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Diamond DA 40 Flight Manual

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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...

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