the wings. Normally fuel is taken from the MAIN tank (left wing). The fuel is injected with high pressure directly into the combustion chambers. The injection nozzles (one per cylinder) are supplied with fuel by the common rail.
• Page 291
  Airplane DA 40 NG AFM Description CAUTION Switching the fuel valve to the EMERGENCY position will start the transferring of fuel with the help of the electrically driven and engine driven fuel pumps from the auxiliary tank through the fuel return line to the main tank at a rate of approximately 45 US gal/h (170 liter/h) with FUEL PUMPS switch in OFF position.
• Page 292
  Airplane DA 40 NG AFM Description Fuel Valve The fuel valve is located at the center console. The selectable positions are NORMAL, EMERGENCY and OFF. The desired position is reached by turning the valve handle while pulling up the safety latch on the valve handle. This is to ensure that a selection is not made unintentionally.
• Page 293
  Airplane DA 40 NG AFM Description A gascolator is located at the bottom side of the fuselage which is the lowest point of the entire fuel system. A drain valve (pull to drain) is mounted to the gascolator, to allow the remove of water and sediment which has collected in the fuel system.
• Page 294
  Airplane DA 40 NG AFM Description Alternate Means For Fuel Quantity Indication The alternate means for fuel quantity indication allows the fuel quantity in the tank to be determined during the pre-flight inspection. It functions according to the principle of communicating containers. The fuel quantity measuring device has a recess which fits the airfoil of the wing.

• Page 295: Cooling System

  Airplane DA 40 NG AFM Description 7.9.5 COOLING SYSTEM The engine is liquid cooled. The liquid cooling system consists of a radiator circuit (coolant heat exchanger) and a bypass circuit (cabin heat exchanger). The radiator circuit is only open during hot coolant temperatures. This assures that a cold engine will warm up quickly.

• Page 296
  Airplane DA 40 NG AFM Description 7.9.6 TURBO CHARGER SYSTEM Engine Air Intake Intercooler Air Filter Box Air Filter Turbine Engine Alternate Air Valve Charger Waste Gate Exhaust The intake air is compressed in the compressor which is driven by the turbine, and is subsequently cooled down in the intercooler.

• Page 297: Oil Systems

  Airplane DA 40 NG AFM Description 7.9.7 OIL SYSTEMS The engine has two separate oil systems. Lubrication System (Engine and Turbo Charger) The engine lubrication is a wet sump lubrication system. Oil is cooled by a separate cooler on the underside of the engine.

• Page 298: Electrical System

  Airplane DA 40 NG AFM Description 7.10 ELECTRICAL SYSTEM Electrical System Schematic Page 7 — 38 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E…

• Page 299: General

  Airplane DA 40 NG AFM Description 7.10.1 GENERAL The DA 40 NG has a 28 Volt DC system, which can be sub-divided into: — Power generation — Storage — Distribution — Consumers Power Generation Power generation is provided by a 70 Ampère alternator (generator) which is mounted on the bottom left side of the engine.

• Page 300
  Airplane DA 40 NG AFM Description Storage Main battery power is stored in a 24 V, 13.6 Ah lead-acid battery mounted behind the baggage compartment frame. The main battery is connected to the battery bus via the battery-relay which is installed in the relay junction box behind the baggage compartment frame.
• Page 301
  Airplane DA 40 NG AFM Description Distribution Electrical power is distributed via the hot battery bus, the battery bus 1, the battery bus 2, the ECU-bus, the main bus, the essential bus and the avionic bus. Hot Battery Bus: The hot battery bus is directly connected to the main-battery installed in the relay junction box and cannot be disconnected from the main battery.
• Page 302
  Airplane DA 40 NG AFM Description Main Bus: The main bus is connected to the battery bus via the power-relay. It provides power to the consumers directly connected to the main bus and the avionic bus via the avionic master-relay. The AVIONIC MASTER switch must be set to ON to connect the main bus to the avionic bus.
• Page 303
  Airplane DA 40 NG AFM Description Voltmeter The voltmeter shows the voltage of the essential bus. Under normal operating conditions the alternator voltage is shown, otherwise it is the voltage of the main battery. Ammeter The ammeter displays the intensity of current which is supplied to the electrical system by the alternator, including the current for battery charging.
• Page 304
  Airplane DA 40 NG AFM Description Instrument Lighting With a rotary button (INSTRUMENT) in the left-hand section of the instrument panel the internal lighting of the instruments is switched on and its brightness is adjusted. Right Wing Tip Light Assy…
• Page 305
  Airplane DA 40 NG AFM Description Pitot Heating The Pitot probe, which provides measurement for the Pitot-static system, is electrically heated. The heating is activated with a switch (PITOT) on the row of switches on the instrument panel. The temperature is automatically kept constant by means of a thermal switch on the Pitot probe, and as an additional safety measure a thermal fuse is built in.
• Page 306
  Airplane DA 40 NG AFM Description 7.10.2 ENGINE CONTROL UNIT / ECU Engine Control and Regulation The Electrical ECU is used to control the engine actuator (e.g. fuel injector) according to the engine sensor information. The ECU monitors, controls and regulates all important parameters for engine operation.
• Page 307
  Airplane DA 40 NG AFM Description In accordance with the received signals and a comparison with the programmed characteristic diagrams the necessary inputs are calculated and transmitted by the following signal lines to the engine: — Signal for propeller governor pressure valve…
• Page 308
  Airplane DA 40 NG AFM Description 7.11 PITOT-STATIC SYSTEM Total pressure is measured at the leading edge of a Pitot probe under the left wing. Static pressure is measured through the static ports in the rear fuselage. To protect against dirt and condensation there are filters in the system.
• Page 309
  DA 40 NG AFM Handling CHAPTER 8 AIRPLANE HANDLING, CARE AND MAINTENANCE Page INTRODUCTION ……..8-2 AIRPLANE INSPECTION INTERVALS .

• Page 310: Introduction

  Handling DA 40 NG AFM 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. 6.02.15) lists certain inspection and maintenance requirements which must be followed if the airplane is to retain a new plane performance and reliability.

• Page 311: Airplane Alterations Or Repairs

  DA 40 NG AFM Handling 8.3 AIRPLANE ALTERATIONS OR REPAIRS Alterations or repairs of the airplane may be carried out only according to the Airplane Maintenance Manual, Doc. No. 6.02.15, and only by authorized personnel. 8.4 GROUND HANDLING / ROAD TRANSPORT 8.4.1 GROUND HANDLING WITHOUT TOW BAR…

• Page 312: Ground Handling With Tow Bar

  Handling DA 40 NG AFM 8.4.2 GROUND HANDLING WITH TOW BAR For pushing or pulling the airplane on the ground, it is recommended to use the tow bar which is available from the manufacturer. The tow bar is bent apart and engaged in the appropriate holes in the nose wheel fairing as shown on the picture below.

• Page 313
  DA 40 NG AFM Handling WARNING The tow bar must be removed before starting the engine. 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.

• Page 314: Parking

  Handling DA 40 NG AFM 8.4.3 PARKING For short term parking, the airplane must be positioned into the wind, the parking brake must be engaged and the wing flaps must be in the retracted position. For extended and unattended parking, as well as in unpredictable wind conditions, the airplane must be anchored to the ground or placed in a hangar.

• Page 315
  +25 °C (77 °F), in order to prevent excessive heat generation within the instrument panel which can cause damage to the equipment. Such a canopy cover is available from Diamond Aircraft Industries, P/N: S_30172. Doc. # 6.01.15-E Rev. 3…
• Page 316
  Handling DA 40 NG AFM Page 8 — 8 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E…

• Page 317: Mooring

  DA 40 NG AFM Handling 8.4.4 MOORING The tail fin of the airplane has 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 318: Road Transport

  Handling DA 40 NG AFM 8.4.7 ROAD TRANSPORT For transporting the airplane on the road it is recommended that an open trailer be used. All airplane components must be stored on a cushioned surface and secured to avoid any movement during transportation.

• Page 319: Cleaning And Care

  DA 40 NG AFM Handling 8.5 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. 8.5.1 PAINTED SURFACES The entire surface of the airplane is painted with a white weatherproof two component paint.

• Page 320: Propeller

  Handling DA 40 NG AFM 8.5.3 PROPELLER Damage and malfunctions during operation must be inspected by authorized personnel. Surface The manufacturer uses PU paint or acrylic paint which is resistant to almost any solvent. The blades may be treated with commercial automotive cleaning agents or preservatives.

• Page 321: Ground De-Icing

  DA 40 NG AFM Handling 8.6 GROUND DE-ICING Approved de-icing fluids are: Manufacturer Name „Kilfrost“ TKS 80 „Aeroshell“ Compound 07 Any source AL-5 (DTD 406B) 1. Remove any snow from the airplane using a soft brush. 2. Spray de-icing fluid onto ice-covered surfaces using a suitable spray bottle.

• Page 322
  Handling DA 40 NG AFM Intentionally left blank Page 8 — 14 Rev. 3 01-Jul-2014 Doc. # 6.01.15-E…
• Page 323
  DA 40 NG AFM Supplements CHAPTER 9 SUPPLEMENTS Page INTRODUCTION ……..9-2 LIST OF SUPPLEMENTS .
• Page 324
  Supplements DA 40 NG AFM 9.1 INTRODUCTION Chapter 9 contains information concerning additional (optional) equipment of the DA 40 NG. 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.
• Page 325
  01 Apr 2010 G1000 Synthetic Vision 15 Mar 2011 Technology Recirculating Cabin — Air Cooling 01 Jul 2014 Use of the DA 40 NG as Tow- 01 Jul 2014 Plane Doc. # 6.01.15-E Rev. 3 01-Jul-2014 Page 9 — 3…
• Page 326
  Supplements DA 40 NG AFM Airplane S/N: Registration: Date: applicable Sup. Rev. Title Date Landing Gear with Large Tyres and 1280 kg Maximum Landing 01 Jul 2014 Mass Cold Weather Operation 01 Jul 2014 Diesel Operation 06 Dec 2013 Page 9 — 4 Rev.