Diamond DA 62 Flight Manual
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Diamond DA 62 Flight Manual

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  • Page 2: Jan-2019 1

    DA 62 AFM Introduction Intentionally left blank. Page 0 - 0a Rev. 0 Doc. # 11.01.05-E 11-Jan-2019...
  • 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 62 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 62 AFM 0.1 APPROVAL The content of approved chapters is approved by Transport Canada Civil Aviation. 0.2 RECORD OF REVISIONS All revisions of this manual, with the exception of: • Temporary Revisions, • updates of the modification level (Section 1.1), •...
  • Page 5 DA 62 AFM Introduction Rev. Chapter Date of Approval Date Reason Page(s) Approval No. Signature Revision Date Inserted Doc. # 11.01.05-E Rev. 0 Page 0 - 3 11-Jan-2019...

  • Page 6: Table Of Contents

    Introduction DA 62 AFM 0.3 LIST OF EFFECTIVE PAGES Page Date Page Date 11-Jan-2019 11-Jan-2019 0-0a 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 1-10 11-Jan-2019 11-Jan-2019 1-11 11-Jan-2019 11-Jan-2019 1-12 11-Jan-2019...
  • Page 7 DA 62 AFM Introduction Page Date Page Date DOT-appr. 2-1 11-Jan-2019 DOT-appr. 2-28 11-Jan-2019 DOT-appr. 2-2 11-Jan-2019 DOT-appr. 2-29 11-Jan-2019 DOT-appr. 2-3 11-Jan-2019 DOT-appr. 2-30 11-Jan-2019 DOT-appr. 2-4 11-Jan-2019 DOT-appr. 2-31 11-Jan-2019 DOT-appr. 2-5 11-Jan-2019 DOT-appr. 2-32 11-Jan-2019 DOT-appr. 2-6 11-Jan-2019 DOT-appr.

  • Page 8: Table Of Contents

    Introduction DA 62 AFM Page Date Page Date 11-Jan-2019 3-28 11-Jan-2019 11-Jan-2019 3-29 11-Jan-2019 11-Jan-2019 3-30 11-Jan-2019 11-Jan-2019 3-31 11-Jan-2019 11-Jan-2019 3-32 11-Jan-2019 11-Jan-2019 3-33 11-Jan-2019 11-Jan-2019 3-34 11-Jan-2019 11-Jan-2019 3-35 11-Jan-2019 11-Jan-2019 3-36 11-Jan-2019 3-10 11-Jan-2019 3-37 11-Jan-2019 3-11...

  • Page 9: Table Of Contents

    DA 62 AFM Introduction Page Date Page Date 3-55 11-Jan-2019 4A-1 11-Jan-2019 3-56 11-Jan-2019 4A-2 11-Jan-2019 3-57 11-Jan-2019 4A-3 11-Jan-2019 3-58 11-Jan-2019 4A-4 11-Jan-2019 3-59 11-Jan-2019 4A-5 11-Jan-2019 3-60 11-Jan-2019 4A-6 11-Jan-2019 3-61 11-Jan-2019 4A-7 11-Jan-2019 3-62 11-Jan-2019 4A-8 11-Jan-2019...

  • Page 10: Table Of Contents

    Introduction DA 62 AFM Page Date Page Date 4A-28 11-Jan-2019 4A-55 11-Jan-2019 4A-29 11-Jan-2019 4A-56 11-Jan-2019 4A-30 11-Jan-2019 4A-57 11-Jan-2019 4A-31 11-Jan-2019 4A-58 11-Jan-2019 4A-32 11-Jan-2019 4A-59 11-Jan-2019 4A-33 11-Jan-2019 4A-60 11-Jan-2019 4A-34 11-Jan-2019 4A-61 11-Jan-2019 4A-35 11-Jan-2019 4A-62 11-Jan-2019...

  • Page 11: Table Of Contents

    DA 62 AFM Introduction Page Date Page Date 4B-1 11-Jan-2019 4B-28 11-Jan-2019 4B-2 11-Jan-2019 4B-29 11-Jan-2019 4B-3 11-Jan-2019 4B-30 11-Jan-2019 4B-4 11-Jan-2019 4B-31 11-Jan-2019 4B-5 11-Jan-2019 4B-32 11-Jan-2019 4B-6 11-Jan-2019 4B-33 11-Jan-2019 4B-7 11-Jan-2019 4B-34 11-Jan-2019 4B-8 11-Jan-2019 4B-35 11-Jan-2019...

  • Page 12: Table Of Contents

    Introduction DA 62 AFM Page Date Page Date 11-Jan-2019 5-28 11-Jan-2019 11-Jan-2019 5-29 11-Jan-2019 11-Jan-2019 5-30 11-Jan-2019 11-Jan-2019 5-31 11-Jan-2019 11-Jan-2019 5-32 11-Jan-2019 11-Jan-2019 5-33 11-Jan-2019 11-Jan-2019 5-34 11-Jan-2019 11-Jan-2019 5-35 11-Jan-2019 11-Jan-2019 5-36 11-Jan-2019 5-10 11-Jan-2019 5-37 11-Jan-2019 5-11...

  • Page 13: Table Of Contents

    DA 62 AFM Introduction Page Date Page Date 5-55 11-Jan-2019 5-82 11-Jan-2019 5-56 11-Jan-2019 5-83 11-Jan-2019 5-57 11-Jan-2019 5-84 11-Jan-2019 5-58 11-Jan-2019 5-85 11-Jan-2019 5-59 11-Jan-2019 5-86 11-Jan-2019 5-60 11-Jan-2019 5-87 11-Jan-2019 5-61 11-Jan-2019 5-88 11-Jan-2019 5-62 11-Jan-2019 5-89 11-Jan-2019...

  • Page 14: Table Of Contents

    Introduction DA 62 AFM Page Date Page Date 11-Jan-2019 6-29 11-Jan-2019 11-Jan-2019 Page Date 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 11-Jan-2019 6-10 11-Jan-2019 11-Jan-2019 6-11 11-Jan-2019 11-Jan-2019 6-12 11-Jan-2019 7-10 11-Jan-2019 6-13 11-Jan-2019...

  • Page 15: Table Of Contents

    DA 62 AFM Introduction Page Date Page Date 7-26 11-Jan-2019 7-54 11-Jan-2019 7-27 11-Jan-2019 7-55 11-Jan-2019 7-28 11-Jan-2019 7-56 11-Jan-2019 7-29 11-Jan-2019 7-57 11-Jan-2019 7-58 11-Jan-2019 7-30 11-Jan-2019 7-59 11-Jan-2019 7-31 11-Jan-2019 7-60 11-Jan-2019 7-32 11-Jan-2019 7-61 11-Jan-2019 7-33 11-Jan-2019...

  • Page 16: Table Of Contents

    Introduction DA 62 AFM Page Date Page Date 7-82 11-Jan-2019 11-Jan-2019 7-83 11-Jan-2019 11-Jan-2019 7-84 11-Jan-2019 11-Jan-2019 7-85 11-Jan-2019 11-Jan-2019 7-86 11-Jan-2019 11-Jan-2019 7-87 11-Jan-2019 11-Jan-2019 7-88 11-Jan-2019 11-Jan-2019 7-89 11-Jan-2019 11-Jan-2019 7-90 11-Jan-2019 11-Jan-2019 7-91 11-Jan-2019 8-10 11-Jan-2019 7-92...
  • Page 17 DA 62 AFM Introduction TABLE OF CONTENTS Chapter GENERAL (a non-approved chapter) ........1 OPERATING LIMITATIONS (an approved chapter).

  • Page 18: Table Of Contents

    DA 62 AFM General CHAPTER 1 GENERAL Page INTRODUCTION ........1-2 CERTIFICATION BASIS .

  • Page 19: Introduction

    General DA 62 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 AWM 523 requirement.
  • Page 20 Cockpit Reference Guide is the bag on the rear side of the forward right seat. CAUTION The DA 62 is a twin 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 21: Certification Basis

    General DA 62 AFM 1.2 CERTIFICATION BASIS The DA 62 has been approved by Transport Canada in accordance with the Canadian Airworthiness Manual (AWM) Chapter 523, Type Certificate No. A-273 Category of Airworthiness: NORMAL 1.3 WARNINGS, CAUTIONS AND NOTES Special statements in the Airplane Flight Manual concerning the safety or operation of...

  • Page 22: Dimensions

    DA 62 AFM General 1.4 DIMENSIONS NOTE All dimensions shown below are approximate. Overall Dimensions Span : 14.57 m 47 ft 10 in Length : 9.17 m 30 ft 1 in Height : 2.82 m 9 ft 3 in Wing...
  • Page 23 General DA 62 AFM Wing Flaps Area (total, left + right) : 2.16 m² 23.25 sq.ft. Horizontal Tail Area : 2.91 m 31.32 sq.ft. Elevator area : 0.82 m² 8.83 sq.ft. Angle of incidence : -2° relative to longitudinal axis of airplane...

  • Page 24: Definitions And Abbreviations

    DA 62 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 25 General DA 62 AFM Maximum Structural Cruising Speed. This speed may be exceeded only in smooth air, and then only with caution. Rotation Speed. Stalling Speed, or the minimum continuous speed at which the airplane is still controllable in the given configuration.
  • Page 26 DA 62 AFM General QNH: Theoretical atmospheric pressure at MSL, calculated from the elevation of the of the measuring point above MSL, and the actual atmospheric pressure at the measuring point. Density Altitude: Altitude in ISA conditions at which the air density is equal to the current air density.
  • Page 27 General DA 62 AFM MET: Weather, weather advice. NAV: Navigation, route planning. RoC: Rate of Climb. (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.
  • Page 28 DA 62 AFM General Maximum Landing Mass: The highest mass for landing conditions at the maximum descent velocity. This velocity was used in the strength calculations to determine the landing gear loads during a particularly hard landing. Moment Arm: The horizontal distance from the Datum Plane to the Center of Gravity of a component.
  • Page 29 General DA 62 AFM (f) Designation of the Circuit Breakers on the Instrument Panel LH MAIN BUS: COM1 COM Radio No. 1 GPS/NAV1 Global Positioning System and NAV Receiver No. 1 XPDR Transponder ENG INST Engine Instruments PITOT Pitot Heating System...
  • Page 30 DA 62 AFM General AVIONICS BUS: COM2 COM Radio No. 2 GPS/NAV2 Global Positioning System and NAV Receiver No. 2 AUDIO Audio Panel AFCS/ESP/USP Auto Pilot System Lightning Detection System Automatic Direction Finder Distance Measuring Equipment Wx RDR Weather Radar...
  • Page 31 General DA 62 AFM RH ENG ECU BUS: ECU BUS RH ECU Bus ECU B RH ECU B ECU A RH ECU A RH BUS: ALT.RH RH Alternator BATT Battery RH ENGINE: FUEL PUMP A RH ECU A Fuel Pump...
  • Page 32 DA 62 AFM General (i) Miscellaneous AFM: Airplane Flight Manual AMM: Airplane Maintenance Manual ATC: Air Traffic Control AWM: Airworthiness Manual CAR: Canadian Airworthiness Regulation CFRP: Carbon Fiber Reinforced Plastic DOT: Department of Transport EASA: European Aviation Safety Agency EPU:...

  • Page 33: Units Of Measurement

    General DA 62 AFM 1.6 UNITS OF MEASUREMENT 1.6.1 CONVERSION FACTORS Dimension SI Units US Units Conversion Length [in] inches [mm] millimeters [mm] / 25.4 = [in] [ft] feet meters [m] / 0.3048 = [ft] [NM] nautical [km] kilometers [km] / 1.852 = [NM]...
  • Page 34 DA 62 AFM General Dimension SI Units US Units Conversion Intensity of electric ampères current Electric charge [Ah] ampère-hours (battery capacity) Electric volts potential Time [sec] seconds Doc. No. 11.01.05-E Rev. 0 11-Jan-2019 Page 1 - 17...

  • Page 35: Conversion Chart Liters / Us Gallons

    General DA 62 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 36: Three-View Drawing

    DA 62 AFM General 1.7 THREE-VIEW DRAWING Doc. No. 11.01.05-E Rev. 0 11-Jan-2019 Page 1 - 19...

  • Page 37: G1000 Avionics System

    The display may indicate clear areas between intense returns, but this does not necessarily mean it is safe to fly between them. As installed on the DA 62, the Garmin GWX 70 has a demonstrated range of 160 nautical miles. Refer to Garmin G1000 Pilot’s Guide for the DA 62, P/N 190-01895-( ) for Garmin G1000 or...

  • Page 38: Source Documentation

    DA 62 AFM General 1.9 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: Avionics System

    General DA 62 AFM Documents: E-124, Operation and Installation Manual Hydraulically controlled variable pitch propeller MTV -5, -6, -9, -11, -12, -14, -15, -16, -21, -22, -25 1.9.3 AVIONICS SYSTEM Address: Garmin International, Inc. 1200 East 151 Street Olathe, Kansas 66062...

  • Page 40: Operating Limitations

    DA 62 AFM Operating Limitations CHAPTER 2 OPERATING LIMITATIONS Page INTRODUCTION ........2-3 AIRSPEED.
  • Page 41 Operating Limitations DA 62 AFM 2.16.6 AUTOPILOT LIMITATIONS ......2-42 2.16.7 SMOKING ........2-43 2.16.8 GROUND OPERATION .
  • Page 42 DA 62 AFM Operating Limitations 2.1 INTRODUCTION Chapter 2 of this Airplane Flight Manual provides operating limitations, instrument markings and placards necessary for the safe operation of the airplane, its powerplants, standard systems and standard equipment. The limitations included in this Chapter are approved.
  • Page 43 Operating Limitations DA 62 AFM 2.2 AIRSPEED Airspeed KIAS Remarks above 2200 kg 141 KIAS Do not make full or abrupt control surface (4850 lb) to Operating movement above this 2300 kg (5071 lb) maneuvering speed. above 2100 kg 138 KIAS...
  • Page 44 DA 62 AFM Operating Limitations Airspeed KIAS Remarks Minimum 70 KIAS With one engine control speed inoperative, keep airborne airspeed above this 76 KIAS limit. Max. structural cruising speed 162 KIAS Do not exceed this speed except in smooth air, and then only with caution.
  • Page 45 Operating Limitations DA 62 AFM 2.3 AIRSPEED INDICATOR MARKINGS Marking KIAS Significance White arc 64 -119 KIAS Operating range with flaps fully extended. If MÄM 62-001 is carried out: 69 - 119 KIAS 70 - 162 KIAS Green arc Normal operating range.
  • Page 46 DA 62 AFM Operating Limitations 2.4 POWER-PLANT LIMITATIONS a) Number of engines b) Engine manufacturer Austro Engine c) Engine designation E4P-C d) RPM limitations (shown as propeller RPM) Maximum take-off (rpm) 2300 RPM Maximum continuous (rpm) 2200 RPM Maximum overspeed 2500 RPM max.
  • Page 47 Operating Limitations DA 62 AFM h) Oil temperature Minimum -30 °C (-22 °F) Maximum 139 °C (282 °F) Normal range 50 °C - 135 °C (122 °F - 275 °F) i) Gearbox temperature Minimum -30 °C (-22 ° F) Minimum (full load) 35 °C (95 °F)
  • Page 48 DA 62 AFM Operating Limitations k) Fuel temperature Minimum -30 °C (-22 °F) Maximum 60 °C (140 °F) l) Fuel pressure (absolute) Minimum 4 bar (58.0 psi) Maximum 7 bar (101.5 psi) NOTE The fuel pressure is not indicated on the G1000; a fuel pressure warning will illuminate on the PFD if the pressure is below limit.
  • Page 49 Operating Limitations DA 62 AFM t) Oil specification: SHELL HELIX ULTRA SAE Grade 5W-30: ADDINOL SUPER POWER MV 0537 BP VISCO 5000 REPSOL ELITE COMMON RAIL GULF FORMULA GMX AEROSHELL Oil Diesel Ultra CASTROL Edge 5W-30 A3 CASTROL Edge Professional A3...
  • Page 50 DA 62 AFM Operating Limitations CAUTION Only engine oils conforming to MB 229.5 specification are approved by Austro Engine GmbH to be used for operation. Use only one type of approved E4 engine oil for an oil change. NOTE It is not recommended to mix different SAE grades.
  • Page 51 Operating Limitations DA 62 AFM Up to 10,000 ft pressure altitude: Max. engine OFF time [° C] [° F] [minutes] below -15 below 5 -15 to -5 5 to 23 above -5 above 23 x) Restart airspeed (starter) max. 80 KIAS or airspeed for a stationary propeller, whichever is lower.
  • Page 52 DA 62 AFM Operating Limitations 2.5 ENGINE INSTRUMENT MARKINGS Engine instrument markings and their color code significance are shown in the tables below. Indi- Yellow Green Yellow cation arc/bar arc/bar arc/bar arc/bar arc/bar lower caution normal caution upper prohibited range...
  • Page 53 Operating Limitations DA 62 AFM 2.6 WARNING, CAUTION AND ADVISORY ALERTS 2.6.1 WARNING, CAUTION AND ADVISORY ALERTS ON THE G1000 NOTE The alerts described in the following are displayed on the Garmin G1000. Section 7.10 includes a detailed description of the alerts.
  • Page 54 DA 62 AFM Operating Limitations Warning Alerts Meaning/Cause (Red) L/R ALTN AMPS Left/Right engine alternator output is in the upper red range (too high/> 70 A). L/R ENG FIRE Left/Right engine fire detected. L/R STARTER Left/Right engine starter is engaged.
  • Page 55 Operating Limitations DA 62 AFM Color and Significance of the Caution Alerts on the G1000 Caution Alerts Meaning/Cause (Amber) A fault was detected by the left/right engine ECU A (one reset of minor faults is possible) L/R ECU A FAIL ECU A is being tested during FADEC-test procedure during the 'Before Take-Off Check'.
  • Page 56 DA 62 AFM Operating Limitations Caution Alerts Meaning/Cause (Amber) DEIC PRES HI De-icing pressure is high (if installed). DEIC PRES LO De-icing pressure is low (if installed). Color and Significance of the Advisory Alerts on the G1000 Advisory Alerts Meaning/Cause...
  • Page 57 Operating Limitations DA 62 AFM 2.6.2 OTHER WARNING ALERTS Warning Alerts on the Instrument Panel Warning Alert Meaning/Cause (Red) GEAR UNSAFE Illuminates if the landing gear is neither in the final up nor in WARNING LIGHT the down & locked position.
  • Page 58 DA 62 AFM Operating Limitations 2.7 MASS (WEIGHT) Mass (Weight) Value Minimum flight mass 1600 kg 3329 lb Maximum take-off mass (if MÄM 62-001 is carried out) 2300 kg 5071 lb Maximum take-off mass 1999 kg 4407 lb (if MÄM 62-001 is NOT carried out or if OÄM 62-018 AND MÄM 62-001 are carried out)
  • Page 59 Operating Limitations DA 62 AFM 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 floor of the nose baggage compartment.
  • Page 60 DA 62 AFM Operating Limitations 2.9 APPROVED MANEUVERS The airplane is certified in the Normal Category in accordance with AWM 523. 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 61 Operating Limitations DA 62 AFM 2.10 MANEUVERING LOAD FACTORS NOTE The tables below show structural limitations. The load factor limits for the engine must also be observed. Refer to the corresponding operation manual for the engine. at v at v...

  • Page 62: Flight Crew

    DA 62 AFM Operating Limitations 2.11 OPERATING ALTITUDE The maximum operating altitude is 20,000 ft (6,096 m) pressure altitude. 2.12 FLIGHT CREW Minimum crew 1 (one person) Maximum number of occupants 5 (five persons) 7 (seven persons, if OÄM 62-019 is installed) 2.13 KINDS OF OPERATION...
  • Page 63 Operating Limitations DA 62 AFM NOTE Many of the items of minimum equipment listed in the following table are integrated in the G1000. For Daytime In Addition for In Addition for VFR Flights Night VFR Flights IFR Flights Flight &...
  • Page 64 DA 62 AFM Operating Limitations For Daytime VFR In Addition for In Addition for Flights Night VFR Flights IFR Flights Engine * fuel qty. (2x) * ammeter Instruments * oil press. (2x) * voltmeter * oil temp. (2x) * coolant temp. (2x)
  • Page 65 Operating Limitations DA 62 AFM For Daytime VFR In Addition for In Addition for Flights Night VFR Flights IFR Flights Other * stall warning * Pitot heating * sufficient charge operational system system for the internal minimum battery of the...
  • Page 66 DA 62 AFM Operating 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 67 Operating Limitations DA 62 AFM 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 68 DA 62 AFM Operating Limitations Auxiliary Tanks Main Tanks Total (if installed) US gal Liter US gal Liter US gal Liter Total fuel quantity 2 x 26.0 2 x 98.4 2 x 18.5 2 x 70.0 2 x 44.5 2 x 168.4 Usable fuel 2 x 25.0...
  • Page 69 Operating Limitations DA 62 AFM 2.15 LIMITATION PLACARDS All limitation placards are shown below. A list of all placards is included in the Airplane Maintenance Manual (Doc. No. 7.02.25), Chapter 11. The following limitation placards are in the forward view of the pilot:...

  • Page 70: Doc. No. 11.01.05-E Rev. 0 11-Jan-2019 Page

    DA 62 AFM Operating Limitations On the Instrument Panel: LANDING GEAR = 205 KIAS = 162 KIAS On the Emergency Landing Gear Extension Lever: EMERGENCY Gear Extension Max. 162 KIAS On the Instrument Panel: Standard Tank: Auxiliary Tank (if installed): max.
  • Page 71 Operating Limitations DA 62 AFM (a) Next to Each of the Two Fuel Filler Necks; (b) In Addition Next to Each of the Two Auxiliary Fuel Filler Necks (if installed): WARNING APPROVED FUEL JET-A1, or see Airplane Flight Manual In Each Cowling, on the Door for the Oil Filler Neck:...
  • Page 72 DA 62 AFM Operating Limitations Next to the Flap Selector Switch: In the Nose Baggage Compartments: LH Nose Baggage Compartment: RH Nose Baggage Compartment: Max. Baggage: Max. Baggage: 30 kg (66 lb) 30 kg (66 lb) Doc. No. 11.01.05-E Rev. 0...
  • Page 73 Operating Limitations DA 62 AFM In the Rear Baggage Compartment: If OÄM 62-019 is NOT carried out: If OÄM 62-019 is carried out: Page 2 - 34 Rev. 0 11-Jan-2019 Doc. No. 11.01.05-E approved...
  • Page 74 DA 62 AFM Operating Limitations Beside the Door Locking Device Installed in the Passengers' Door: EMERGENCY EXIT: The keylock must be unlocked during flight! On the Bottom Center of the Instrument Panel: NO SMOKING On the Armrest with Integrated Keypad (if OÄM 62-031 is carried out):...

  • Page 75: Other Limitations

    Operating Limitations DA 62 AFM 2.16 OTHER LIMITATIONS 2.16.1 FUEL TEMPERATURE From -30 °C to 60 °C (from -22 °F to 140 °F). 2.16.2 BATTERY CHARGE Take-off for a Night VFR or IFR flight with a discharged battery is not permitted.
  • Page 76 DA 62 AFM Operating Limitations 2.16.4 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 77 Operating Limitations DA 62 AFM 2.16.5 GARMIN G1000 AVIONICS SYSTEM The Garmin G1000 Cockpit Reference Guide, P/N 190-01896-( ) or Garmin G1000 NXi Cockpit Reference Guide, P/N 190-01905-( ), appropriate revision must be immediately available to the flight crew. The G1000 must utilize the software Garmin 010-01895-00, the Garmin G1000 NXi must utilize the software Garmin 010-01895-04, approved software in accordance with the mandatory service bulletin DAI MSB 62-003, latest version.
  • Page 78 DA 62 AFM Operating Limitations Software Part Number Approved Function Version 006-B0083-() GS1, GS2 006-B0082-() NAV1, NAV2 NOTE The database version is displayed on the MFD power-up page immediately after system power-up and must be acknowledged. The remaining system software versions can be verified on the AUX group sub-page 5, "AUX-SYSTEM...
  • Page 79 Operating Limitations DA 62 AFM approach not approved for GPS overlay with the G1000 GPS receiver is not authorized. Use of the G1000 VOR/ILS receiver to fly approaches not approved for GPS require VOR/ILS navigation data to be present on the display.
  • Page 80 DA 62 AFM Operating Limitations 6. When AHRS is required to meet the items listed in the minimum operational equipment (serviceable) table in Section 2.13 of this AFM, operation is prohibited in the following areas: North of 72° N latitude at all longitudes.
  • Page 81 AFCS/ESP/USP circuit breaker is prohibited until the cause of the malfunction has been determined and corrected. 4. The Garmin G1000 Cockpit Reference Guide for the Diamond DA 62, P/N 010-01896-( ) or Garmin G1000 NXi Cockpit Reference Guide for the Diamond DA62, P/N 010-01905-( ) approved revision must be immediately available to the flight crew.
  • Page 82 DA 62 AFM Operating Limitations The GFC 700 AFCS pre-flight test must be successfully completed prior to use of the autopilot, flight director, yaw damper or manual electric trim. A pilot with the seat belt fastened must occupy the left pilot's seat during all operations.
  • Page 83 Operating Limitations DA 62 AFM 2.16.10 USE OF THE SUN VISORS The sun visors (if installed) may only be used during cruise. During all other phases of flight, the sun visors must be locked in the fully upward position. 2.16.11 PDF/MFD CONTROL UNIT (KEYPAD) The PFD/MFD control unit must be stowed during take-off and landing all emergencies and abnormal operating procedures.

  • Page 84: Emergency Procedures

    Emergency DA 62 AFM Procedures CHAPTER 3 EMERGENCY PROCEDURES Page INTRODUCTION ........3-4 3.1.1 GENERAL .
  • Page 85 Emergency DA 62 AFM Procedures G1000 FAILURES ........3-19 3.5.1 NAVIGATION INFORMATION FAILURE .
  • Page 86 Emergency DA 62 AFM Procedures 3.11 FAILURES IN THE ELECTRICAL SYSTEM ....3-57 3.11.1 COMPLETE FAILURE OF THE ELECTRICAL SYSTEM . . 3-57 3.11.2 HIGH CURRENT .
  • Page 87 Emergency DA 62 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 88 Emergency DA 62 AFM Procedures 3.1.2 CERTAIN AIRSPEEDS IN EMERGENCIES Event One engine inoperative minimum Flaps UP 76 KIAS control speed (air) v Flaps T/O 70 KIAS One engine inoperative speed for 87 KIAS up to 1999 kg (4407 lb)
  • Page 89 Emergency DA 62 AFM Procedures 3.2 AIRPLANE-RELATED G1000 WARNINGS 3.2.1 WARNINGS/GENERAL "Warning" means that the non-observation of the corresponding procedure leads to an immediate or important degradation in flight safety. The warning text is displayed in red color. A warning chime tone of 1.5 seconds duration will sound and repeat without delay until the alarm is acknowledged by the crew.
  • Page 90 Emergency DA 62 AFM Procedures During cruise: Reduce power on affected engine. Increase airspeed. Check coolant temperature in green range. CAUTION If high coolant temperature is indicated and the L/R COOL LVL caution message is not displayed, it can be assumed...
  • Page 91 Emergency DA 62 AFM Procedures 3.2.3 L/R OIL TEMP L/R OIL TEMP Left/Right engine oil temperature is in the upper red range (too high/above 139 °C). Oil temperatures above the limit value of 139 °C can lead to a total loss of power due to engine failure.
  • Page 92 Emergency DA 62 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 93 Emergency DA 62 AFM Procedures 3.2.4 L/R OIL PRES L/R OIL PRES Left/Right 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 94 Emergency DA 62 AFM Procedures 3.2.5 L/R GBOX TEMP Left/Right engine gearbox temperature is in the upper L/R GBOX TEMP 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 95 Emergency DA 62 AFM Procedures 3.2.6 L/R FUEL TEMP Left/Right fuel temperature is in the upper red range L/R FUEL TEMP (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 96 Emergency DA 62 AFM Procedures 3.2.7 L/R FUEL PRESS L/R FUEL PRESS Left/Right engine fuel pressure is low. 1. Fuel quantity ......check 2.
  • Page 97 Emergency DA 62 AFM Procedures 3.2.9 L/R ENG FIRE L/R ENG FIRE Left/Right engine fire detected. Engine fire can lead to a total loss of power due to engine failure as well as severe structural damage. Proceed according to the following procedures as applicable: 3.11.1 - ENGINE FIRE ON GROUND...
  • Page 98 Emergency DA 62 AFM Procedures 3.2.11 DOOR OPEN L/R DOOR OPEN Left/Right door is not closed and locked. REAR DOOR OPEN Rear door is not closed and locked. FWD DOOR OPEN Left or right baggage door is/are not closed and locked.
  • Page 99 Emergency DA 62 AFM Procedures 3.3 AIRPLANE-RELATED G1000 CAUTIONS 3.3.1 L/R ALTN FAIL Left/Right engine alternator has failed. L/R ALTN FAIL (a) One Alternator Failed Proceed according to: 4B.4.6 - L/R ALTN FAIL (b) Both Alternators Failed WARNING If both alternators fail at the same time, reduce all electrical equipment to a minimum.
  • Page 100 Emergency DA 62 AFM Procedures 3.4 G1000 SYSTEM WARNINGS 3.4.1 RED X/YELLOW X A red or yellow X through any display field, such as COM frequencies, NAV frequencies, or engine data, indicates that display field is not receiving valid data.
  • Page 101 Emergency DA 62 AFM Procedures 3.4.5 VERT SPEED FAIL VERT SPEED FAIL The display system is not receiving vertical speed input from the air data computer; accompanied by a red or yellow X through the vertical speed display. Determine vertical speed based on the change of altitude information.
  • Page 102 Emergency DA 62 AFM Procedures 3.5 G1000 FAILURES 3.5.1 NAVIGATION INFORMATION FAILURE If Garmin G1000 GPS navigation information is not available or invalid, utilize remaining operational navigation equipment as required. 3.5.2 PFD OR MFD DISPLAY FAILURE 1. DISPLAY BACKUP button on audio panel . . PUSH...
  • Page 103 Emergency DA 62 AFM Procedures (b) DISPLAY BACKUP button on audio panel ..PUSH (button will be IN) If the system returns to normal mode, leave the DISPLAY BACKUP button IN and continue. lf the system remains in reversionary mode, or abnormal display behavior such as display flashing occurs, then return the DISPLAY BACKUP button to the OUT position.
  • Page 104 Emergency DA 62 AFM Procedures 3.5.4 AIR DATA COMPUTER (ADC) FAILURE NOTE Complete loss of the Air Data Computer is indicated by a red X and yellow text over the airspeed, altimeter, vertical speed, TAS and OAT displays. Some FMS functions, such as true airspeed and wind calculations, will also be lost.
  • Page 105 Emergency DA 62 AFM Procedures 3.5.6 ERRONEOUS OR LOSS OF WARNING/CAUTION ANNUNCIATORS NOTE Loss of an annunciator may be indicated when engine or fuel displays show an abnormal or emergency situation and the annunciator is not present. An erroneous annunciator may be identified when an annunciator appears which does not agree with other displays or system information.
  • Page 106 Emergency DA 62 AFM Procedures 3.6 ABNORMAL ENGINE BEHAVIOUR 1. Full power ......apply If the abnormal engine behavior sustains, refer to 3.7 - ONE ENGINE INOPERATIVE...
  • Page 107 Emergency DA 62 AFM Procedures 3.7 ONE ENGINE INOPERATIVE PROCEDURES WARNING In certain combinations of airplane weight, configuration, ambient conditions, speed and pilot skill, negative climb performance result. Refer Chapter 5 - PERFORMANCE for one engine inoperative performance data. In any event, the sudden application of power during one- engine inoperative operation makes the control of the airplane more difficult.
  • Page 108 Emergency DA 62 AFM Procedures 3.7.1 DETECTING THE INOPERATIVE ENGINE NOTE One engine inoperative means an asymmetric loss of thrust, resulting in uncommanded yaw and roll in direction of the so- called "dead" engine (with coordinated controls). To handle this situation, it is vital to maintain directional control by mainly rudder and additional aileron input.
  • Page 109 Emergency DA 62 AFM Procedures 3.7.2 ENGINE TROUBLESHOOTING WARNING Control over the flight attitude has priority over attempts to solve the current problem ("first fly the airplane"). NOTE With respect to handling and performance, the left-hand engine (pilots view) is considered the "critical" engine.
  • Page 110 Emergency DA 62 AFM Procedures WARNING Do not increase the POWER lever past the propeller speed of 1975 RPM or the setting determined in step 4. An increase of engine power beyond this setting leads into another power loss. NOTE With this power setting the engine can provide up to 65% at the maximum propeller speed of 1975 RPM.
  • Page 111 Emergency DA 62 AFM Procedures If either ECU A or B setting restores normal engine operation, then maintain that ECU setting and land as soon as possible. Otherwise: 3. 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 112 Emergency DA 62 AFM Procedures 3.7.3 ENGINE SECURING (FEATHERING) PROCEDURE Shut down and feathering of the affected engine: 1. Affected engine ..... . . identify & verify 2.
  • Page 113 Emergency DA 62 AFM Procedures 3.7.4 UNFEATHERING & RESTARTING THE ENGINE IN FLIGHT If the reason for the shutdown has been ascertained, and there is no indication of malfunction or engine fire, a restart may be attempted. Restarting the Engine with the Starter...
  • Page 114 Emergency DA 62 AFM Procedures CAUTION Do not engage the starter when the propeller is windmilling. NOTE At airspeeds below 80 KIAS it is possible that the propeller may turn intermittently. If the propeller is turning intermittently, make sure that the starter engagement is timed with the momentarily stationary propeller.
  • Page 115 Emergency DA 62 AFM Procedures Restarting the Engine by Windmilling If the reason for the shutdown has been ascertained, and there is no indication of malfunction or engine fire, a restart may be attempted. Maximum restart altitude: 20,000 ft pressure altitude for immediate restart.
  • Page 116 Emergency DA 62 AFM Procedures CAUTION Do not engage the starter when the propeller is windmilling. Do not attempt restart below 100 KIAS (above 10,000 ft pressure altitude) or 110 KIAS (below 10,000 ft pressure altitude). Do not attempt restart above 115 KIAS.
  • Page 117 Emergency DA 62 AFM Procedures 3.7.5 ENGINE FAILURE DURING TAKE-OFF a) Engine Failure During Ground Roll - Abort take-off. 1. POWER lever......IDLE/BOTH 2.
  • Page 118 Emergency DA 62 AFM Procedures b) Engine Failure After Lift Off If the landing gear is still extended and the remaining runway/surface is adequate: - Abort the take-off & land straight ahead. If the remaining runway/surface is inadequate: - Decide whether to abort or to continue the take-of f.
  • Page 119 Emergency DA 62 AFM Procedures 1. POWER lever......MAX 2. Rudder ......maintain directional control 3.
  • Page 120 Emergency DA 62 AFM Procedures 3.7.6 ENGINE FAILURES IN FLIGHT (a) Engine Failure During Initial Climb WARNING As climb is a flight condition which is associated with high power settings, airspeeds lower than v = 76 KIAS (flaps UP) or 70 KIAS (flaps T/O) should be avoided as a sudden engine failure can lead to loss of control.
  • Page 121 Emergency DA 62 AFM Procedures (b) Engine Failure During Flight 1. Rudder ......maintain directional control 2.
  • Page 122 Emergency DA 62 AFM Procedures 3.7.7 LANDING WITH ONE ENGINE INOPERATIVE Preparation: CAUTION For emergency landing the adjustable backrests (if installed) must be fixed in the upright position. 1. Adjustable backrests ....adjust to the upright position...
  • Page 123 Emergency DA 62 AFM Procedures Not before being certain of "making the field“: 8. Airspeed......as required to operate landing gear 9.
  • Page 124 Emergency DA 62 AFM Procedures NOTE Higher approach speeds result in a significantly longer landing distance during flare. CAUTION In conditions such as (e.g.) strong wind, danger of wind shear or turbulence a higher approach speed should be selected. - Perform normal touchdown and deceleration on ground.
  • Page 125 Emergency DA 62 AFM Procedures If the approach to land is not successful you may consider: 3.7.8 GO-AROUND/BALKED LANDING WITH ONE ENGINE INOPERATIVE CAUTION The go-around/balked landing is not recommended to be initiated below a minimum of 800 ft above ground.
  • Page 126 Emergency DA 62 AFM Procedures If a positive rate of climb cannot be established: - Land so as to keep clear of obstacles. If time allows the following steps can reduce the risk of fire in an event of collision with obstacles after touchdown: 6.
  • Page 127 Emergency DA 62 AFM Procedures If landing is assured: 10. FLAPS ......LDG If landing with landing gear extended: 11.
  • Page 128 Emergency DA 62 AFM Procedures 3.7.9 FLIGHT WITH ONE ENGINE INOPERATIVE CAUTION Even if a positive flight performance can be established with one engine inoperative, land as soon as possible at the next suitable airfield/airport. CAUTION Prolonged operation with excessive side slip/bank angle may cause fuel starvation, which is normally advised by LOW FUEL indication on the G1000.
  • Page 129 Emergency DA 62 AFM Procedures NOTE If the FUEL SELECTOR is set on CROSSFEED, the engine will be supplied with fuel from the main tank on the opposite side. This will extend range and helps to keep the wings laterally balanced (see 2.14 - FUEL).
  • Page 130 Emergency DA 62 AFM Procedures 3.8 ENGINES OUT LANDING 1. ENGINE MASTER..... both OFF 2. Alternator switches ....both OFF 3.
  • Page 131 Emergency DA 62 AFM Procedures Before landing: 9. FLAPS ......LDG If landing with landing gear extended: 10.
  • Page 132 Emergency DA 62 AFM Procedures 3.9 DITCHING CAUTION The airplane has NOT been flight tested in actual ditching. The given recovery method is based on the best judgement of Diamond Aircraft. 1. Heavy objects ......secure 2.
  • Page 133 Emergency DA 62 AFM Procedures 3.10 LANDING GEAR SYSTEM FAILURES 3.10.1 LANDING GEAR UNSAFE WARNING NOTE The landing gear unsafe warning light illuminates if the landing gear is neither in the final up or down and locked position. Illumination of this light is therefore normal during transit.
  • Page 134 Emergency DA 62 AFM Procedures NOTE If the landing gear cannot be retracted to the final up position you may continue the flight with the landing gear extended in the down & locked position. Consider for higher aerodynamic drag, resulting in degraded flight performance, increased fuel consumption and decreased range.
  • Page 135 Emergency DA 62 AFM Procedures 3.10.2 MANUAL EXTENSION OF THE LANDING GEAR NOTE In case of a failure of the electrical pump, which is driving the landing gear actuators, the landing gear can be extended manually at speeds up to 162 KIAS. The manual extension of the landing gear may take up to 20 seconds.
  • Page 136 Emergency DA 62 AFM Procedures 7. Gear indicator lights ....check 3 green lights NOTE If the landing gear is correctly extended and locked, as indicated by the 3 green lights, the red light is illuminated additionally if the GEAR circuit breaker is pulled.
  • Page 137 Emergency DA 62 AFM Procedures 3.10.3 LANDING WITH GEAR UP NOTE This procedure applies if the landing gear is completely retracted. 1. Approach ......with power at normal approach airspeeds and flap settings 2.
  • Page 138 Emergency DA 62 AFM Procedures 3.10.4 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 139 Emergency DA 62 AFM Procedures 3.10.5 LANDING WITH DEFECTIVE BRAKES Consider the greater rolling distance. 1. Safety harness ......check fastened and tightened...
  • Page 140 Emergency DA 62 AFM Procedures 3.11 FAILURES IN THE ELECTRICAL SYSTEM 3.11.1 COMPLETE FAILURE OF THE ELECTRICAL SYSTEM 1. Circuit breakers ..... . . check if all OK (pressed in) If there is still no electrical power available: 2.
  • Page 141 Emergency DA 62 AFM Procedures NOTE The Standby Attitude Module will have electrical power for at least 1.0 hours. Make use of the Standby Attitude Module. Engine power can be set via visual reference of the POWER lever position. END OF CHECKLIST 3.11.2 HIGH CURRENT...
  • Page 142 Emergency DA 62 AFM Procedures 3.11.3 STARTER MALFUNCTION If the starter does not disengage from the engine after starting (starter engaged warning (STARTER L/R) on the G1000 annunciator field illuminates after the engine has started): On Ground: 1. POWER lever affected engine ... IDLE 2.

  • Page 143: Smoke And Fire

    Emergency DA 62 AFM Procedures 3.12 SMOKE AND FIRE NOTE The cabin hand fire extinguisher is located inside the airplane passenger compartment on the RH side of the cabin floor behind the co-pilot seat. To release the fire extinguisher bottle out of the bracket, it is necessary to catch the bottle at the agent-outlet nozzle near the Y-spring.
  • Page 144 Emergency DA 62 AFM Procedures 3.12.3 ENGINE FIRE IN FLIGHT 1. Cabin heat & Defrost..... OFF 2. Emergency Windows ....2 x OPEN Proceed according to 3.7.6 - ENGINE FAILURES IN FLIGHT and shut down the engine...
  • Page 145 Emergency DA 62 AFM Procedures 3.12.5 ELECTRICAL FIRE IN FLIGHT 1. AVIONIC MASTER ....OFF 2. ELECT. MASTER ..... OFF 3.

  • Page 146: Other Emergencies

    Emergency DA 62 AFM Procedures 3.13 OTHER EMERGENCIES 3.13.1 SUSPICION OF CONTAMINATION IN THE CABIN (CARBON MONOXIDE, COOLANT LIQUID ODOUR OR VAPOR) Carbon Monoxide Carbon monoxide (CO) is a gas which is developed during the combustion process. It is poisonous and without smell. Increased concentrations of carbon monoxide gas can be fatal.
  • Page 147 Emergency DA 62 AFM Procedures 3.13.2 UNLOCKED DOORS 1. Airspeed......reduce immediately 2.
  • Page 148 Emergency DA 62 AFM Procedures Front Baggage Door Open 1. Airspeed ......reduce, so that door is in a stable position 2.
  • Page 149 Emergency DA 62 AFM Procedures 3.13.3 DEFECTIVE PROPELLER RPM REGULATING SYSTEM CAUTION The POWER lever should be moved slowly, in order to avoid over-speeding and excessively rapid RPM changes. The light wooden propeller blades produce more rapid RPM changes than metal blades.
  • Page 150 Emergency DA 62 AFM Procedures NOTE If the problem does not clear itself, switch back to AUTO and land on the nearest suitable airfield. (b) Propeller Overspeed NOTE This procedure applies for continued propeller overspeed due to a malfunction in the propeller constant speed unit or a engine control unit malfunction.
  • Page 151 Emergency DA 62 AFM Procedures (c) Fixed RPM 1. POWER setting ..... . . change If the problem does not clear: 2.
  • Page 152 Emergency DA 62 AFM Procedures 3.13.4 UNINTENTIONAL FLIGHT INTO ICING 1. Leave the icing area (by changing altitude or turning back) 2. PITOT HEAT ......ON 3.
  • Page 153 Emergency DA 62 AFM Procedures 3.13.5 FUEL SUPPLY FAILURE 1. FUEL SELECTOR ....CROSSFEED/affected engine (above 10000 ft turn LH/RH FUEL...
  • Page 154 Emergency DA 62 AFM Procedures 3.13.6 RECOVERY FROM AN UNINTENTIONAL SPIN CAUTION Spin recovery has NOT been shown during certification as it is NOT required for this airplane category. The given recovery method is based on general experience! CAUTION Intentional spins are prohibited in this airplane. In the event a spin is encountered unintentionally, immediate recovery actions must be taken.
  • Page 155 Emergency DA 62 AFM Procedures 3.13.7 EMERGENCY DESCENT 1. FLAPS ......UP 2.
  • Page 156 Emergency DA 62 AFM Procedures 3.13.9 AUTOPILOT OR ELECTRIC TRIM MALFUNCTION/FAILURE NOTE An autopilot or electric trim malfunction may be recognized by an unexpected deviation from the desired flight path, abnormal flight control or trim wheel movement, or flight director commands which cause unexpected or contradictory information on the other cockpit displays.
  • Page 157 Emergency DA 62 AFM Procedures NOTE Accomplish items 1 and 2 simultaneously! 1. Airplane control stick ....grasp firmly and regain airplane control 2.
  • Page 158 Normal Operating DA 62 AFM Procedures CHAPTER 4A NORMAL OPERATING PROCEDURES Page 4A.1 INTRODUCTION ........4A-3 4A.2 AIRSPEEDS FOR NORMAL OPERATING PROCEDURES .
  • Page 159 Normal Operating DA 62 AFM Procedures 4A.6.14 SHUT-DOWN ....... . 4A-62 4A.6.15 EXIT AIRPLANE .
  • Page 160 Reference Guide, P/N 190-01896-00 or later and the Garmin G1000 Pilot’s Guide for the Diamond DA 62, P/N 190-01895-00 or later. If MÄM 62-254 is installed, normal operating procedures for GFC 700 are described in the Garmin G1000 NXi Cockpit Reference Guide, P/N 190-01905-00 or later and the Garmin G1000 NXi Pilot’s Guide for the Diamond DA 62,...
  • Page 161 Normal Operating DA 62 AFM Procedures 4A.2 AIRSPEEDS FOR NORMAL OPERATING PROCEDURES Speed [KIAS] FLAPS up to 1999 kg above 1999 kg (4407 lb) (4407 lb) min. 80 min. 80 Airspeed for rotation (take-off run, v min. 76 min. 78 Airspeed for take-off climb min.
  • Page 162 Normal Operating DA 62 AFM Procedures 4A.3 ADVISORY ALERTS ON THE G1000 The G1000 provides the following advisory-alerts on the PFD in the alert area: 4A.3.1 ADVISORY/GENERAL CHARACTERISTICS White color coded text. 4A.3.2 L/R GLOW ON Left/Right engine glow plug active.
  • Page 163 Procedures 4A.4 FLIGHT CHARACTERISTICS The DA 62 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. With the landing gear extended and at aft CG-locations, with flaps up and full power...
  • Page 164 Normal Operating DA 62 AFM Procedures 4A.6 CHECKLISTS FOR NORMAL OPERATING PROCEDURES 4A.6.1 PRE-FLIGHT INSPECTION I. Cabin check Preparation: Parking brake ......set ON MET, NAV, mass and balance .
  • Page 165 Normal Operating DA 62 AFM Procedures Below instrument panel in front of right seat: ALTERNATE AIR..... . check CLOSED On the instrument panel: ALTERNATOR.
  • Page 166 Normal Operating DA 62 AFM Procedures b) Fuel quantity ......check indication, verify using alternate means (see Section 7.9.5) c) Position lights, strobe lights (ACL).
  • Page 167 Normal Operating DA 62 AFM Procedures g) ELECT. MASTER ..... OFF h) Flight controls......check free and correct movement up to full deflection Trims .
  • Page 168 Normal Operating DA 62 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 169 Normal Operating DA 62 AFM Procedures 2. Left engine nacelle: a) 3 air inlets/2 air outlets ....clear b) Engine oil level ......check dipstick (inspection hole in the side cowling) c) Gearbox oil level .
  • Page 170 Normal Operating DA 62 AFM Procedures Nacelle underside ..... check for excessive contamination particularly by oil, fuel, and other fluids Auxiliary tank drain (if installed) .
  • Page 171 Normal Operating DA 62 AFM Procedures l) Tie-down ......check, clear m) Aileron and linkage cover....visual inspection n) Aileron hinges and safety pin .
  • Page 172 Normal Operating DA 62 AFM Procedures 6. Fuselage, right side: a) Fuselage skin ......visual inspection b) Rear window + window ....visual inspection c) RH Pilot door .
  • Page 173 Normal Operating DA 62 AFM Procedures d) Openings on lower surface ....check for foreign objects and for traces of fuel (if tank is full, fuel may spill over through the tank vent) e) Tank filler .
  • Page 174 Normal Operating DA 62 AFM Procedures f) Venting pipe......check for blockage g) Exhaust ......visual inspection WARNING The exhaust can cause burns when hot.
  • Page 175 Normal Operating DA 62 AFM Procedures 10. Front fuselage and nose landing gear: a) Left and right front baggage door ..visual inspection, closed and locked b) Nose landing gear strut ....visual inspection, sufficient height (typical visible length of bare piston: at least 10 cm/3.9 in)
  • Page 176 Normal Operating DA 62 AFM Procedures 4A.6.2 BEFORE STARTING ENGINE 1. Preflight inspection ....complete 2. Passengers ......instructed...
  • Page 177 Normal Operating DA 62 AFM Procedures NOTE The pilot must ensure that a passenger sitting on a front seat is instructed in the operation of the adjustable backrest and the doors. 4. Adjustable backrests ....adjust to the upright position...
  • Page 178 Normal Operating DA 62 AFM Procedures 14. ELECT. MASTER ..... ON CAUTION When switching the ELECT. MASTER ON, the electrically driven hydraulic gear pump may activate itself for 5 to 20 seconds in order to restore the system pressure.
  • Page 179 Normal Operating DA 62 AFM Procedures 4A.6.3 STARTING ENGINE NOTE At ambient temperatures below -22°C, the engine may not start at the first attempt. In this case, wait 60 seconds between the start attempts. 1. Strobe lights (ACL)..... ON 2.
  • Page 180 Normal Operating DA 62 AFM Procedures CAUTION Do not overheat the starter motor. Do not operate the starter motor for more than 10 seconds. At ambient temperatures below -22°C, it is possible that the engine will not start at the first attempt. In this case, wait 60 seconds between the start attempts.
  • Page 181 Normal Operating DA 62 AFM Procedures 4A.6.4 BEFORE TAXIING 1. AVIONIC MASTER ....ON 2. Power lever ......as required, max. 50% if engine temperature below green range 3.
  • Page 182 Normal Operating DA 62 AFM Procedures NOTE The AFCS system 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 completion of the preflight test, the PFT is removed, the red AFCS annunciation is removed, and the autopilot disconnect tone sounds.
  • Page 183 Normal Operating DA 62 AFM Procedures 4A.6.5 TAXIING 1. Parking brake ......release 2. Brakes ......test on moving off 3.
  • Page 184 Normal Operating DA 62 AFM Procedures 4A.6.6 BEFORE TAKE-OFF 1. Position airplane into wind if possible. 2. Parking brake ......set...
  • Page 185 Normal Operating DA 62 AFM Procedures 9. Annunciations/Engine/System Page ..check OK/normal range (except oil oil pressure may be in the yellow range with a warm engine and power lever set to IDLE) 10. Circuit breakers ..... . . check pressed in 11.
  • Page 186 Normal Operating DA 62 AFM Procedures ECU/fuel pumps test sequence NOTE The following test sequence can be executed for both engines simultaneously, or in sequence. The engine/gearbox oil temperatures have to be in the green range before starting the test sequence. Efficient engine warm up may require higher power settings (max.
  • Page 187 Normal Operating DA 62 AFM Procedures NOTE Releasing the ECU TEST BUTTON or manipulating the power lever before the test sequence is completed will abort the test sequence. During the following ECU and fuel pump test, a shake of the engine might occur.
  • Page 188 Normal Operating DA 62 AFM Procedures CAUTION Running the engine with the VOTER switch on ECU A or ECU B, other than for this test or in an emergency is prohibited. The engine control system redundancy is only given with the VOTER switch set to AUTO.
  • Page 189 Normal Operating DA 62 AFM Procedures Test sequence completed. 14. ECU TEST button ..... release 15. Parking brake ......release Available power check: 1.
  • Page 190 Normal Operating DA 62 AFM Procedures -35°C -20°C -10°C 0°C 10°C 20°C 30°C 40°C 50°C Altitude [ft] -31°F -4°F 14°F 32°F 50°F 68°F 86°F 104°F 122°F 2000 4000 6000 8000 10000 6. POWER lever ......IDLE 7.
  • Page 191 Normal Operating DA 62 AFM Procedures Governor Test: NOTE During the governor test, the engines will produce maximum thrust, therefore firmly apply brakes. Also verify that the surrounding area is free of debris, dirt, loose stones or pebbles, or any other object that could become a hazard.
  • Page 192 Normal Operating DA 62 AFM Procedures 4A.6.7 TAKE-OFF a) Standard Procedure (Take-off with Flaps T/O) 1. Transponder ......as required 2.
  • Page 193 Normal Operating DA 62 AFM Procedures When safe climb is established: 7. LANDING GEAR ..... . apply brakes; UP, check unsafe light...
  • Page 194 Normal Operating DA 62 AFM Procedures NOTE In strong crosswinds, steering can be augmented by use of the toe brakes. It should be noted, however, that this method increases the take-off roll, and should not generally be used. 5. Nose wheel lift-off: ..... v min.
  • Page 195 Normal Operating DA 62 AFM Procedures 4A.6.8 CLIMB Initial Climb Check 1. Landing light......OFF/as required 2.
  • Page 196 Normal Operating DA 62 AFM Procedures NOTE Operating in the gearbox temperature cautionary range is permitted. However, prolonged operation recommended. END OF CHECKLIST GFC 700 Operation During Climb NOTE The NOSE UP and NOSE DN buttons on the mode controller on the MFD are referenced to airplane movement.
  • Page 197 Normal Operating DA 62 AFM Procedures NOTE If the altitude preselect is not changed before selecting VS, the autopilot may re-capture the current altitude immediately after entering VS mode. Always ensure that the altitude preselect is adjusted prior to selecting VS.
  • Page 198 Normal Operating DA 62 AFM Procedures NOTE If the altitude preselect is not changed before selecting FLC, the autopilot may re-capture the current altitude immediately after entering FLC mode. Always ensure that the altitude preselect is adjusted prior to selecting FLC.
  • Page 199 Normal Operating DA 62 AFM Procedures c) To Capture a Selected Altitude 1. Altimeter setting ..... . . adjust to appropriate value 2.
  • Page 200 Normal Operating DA 62 AFM Procedures d) Navigation Capture and Track 1. Navigation source ..... select VOR or GPS using CDI button on PFD 2.
  • Page 201 Normal Operating DA 62 AFM Procedures 4A.6.9 CRUISE 1. POWER lever......up to 95% NOTE The recommended cruise power setting is 75%.
  • Page 202 Normal Operating DA 62 AFM Procedures 2. Transfer the second half of the auxiliary fuel: Repeat the procedure described above. NOTE Transfer the fuel from the auxiliary tanks to the main tanks as soon as possible. The fuel in the auxiliary tanks must be transferred to the main tanks to become available for the current flight mission.
  • Page 203 Normal Operating DA 62 AFM Procedures NOTE If the altitude preselect is not changed before selecting VS, the autopilot may re-capture the current altitude immediately after entering VS mode. Always ensure that the altitude preselect is adjusted prior to selecting VS.
  • Page 204 Normal Operating DA 62 AFM Procedures NOTE If the altitude preselect is not changed before selecting FLC, the autopilot may re-capture the current altitude immediately after entering FLC mode. Always ensure that the altitude preselect is adjusted prior to selecting FLC.
  • Page 205 Normal Operating DA 62 AFM Procedures NOTE In ALT mode, the autopilot will maintain the reference altitude shown in the autopilot window of the PFD regardless of the altitude in the altitude preselect window or the altimeter's barometric pressure setting. If the altimeter setting is changed, the autopilot will climb or descend to maintain the reference altitude.
  • Page 206 Normal Operating DA 62 AFM Procedures e) Navigation Capture and Track 1. Navigation source ..... select VOR or GPS using CDI button on PFD 2.
  • Page 207 Normal Operating DA 62 AFM Procedures 4A.6.10 DESCENT 1. POWER lever......as required 2. Airspeed......as required 3.
  • Page 208 Normal Operating DA 62 AFM Procedures NOTE If the altitude preselect is not changed before selecting VS, the autopilot may re-capture the current altitude immediately after entering VS mode. Always ensure that the altitude preselect is adjusted prior to selecting VS.
  • Page 209 Normal Operating DA 62 AFM Procedures NOTE If the altitude preselect is not changed before selecting FLC, the autopilot may re-capture the current altitude immediately after entering FLC mode. Always ensure that the altitude preselect is adjusted prior to selecting FLC.
  • Page 210 Normal Operating DA 62 AFM Procedures NOTE In ALT mode, the autopilot will maintain the reference altitude shown in the autopilot window of the PFD regardless of the altitude in the altitude preselect window or the altimeter's barometric pressure setting. If the altimeter setting is changed, the autopilot will climb or descend to maintain the reference altitude.
  • Page 211 Normal Operating DA 62 AFM Procedures 4A.6.11 APPROACH & LANDING Approach: CAUTION For landing the adjustable backrests must be fixed in the upright position. 1. Adjustable backrests ....adjust to the upright position...
  • Page 212 Normal Operating DA 62 AFM Procedures Before landing: 12. Airspeeds up to 1999 kg (4407 lb): ..min. 91 KIAS with FLAPS UP min. 88 KIAS with FLAPS T/O Airspeeds above 1999 kg (4407 lb): ..min. 95 KIAS with FLAPS UP min.
  • Page 213 Normal Operating DA 62 AFM Procedures GFC 700 Operation During Approach and Landing a) VOR 1. Navigation source ..... select VOR using CDI button on 2.
  • Page 214 Normal Operating DA 62 AFM Procedures b) ILS 1. Navigation source ..... select LOC using CDI button on 2. Course bearing pointer ....set using course knob 3.
  • Page 215 Normal Operating DA 62 AFM Procedures c) GPS 1. Navigation source ..... select GPS using CDI button on 2. Approach ......load in FMS and ACTIVATE 3.
  • Page 216 Normal Operating DA 62 AFM Procedures NOTE The course pointer must be at least 115° from the current magnetic heading before BC will be annunciated in the lateral mode field. Until that point, LOC will be annunciated. Selecting NAV mode for back course approaches inhibits the glideslope from coupling.
  • Page 217 Normal Operating DA 62 AFM Procedures 4A.6.12 GO AROUND 1. POWER lever......MAX 2. FLAPS ......position T/O 3.
  • Page 218 Normal Operating DA 62 AFM Procedures 3. Balked landing ......execute 4. Missed approach procedure ... . . execute (as applicable) 5.
  • Page 219 Normal Operating DA 62 AFM Procedures 4A.6.14 SHUT-DOWN 1. Parking brake ......set 2. POWER lever......up to 10% load for 1 minute 3.
  • Page 220 Normal Operating DA 62 AFM Procedures CAUTION Before shut-down the engine must run for at least 1 minute with the power lever up to 10% to avoid heat damage of the turbo charger. CAUTION Do not shut down an engine with the FUEL SELECTOR valve.
  • Page 221 Normal Operating DA 62 AFM Procedures 4A.6.15 EXIT AIRPLANE Exit the airplane to the aft on designated areas on the inner wing section LH or RH. 4A.6.16 POST FLIGHT INSPECTION 1. Record any problem found in flight and during the post-flight check in the log book.
  • Page 222 Normal Operating DA 62 AFM Procedures 4A.6.18 FLIGHT IN RAIN 1. ALTERNATE AIR ....OPEN CAUTION During operation on ground, ALTERNATE AIR must be CLOSED.
  • Page 223 Normal Operating DA 62 AFM Procedures Use of Fuel Additives CAUTION Only approved fuel additives not exceeding the approved concentrations may be used; refer to Section 2.14 FUEL. The instructions of the fuel additive supplier must be followed. Failure to exactly follow the fuel additive mixing procedures...
  • Page 224 Normal Operating DA 62 AFM Procedures Typical Dosing Quantities: (a) KATHON FP 1.5 Fuel Additive * Fuel Quantity KATHON FP 1.5 (100 ppm) Liter US gal 13.2 40.2 88.68 0.13 26.4 80.4 177.37 0.26 39.6 120.6 266.05 11.6 0.39 52.8 160.8...
  • Page 225 Normal Operating DA 62 AFM Procedures Refueling of the Auxiliary Tanks (if installed) CAUTION If the auxiliary tanks are used then both tanks must be refueled to the maximum level. Only then the pilot has proper information concerning the fuel quantity in the auxiliary tanks.
  • Page 226 Normal Operating DA 62 AFM Procedures 4A.6.20 FLIGHT AT HIGH ALTITUDE At high altitudes, the provision of oxygen for the occupants is necessary. Legal requirements for the provision of oxygen should be adhered to. Also see Section 2.11 - OPERATING ALTITUDE.
  • Page 227 Normal Operating DA 62 AFM Procedures CAUTION Do not engage the starter when the propeller is windmilling. NOTE At airspeeds below 80 KIAS it is possible that the propeller may turn intermittently. If the propeller is turning intermittently, make sure that the starter engagement is timed with the momentarily stationary propeller.
  • Page 228 Normal Operating DA 62 AFM Procedures 6. STARTER of selected engine ... . . engage when propeller is stationary CAUTION After the engine has started, the POWER lever should be set to a moderate power setting until engine temperature have reached the green range.
  • Page 229 Abnormal Operating DA 62 AFM Procedures CHAPTER 4B ABNORMAL OPERATING PROCEDURES Page 4B.1 PRECAUTIONARY LANDING ......4B-3 4B.2 ENGINE INSTRUMENT INDICATIONS OUTSIDE...
  • Page 230 Abnormal Operating DA 62 AFM Procedures 4B.3.12 LOI ......... 4B-25 4B.3.13 AHRS ALIGNING - KEEP WINGS LEVEL .
  • Page 231 Abnormal Operating DA 62 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 232 Abnormal Operating DA 62 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: ENGINE MASTER ..both OFF FUEL SELECTOR .
  • Page 233 Abnormal Operating DA 62 AFM Procedures 4B.2 ENGINE INSTRUMENT INDICATIONS OUTSIDE OF GREEN RANGE ON THE G1000 4B.2.1 RPM High RPM 1. Reduce power of affected engine. 2. Keep RPM within the green range using the power lever. If the above mentioned measures do not solve the problem, refer to 3.13.3 - DEFECTIVE PROPELLER RPM REGULATING SYSTEM.
  • Page 234 Abnormal Operating DA 62 AFM Procedures 4B.2.2 COOLANT TEMPERATURE (a) High Coolant Temperature Proceed according to: 3.2.2 - L/R ENG TEMP (b) Low Coolant Temperature Check G1000 for L/R COOL LVL caution message (low coolant level). NOTE During an extended descent from high altitudes with a low power setting, coolant temperature may decrease.
  • Page 235 Abnormal Operating DA 62 AFM Procedures 4B.2.3 OIL TEMPERATURE (a) High Oil Temperature Proceed according to: 3.2.3 - L/R OIL TEMP (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 236 Abnormal Operating DA 62 AFM Procedures 4B.2.4 OIL PRESSURE (a) High Oil Pressure Check oil temperature. Check coolant temperature. If the temperatures are within the green range: Expect false oil pressure indication. Keep monitoring temperatures. If the temperatures are outside of the green range: Reduce power on affected engine.
  • Page 237 Abnormal Operating DA 62 AFM Procedures 4B.2.5 GEARBOX TEMPERATURE High Gearbox Temperature Proceed according to: 3.2.5 - L/R GBOX TEMP 4B.2.6 FUEL TEMPERATURE (a) High Fuel Temperature Proceed according to: 3.2.6 - L/R FUEL TEMP (b) Low Fuel Temperature Increase power on affected engine.
  • Page 238 Abnormal Operating DA 62 AFM Procedures 4B.2.7 VOLTAGE (a) Low Voltage Indication on the Ground with Engines Running 1. ALTERNATORS ..... . check ON 2.
  • Page 239 Abnormal Operating DA 62 AFM Procedures 4B.3 CAUTION-ALERTS ON THE G1000 The G1000 provides the following CAUTION-alerts on the PFD in the ALERT area. 4B.3.1 CAUTIONS/GENERAL * Amber color coded text. CHARACTERISTICS * Single warning chime tone of 1.5 seconds duration.
  • Page 240 Abnormal Operating DA 62 AFM Procedures 4B.3.2 L/R ECU A FAIL * Left/Right engine ECU A has detected a failure L/R ECU A FAIL * is being tested during ECU test procedure before take-off check. Depending on the type of failure, the ECU failure cautions are either ‘non latched', i.e.
  • Page 241 Abnormal Operating DA 62 AFM Procedures ALTERNATE AIR ..... OPEN Fuel pumps LH/RH ....ON Circuit breakers .
  • Page 242 Abnormal Operating DA 62 AFM Procedures 1. Safe altitude ......check 2. Airspeed......up to 1999 kg (4407 lb): min.
  • Page 243 Abnormal Operating DA 62 AFM Procedures 4B.3.3 L/R ECU B FAIL Left/Right engine ECU B has detected a failure L/R ECU B FAIL is being tested during ECU test procedure before take-off check. Depending on the type of failure, the ECU failure cautions are either ‘non latched', i.e.
  • Page 244 Abnormal Operating DA 62 AFM Procedures 1. ALTERNATE AIR..... . OPEN 2. Fuel pumps LH/RH ....ON 3.
  • Page 245 Abnormal Operating DA 62 AFM Procedures 1. Safe altitude ..... . . check 2. Airspeed ......up to 1999 kg (4407 lb): min.
  • Page 246 Abnormal Operating DA 62 AFM Procedures 4B.3.4 L/R FUEL LOW Left/Right engine main tank fuel quantity is low. L/R FUEL LOW 1. Fuel quantity ......check...
  • Page 247 Abnormal Operating DA 62 AFM Procedures 2. FUEL SELECTOR ..... CROSSFEED (engine with LOW FUEL indication); above 10000 ft turn LH/RH FUEL PUMP to ON...
  • Page 248 Abnormal Operating DA 62 AFM Procedures 4B.3.6 L/R ALTN FAIL Left/Right engine alternator has failed. L/R ALTN FAIL (a) One Alternator Failed 1. ALTERNATOR......OFF/affected side 2.
  • Page 249 Abnormal Operating DA 62 AFM Procedures 4B.3.7 L/R COOL LVL Left/Right engine coolant level is low. L/R COOL LVL 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 250 Abnormal Operating DA 62 AFM Procedures 4B.3.8 PITOT FAIL/HT OFF Pitot heating system has failed. PITOT FAIL Pitot heating system is OFF. PITOT HT OFF 1. PITOT HEAT ......check ON/as required...
  • Page 251 Abnormal Operating DA 62 AFM Procedures 4B.3.9 STALL HT FAIL/OFF Stall warning heat has failed. STAL HT FAIL Stall warning heat is OFF. STAL HT OFF 1. PITOT HEAT ......check ON/as required...
  • Page 252 Abnormal Operating DA 62 AFM Procedures 4B.3.10 L/R AUXILIARY FUEL TANK EMPTY (IF INSTALLED) Left/Right auxiliary fuel tank empty (displayed only when L/R AUX FUEL E AUX PUMP switch is ON). The auxiliary fuel tank empty caution message indicates an empty auxiliary fuel tank while the auxiliary fuel pump is switched ON.
  • Page 253 Abnormal Operating DA 62 AFM Procedures 4B.3.12 LOI GPS integrity is insufficient for the current phase of flight. (a) Enroute, Oceanic, Terminal, or Initial Approach Phase of Flight If the LOI annunciation is displayed in the enroute, oceanic, terminal, or initial approach...
  • Page 254 Abnormal Operating DA 62 AFM Procedures 4B.3.13 AHRS ALIGNING - KEEP WINGS LEVEL AHRS ALIGN: The AHRS (Attitude and Heading Reference System) is Keep Wings aligning. Level Keep wings level using standby attitude indicator. END OF CHECKLIST Page 4B - 26 Rev.
  • Page 255 Abnormal Operating DA 62 AFM Procedures 4B.4 FAILURES IN FLAP OPERATING SYSTEM Failure in Position Indication or Function 1. FLAPS position ..... . . check visually 2.
  • Page 256 Abnormal Operating DA 62 AFM Procedures (c) Only LDG available: Perform normal landing. END OF CHECKLIST Page 4B - 28 Rev. 0 11-Jan-2019 Doc. No. 11.01.05-E...
  • Page 257 Abnormal Operating DA 62 AFM Procedures 4B.5 FAILURES IN ELECTRICAL RUDDER PEDAL ADJUSTMENT Runaway of Electrical Rudder Pedal Adjustment NOTE The circuit breaker for the rudder pedal adjustment is located on the RH side of the instrument panel. 1. PEDALS circuit breaker ....pull END OF CHECKLIST Doc.
  • Page 258 Abnormal Operating DA 62 AFM Procedures 4B.6 FAILURES IN HYDRAULIC SYSTEM 4B.6.1 CONTINUOUS HYDRAULIC PUMP OPERATION 1. Landing gear indication lights... . . check 2. Prepare for manual landing gear extension. Refer to Section 3.9.2 - MANUAL EXTENSION OF THE LANDING GEAR.
  • Page 259 Abnormal Operating DA 62 AFM Procedures 4B.7 STARTING ENGINE WITH EXTERNAL POWER 4B.7.1 BEFORE STARTING ENGINE 1. Pre-flight inspection ....complete 2.
  • Page 260 Abnormal Operating DA 62 AFM Procedures CAUTION When switching the external power unit ON, the electrically driven hydraulic gear pump may activate itself for 5 to 20 seconds in order to restore the system pressure. Should the pump continue to operate continuously or periodically, terminate flight.
  • Page 261 Abnormal Operating DA 62 AFM Procedures 4B.7.2 STARTING ENGINE 1. Strobe lights (ACL) ....ON 2. Fuel pumps LH/RH ....check OFF 3.
  • Page 262 Abnormal Operating DA 62 AFM Procedures CAUTION Do not overheat the starter motor. Do not operate the starter motor for more than 10 seconds. At ambient temperatures below -20°C it is possible that the engine will not run at the first attempt. In this case, wait 60 seconds between the start attempts.
  • Page 263 Abnormal Operating DA 62 AFM Procedures 4B.8 LIGHTNING STRIKE 1. Airspeed ......as low as practicable, do not exceed v (refer to Section 2.2)
  • Page 264 Abnormal Operating DA 62 AFM Procedures 4B.9 FAILURES IN THE AUTOPILOT SYSTEM 4B.9.1 AUTOPILOT DISCONNECT (Yellow AP Flashing on PFD) 1. AP DISC switch ......DEPRESS AND RELEASE (to cancel disconnect tone) 2.
  • Page 265 Abnormal Operating DA 62 AFM Procedures 4B.9.3 LOSS OF NAVIGATION INFORMATION (Yellow VOR, VAPP, GPS or LOC flashing on PFD) NOTE If a navigation signal is lost while the autopilot is tracking it, the autopilot will roll the airplane wings level and default to roll mode (ROL).
  • Page 266 Abnormal Operating DA 62 AFM Procedures 4B.9.4 AUTOPILOT OUT OF TRIM (Yellow AIL, AIL, ELE, ELE, RUD or RUD on PFD) For ELE, or ELE Indication: WARNING Do not attempt to overpower the autopilot in the event of a pitch mistrim. The autopilot servos will oppose pilot input and will cause pitch trim to run opposite the direction of pilot input.
  • Page 267 Abnormal Operating DA 62 AFM Procedures 2. Airplane attitude ..... . . maintain/regain airplane control, use standby attitude indicator if necessary 3.
  • Page 268 Abnormal Operating DA 62 AFM Procedures If annunciation remains: 2. Control stick ......GRASP FIRMLY with both hands...
  • Page 269 Abnormal Operating DA 62 AFM Procedures 4B.9.5 FLASHING YELLOW MODE ANNUNCIATION NOTE Abnormal mode transitions (those not initiated by the pilot or by normal sequencing of the autopilot) will be annunciated by flashing the disengaged mode in yellow on the PFD. Upon loss of a selected mode, the system will revert to the default mode for the affected axis, either ROL or PIT.
  • Page 270 Abnormal Operating DA 62 AFM Procedures 4B.9.6 EFFECTS OF G1000 LOSSES UPON AUTOPILOT OPERATION G1000 System Loss Effect upon Autopilot Operation AHRS The autopilot disconnects, and autopilot, yaw damper and flight director are inoperative. Manual electric trim is available. HDG function of AHRS The autopilot will remain engaged with the loss of the HDG Mode.
  • Page 271 Abnormal Operating DA 62 AFM Procedures 4B.10 L/R AUX FUEL TRANSFER FAIL (IF AUX. TANKS ARE INSTALLED) If the fuel quantity in a main tank does not increase during fuel transfer: 1. Switch OFF both AUX PUMPS. 2. Check fuel pump LH/RH OFF.
  • Page 272 DA 62 AFM Performance CHAPTER 5 PERFORMANCE Page INTRODUCTION ........5-2 USE OF THE PERFORMANCE TABLES AND DIAGRAMS .
  • Page 273 Performance DA 62 AFM 5.1 INTRODUCTION The performance tables and diagrams on the following pages are presented so that, on the one hand, you can see what performance you can expect from your airplane, while on the other hand they allow comprehensive and sufficiently accurate flight planning. The...
  • Page 274 DA 62 AFM Performance 5.3 PERFORMANCE TABLES AND DIAGRAMS 5.3.1 AIRSPEED CALIBRATION NOTE The position of the landing gear (extended/retracted) and flaps (extended/retracted) has no significant influence on the airspeed indicator system. Airspeed Indicator Calibration Indicated Airspeed [KIAS] Calibrated Airspeed [KCAS] 11-Jan-2019 Doc.
  • Page 275 Performance DA 62 AFM 5.3.2 FUEL FLOW DIAGRAM CAUTION The table shows the fuel flow per hour for one engine. NOTE The fuel calculations on the FUEL CALC portion of the G1000 MFD do NOT use the airplane's fuel quantity indicators. The...
  • Page 276 DA 62 AFM Performance 5.3.3 INTERNATIONAL STANDARD ATMOSPHERE 11-Jan-2019 Doc. No. 11.01.05-E Rev. 0 Page 5 - 5...
  • Page 277 Performance DA 62 AFM 5.3.4 STALLING SPEEDS Stalling Speeds at Various Flight Masses Airspeeds, most forward CG, power off: 1800 kg Bank Angle (3968 lb) 0° 30° 45° 60° Gear Flaps KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS DOWN...
  • Page 278 DA 62 AFM Performance Bank Angle 2100 kg (4630 lb) 0° 30° 45° 60° Gear Flaps KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS DOWN DOWN 2200 kg Bank Angle (4850 lb) 0° 30° 45° 60° Gear Flaps KIAS KCAS...
  • Page 279 Performance DA 62 AFM 5.3.5 WIND COMPONENTS Example: Flight direction 360° Wind 32°/30 kts Result: Crosswind component 16 kts Max. demonstrated crosswind component 25 kts 11-Jan-2019 Page 5 - 8 Rev. 0 Doc. No. 11.01.05-E...
  • Page 280 DA 62 AFM Performance 5.3.6 TAKE-OFF DISTANCE Conditions: - Power lever......both MAX - Flaps ....... UP or T/O - Runway.
  • Page 281 Performance DA 62 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 282 DA 62 AFM Performance Take-Off Distances (SI/Metric System) Take-Off Distance - Normal Procedure - 2300 kg/5071 lb Weight: 2300 kg/5071 lb Flaps: 78 KIAS Power: 86 KIAS Runway: dry, paved, level 50ft Distances are given in meter [m] Outside Air Temperature - [°C]/[°F] Press.
  • Page 283 Performance DA 62 AFM Take-Off Distance - Normal Procedure - 2200 kg/4850 lb Weight: 2200 kg/4850 lb Flaps: 78 KIAS Power: 86 KIAS Runway: dry, paved, level 50ft Distances are given in meter [m] Outside Air Temperature - [°C]/[°F] Press. Alt.
  • Page 284 DA 62 AFM Performance Take-Off Distance - Normal Procedure - 2100 kg/4630 lb Weight: 2100 kg/4630 lb Flaps: 78 KIAS Power: 86 KIAS Runway: dry, paved, level 50ft Distances are given in meter [m] Outside Air Temperature - [°C]/[°F] Press. Alt.
  • Page 285 Performance DA 62 AFM Take-Off Distance - Normal Procedure - 1999 kg/4407 lb Weight: 1999 kg/4407 lb Flaps: Power: 76 KIAS 83 KIAS Runway: dry, paved, level 50ft Distances are given in meter [m] Outside Air Temperature - [°C]/[°F] Press. Alt.
  • Page 286 DA 62 AFM Performance Take-Off Distance - Normal Procedure - 1900 kg/4189 lb Weight: 1900 kg/4189 lb Flaps: 76 KIAS Power: 83 KIAS Runway: dry, paved, level 50ft Distances are given in meter [m] Outside Air Temperature - [°C]/[°F] Press. Alt.
  • Page 287 Performance DA 62 AFM Take-Off Distance - Normal Procedure - 1800 kg/3968 lb Weight: 1800 kg/3968 lb Flaps: Power: 76 KIAS 83 KIAS Runway: dry, paved, level 50ft Distances are given in meter [m] Outside Air Temperature - [°C]/[°F] Press. Alt.
  • Page 288 DA 62 AFM Performance Take-Off Distance - Flaps UP - 2300 kg/5071 lb Weight: 2300 kg/5071 lb Flaps: 80 KIAS Power: 89 KIAS Runway: dry, paved, level 50ft Distances are given in meter [m] Outside Air Temperature - [°C]/[°F] Press. Alt.
  • Page 289 Performance DA 62 AFM Take-Off Distance - Flaps UP - 2200 kg/4850 lb Weight: 2200 kg/4850 lb Flaps: Power: 80 KIAS 89 KIAS Runway: dry, paved, level 50ft Distances are given in meter [m] Outside Air Temperature - [°C]/[°F] Press. Alt.
  • Page 290 DA 62 AFM Performance Take-Off Distance - Flaps UP - 2100 kg/4630 lb Weight: 2100 kg/4630 lb Flaps: 80 KIAS Power: 89 KIAS Runway: dry, paved, level 50ft Distances are given in meter [m] Outside Air Temperature - [°C]/[°F] Press. Alt.
  • Page 291 Performance DA 62 AFM Take-Off Distance - Flaps UP - 1999 kg/4407 lb Weight: 1999 kg/4407 lb Flaps: Power: 80 KIAS 87 KIAS Runway: dry, paved, level 50ft Distances are given in meter [m] Outside Air Temperature - [°C]/[°F] Press. Alt.
  • Page 292 DA 62 AFM Performance Take-Off Distance - Flaps UP- 1900 kg/4189 lb Weight: 1900 kg/4189 lb Flaps: 80 KIAS Power: 87 KIAS Runway: dry, paved, level 50ft Distances are given in meter [m] Outside Air Temperature - [°C]/[°F] Press. Alt.
  • Page 293 Performance DA 62 AFM Take-Off Distance - Flaps UP - 1800 kg/3968 lb Weight: 1800 kg/3968 lb Flaps: Power: 80 KIAS 87 KIAS Runway: dry, paved, level 50ft Distances are given in meter [m] Outside Air Temperature - [°C]/[°F] Press. Alt.
  • Page 294 DA 62 AFM Performance Take-Off Distances (US/Imperial System) Take-Off Distance - Normal Procedure - 2300 kg/5071 lb Weight: 2300 kg/5071 lb Flaps: 78 KIAS Power: 86 KIAS Runway: dry, paved, level 50ft Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F] Press.
  • Page 295 Performance DA 62 AFM Take-Off Distance - Normal Procedure - 2200 kg/4850 lb Weight: 2200 kg/4850 lb Flaps: 78 KIAS Power: 86 KIAS Runway: dry, paved, level 50ft Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F] Press. Alt.
  • Page 296 DA 62 AFM Performance Take-Off Distance - Normal Procedure - 2100 kg/4630 lb Weight: 2100 kg/4630 lb Flaps: 78 KIAS Power: 86 KIAS Runway: dry, paved, level 50ft Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F] Press. Alt.
  • Page 297 Performance DA 62 AFM Take-Off Distance - Normal Procedure - 1999 kg/4407 lb Weight: 1999 kg/4407 lb Flaps: Power: 76 KIAS 83 KIAS Runway: dry, paved, level 50ft Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F] Press. Alt.
  • Page 298 DA 62 AFM Performance Take-Off Distance - Normal Procedure - 1900 kg/4189 lb Weight: 1900 kg/4189 lb Flaps: 76 KIAS Power: 83 KIAS Runway: dry, paved, level 50ft Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F] Press. Alt.
  • Page 299 Performance DA 62 AFM Take-Off Distance - Normal Procedure - 1800 kg/3968 lb Weight: 1800 kg/3968 lb Flaps: Power: 76 KIAS 83 KIAS Runway: dry, paved, level 50ft Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F] Press. Alt.
  • Page 300 DA 62 AFM Performance Take-Off Distance - Flaps UP - 2300 kg/5071 lb Weight: 2300 kg/5071 lb Flaps: 80 KIAS Power: 89 KIAS Runway: dry, paved, level 50ft Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F] Press. Alt.
  • Page 301 Performance DA 62 AFM Take-Off Distance - Flaps UP - 2200 kg/4850 lb Weight: 2200 kg/4850 lb Flaps: Power: 80 KIAS 89 KIAS Runway: dry, paved, level 50ft Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F] Press. Alt.
  • Page 302 DA 62 AFM Performance Take-Off Distance - Flaps UP - 2100 kg/4630 lb Weight: 2100 kg/4630 lb Flaps: 80 KIAS Power: 89 KIAS Runway: dry, paved, level 50ft Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F] Press. Alt.
  • Page 303 Performance DA 62 AFM Take-Off Distance - Flaps UP - 1999 kg/4407 lb Weight: 1999 kg/4407 lb Flaps: Power: 80 KIAS 87 KIAS Runway: dry, paved, level 50ft Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F] Press. Alt.
  • Page 304 DA 62 AFM Performance Take-Off Distance - Flaps UP- 1900 kg/4189 lb Weight: 1900 kg/4189 lb Flaps: 80 KIAS Power: 87 KIAS Runway: dry, paved, level 50ft Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F] Press. Alt.
  • Page 305 Performance DA 62 AFM Take-Off Distance - Flaps UP - 1800 kg/3968 lb Weight: 1800 kg/3968 lb Flaps: Power: 80 KIAS 87 KIAS Runway: dry, paved, level 50ft Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F] Press. Alt.
  • Page 306 DA 62 AFM Performance 5.3.7 CLIMB PERFORMANCE - TAKE-OFF CLIMB Conditions: - Power lever......both 95% - Flaps .
  • Page 307 Performance DA 62 AFM Take-Off Climb - Flaps T/O Flaps: T/O Power: 95% Gear: retracted 86 KIAS Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C]/[°F] Alt. Alt. [ft] 2000 1219 4000 6000 1829 8000 2438 3048...
  • Page 308 DA 62 AFM Performance Take-Off Climb - Flaps T/O Flaps: T/O Power: 95% 86 KIAS Gear: retracted Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C]/[°F] Alt. Alt. [ft] 1130 1130 1120 1120 1110 1100 1050 1114...
  • Page 309 Performance DA 62 AFM Take-Off Climb - Flaps T/O Flaps: T/O Power: 95% Gear: retracted 83 KIAS Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C]/[°F] Alt. Alt. [ft] 1210 1200 1200 1190 1190 1180 1130 1010 1193...
  • Page 310 DA 62 AFM Performance Take-Off Climb - Flaps T/O Flaps: T/O Power: 95% 83 KIAS Gear: retracted Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C]/[°F] Alt. Alt. [ft] 1380 1380 1380 1370 1370 1360 1300 1170 1371...
  • Page 311 Performance DA 62 AFM Take-Off Climb - Flaps UP Flaps: UP Power: 95% Gear: retracted 89 KIAS Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C]/[°F] Alt. Alt. [ft] 1040 1040 1030 1020 1020 1010 1019 1020 1010...
  • Page 312 DA 62 AFM Performance Take-Off Climb - Flaps UP Flaps: UP Power: 95% 89 KIAS Gear: retracted Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C]/[°F] Alt. Alt. [ft] 1190 1190 1180 1170 1170 1160 1110 1000 1171...
  • Page 313 Performance DA 62 AFM Take-Off Climb - Flaps UP Flaps: UP Power: 95% Gear: retracted 87 KIAS Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C]/[°F] Alt. Alt. [ft] 1254 1270 1270 1260 1260 1250 1240 1190...
  • Page 314 DA 62 AFM Performance Take-Off Climb - Flaps UP Flaps: UP Power: 95% 87 KIAS Gear: retracted Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C]/[°F] Alt. Alt. [ft] 1450 1450 1440 1440 1430 1430 1360 1230 1435...
  • Page 315 Performance DA 62 AFM 5.3.8 CLIMB PERFORMANCE - CRUISE CLIMB Conditions: - Power lever ......both 95% - Flaps .
  • Page 316 DA 62 AFM Performance Cruise Climb Flaps: UP Power: 95% : 96 KIAS Gear: retracted CLIMB Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C]/[°F] Alt. Alt. [ft] 1050 1040 1040 1030 1030 1020 1028 2000 1030 1020...
  • Page 317 Performance DA 62 AFM Cruise Climb Flaps: UP Power: 95% Gear: retracted : 96 KIAS CLIMB Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C]/[°F] Alt. Alt. [ft] 1200 1190 1180 1180 1170 1170 1110 1000 1177...
  • Page 318 DA 62 AFM Performance Cruise Climb Flaps: UP Power: 95% : 93 KIAS Gear: retracted CLIMB Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C]/[°F] Alt. Alt. [ft] 1280 1270 1270 1260 1260 1250 1200 1080 1261...
  • Page 319 Performance DA 62 AFM Cruise Climb Flaps: UP Power: 95% Gear: retracted : 93 KIAS CLIMB Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C]/[°F] Alt. Alt. [ft] 1460 1450 1450 1440 1440 1430 1370 1230 1439...
  • Page 320 DA 62 AFM Performance 5.3.9 ONE ENGINE INOPERATIVE CLIMB PERFORMANCE Conditions: - Remaining engine ....95% load - Dead engine ......feathered and secured - Flaps .
  • Page 321 Performance DA 62 AFM One Engine Inoperative Climb Flaps: UP Power: 95% Gear: retracted : 89 KIAS Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C]/[°F] Alt. Alt. [ft] 2000 4000 1219 6000 1829 8000 2438 10000...
  • Page 322 DA 62 AFM Performance One Engine Inoperative Climb Flaps: UP Power: 95% 89 KIAS Gear: retracted Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C]/[°F] Alt. Alt. [ft] 2000 1219 4000 1829 6000 2438 8000 3048 10000...
  • Page 323 Performance DA 62 AFM One Engine Inoperative Climb Flaps: UP Power: 95% Gear: retracted 87 KIAS Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C]/[°F] Alt. Alt. [ft] 2000 4000 1219 1829 6000 8000 2438 10000 3048...
  • Page 324 DA 62 AFM Performance One Engine Inoperative Climb Flaps: UP Power: 95% 87 KIAS Gear: retracted Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C]/[°F] Alt. Alt. [ft] 2000 1219 4000 1829 6000 2438 8000 3048 10000...
  • Page 325 Performance DA 62 AFM 5.3.10 TIME, FUEL & DISTANCE TO CLIMB Conditions: - Power lever ......both 95% - Flaps .
  • Page 326 DA 62 AFM Performance Time, Fuel and Distance to Climb Flaps: UP Power: 95% : 96 KIAS Gear: retracted climb Press. Press. Dist- Alt. Alt. Time Fuel ance [ft] [°C] [°F] [kt] [ft/min] [m/s] [min] [NM] gal] 1030 2000 1015...
  • Page 327 Performance DA 62 AFM Time, Fuel and Distance to Climb Flaps: UP Power: 95% : 96 KIAS Gear: retracted climb Press. Press. Dist- Alt. Alt. Time Fuel ance [ft] [°C] [°F] [kt] [ft/min] [m/s] [min] [NM] gal] 1175 2000 1165...
  • Page 328 DA 62 AFM Performance Time, Fuel and Distance to Climb Power: 95% Flaps: UP : 93 KIAS Gear: retracted climb Press. Press. Dist- Alt. Alt. Time Fuel ance [ft] [°C] [°F] [kt] [ft/min] [m/s] [min] [NM] gal] 1260 2000 1250...
  • Page 329 Performance DA 62 AFM Time, Fuel and Distance to Climb Flaps: UP Power: 95% : 93 KIAS Gear: retracted climb Press. Press. Dist- Alt. Alt. Time Fuel ance [ft] [°C] [°F] [kt] [ft/min] [m/s] [min] [NM] gal] 1440 2000 1425...
  • Page 330 DA 62 AFM Performance 5.3.11 CRUISE PERFORMANCE Conditions: - Flaps ....... UP - Landing gear .
  • Page 331 Performance DA 62 AFM Cruise Performance up to 1999 kg (4407 lb) 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] 19.3 172 19.3 19.3 19.3 177 19.2...
  • Page 332 DA 62 AFM Performance Cruise Performance above 1999 kg (4407 lb) up to 2300 kg (5071 lb) 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] 19.3 170 19.3...
  • Page 333 Performance DA 62 AFM 5.3.12 LANDING DISTANCES Conditions: - Power lever ......both IDLE - Flaps ....... LDG, T/O or UP - Runway .
  • Page 334 DA 62 AFM Performance WARNING For a safe landing, the available runway length must be at least equal to the landing distance over a 50 ft (15 m) obstacle. 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.
  • Page 335 Performance DA 62 AFM Landing Distances (SI/Metric System) Landing Distance - Flaps LDG - 2300 kg/5071 lb Weight: 2300 kg/5071 lb Flaps: 89 KIAS Power: IDLE Runway: dry, paved, level Distances are given in meter [m] Outside Air Temperature - [°C]/[°F] Press.
  • Page 336 DA 62 AFM Performance Landing Distance - Flaps LDG - 2200 kg/4850 lb Weight: 2200 kg/4850 lb Flaps: 89 KIAS Power: IDLE Runway: dry, paved, level Distances are given in meter [m] Outside Air Temperature - [°C]/[°F] Press. Alt. [ft]/[m]...
  • Page 337 Performance DA 62 AFM Landing Distance - Flaps LDG - 2100 kg/4630 lb Weight: 2100 kg/4630 lb Flaps: 89 KIAS Power: IDLE Runway: dry, paved, level Distances are given in meter [m] Outside Air Temperature - [°C]/[°F] Press. Alt. [ft]/[m]...
  • Page 338 DA 62 AFM Performance Landing Distance - Flaps LDG - 1999 kg/4407 lb Weight: 1999 kg/4407 lb Flaps: 84 KIAS Power: IDLE Runway: dry, paved, level Distances are given in meter [m] Outside Air Temperature - [°C]/[°F] Press. Alt. [ft]/[m]...
  • Page 339 Performance DA 62 AFM Landing Distance - Flaps LDG - 1900 kg/4189 lb Weight: 1900 kg/4189 lb Flaps: 84 KIAS Power: IDLE Runway: dry, paved, level Distances are given in meter [m] Outside Air Temperature - [°C]/[°F] Press. Alt. [ft]/[m]...
  • Page 340 DA 62 AFM Performance Landing Distance - Flaps LDG - 1800 kg/3968 lb Weight: 1800 kg/3968 lb Flaps: 84 KIAS Power: IDLE Runway: dry, paved, level Distances are given in meter [m] Outside Air Temperature - [°C]/[°F] Press. Alt. [ft]/[m]...
  • Page 341 Performance DA 62 AFM Landing Distance - Abnormal Flap Position - 2300 kg/5071 lb Weight: 2300 kg/5071 lb Flaps: T/O or UP 91 KIAS (Flaps T/O) Power: IDLE 95 KIAS (Flaps UP) Runway: dry, paved, level Distances are given in meter [m] Outside Air Temperature - [°C]/[°F]...
  • Page 342 DA 62 AFM Performance Landing Distance - Abnormal Flap Position - 2200 kg/4850 lb Weight: 2200 kg/4850 lb Flaps: T/O or UP 91 KIAS (Flaps T/O) Power: IDLE 95 KIAS (Flaps UP) Runway: dry, paved, level Distances are given in meter [m] Outside Air Temperature - [°C]/[°F]...
  • Page 343 Performance DA 62 AFM Landing Distance - Abnormal Flap Position - 2100 kg/4630 lb Weight: 2100 kg/4630 lb Flaps: T/O or UP 91 KIAS (Flaps T/O) Power: IDLE 95 KIAS (Flaps UP) Runway: dry, paved, level Distances are given in meter [m] Outside Air Temperature - [°C]/[°F]...
  • Page 344 DA 62 AFM Performance Landing Distance - Abnormal Flap Position - 1999 kg/4407 lb Weight: 1999 kg/4407 lb Flaps: T/O or UP 88 KIAS (Flaps T/O) Power: IDLE 91 KIAS (Flaps UP) Runway: dry, paved, level Distances are given in meter [m] Outside Air Temperature - [°C]/[°F]...
  • Page 345 Performance DA 62 AFM Landing Distance - Abnormal Flap Position - 1900 kg/4189 lb Weight: 1900 kg/4189 lb Flaps: T/O or UP 88 KIAS (Flaps T/O) Power: IDLE 91 KIAS (Flaps UP) Runway: dry, paved, level Distances are given in meter [m] Outside Air Temperature - [°C]/[°F]...
  • Page 346 DA 62 AFM Performance Landing Distance - Abnormal Flap Position - 1800 kg/3968 lb Weight: 1800 kg/3968 lb Flaps: T/O or UP 88 KIAS (Flaps T/O) Power: IDLE 91 KIAS (Flaps UP) Runway: dry, paved, level Distances are given in meter [m] Outside Air Temperature - [°C]/[°F]...
  • Page 347 Performance DA 62 AFM Landing Distances (US/Imperial System) Landing Distance - Flaps LDG - 2300 kg/5071 lb Weight: 2300 kg/5071 lb Flaps: 89 KIAS Power: IDLE Runway: dry, paved, level Distances are given in feet [ft] perature - [°C]/[°F] Outside Air Tem Press.
  • Page 348 DA 62 AFM Performance Landing Distance - Flaps LDG - 2200 kg/4850 lb Weight: 2200 kg/4850 lb Flaps: 89 KIAS Power: IDLE Runway: dry, paved, level Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F] Press. Alt. [ft]/[m]...
  • Page 349 Performance DA 62 AFM Landing Distance - Flaps LDG - 2100 kg/4630 lb Weight: 2100 kg/4630 lb Flaps: 89 KIAS Power: IDLE Runway: dry, paved, level Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F] Press. Alt. [ft]/[m]...
  • Page 350 DA 62 AFM Performance Landing Distance - Flaps LDG - 1999 kg/4407 lb Weight: 1999 kg/4407 lb Flaps: 84 KIAS Power: IDLE Runway: dry, paved, level Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F] Press. Alt. [ft]/[m]...
  • Page 351 Performance DA 62 AFM Landing Distance - Flaps LDG - 1900 kg/4189 lb Weight: 1900 kg/4189 lb Flaps: 84 KIAS Power: IDLE Runway: dry, paved, level Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F] Press. Alt. [ft]/[m]...
  • Page 352 DA 62 AFM Performance Landing Distance - Flaps LDG - 1800 kg/3968 lb Weight: 1800 kg/3968 lb Flaps: 84 KIAS Power: IDLE Runway: dry, paved, level Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F] Press. Alt. [ft]/[m]...
  • Page 353 Performance DA 62 AFM Landing Distance - Abnormal Flap Position - 2300 kg/5071 lb Weight: 2300 kg/5071 lb Flaps: T/O or UP 91 KIAS (Flaps T/O) Power: IDLE 95 KIAS (Flaps UP) Runway: dry, paved, level Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F]...
  • Page 354 DA 62 AFM Performance Landing Distance - Abnormal Flap Position - 2200 kg/4850 lb Weight: 2200 kg/4850 lb Flaps: T/O or UP 91 KIAS (Flaps T/O) Power: IDLE 95 KIAS (Flaps UP) Runway: dry, paved, level Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F]...
  • Page 355 Performance DA 62 AFM Landing Distance - Abnormal Flap Position - 2100 kg/4630 lb Weight: 2100 kg/4630 lb Flaps: T/O or UP 91 KIAS (Flaps T/O) Power: IDLE 95 KIAS (Flaps UP) Runway: dry, paved, level Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F]...
  • Page 356 DA 62 AFM Performance Landing Distance - Abnormal Flap Position - 1999 kg/4407 lb Weight: 1999 kg/4407 lb Flaps: T/O or UP 88 KIAS (Flaps T/O) Power: IDLE 91 KIAS (Flaps UP) Runway: dry, paved, level Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F]...
  • Page 357 Performance DA 62 AFM Landing Distance - Abnormal Flap Position - 1900 kg/4189 lb Weight: 1900 kg/4189 lb Flaps: T/O or UP 88 KIAS (Flaps T/O) Power: IDLE 91 KIAS (Flaps UP) Runway: dry, paved, level Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F]...
  • Page 358 DA 62 AFM Performance Landing Distance - Abnormal Flap Position - 1800 kg/3968 lb Weight: 1800 kg/3968 lb Flaps: T/O or UP 88 KIAS (Flaps T/O) Power: IDLE 91 KIAS (Flaps UP) Runway: dry, paved, level Distances are given in feet [ft] Outside Air Temperature - [°C]/[°F]...
  • Page 359 Performance DA 62 AFM 5.3.13 GO-AROUND CLIMB PERFORMANCE Conditions: - Power lever ......both MAX - Flaps .
  • Page 360 DA 62 AFM Performance Go-Around Climb Performance Flaps: LDG Power: MAX : 89 KIAS Gear: extended Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C]/[°F] Alt. Alt. [ft] 2000 4000 1219 6000 1829 2438 8000 3048 10000...
  • Page 361 Performance DA 62 AFM Go-Around Climb Performance Flaps: LDG Power: MAX : 84 KIAS Gear: extended Rate of Climb - [ft/min] Press. Press. Outside Air Temperature - [°C]/[°F] Alt. Alt. [ft] 2000 1219 4000 1829 6000 8000 2438 10000 3048...
  • Page 362 DA 62 AFM Performance 5.3.14 APPROVED NOISE DATA Max. Flight Mass 1999 kg (4407 lb) ICAO Annex 16 Chapter X, App.6 ... . . 73.9 dB(A) Max. Flight Mass 2300 kg (5071 lb) ICAO Annex 16 Chapter X, App.6 .
  • Page 363 Performance DA 62 AFM Intentionally left blank. 11-Jan-2019 Page 5 - 92 Rev. 0 Doc. No. 11.01.05-E...
  • Page 364 DA 62 AFM Mass and Balance CHAPTER 6 MASS AND BALANCE Page INTRODUCTION ........6-2 DATUM PLANE .
  • Page 365 Mass and Balance DA 62 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 366 DA 62 AFM Mass and Balance NOTE Refer to Section 1.6 - UNITS OF MEASUREMENT for conversion of SI units to US units and vice versa. 6.2 DATUM PLANE The Datum Plane (DP) is a plane which is normal to the airplane’s longitudinal axis and in front of the airplane as seen from the direction of flight.
  • Page 367 Mass and Balance DA 62 AFM 6.3 MASS AND BALANCE REPORT The empty mass and the corresponding CG position established before delivery are the first entries in the Mass and Balance Report. Every change in permanently installed equipment, and every repair to the airplane which affects the empty mass or the empty mass CG must be recorded in the Mass and Balance Report.
  • Page 368 DA 62 AFM Mass and Balance MASS AND BALANCE REPORT Doc. No. 11.01.05-E Rev. 0 11-Jan-2019 Page 6 - 5...
  • Page 369 DA 62 AFM 6.4 FLIGHT MASS AND CENTER OF GRAVITY The following information enables you to operate your DA 62 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 370 DA 62 AFM Mass and Balance CAUTION If the auxiliary tanks are in use, both tanks must be refueled to the maximum level to provide proper information to the pilot about the fuel quantity in the auxiliary fuel tanks. If the auxiliary tanks are not in use, the pilot must ensure that they are empty.
  • Page 371 Mass and Balance DA 62 AFM 6. 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 permissible range.
  • Page 372 DA 62 AFM Mass and Balance 6.4.1 MOMENT ARMS The most important lever arms aft of the Datum Plane: Lever Arm Item [in] Occupants on front seats 2.30 90.6 Occupants on rear seats, row I 3.25 128.0 Occupants on rear seats, row II (if OÄM 62-019 is 4.15...
  • Page 373 Mass and Balance DA 62 AFM 6.4.2 LOADING DIAGRAMS Page 6 - 10 Rev. 0 11-Jan-2019 Doc. No. 11.01.05-E...
  • Page 374 DA 62 AFM Mass and Balance Doc. No. 11.01.05-E Rev. 0 11-Jan-2019 Page 6 - 11...
  • Page 375 Mass and Balance DA 62 AFM 6.4.3 CALCULATION OF LOADING CONDITION 1. Complete the form on the next page. 2. Divide the total moments from rows 11 and 14 by the related total mass to obtain the CG positions. In our example: empty tanks: 5003.65 kgm/2035 kg = 2.459 m...
  • Page 376 DA 62 AFM Mass and Balance DA 62 Your DA 62 (Example) CALCULATION OF Mass Moment Mass Moment LOADING CONDITION [kg] [kgm] [kg] [kgm] [lb] [in.lb] [lb] [in.lb] Empty mass (from Mass 1600 3885.0 and Balance Report) 3528 337,203 Front seats 368.0...
  • Page 377 Mass and Balance DA 62 AFM DA 62 Your DA 62 (Example) CALCULATION OF Mass Moment Mass Moment LOADING CONDITION [kg] [kgm] [kg] [kgm] [lb] [in.lb] [lb] [in.lb] Usable fuel, auxiliary tanks (if installed), 371.2 (0.84 kg/liter) 32,219 (7.01 lb/US gal) Lever arm: 3.2 m...
  • Page 378 DA 62 AFM Mass and Balance 6.4.4 PERMISSIBLE CENTER OF GRAVITY RANGE Doc. No. 11.01.05-E Rev. 0 11-Jan-2019 Page 6 - 15...
  • Page 379 Mass and Balance DA 62 AFM The flight CG position must be within the following limits: Most forward flight CG: 2.340 m (92.13 in) aft of datum plane at 1600 kg (3527 lb) to 1800 kg (3968 lb) 2.460 m (96.85 in) aft of datum plane at max. take-off mass (see Section 2.7)
  • Page 380 DA 62 AFM Mass and Balance 6.4.5 PERMISSIBLE MOMENT RANGE The flight mass moments shown in the diagram are those from the example in Table 6.4.3 - CALCULATION OF LOADING CONDITION, rows 11 and 14. Doc. No. 11.01.05-E Rev. 0...
  • Page 381 Mass and Balance DA 62 AFM 6.5 EQUIPMENT LIST AND EQUIPMENT INVENTORY All equipment that is approved for installation in the DA 62 is shown in the Equipment List below. NOTE The equipment listed below cannot be installed in any arbitrary combination.
  • Page 382 DA 62 AFM Mass and Balance Airplane Serial No.: Registration: Date: Mass Lever Arm Description Type Part No. Manufacturer installed AVIONICS COOLING Avionics cooling fan # 1 SAFE 328 305 467-00 Sandia Aerospace Avionics cooling fan # 2 SAFE 328...
  • Page 383 DA 62 AFM Mass and Balance Airplane Serial No.: Registration: Date: Mass Lever Arm Description Type Part No. Manufacturer installed ELECTRICAL POWER Main battery RG24-15 Concorde Emergency battery D60-2560-91-00 Diamond Aircraft ECU backup battery LH (2 pcs.) LC-R127R2P Panasonic ECU backup battery RH (2 pcs.)
  • Page 384 DA 62 AFM Mass and Balance Airplane Serial No.: Registration: Date: Mass Lever Arm Description Type Part No. Manufacturer installed CABIN COOLING SYSTEM Cabin cooling central unit D44-2153-00-00 Diamond Aircraft 47.8 21.7 194.9 4.95 EQUIPMENT Safety belt, pilot 5-01-() Series...
  • Page 385 DA 62 AFM Mass and Balance Airplane Serial No.: Registration: Date: Mass Lever Arm Description Type Part No. Manufacturer installed HYDRAULIC Motor pump unit X11-0001-00-00.00/A Hydraulik Mayer Hydraulic fluid tank X11-0002-00-00.00 Hydraulik Mayer Hydraulic control unit X11-0003-00-00.00/A Hydraulik Mayer High pressure filter X11-0004-00-00.00...
  • Page 386 DA 62 AFM Mass and Balance Airplane Serial No.: Registration: Date: Mass Lever Arm Description Type Part No. Manufacturer installed LANDING GEAR Main landing gear LH D67-3211-01-00 Diamond Aircraft Main landing gear RH D64-3212-01-00 Diamond Aircraft Nose landing gear assy...
  • Page 387 DA 62 AFM Mass and Balance Airplane Serial No.: Registration: Date: Mass Lever Arm Description Type Part No. Manufacturer installed COMMUNICATION / NAVIGATION COMM #1 antenna CI 2580-200 Comant COMM #2 antenna CI 292-2 Comant Audio panel / Marker / ICS...
  • Page 388 DA 62 AFM Mass and Balance Airplane Serial No.: Registration: Date: Mass Lever Arm Description Type Part No. Manufacturer installed TAS processor TAS 605 70-2420-x TAS605 Avidyne TAS processor TAS 610 70-2420-x TAS610 Avidyne TAS processor TAS 615 70-2420-x TAS615...
  • Page 389 DA 62 AFM Mass and Balance Airplane Serial No.: Registration: Date: Mass Lever Arm Description Type Part No. Manufacturer installed ADF receiver RA 3502-(01) 0505.757-912 Becker ADF / RMI converter AC 3504-(01) 0856.010-912 Becker ADF antenna AN 3500 0832.601-912 Becker...
  • Page 390 DA 62 AFM Mass and Balance Airplane Serial No.: Registration: Date: Mass Lever Arm Description Type Part No. Manufacturer installed ENGINE LH engine E4P-C E4PC-00-000-000 Austro Engine RH engine E4P-C E4PC-00-000-000 Austro Engine LH engine control unit EECU-E4-01 E4A-92-100-000 Austro Engine...
  • Page 391 DA 62 AFM Mass and Balance Airplane Serial No.: Registration: Date: Mass Lever Arm Description Type Part No. Manufacturer installed ENGINE EXHAUST LH Exhaust pipe with muffler D67-7806-01-00 Diamond Aircraft RH Exhaust pipe with muffler D67-7806-01-00 Diamond Aircraft PROPELLER MTV-6-R-C-...
  • Page 392 DA 62 AFM Mass and Balance Airplane Serial No.: Registration: Date: Mass Lever Arm Description Type Part No. Manufacturer installed LH fuel inline filter FX375-MK Adair RH fuel inline filter FX375-MK Adair LH solenoid valve VE 131,4 GV Parker RH solenoid valve...
  • Page 393 DA 62 AFM Airplane Description CHAPTER 7 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS Page INTRODUCTION ........7-3 AIRFRAME .
  • Page 394 Airplane Description DA 62 AFM 7.10.3 WARNING, CAUTION AND ADVISORY MESSAGES . . . 7-71 7.11 PITOT-STATIC SYSTEM....... . 7-77 7.12...
  • Page 395 DA 62 AFM Airplane Description 7.1 INTRODUCTION Chapter 7 contains a description of the airplane and its systems, together with operating instructions. For details about optional equipment, see Chapter 9. 7.2 AIRFRAME Fuselage The CFRP fuselage is of semi monocoque molded construction. The center wing is attached to the fuselage with bolts.

  • Page 396: Flight Controls

    Airplane Description DA 62 AFM 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. Rudder forces can be balanced by a trim tab on the rudder, which is also operated by a Bowden cable.
  • Page 397 DA 62 AFM Airplane Description Flaps The flaps are a two piece construction. The inner part of the flap is mounted to the center wing and the outer part to the wing. Both parts are connected to each other with a form fit connection.
  • Page 398 Airplane Description DA 62 AFM 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 399 DA 62 AFM Airplane Description Elevator Construction: GFRP sandwich. Hinges: 5 hinges. Operation: Steel pushrods; Two of the bellcrank bearings are accessible for visual inspection next to the lower hinge of the rudder. The elevator horn and its bearing, as well as the connection to the pushrod, can be visually inspected at the upper end of the rudder.
  • Page 400 Airplane Description DA 62 AFM Rudder Construction: GFRP sandwich. Hinges: Upper hinge: One bolt. Lower hinge: Bearing bracket including rudder stops, held by 4 screws to the rear web of the vertical stabilizer. The mating part on the rudder is a bracket which is attached to the rudder by 2 bolts. The bolts and nuts are accessible to visual inspection.
  • Page 401 DA 62 AFM Airplane Description Elevator Trim The trim control is a black wheel in the center console to the rear of the power lever. To guard against overrotating, the trim wheel incorporates a friction device. A mark on the wheel shows the take-off (T/O) position.
  • Page 402 Airplane Description DA 62 AFM Electrical Pedal Adjustment NOTE The pedals may only be adjusted on the ground! The pedals are adjusted using a rocker switch, located on the outboard sides of the instrument panel. The related circuit breaker is located on the right side of the instrument panel.

  • Page 403: Instrument Panel

    DA 62 AFM Airplane Description 7.4 INSTRUMENT PANEL CAUTION Do not inadvertently operate the VOTER switch when adjusting the LH instrument panel ventilation nozzle. In case of inadvertent switch operation, bring the switch back to the desired position, typically AUTO.
  • Page 404 *) Designations and abbreviations used to identify the circuit breakers are explained in Section 1.5 - DEFINITIONS AND ABBREVIATIONS. NOTE The figure above shows the typical DA 62 installation position for the equipment. The actual installation may vary due to the approved equipment version.

  • Page 405: Landing Gear

    DA 62 AFM Airplane Description 7.5 LANDING GEAR The landing gear is a fully retractable, hydraulically operated, tricycle landing gear. Struts for the landing gear are air oil assemblies. The hydraulic pressure for the landing gear operation is provided by an electrically powered hydraulic pump, which is activated by a pressure switch, when the required pressure is too low.
  • Page 406 Airplane Description DA 62 AFM To test the gear warning system (refer to 4A.6.1 - PRE-FLIGHT INSPECTION) push the test button near the gear selector switch. The aural gear alert should appear. CAUTION If the aural alert does not appear, unscheduled maintenance is necessary.
  • Page 407 Airplane Description Hydraulic Gear Extension System Schematic The main landing gear of the DA 62 is extended with three hydraulic cylinders. The following schematic figures show the system conditions for each operating mode. The first figure below shows the extension of the landing gear is shown. To reduce the amount of pumped hydraulic fluid during this operation, the return flow is partly led into the feeding flow of the system.
  • Page 408 Airplane Description DA 62 AFM The operating mode for the retraction of the landing gear is shown in the next figure. While energizing the right hydraulic valve, the fluid flow in the hydraulic system is started due to different piston areas of the landing gear cylinders, although the pressure on both sides of the system is equal.
  • Page 409 DA 62 AFM Airplane Description For an emergency extension of the landing gear, the hydraulic fluid can pass through an emergency extension valve so that the gear is extended by gravity. The condition of the system is shown in the figure below.
  • Page 410 Airplane Description DA 62 AFM Wheel Brakes Hydraulically operated disk brakes act on the wheels of the main landing gear. The wheel brakes are individually operated by means of toe pedals. Parking Brake The lever is located on the small center console under the instrument panel and is in the upper position when the brakes are released.
  • Page 411 DA 62 AFM Airplane Description 7.6 SEATS AND SAFETY HARNESSES To increase passive safety, the seats are constructed using a carbon fiber/Kevlar hybrid material and GFRP. The seats are removable to allow maintenance and inspection of the underlying controls. Covers on the control sticks prevent loose objects from falling into the area of the controls.
  • Page 412 Airplane Description DA 62 AFM CAUTION Don not apply a load of more than 90 daN (202 lbf) to the top of the backrest. Otherwise damage of the adjustment mechanism may result. For adjustment, press the button and bend the backrest forward or backward to the desired backrest angle.
  • Page 413 DA 62 AFM Airplane Description 7.7 BAGGAGE COMPARTMENTS 7.7.1 NOSE BAGGAGE COMPARTMENTS There are two nose baggage compartments, one LH and one RH. They are located in the nose section of the airplane and are accessible through the LH and RH baggage doors respectively.
  • Page 414 Airplane Description DA 62 AFM Figure 1: Rear Baggage Compartment I Page 7 - 22 Rev. 0 11-Jan-2019 Doc. No. 11.01.05-E...
  • Page 415 DA 62 AFM Airplane Description Figure 2: Rear Baggage Compartment II Doc. No. 11.01.05-E Rev. 0 11-Jan-2019 Page 7 - 23...
  • Page 416 Airplane Description DA 62 AFM Figure 3: Rear Baggage Compartment III Page 7 - 24 Rev. 0 11-Jan-2019 Doc. No. 11.01.05-E...
  • Page 417 DA 62 AFM Airplane Description Figure 4: Rear Baggage Compartment IV (if OÄM 62-019 is carried out) Doc. No. 11.01.05-E Rev. 0 11-Jan-2019 Page 7 - 25...
  • Page 418 Airplane Description DA 62 AFM Figure 5: Rear Baggage Compartment V (if OÄM 62-019 is carried out) Page 7 - 26 Rev. 0 11-Jan-2019 Doc. No. 11.01.05-E...
  • Page 419 DA 62 AFM Airplane Description 7.8 FRONT DOORS, REAR DOOR AND CABIN INTERIOR LH & RH PILOT DOORS The LH & RH pilot doors are closed by pulling down on a handle, which are located between the window and the frame. The doors are locked separately by means of a lever on each frame.
  • Page 420 Airplane Description DA 62 AFM Passenger Door The passenger door is closed in the same way, by pulling down on the handle and locking it with the lever. A gas pressure damper prevents the door from dropping; in strong winds the assembly must be securely held.
  • Page 421 DA 62 AFM Airplane Description Heating and Ventilation Heating and ventilation are operated using two levers located on the small center console under the instrument panel. Right lever: = HEATING ON (seats, floor) down = HEATING OFF Center lever :...
  • Page 422 Airplane Description DA 62 AFM Egress Hammer An Egress Hammer is installed on the floor panel behind the co-pilot’s seat. If the doors can not be opened in case of an emergency use the Egress Hammer to break through the door windows.
  • Page 423 DA 62 AFM Airplane Description 7.9 POWER PLANT 7.9.1 ENGINES, GENERAL There are two Austro Engine E4P-C engines installed, which have 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 424 Airplane Description DA 62 AFM 7.9.2 PROPELLER Two mt-Propeller MTV-6-R-C-F/CF 194-80 hydraulically regulated 3-bladed constant speed feathering propellers are installed. Each propeller 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. These blades combine the lowest weight whilst minimizing vibration.
  • Page 425 DA 62 AFM Airplane Description Pressure Accumulator: The pressure accumulator is a nitrogen oil type. It is connected to the gearbox oil circuit via an electric valve at the accumulator, which is operated with the ENGINE MASTER switch. When the ENGINE MASTER switch is set to ON the valve is opened. During engine operation the accumulator makes sure that enough oil pressure is available even if the oil feed by the gearbox oil pump is decreasing due to negative acceleration.
  • Page 426 Airplane Description DA 62 AFM Unfeathering: To unfeather the propeller, the associated ENGINE MASTER switch must be set to ON. This will open the electric valve at the pressure accumulator. The pressure stored in the accumulator will move the propeller blades into a low pitch position. As soon as the propeller starts turning and the gearbox oil operates, the accumulator will be refilled.
  • Page 427 DA 62 AFM Airplane Description 7.9.3 OPERATING CONTROLS Power Lever Engine performance is controlled by a power lever for each engine. Both power levers are situated on the large center console. ‘Front’ and ‘rear’ are defined in relation to the direction of flight.
  • Page 428 Airplane Description DA 62 AFM CAUTION The power lever should be moved slowly, in order to avoid over-speeding, and excessively rapid RPM changes. The light wooden propeller blades produce more rapid RPM changes than metal blades. WARNING It is possible that the propeller blades remain in the position of highest pitch in case of a malfunction of the engine control unit.
  • Page 429 DA 62 AFM Airplane Description ECU VOTER There are two VOTER switches, one for each engine. For normal operation, both switches are set to AUTO. Each engine is controlled by either ECU A or ECU B. In case of a failure of the active electrical engine control unit (ECU) there should be an automatic switch-over to the other ECU.
  • Page 430 Airplane Description DA 62 AFM Alternate Air In the event of power loss because of icing or blocking of the air filter, there is the possibility of drawing air from the engine compartment. The ALTERNATE AIR operating lever which serves both engines simultaneously is located under the instrument panel to the right of the center console.
  • Page 431 DA 62 AFM Airplane Description 7.9.4 ENGINE INSTRUMENTS The engine instruments are displayed on the Garmin G1000 MFD. Also refer to Section 7.13.3 - MULTI FUNCTION DISPLAY (MFD). Indications for the LH engine are on the left side, indications for the RH engine are on the right side.
  • Page 432 Airplane Description DA 62 AFM Display when pushing the ENGINE button (if MÄM 62-254 is installed): Page 7 - 40 Rev. 0 11-Jan-2019 Doc. No. 11.01.05-E...
  • Page 433 G1000 MFD to show the different display modes. The pictured engine instrument markings may not stringently agree with the current engine limitations of the DA 62. NOTE The fuel calculations on the FUEL CALC portion do NOT use the airplane's fuel quantity indicators.
  • Page 434 Airplane Description DA 62 AFM 7.9.5 FUEL SYSTEM General Page 7 - 42 Rev. 0 11-Jan-2019 Doc. No. 11.01.05-E...
  • Page 435 DA 62 AFM Airplane Description Fuel is stored in the tanks which are located in the wings. Normally fuel for the right engine is taken from the right wing main tank, and for the left engine from the left wing main tank.
  • Page 436 Airplane Description DA 62 AFM Fuel Selector Valves For each engine, one fuel selector valve is provided. The control levers for the fuel selector valves are situated on the center console behind the power levers. The positions are ON, CROSSFEED and OFF. During normal operation, each engine takes the fuel from the tank on the same side as the engine.
  • Page 437 DA 62 AFM Airplane Description Scheme of the Fuel Selector Valve Positions: Possible operating modes of the three fuel selector valve positions are outlined systematically in the following scheme. The figures below, show fuel flows for the RH engine (fuel flows LH are alike): With the LH fuel selector valve in the crossfeed position, the fuel from the RH tank is transferred to the LH engine.
  • Page 438 Airplane Description DA 62 AFM Page 7 - 46 Rev. 0 11-Jan-2019 Doc. No. 11.01.05-E...
  • Page 439 DA 62 AFM Airplane Description Main Fuel Tanks Each tank consists of three aluminum chambers which are connected by a flexible hose. The tank is filled through a filler in the outboard fuel chamber. Only four liters (1 US gal) of fuel in each wing are unusable, so that a total quantity of 96 liters (25.4 US gal) in each...
  • Page 440 Airplane Description DA 62 AFM Auxiliary Fuel Tanks (if installed) The auxiliary tanks are optional equipment (OÄM 62-001). Description The auxiliary fuel tanks are installed in the rear section of the engine nacelles, above the wing main spars. Each auxiliary fuel tank has a filler cap located on the top surface of the nacelle.
  • Page 441 DA 62 AFM Airplane Description If MÄM 62-254 is installed: One fuel probe measures the fuel quantity in each auxiliary tank. The indication is provided by the G1000 flight display. Information about fuel consumption can be found in Chapter 5 -PERFORMANCE.
  • Page 442 Airplane Description DA 62 AFM Alternate Means for Fuel Quantity Indication for the Fuel Tank: The alternate means for fuel quantity indication allows the fuel quantity in the tank to be determined during the preflight inspection. It functions according to the principle of communicating containers.
  • Page 443 DA 62 AFM Airplane Description Alternate Means II for Fuel Quantity Indication for the Fuel Tank: For an exact indication, the airplane must stand on horizontal ground with the wings level. The fuel indicator II includes a protractor for an additional pitch angle measurement. The fuel indicator II is placed on the LH nose baggage compartment floor.
  • Page 444 Airplane Description DA 62 AFM Fuel Quantity Indicator II, Pitch Angle Measurement in Baggage Compartment Page 7 - 52 Rev. 0 11-Jan-2019 Doc. No. 11.01.05-E...
  • Page 445 DA 62 AFM Airplane Description Fuel Quantity Indicator II, Main Tank Doc. No. 11.01.05-E Rev. 0 11-Jan-2019 Page 7 - 53...
  • Page 446 Airplane Description DA 62 AFM Fuel Quantity Indicator II, Aux Tank Page 7 - 54 Rev. 0 11-Jan-2019 Doc. No. 11.01.05-E...
  • Page 447 DA 62 AFM Airplane Description Standard Tank Configuration Fuel Quantity Indicator II: Pitch Angle Reading Usable Fuel Quantity 2° 3° 4° 5° 5° US gal Liter 11.4 15.1 18.9 22.7 26.5 30.3 34.1 37.9 41.6 45.4 49.2 53.0 56.8 60.6 64.4...
  • Page 448 Airplane Description DA 62 AFM Auxiliary Tank (if installed) Configuration Fuel Quantity Indicator II: Pitch Angle Reading Usable Fuel Quantity 2° 3° 4° 5° 5° US gal Liter 92/85 92/86 92/86 92/85 112/105 110/100 110/100 11.4 15.1 18.9 22.7 26.5 30.3...
  • Page 449 DA 62 AFM Airplane Description Fuel Temperature Max. fuel temperature: 60 °C (140 °F) Fuel Grade Approved fuel grades are listed in Section 2.14 - FUEL. NOTE In order to provide information about the fuel grade, it is recommended to enter the fuel grade in the airplane log each time fuel is refilled.
  • Page 450 Airplane Description DA 62 AFM 7.9.6 COOLING SYSTEM The engine is liquid cooled. The liquid cooling system consists of two circuits. The first (small) cooling circuit is always active and includes an integral gearbox oil/coolant heat exchanger and a cabin air heat exchanger.
  • Page 451 DA 62 AFM Airplane Description 7.9.7 OIL SYSTEMS Each engine has two separate oil systems. Lubrication System (Engine and Turbo-Charger) The engine lubrication is a wet sump lubrication system. The oil is cooled by a water/oil-cooler on the upperside of the engine.
  • Page 452 Airplane Description DA 62 AFM 7.9.8 TURBO-CHARGER SYSTEM The exhaust system contains a manifold which collects exhaust gases from the outlets of the cylinders and feeds them to the turbine of the turbo charger. Behind the turbine, the exhaust gases are guided through the lower cowling to the exterior of the airplane.
  • Page 453 Airplane Description 7.9.9 FIRE DETECTION SYSTEM The fire detection system in the DA 62 consists of an overheat detector in the hot area of each engine. In case of an increase of the engine compartment temperature above 250 °C (480 °F) the overheat detector closes the electric circuit and a warning message appears in the annunciation window of the G1000 PFD.
  • Page 454 Airplane Description DA 62 AFM 7.10 ELECTRICAL SYSTEM Page 7 - 62 Rev. 0 11-Jan-2019 Doc. No. 11.01.05-E...
  • Page 455 DA 62 AFM Airplane Description 7.10.1 GENERAL The DA 62 has 28 Volt DC system, which can be sub-divided into: - Power generation - Storage - Distribution - Consumers Power Generation Power generation is provided by two 70 Ampère alternators (generators) which are mounted on the bottom left side of each engine.
  • Page 456 Airplane Description DA 62 AFM Alternator Control: Each alternator has an alternator control unit. It measures the alternator output voltage and controls the current through the alternator field coils via a pulse-width modulated signal. To keep the output voltage stable in all load and speed situations, the alternator field signal is modulated accordingly.
  • Page 457 DA 62 AFM Airplane Description Distribution Electrical power is distributed via the HOT BATTERY BUS, the BATTERY BUS, the LH (RH) ECU BUS, the LH (RH) MAIN BUS, and the AVIONIC BUS. HOT BATTERY BUS: The HOT BATTERY BUS is directly connected to the main battery and cannot be disconnected from the main battery.
  • Page 458 Airplane Description DA 62 AFM MAIN BUS: The LH (RH) MAIN BUS is connected to the BATTERY BUS via a 90 Ampère circuit breaker. The LH MAIN BUS provides power to the consumers directly connected to the LH MAIN BUS. The RH MAIN BUS provides power to the consumers directly connected to the RH MAIN BUS and the AVIONIC BUS via the avionics master relay.
  • Page 459 DA 62 AFM Airplane Description Position and Strobe Lights Combined position and strobe lights (anti collision lights) are installed on both wing tips. Each system is operated by a switch (POSITION, STROBE) located on the row of switches on the instrument panel.
  • Page 460 External Power Socket The DA 62 has an external 28 Volt DC power socket located on the lower surface of the fuselage nose section. When external power is connected, the control relay is energized and the external power comes online.
  • Page 461 DA 62 AFM Airplane Description 7.10.2 ELECTRONIC ENGINE CONTROL UNIT/ECU Engine Control and Regulation The electronic ECU is used to control the engine actuators (e.g. fuel injectors) according to the engine sensor information. The ECU monitors, controls and regulates all important parameters for engine operation.
  • Page 462 Airplane Description DA 62 AFM 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 463 DA 62 AFM Airplane Description 7.10.3 WARNING, CAUTION AND ADVISORY MESSAGES Crew Alerting System (CAS) The G1000 crew alerting system (CAS) is designed to provide visual and aural alerts to the flight crew. Alerts are divided into three levels as follows:...
  • Page 464 Airplane Description DA 62 AFM Alert Levels Level Text Color Importance Audible Tone Warning chime May require tone which repeats Warning immediate without delay until corrective action acknowledged by the crew May require future Single warning Caution Amber corrective action...
  • Page 465 DA 62 AFM Airplane Description Warning Alerts on the G1000 Warning Alerts Meaning/Cause The annunciation is active when the engine coolant L/R ENG TEMP temperature is greater than 100 °C (212 °F). The annunciation is active when the engine oil temperature is L/R OIL TEMP greater than 139 °C (282 °F).
  • Page 466 Airplane Description DA 62 AFM Warning Alerts Meaning/Cause The annunciation is active when the display system is not AIRSPEED FAIL receiving airspeed input from the air data computer. The annunciation is active when the display system is not ALTITUDE FAIL receiving altitude input from the air data computer.
  • Page 467 DA 62 AFM Airplane Description Caution Alerts on the G1000 Caution Alerts Meaning/Cause L/R ECU A FAIL The annunciation is active when a fault was detected by ECU A or ECU B. L/R ECU B FAIL The annunciation is active when the fuel quantity is below L/R FUEL LOW 4 ±...
  • Page 468 Airplane Description DA 62 AFM Annunciation Advisory Alerts on the G1000 Advisory Alerts Meaning/Cause L/R GLOW ON The annunciation is active when the glow plugs are powered. L/R AUXPUMP The annunciation is active when fuel transfer from auxiliary to main tank is in progress (if installed).

  • Page 469: Stall Warning System

    7.12 STALL WARNING SYSTEM The lift detector of the DA 62 is located on the front edge of the left wing below the wing chord line. It is supplied electrically and provides a stall warning, before the angle of attack becomes critical.
  • Page 470 The headset phones are not affected by the switch. Refer to the Garmin G1000 Cockpit Reference Guide, P/N 190-01896-( ), and Garmin G1000 Pilot's Guide for the Diamond DA 62, P/N 190-01895-( ), for complete descriptions of the G1000 system and operating procedures.
  • Page 471 DA 62 AFM Airplane Description NOTE Near the DME ground station, it can happen under certain adverse conditions that the Bendix/King KN 63 DME loses the direct signal from the ground station and locks onto an "echo". This will result in an inaccurate indication of the distance.
  • Page 472 Airplane Description DA 62 AFM 7.13.2 PRIMARY FLIGHT DISPLAY (PFD) The primary flight display (PFD; see figure below) typically displays airspeed, attitude, altitude, and heading information in a traditional format. Slip information is shown as a trapezoid under the bank pointer. One width of the trapezoid is equal to a one ball width slip.
  • Page 473 DA 62 AFM Airplane Description The PFD displays the crew alerting (annunciator) system. When a warning or caution message is received, a warning or caution annunciator will flash on the PFD, accompanied by an aural tone. A warning is accompanied by a repeating tone, and a caution is accompanied by a single tone.
  • Page 474 Airplane Description DA 62 AFM Advisory messages related to G1000 system status are shown in white and are accompanied by a white flashing ADVISORY alert. Refer to the G1000 Pilot's Guide and Cockpit Reference Guide for descriptions of the messages and recommended actions (if applicable).
  • Page 475 DA 62 AFM Airplane Description 7.13.4 AUDIO PANEL The audio panel contains traditional transmitter and receiver selectors, as well as an integral intercom and marker beacon system. The marker beacon lights appear on the PFD. In addition, a clearance recorder records the last 2 ½ minutes of received audio.
  • Page 476 Airplane Description DA 62 AFM 190-01895-( ) or Garmin G1000 NXi Pilot’s Guide, P/N 190-01904-( ) in the latest effective issue for more information. 7.13.8 PFD/MFD CONTROL UNIT (KEYPAD) The optional PFD/MFD control unit is a user interface allowing for ease of data entry, PFD/MFD operation and NAV/COM tuning.
  • Page 477 DA 62 AFM Airplane Description 7.14 AVIONICS 7.14.1 AUTOPILOT SYSTEM General The GFC 700 automatic flight control system (AFCS) is a 3 axis autopilot and flight director system which provides the pilot with the following features: altitude preselect and altitude hold (ALT);...
  • Page 478 Airplane Description DA 62 AFM The GFC 700 may be manually disconnected by any of the following means: - Depressing the red AP DISC button on the pilot's or co-pilot's control stick - Moving the left (outboard) side of the manual electric trim switch on the pilot's control...
  • Page 479 HDG mode, then reselecting NAV mode. The GFC 700 automatic flight control system (AFCS) installed in the Diamond DA 62 consists of the following components: One GDU which contains the following mode control buttons:...
  • Page 480 Airplane Description DA 62 AFM (Flight level change mode on/off) NOSE UP and NOSE DN (Vertical mode reference change) (Yaw damper on/off) This GDU is installed as the MFD. Servos with autopilot processing logic in the pitch, roll, yaw and pitch trim control...
  • Page 481 AP DISC switch or the left side of the MET switch. Refer to the Garmin G1000 Cockpit Reference Guide, P/N 190-01896-( ), and Garmin G1000 Pilot's Guide for the Diamond DA 62, P/N 190-01895-( ), for complete descriptions of the G1000 system and operating procedures.
  • Page 482 Airplane Description DA 62 AFM Power Supply The AVIONIC MASTER switch supplies power to the avionics bus bar of the radio circuit breakers and the AFCS/ESP/USP circuit breaker. The following circuit breaker is used to protect the following element of the GFC 700...
  • Page 483 DA 62 AFM Airplane Description 7.14.2 AUTOMATIC FLIGHT CONTROL SYSTEM ANNUNCIATIONS AND ALERTS Automatic Flight Control System (AFCS) Status Alerts The following annunciations can appear on the PFD above the airspeed and attitude indicators. Only one annunciation occurs at a time, and messages are priorized by criticality.
  • Page 484 Airplane Description DA 62 AFM Caution Alerts on the Automatic Flight Control System (AFCS) Caution Alerts Meaning/Cause ELEVATOR MISTRIM UP - Pitch servo providing sustained force in the indicated direction. ELEVATOR MISTRIM DOWN - Pitch servo providing sustained force in the indicated direction.
  • Page 485 The MD302 Standby Attitude Module is not connected to an external ARINC 429 source (Garmin G1000), thus heading information and automatic BARO synchronization is not available in the DA 62. Doc. No. 11.01.05-E Rev. 0...
  • Page 486 Airplane Description DA 62 AFM Intentionally left blank. Page 7 - 94 Rev. 0 11-Jan-2019 Doc. No. 11.01.05-E...
  • Page 487 Handling, Care, DA 62 AFM Maintenance CHAPTER 8 AIRPLANE HANDLING, CARE AND MAINTENANCE Page INTRODUCTION ........8-2 AIRPLANE INSPECTION INTERVALS .
  • Page 488 Handling, Care, DA 62 AFM Maintenance 8.1 INTRODUCTION Chapter 8 contains the manufacturer's recommended procedures for proper ground handling and servicing of the airplane. The Airplane Maintenance Manual (Doc. No. 7.02.25) lists certain inspection and maintenance requirements which must be followed if the airplane is to retain a new plane performance and reliability.
  • Page 489 Handling, Care, DA 62 AFM Maintenance 8.3 AIRPLANE ALTERATIONS OR REPAIRS Alterations or repairs to the airplane may be carried out only according to the Airplane Maintenance Manual, Doc. No. 7.02.25, and only by authorized personnel. 8.4 SERVICING 8.4.1 REFUELING WARNING Do not allow fire, sparks or heat near fuel.
  • Page 490 Handling, Care, DA 62 AFM Maintenance CAUTION Use only approved fuel types given in Chapter 2. 1. Ground the airplane and the fuel supply vehicle electrically. 2. Remove the fuel filler cap (located on top of the outer wing). Check cap retaining cable for damage.
  • Page 491 Handling, Care, DA 62 AFM Maintenance 8.4.4 TIRE INFLATION PRESSURE CHECK 1. Remove dust cap from valve stem by turning counterclockwise. 2. Connect tire gauge to valve stem, read pressure. 3. Correct pressure if necessary (nose wheel 3.2 bar/46 psi, main wheels 3.8 bar/55 psi).
  • Page 492 Handling, Care, DA 62 AFM Maintenance 8.5 GROUND HANDLING/ROAD TRANSPORT 8.5.1 GROUND HANDLING 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 engaged in the appropriate hole in the nose wheel as shown on the picture.
  • Page 493 Handling, Care, DA 62 AFM Maintenance If the airplane is towed by a towing vehicle, do not turn the nose wheel more than 40 degrees either side of the center position or damage to the gear will result. When towing the airplane with a towing vehicle, a qualified person must sit in the cockpit ready for immediate braking action, in the event the towing becomes uncoupled.
  • Page 494 Handling, Care, DA 62 AFM Maintenance 8.5.2 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 495 Handling, Care, DA 62 AFM Maintenance The control surfaces gust lock is installed as follows: 1. Move the rudder pedals to the middle position. 2. Engage the control surfaces gustlock with the pedals. 3. Engage the stick, wrap straps around stick once.
  • Page 496 Handling, Care, DA 62 AFM Maintenance Page 8 - 10 Rev. 0 11-Jan-2019 Doc. No. 11.01.05-E...
  • Page 497 Handling, Care, DA 62 AFM Maintenance 8.5.3 MOORING Near the lower end of the tail fin of the airplane there is a hole which can be used to tie down the airplane to the ground. Also on each wing near the wing tip, an eyelet with a metric M8 thread can be installed and used as tie-down points.

  • Page 498: Cleaning And Care

    Handling, Care, DA 62 AFM Maintenance 8.6 CLEANING AND CARE CAUTION The airplane must be kept clean. The bright surface prevents the structure from overheating. CAUTION Excessive dirt deteriorates the flight performance. 8.6.1 PAINTED SURFACES The entire surface of the airplane is painted with a white weatherproof two component paint.
  • Page 499 Handling, Care, DA 62 AFM Maintenance 8.6.2 FRONT AND REAR DOOR The windscreen and all windows should be cleaned with 'Plexiklar' or any other acrylic glass detergent if available; otherwise, use lukewarm water. Final cleaning should be carried out with a clean piece of chamois leather or soft cloth. Never rub or polish dry acrylic glass.
  • Page 500 Handling, Care, DA 62 AFM Maintenance The leather interior should be treated with leather sealer within 3 months since new, and then at intervals of 3 to 6 months. Clean the leather interior with an appropriate mild leather cleaning agent and a soft cleaning brush for leather.
  • Page 501 Handling, Care, DA 62 AFM Maintenance 8.7 GROUND DE-ICING Approved deicing fluids are: Manufacturer Name Kilfrost TKS 80 Aeroshell Compound 07 AL-5 (DTD 406B) 1. Remove any snow from the airplane using a soft brush. 2. Spray deicing fluid onto ice-covered surfaces using a suitable spray bottle.
  • Page 502 Handling, Care, DA 62 AFM Maintenance Intentionally left blank. Page 8 - 16 Rev. 0 11-Jan-2019 Doc. No. 11.01.05-E...
  • Page 503 DA 62 AFM Supplements CHAPTER 9 SUPPLEMENTS Page INTRODUCTION ........9-2 LIST OF SUPPLEMENTS .
  • Page 504 DA 62 AFM 9.1 INTRODUCTION Chapter 9 contains information concerning additional (optional) equipment of the DA 62. 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 505 DA 62 AFM Supplements 9.2 LIST OF SUPPLEMENTS Airplane S/N: Registration: Date: Sup. Rev. applicable Title Date Integrated Avionics System Garmin G1000 and G1000 NXi, 31-Jan-2017 SBAS and P-RNAV Operation Electronic Stability and Protection 01-Apr-2015 System (ESP) On Top Exhaust System...
  • Page 506 Supplements DA 62 AFM Airplane S/N: Registration: Date: applicable Sup. Rev. Title Date Page 9 - 4 Rev. 0 11-Jan-2019 Doc. No. 11.01.05-E...

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