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Diamond Aircraft DA 50 C Airplane Flight Manual
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Diamond Aircraft DA 50 C Airplane Flight Manual

Diamond Aircraft DA 50 C Airplane Flight Manual

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Airworthiness Category
Requirement
Serial Number
Registration
Doc. No.
Date of Issue
This Airplane Flight Manual has been approved by EASA under type
certificate No. EASA.A.639.
This Airplane Flight Manual is approved in accordance with 14 CFR Section 21.29 for
U.S. registered aircraft, and is approved by the Federal Aviation Administration.
DIAMOND AIRCRAFT INDUSTRIES GMBH
N.A. OTTO-STR. 5
A-2700 WIENER NEUSTADT
AUSTRIA
AIRPLANE FLIGHT MANUAL
DA 50 C
: Normal
: CS-23
: ________
: ________
: 9.01.01-E
: 26-Aug-2020
Page 0 - 0

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Summary of Contents for Diamond Aircraft DA 50 C

  • Page 1 AIRPLANE FLIGHT MANUAL DA 50 C Airworthiness Category : Normal Requirement : CS-23 Serial Number : ________ Registration : ________ Doc. No. : 9.01.01-E Date of Issue : 26-Aug-2020 This Airplane Flight Manual has been approved by EASA under type certificate No.
  • Page 2 AFM DA 50 C TABLE OF CONTENTS Subject Page 00 - Front Matter ............................00-1 00-01 -Certification Basis - Description .................... 00-2 00-02 -List of Incorporated AFM Changes - Change record ............00-3 01 - General ............................... 01-1 01-01 -AFM Introduction - Description ..................... 01-2 01-02 -Warnings, Cautions and Notes - Description ................
  • Page 3 AFM DA 50 C Subject Page Emergency Procedures General 03-01 -Emergency procedures - Description ................03-3 03-02 -Certain Airspeeds in Emergencies - Description ............. 03-4 03-03 -Selecting Emergency Frequency - Emergency operation procedure ......03-5 Airplane Related CAS Warnings 03-04 -Airplane related G1000 Warning Messages - Emergency operation procedure ..............................
  • Page 4 AFM DA 50 C Subject Page 03-30 -Electrical Fire with Smoke on Ground - Emergency operation procedure ..... 03-43 03-31 -If Take-Off Can Be Aborted - Emergency operation procedure ........03-44 03-32 -If Take-Off CANNOT Be Aborted - Emergency operation procedure ......03-45 03-33 -Engine Fire in Flight - Emergency operation procedure ..........
  • Page 5 AFM DA 50 C Subject Page 03A-18 -Lightning Strike - Special operation ................03A-24 03A-19 -Defective Fuel Transfer System - Emergency operation procedure ......03A-25 Autopilot Failures 03A-20 -Autopilot Diconnect - Emergency operation procedure ..........03A-27 03A-21 -Autopilot Overspeed Recovery - Emergency operation procedure ......03A-28 03A-22 -Loss of Navigation Information - Emergency operation procedure ......
  • Page 6 AFM DA 50 C Subject Page 04-25 -Engine Shut Down - Post-operation procedure ............. 04-51 04-26 -Exit Airplane - Post-operation procedure ............... 04-52 04-27 -Post Flight Inspection - Post-operation procedure ............04-53 04-28 -Parking - Post-operation procedure ................04-54 04-29 -Flight in Rain - Normal operation procedure ..............04-55 04-30 -Refueling - Description ....................
  • Page 7 AFM DA 50 C Subject Page Landing Distances 05-24 -Landing Distances - Description ..................05-41 05-25 -Landing Distances 1999 kg - Description ..............05-43 05-26 -Landing Distances 1800 kg - Description ..............05-45 05-27 -Landing Distances 1600 kg - Description ..............05-47 Landing Distance Abnormal Flap Position 05-28 -Landing Distances - Abnormal Flap Position 1999 kg - Description ......
  • Page 8 AFM DA 50 C Subject Page 07-05 -Rudder - Description ......................07-7 07-06 -Elevator - Description ...................... 07-8 07-07 -Elevator Trim - Description ....................07-9 07-08 -Rudder Trim - Description ....................07-10 07-09 -Rudder Pedal - Description .................... 07-11 Instrument Panel 07-10 -Instrument Panel - Description ..................
  • Page 9 AFM DA 50 C Subject Page 07-35 -Crew Alerting System (CAS) - Description ..............07-69 Garmin G1000 NXI 07-36 -Garmin G1000 NXi Integrated Avionics System - Description ........07-72 07-37 -Primary Flight Display (PFD) - Description ..............07-73 07-38 -Multi-Function Display (MFD) - Description ..............07-75 07-39 -Audio Panel - Description ....................
  • Page 10 AFM DA 50 C Subject Page 09-01 -Supplements - Description ....................09-2 Doc No.: 9.01.01-E Page ix Issue : 011 14-Dec-2022...
  • Page 11 AFM DA 50 C LIST OF EFFECTIVE DATA MODULES Document title Data Module Code Issue date Certification Basis - Description DA50-A-00-00-00-01A-040A-D 16-05-2022 List of Incorporated AFM Changes - Change record DA50-A-00-40-01-00A-00TA-D 14-12-2022 AFM Introduction - Description DA50-A-00-40-00-01A-040A-D 09-09-2021 Warnings, Cautions and Notes - Description...
  • Page 12 AFM DA 50 C Document title Data Module Code Issue date Selecting Emergency Frequency - Emergency operation procedure DA50-A-15-41-02-00A-141A-D 26-08-2020 Airplane related G1000 Warning Messages - Emergency operation procedure DA50-A-15-49-00-00A-141A-D 18-05-2022 ALTN 1/2 AMPS - Emergency operation procedure DA50-A-15-42-00-03A-141A-D 26-08-2020...
  • Page 13 AFM DA 50 C Document title Data Module Code Issue date If Take-Off Can Be Aborted - Emergency operation procedure DA50-A-15-43-01-00A-141A-D 28-05-2021 If Take-Off CANNOT Be Aborted - Emergency operation procedure DA50-A-15-43-01-01A-141A-D 28-05-2021 Engine Fire in Flight - Emergency operation procedure...
  • Page 14 AFM DA 50 C Document title Data Module Code Issue date Defective Fuel Transfer System - Emergency operation procedure DA50-A-15-44-02-01A-141A-D 28-05-2021 Autopilot Diconnect - Emergency operation procedure DA50-A-15-47-10-01A-141A-D 15-07-2021 Autopilot Overspeed Recovery - Emergency operation procedure DA50-A-15-47-10-02A-141A-D 15-07-2021 Loss of Navigation Information - Emergency operation...
  • Page 15 AFM DA 50 C Document title Data Module Code Issue date Exit Airplane - Post-operation procedure DA50-A-15-35-00-03A-151A-D 26-08-2020 Post Flight Inspection - Post-operation procedure DA50-A-15-35-00-04A-151A-D 26-08-2020 Parking - Post-operation procedure DA50-A-15-35-00-05A-151A-D 16-08-2022 Flight in Rain - Normal operation procedure DA50-A-15-36-00-03A-131A-D...
  • Page 16 AFM DA 50 C Document title Data Module Code Issue date Landing Distances - Abnormal Flap Position 1600 kg - Description DA50-A-15-62-09-03A-040A-D 09-09-2021 Go-Around Climb Performance - Description DA50-A-15-62-07-00A-040A-D 26-08-2020 Go-Around Climb Performance 1999 kg - Description DA50-A-15-62-07-01A-040A-D 06-05-2022 Go-Around Climb Performance 1800 kg - Description...
  • Page 17 AFM DA 50 C Document title Data Module Code Issue date Propeller - Description DA50-A-61-00-00-99A-040A-D 28-05-2021 Propeller Control - Description DA50-A-61-20-00-99A-040A-D 26-08-2020 Engine Operating Controls - Description DA50-A-76-00-99-00A-040A-D 09-09-2021 Engine Instruments - Description DA50-A-77-00-00-99A-040A-D 09-09-2021 Cooling System - Description DA50-A-75-20-00-99A-040A-D...
  • Page 18 AFM DA 50 C Document title Data Module Code Issue date Mooring - Description DA50-A-15-37-02-02A-040A-D 26-08-2020 Jacking - Description DA50-A-15-37-02-03A-040A-D 26-08-2020 Cleaning and Care - Description DA50-A-15-37-03-00A-040A-D 28-05-2021 Cleaning the Aircraft from Ice and Snow - Description DA50-A-15-37-04-00A-040A-D 08-06-2022 Supplements - Description...
  • Page 19 AFM DA 50 C LIST OF FIGURES Figure Title Page 01 - General Three-View Drawing ....................... 01-13 02 - Operating Limitations Permissible Center of Gravity Range ................02-9 Limitation Placards 1 ....................... 02-16 Limitation Placards 2 ....................... 02-17 Limitation Placards 3 ....................... 02-18 Limitation Placards 4 .......................
  • Page 20 AFM DA 50 C Figure Title Page Landing Gear Retracted ....................07-22 Emergency Extension of the Landing Gear ..............07-23 Seats and Safety Harnesses Pilots Seat ........................07-27 Doors and Interior Emergency Exit Window ....................07-32 Powerplant Propeller Setpoint Curve ....................07-40 G1000 NXi Engine page ....................
  • Page 21 AFM DA 50 C Front Matter FRONT MATTER Doc No.: 9.01.01-E Page 00-1 Issue : 011 14-Dec-2022...
  • Page 22 AFM DA 50 C Front Matter 00-01 Certification Basis Description Certification Basis CAUTION THE DA 50 C IS A SINGLE ENGINE AIRPLANE. WHEN THE OPERATING LIMITATIONS MAINTENANCE REQUIREMENTS ARE COMPLIED WITH, IT HAS THE HIGH DEGREE OF RELIABILITY, WHICH IS REQUIRED BY THE CERTIFICATION BASIS.
  • Page 23 AFM DA 50 C Front Matter 00-02 List of Incorporated AFM Changes Change record List of Incorporated AFM Changes Issue 1 Basic Manual Issue date: 26-Aug-2020 Issue 2 Following changes are incorporated in Issue 2 Change Title MÄM 50-013 Baggage Compartment...
  • Page 24 AFM DA 50 C Front Matter Issue 3 Following changes are incorporated in Issue 3 Change Title MÄM 50-117 AFM Landing Distance - Imperial Values 50-118 AFM Doc. No. 9.01.01-E Issue 3 OÄM 50-006 Avidyne TAS 605A Series 50-009 Electronic Stability and Protection...
  • Page 25 AFM DA 50 C Front Matter Issue 5 Following changes are incorporated in Issue 5 Change Title MÄM 50-136 No. 3 Jet Fuel 50-145 AFM Doc. No. 9.01.01-E Issue 5 OÄM 50-003 ADF Installation Table 4 Issue 5 Changes The technical content of Issue 5 has been approved under the authority of the DOA ref. EASA.21J.
  • Page 26 AFM DA 50 C Front Matter Issue 7 Following changes are incorporated in Issue 7 Change Title MÄM 50-097 Exhaust System Modification 50-148 Use of PED 50-166 AFM Doc. No. 9.01.01-E Issue 7 50-175 Power Lever Marking Harmonization OÄM 50-032...
  • Page 27 AFM DA 50 C Front Matter Issue 9 Following changes are incorporated in Issue 9 Change Title MÄM 50-229 Cleaning from Ice and Snow 50-238 AFM Doc. No. 9.01.01-E Issue 9 OÄM 50-011 Ice Protection System for flights into known icing Table 8 Issue 9 Changes The technical content of Issue 9 has been approved under the authority of the DOA ref.
  • Page 28 AFM DA 50 C Front Matter Issue 11 Following changes are incorporated in Issue 11 Change Title MÄM 50-199 Jet A Fuel (ASTM D1655) 50-217 AFM - Doc. No. 9.01.01-E Incorporation of FAA Comments 50-259 Fuel Level Check Tool Information...
  • Page 29 AFM DA 50 C General GENERAL Doc No.: 9.01.01-E Page 01-1 Issue : 011 14-Dec-2022...
  • Page 30 AFM DA 50 C General 01-01 AFM Introduction Description Introduction This Airplane Flight Manual has been prepared in order to provide pilots and instructors with all the information required for the safe and efficient operation of the airplane. The Airplane Flight Manual includes all the data which must be made available to the pilot according to the CS-23 requirements.
  • Page 31 AFM DA 50 C General 01-02 Warnings, Cautions and Notes Description Warnings, Cautions and Notes WARNING MEANS THAT NON-OBSERVATION CORRESPONDING PROCEDURE LEADS TO AN IMMEDIATE OR IMPORTANT DEGRADATION IN FLIGHT SAFETY. CAUTION MEANS THAT NON-OBSERVATION CORRESPONDING PROCEDURE LEADS TO A MINOR OR TO A MORE OR LESS LONG TERM DEGRADATION IN FLIGHT SAFETY.
  • Page 32 01-03 Dimensions and areas Description Dimensions The DA 50 C uses the System Internationale (SI) for dimensions and areas. Imperial dimensions are also given in brackets. For example: Wing span 13.41 m (44 ft). DA 50 C Dimensions Overall Dimensions Wing span 13.41 m (44 ft)
  • Page 33 Nose Wheel Tire 5.00-5, for details refer to AMM Tire inflation pressure (unloaded) 6.1 bar (88.5 psi) Damper gas pressure (unloaded) 8 bar (116 psi) Table 1 DA 50 C Dimensions Doc No.: 9.01.01-E Page 01-5 Issue : 011 14-Dec-2022 DA50-A-06-00-00-00A-040A-D...
  • Page 34 AFM DA 50 C General 01-04 Acronyms Description Acronyms Airspeeds Indicated Airspeed as shown on an airspeed indicator. KCAS Calibrated Airspeed in knots. Indicated airspeed, corrected for installation and instrument errors. Calibrated Airspeed equals TAS at standard atmospheric conditions (ISA) at MSL.
  • Page 35 AFM DA 50 C General reaches -56.5 °C (-69.7 °F) is -0.0065 °C/m (-0.00357 °F/ft), and above this 0 °C/m (0 °F/ft). Mean Sea Level. Outside Air Temperature. Theoretical atmospheric pressure at MSL, calculated from the elevation of the measuring point above MSL and the actual atmospheric pressure at the measuring point.
  • Page 36 AFM DA 50 C General Moment Arm The horizontal distance from the Datum Plane to the Center of Gravity of a component. Moment The mass of a component multiplied by its moment arm. Usable Fuel The quantity of fuel available for flight planning.
  • Page 37 AFM DA 50 C General STALL/STATIC HT. Stall Warning/Static Heating System RUDDER TRIM Rudder Trim System AIR CTRL. ECS Fan ALT1 Alternator 1 ALT2 Alternator 2 ECS Control MAIN TIE Main Tie Relay USB PORTS USB Ports PEDALS Adjustable Rudder Pedals...
  • Page 38 AFM DA 50 C General Acceptable Means of Compliance Airplane Maintenance Manual AIRAC Aeronautical Information Regulation and Control Air Traffic Control B-RNAV Basic Area Navigation Crew Alerting System CFRP Carbon Fiber Reinforced Plastic EASA European Aviation Safety Agency Electronic Flight Bag...
  • Page 39 AFM DA 50 C General 01-05 Conversion Factors Description Conversion Factors Dimension SI-Units US-Units Conversion Length [mm] millimeters [in] inches [mm] / 25.4 = [in] [m] meters [ft] feet [m] / 0.3048 = [ft] [km] kilometers [NM] nautical miles [km] / 1.852 = [NM]...
  • Page 40 AFM DA 50 C General 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 31.7 121.1 34.3 128.7 37.0 136.3 39.6...
  • Page 41 AFM DA 50 C General 01-06 Three-View Drawing Description Three-View Drawing Figure 1 - Three-View Drawing Doc No.: 9.01.01-E Page 01-13 Issue : 011 14-Dec-2022 DA50-A-06-00-00-01A-040A-D...
  • Page 42 AFM DA 50 C General 01-07 G1000 NXi Avionics System Description G1000 NXi Avionics System The DA 50C airplane is equipped with a Garmin G1000 NXi Avionics System. The Garmin GNSS navigation system installed in this airplane is a GPS system with a Satellite Based...
  • Page 43 AFM DA 50 C General Specification Reference Document ICAO Flight Plan Integrated flight Code deck G1000 NXi EASA or JAA with SBAS 13.00 or later is in- stalled. FAA AC 90-107 EASA AMC 20-28 RNP AR APCH FAA AC 90-101A...
  • Page 44 AFM DA 50 C Operating Limitations OPERATING LIMITATIONS Doc No.: 9.01.01-E Page 02-1 Issue : 011 14-Dec-2022...
  • Page 45 AFM DA 50 C Operating Limitations 02-01 Aircraft release/operating limitations Description Aircraft Operating Limitations Introduction WARNING OPERATION AIRPLANE OUTSIDE APPROVED OPERATING LIMITATIONS PERMISSIBLE. Chapter 2 of this Airplane Flight Manual includes operating limitations, instrument markings, and placards necessary for the safe operation of the airplane, its power-plant, standard systems and standard equipment.
  • Page 46 AFM DA 50 C Operating Limitations 02-02 Airspeed Limitations Description Airspeed Limitations Airspeed KIAS Remarks Operating maneuverung above 1850 kg 133 KIAS Do not make full or abrupt speed above 1650 kg 125 KIAS control surface movement above this speed.
  • Page 47 AFM DA 50 C Operating Limitations 02-03 Airspeed Indicator Markings Description Airspeed Indicator Markings Marking KIAS Significance White arc 59 - 121 Operating range with flaps fully extended Green arc 72 - 152 Normal operating range Yellow arc 152 - 191 "Caution"...
  • Page 48 AFM DA 50 C Operating Limitations 02-04 Power Plant Limitations Description Power Plant Limitations Engine Manufacturer Continental Aerospace Technologies Type Centurion 3.0 (CD-300) Engine power Take-off power (max. 5 min) 100% 300 hp (221 kW) at 2340 Propeller RPM Max. continuous power...
  • Page 49 AFM DA 50 C Operating Limitations Starting min. -25 °C Coolant temperature Normal operation 60 °C - 101 °C Maximum 105 °C Starting min. -25 °C Gearbox temperature Minimum 50 °C Maximum 110 °C Fuel pressure (gauge pressure) Minimum -0.3 bar Maximum 1.0 bar...
  • Page 50 AFM DA 50 C Operating Limitations 02-05 Engine Instrument Markings Description Engine Instrument Markings Engine instrument markings and their colour code significance are shown in the table below. Red arc/bar Yellow arc/bar Green arc/bar Yellow arc/bar Red arc/bar lower normal...
  • Page 51 AFM DA 50 C Operating Limitations 02-06 Mass (Weight) Description Mass (Weight) WARNING EXCEEDING THE MASS LIMITS WILL LEAD TO AN OVERSTRESSING OF THE AIRPLANE AS WELL AS TO A DEGRADATION OF FLIGHT CHARACTERISTICS AND FLIGHT PERFORMANCE. Value Mass (Weight)
  • Page 52 AFM DA 50 C Operating Limitations 02-07 Center of Gravity Description Centre of Gravity The Datum Plane (DP) is located 2.196 m forward of the most forward point of the root rib on the stub wing. The flight CG position must be within the following limits: Most forward flight CG: 2.315 m aft of datum plane at 1480 kg to 1750 kg...
  • Page 53 AFM DA 50 C Operating Limitations 02-08 Approved Maneuvres, Attitudes and Flight Conditions Description Approved Maneuvers CAUTION AEROBATICS, SPINNING, AND FLIGHT MANEUVERS WITH MORE THAN 60° OF BANK ARE NOT PERMITTED IN THE NORMAL CATEGORY. CAUTION INTENTIONAL NEGATIVE G-MANEUVERS PERMITTED.
  • Page 54 AFM DA 50 C Operating Limitations 02-09 Maneuvring Load Factors Description Maneuvring Load Factors WARNING THE TABLE BELOW SHOWS STRUCTURAL LIMITATIONS. EXCEEDING THE MAXIMUM LOAD FACTORS WILL LEAD TO AN OVERSTRESSING OF THE AIRPLANE. CAUTION INTENTIONAL NEGATIVE G-MANEUVERS PERMITTED. at v...
  • Page 55 AFM DA 50 C Operating Limitations 02-10 Operating Altitude Description Operating Altitude The maximum operating altitude is 20,000 ft (6,096 m) pressure altitude. NOTE Additional altitude restrictions based on operational requirements for supplemental oxygen may apply. Doc No.: 9.01.01-E Page 02-12...
  • Page 56 AFM DA 50 C Operating Limitations 02-11 Flight Crew Description Flight Crew Minimum crew: 1 (one person) Maximum number of 5 (five persons) occupants: Doc No.: 9.01.01-E Page 02-13 Issue : 011 14-Dec-2022 DA50-A-15-10-00-11A-040A-D...
  • Page 57 AFM DA 50 C Operating Limitations 02-12 Kinds of Operation Description Kinds of Operation Provided that national operational requirements are met, the following kinds of operation are approved: Daytime flights according to Visual Flight Rules (VFR) With the appropriate equipment: night flights according to Visual Flight Rules (NVFR)
  • Page 58 AFM DA 50 C Operating Limitations For daytime VFR flights In addition for night VFR In addition for IFR flights flights Load Propeller RPM Fuel temperature left & right tank Fuel flow Fuel pressure ECU A/B caution Electrical Alternator (1x)
  • Page 59 02-13 Limitation Placards Description Limitation Placards All limitation placards relevant for the DA 50 C airplane are shown below. A list of all placards is included in the Airplane Maintenance Manual, latest revision, Chapter 11. Figure 2 - Limitation Placards 1 Doc No.: 9.01.01-E...
  • Page 60 AFM DA 50 C Operating Limitations On the Instrument Panel: LANDING GEAR  = 162 KIAS On the Emergency Landing Gear Extension Lever: EMERGENCY Gear Extension Max. 102 KIAS On the Instrument Panel: max. usable fuel:  LH (Main) Tank: 25.0 US gal RH (Aux) Tank: 24.0 US gal max. difference LH/RH tank: 9 US gal Figure 3 - Limitation Placards 2 Doc No.: 9.01.01-E Page 02-17 Issue : 011 14-Dec-2022 DA50-A-11-30-00-99A-040A-D...
  • Page 61 AFM DA 50 C Operating Limitations Next to Each of the Two Filler Necks: WARNING APPROVED FUEL JET A-1 or see Airplane Flight Manual On the Engine Cowling: Engine Oil AeroShell Oil Diesel Ultra Figure 4 - Limitation Placards 3 Doc No.: 9.01.01-E Page 02-18 Issue : 011 14-Dec-2022 DA50-A-11-30-00-99A-040A-D...
  • Page 62 AFM DA 50 C Operating Limitations Figure 5 - Limitation Placards 4 Doc No.: 9.01.01-E Page 02-19 Issue : 011 14-Dec-2022 DA50-A-11-30-00-99A-040A-D...
  • Page 63 AFM DA 50 C Operating Limitations Figure 6 - Limitation Placards 5 Doc No.: 9.01.01-E Page 02-20 Issue : 011 14-Dec-2022 DA50-A-11-30-00-99A-040A-D...
  • Page 64 AFM DA 50 C Operating Limitations Figure 7 - Limitation Placards 6 Figure 8 - Limitation Placards 5 Doc No.: 9.01.01-E Page 02-21 Issue : 011 14-Dec-2022 DA50-A-11-30-00-99A-040A-D...
  • Page 65 AFM DA 50 C Operating Limitations Figure 9 - Limitation Placards 8 (if Tablet Mount is installed) Doc No.: 9.01.01-E Page 02-22 Issue : 011 14-Dec-2022 DA50-A-11-30-00-99A-040A-D...
  • Page 66 AFM DA 50 C Operating Limitations 02-14 Fuel Description Fuel Approved fuel designations: JET A-1 (ASTM D 1655) JET A (ASTM D 1655) No.3 Jet Fuel (China, GB 6537-2018) NOTE Use only uncontaminated fuel from reliable sources. Main tank (LH)
  • Page 67 AFM DA 50 C Operating Limitations NOTE The instructions of the fuel additive supplier must be followed. 1.2 Operation with Anti-Icing Fuel Additives The application of the following additive is permitted: PRIST Hi-Flash MIL- max. 1500 ppm DTL-85470(B) ASTM D...
  • Page 68 AFM DA 50 C Operating Limitations 02-15 Temperature Limitations Description Temperature Limits The airplane may only be operated when its temperature prior to operation is not less than -25 °C (-13 ° With the airplane cold soaked and its temperature below -20 °C (-4 °F) the use of an external pre-heater for the engine and pilot compartment prior to operation is mandatory.
  • Page 69 AFM DA 50 C Operating Limitations 02-16 Battery Charge Description Battery Charge Take-off for a Night VFR or IFR flight with an empty main battery is not permitted. The use of an external power supply for engine starting with an empty airplane main battery is not permitted if the subsequent flight is intended to be a Night VFR or an IFR flight.
  • Page 70 AFM DA 50 C Operating Limitations 02-17 Door Locking Device Description Door Locking Device The LH and RH crew doors and the passenger door must not be blocked by the key lock during operation of the airplane. Doc No.: 9.01.01-E...
  • Page 71 AFM DA 50 C Operating Limitations 02-18 Electronic Equipment Description Portable Electronic Devices The use of Portable Electronic Devices (PED) during low visibility approaches is prohibited. NOTE Refer to EASA AMC 20-25 or FAA AC 120.76A for the use of PED associated to electronic flight bag (EFB) operation The use of any device as an EFB may require separate approvals.
  • Page 72 AFM DA 50 C Operating Limitations 02-19 Smoking Description Smoking Smoking in the airplane is not permitted. Doc No.: 9.01.01-E Page 02-29 Issue : 011 14-Dec-2022 DA50-A-15-10-00-19A-040A-D...
  • Page 73 AFM DA 50 C Operating Limitations 02-20 Garmin G1000 NXi Avionics System Description Garmin G1000 Avionics System The Garmin G1000 NXi Cockpit Reference Guide, P/N 190-02800-( ), appropriate revision must be immediately available to the flight crew. The Garmin G1000 NXi must utilize the software Garmin 190-02576-( ), approved software in accordance with the mandatory service bulletin DAI MSB 50-003, latest version.
  • Page 74 AFM DA 50 C Operating Limitations ALT, VS : ft, fpm (sets altitude units to "feet" and "feet per minute") POSITION : deg-min (sets navigation grid units to decimal minutes) NOTE Navigation Information is referenced to WGS-84 reference system, and should only be used where the Aeronautical Information Publication (including electronic data and aeronautical charts) conforms to WGS-84 or equivalent.
  • Page 75 AFM DA 50 C Operating Limitations Software Part Number Approved Version Function System for approved version see DAI MSB 50-003 latest version 010-02576-( ) Manifest 006-B0093-( ) GPS1, GPS2 006-B0172-( ) GTX1-GIA1, GTX1-GIA2 006-B0190-( ) GIA1, GIA2 006-B0193-( ) GEA1-GIA1; GEA1-GIA2...
  • Page 76 AFM DA 50 C Operating Limitations 02-21 Garmin G1000 NXi GPS Navigation System Limitations Description G1000 NXi GPS Navigation System Limitations Flight Preparation Phase For flight planning purposes, operations on RNP and RNAV procedures when SBAS signals are not available, the availability of GPS integrity RAIM shall be confirmed for the intended route of flight. In...
  • Page 77 AFM DA 50 C Operating Limitations Preflight Phase SBAS functionality must be enabled on the G1000 NXi GPS Status page (refer to the G1000 NXi Pilot’s Guide for procedure). The pilot must confirm at system initialization that the Navigation database is current. GPS/SBAS...
  • Page 78 AFM DA 50 C Operating Limitations NOTE Not all published Instrument Approach Procedures (IAP) are in the Navigation database. Pilots planning on flying an RNAV instrument approach must ensure that the Navigation database contains the planned RNAV Instrument Approach Procedure and that approach procedure must be loaded from the Navigation database into the FMS flight plan by its name.
  • Page 79 AFCS / ESP circuit breaker is prohibited, until the cause of the malfunction has been determined and corrected. The Garmin G1000 NXi Cockpit Reference Guide for the Diamond DA 50 C, P/N 190-02800- ( ) approved revision must be immediately available to the flight crew.
  • Page 80 AFM DA 50 C EMERGENCY PROCEDURES Doc No.: 9.01.01-E Page 03-1 Issue : 011 14-Dec-2022...
  • Page 81 AFM DA 50 C EMERGENCY PROCEDURES GENERAL Doc No.: 9.01.01-E Page 03-2 Issue : 011 14-Dec-2022...
  • Page 82 AFM DA 50 C 03-01 Emergency procedures Description Introduction WARNING IN EACH EMERGENCY, CONTROL OVER THE FLIGHT ATTITUDE AND THE PREPARATION OF A POSSIBLE EMERGENCY LANDING HAVE PRIORITY OVER ATTEMPTS TO SOLVE THE CURRENT PROBLEM ("FIRST FLY THE AIRCRAFT"). PRIOR TO THE FLIGHT THE PILOT MUST CONSIDER THE SUITABILITY OF THE TERRAIN FOR AN EMERGENCY LANDING FOR EACH PHASE OF THE FLIGHT.
  • Page 83 AFM DA 50 C 03-02 Certain Airspeeds in Emergencies Description Certain Airspeeds in Emergencies Event KIAS Airspeed for best glide angle (Flaps UP) Airspeed for emergency landing with engine off Flaps UP Flaps T/O Flaps LDG ≤ 102 Emergency gear extension...
  • Page 84 AFM DA 50 C 03-03 Selecting Emergency Frequency Emergency operation procedure 1 Selecting Emergency Frequency In an in-flight emergency, depressing and holding the Com transfer button ↔ on the G1000 for 2 seconds will tune the emergency frequency of 121.500 MHz. If the display is available, it will also show it in the "Active"...
  • Page 85 AFM DA 50 C AIRPLANE RELATED CAS WARNINGS Doc No.: 9.01.01-E Page 03-6 Issue : 011 14-Dec-2022...
  • Page 86 AFM DA 50 C 03-04 Airplane related G1000 Warning Messages Emergency operation procedure 1 Crew Alert System (CAS) Warning Messages CAS Message Cause Corrective Action Engine alternator 1 output is higher 03-05 - ALTN 1/2 AMPS - ALTN 1 AMPS than 70 A.
  • Page 87 AFM DA 50 C CAS Message Cause Corrective Action Front right door is not closed and 03-11 - Unlocked Doors - R DOOR OPEN locked. Emergency operation procedure. Fuel temperature in right fuel tank 03-12 - L/R FUEL TEMP - R FUEL TEMP is above 60 °C.
  • Page 88 AFM DA 50 C 03-05 ALTN 1/2 AMPS Emergency operation procedure 1 Alternator High Load / High Current ALTN 1 AMPS ALTN 2 AMPS Engine alternator output is in the upper red range (too high / above 70 A). This warning is indicated when the consumption of electrical power is too high.
  • Page 89 AFM DA 50 C 03-06 ALTN 1/2 FAIL Emergency operation procedure 1 Alternator 1 and Alternator 2 Failure ALTN 1 FAIL ALTN 2 FAIL Both engine alternators have failed. WARNING THE ECU, WHICH IS ABSOLUTELY NECESSARY FOR ENGINE OPERATION, NEEDS ELECTRICAL POWER.
  • Page 90 AFM DA 50 C 03-07 COOLANT TEMP Emergency operation procedure 1 Coolant Temperature High COOLANT TEMP Engine coolant temperature is in the upper red range (too high / above 105 °C). Coolant temperatures above the limit value of 105 °C can lead to a total loss of power due to engine failure.
  • Page 91 AFM DA 50 C POWER............................reduce Airspeed................increase, if necessary by initiating a descent COWL FLAP.............................open COOLANT TEMP....................check for green range If the coolant temperature does not return to the green range, perform a precautionary landing on the nearest suitable airfield. Prepare for an engine failure in accordance with 03-18 - Engine Failure in Flight - Emergency operation procedure.
  • Page 92 AFM DA 50 C 03-08 ENG OIL TEMP Emergency operation procedure 1 Engine Oil Temperature High ENG OIL TEMP Engine oil temperature is in the upper red range (too high / above 125 °C). Oil temperatures above the limit value of 125 °C can lead to a total loss of power due to engine failure.
  • Page 93 AFM DA 50 C 03-09 FUEL PRESS Emergency operation procedure 1 Fuel Pressure FUEL PRESS Engine fuel pressure is below -0.3 bar or above 1.0 bar. Fuel Pressure Low Fuel quantity............................check FUEL valve........................check NORMAL EMERGENCY FUEL PUMP switch.....................ON If FUEL PRESS warning remains FUEL valve........................EMERGENCY...
  • Page 94 AFM DA 50 C 03-10 GB OIL TEMP Emergency operation procedure 1 Gearbox Oil Temperature High GB OIL TEMP Engine gearbox temperature is in the upper red range (too high / above 110 °C). Gearbox temperatures above the limit value of 110 °C can lead to a total loss of power due to engine failure.
  • Page 95 AFM DA 50 C 03-11 Unlocked Doors Emergency operation procedure 1 Unlocked Doors L DOOR OPEN R DOOR OPEN REAR DOOR OPEN Left, Right or Rear Door is not closed. Airspeed........................reduce immediately Doors........................check visually if closed Rear door......................check visually if closed Doors Unlocked Airspeed...........................below 140 KIAS...
  • Page 96 AFM DA 50 C 03-12 L/R FUEL TEMP Emergency operation procedure 1 Fuel Temperature High L FUEL TEMP R FUEL TEMP Fuel temperature is in the upper red range (too high / above 61 °C). Fuel temperatures above the limit value of 61 °C can lead to a noticeable reduction of the high pressure pump efficiency.
  • Page 97 AFM DA 50 C 03-13 OIL PRES Emergency operation procedure 1 Oil Pressure OIL PRES Engine oil pressure is in the lower red range (too low / below 2.0 bar) or higher red range (too high / above 7.5 bar).
  • Page 98 AFM DA 50 C Coolant temperature........................check If temperatures are within green range Expect wrong oil pressure indication. Keep monitoring temperatures. If temperatures are not within green range POWER............................reduce Expect engine failure and prepare for an emergency landing without engine power in accordance with 03-41 - Emergency Landing with Engine Off - Emergency operation procedure.
  • Page 99 AFM DA 50 C 03-14 Starter Malfunction Emergency operation procedure 1 Starter Malfunction STARTER If the starter does not disengage from the engine after starting (Starter engaged warning STARTER illuminates after the engine has started). On Ground POWER lever.........................Ground Idle (GI) ENGINE MASTER..........................OFF...
  • Page 100 AFM DA 50 C 03-15 ENG INTAKE Emergency operation procedure 1 Engine Air Intake Temperature High ENG INTAKE Engine air intake temperature is high (above 80 °C) for more than 30 seconds. High engine intake temperatures leads to reduces power output.
  • Page 101 AFM DA 50 C ENGINE FAILURES Doc No.: 9.01.01-E Page 03-22 Issue : 011 14-Dec-2022...
  • Page 102 AFM DA 50 C 03-16 Engine Failure during Take-Off Emergency operation procedure 1 Engine Failure during Take-Off Take-Off Can Still Be Aborted (Sufficient Runway Length Available) POWER lever.........................Ground Idle (GI) Brakes...........................Apply, as needed ENGINE MASTER..........................OFF FUEL valve........................OFF (lift and turn) NOTE Inform ATC if needed.
  • Page 103 AFM DA 50 C 03-17 Engine Failures on Ground Emergency operation procedure 1 Engine Failures on Ground POWER lever.........................Ground Idle (GI) Brakes.............................as required WARNING IF THE PROBLEM CANNOT BE CLEARED, TAKE-OFF IS PROHIBITED. CAUTION IF THE OIL PRESSURE IS IN THE RED RANGE, THE ENGINE MUST BE SHUT DOWN IMMEDIATELY.
  • Page 104 AFM DA 50 C 03-18 Engine Failure in Flight Emergency operation procedure 1 Engine Failure in Flight WARNING CONTROL OVER THE FLIGHT ATTITUDE HAS PRIORITY OVER ATTEMPTS TO SOLVE THE CURRENT PROBLEM ("FIRST FLY THE AIRPLANE"). NOTE As long as there is no major mechanical engine defect, the propeller will continue to windmill.
  • Page 105 AFM DA 50 C If Failure persists FADEC switch...........................FORCE B NOTE If selecting FORCE B does not solve the problem, switch back to AUTO. If engine failure does not clear itself immediately, and the engine is no longer producing sufficient power...
  • Page 106 AFM DA 50 C 03-19 Restart Engine in Flight Emergency operation procedure 1 Restart Engine in Flight The propeller probably continues to windmill. A stopped propeller may indicate a major mechanical defect. In this case use starter assisted restart with extreme caution.
  • Page 107 AFM DA 50 C 03-20 Defective RPM Regulating System Emergency operation procedure 1 Defective RPM Regulating System WARNING IN CASE OF DEFECTIVE RPM REGULATING SYSTEM, REDUCED ENGINE PERFORMANCE SHOULD BE ANTICIPATED. CAUTION FOLLOWING A FAILURE OF THE PROPELLER CONTROL REGULATOR THE RPM SHOULD BE ADJUSTED WITH THE POWER LEVER.
  • Page 108 AFM DA 50 C After RPM has Stabilized Below 2300 RPM Airspeed..................as required, do not exceed 2300 RPM POWER lever................as required, do not exceed 2300 RPM If the Problem Does Not Clear: FADEC switch...........................FORCE B If Selecting FORCE B Does Not Solve the Problem FADEC switch..........................AUTO...
  • Page 109 AFM DA 50 C 03-21 Defective Cowl Flap Emergency operation procedure 1 Defective Cowl Flap Cowl flap indicator light does not indicate the selected cowl flap position. Coolant temperature........................check The flight can be continued, but coolant temperature has to be monitored.
  • Page 110 AFM DA 50 C 03-22 Inflight Engine Troubleshooting Emergency operation procedure 1 Engine Troubleshooting WARNING CONTROL OVER THE FLIGHT ATTITUDE HAS PRIORITY OVER ATTEMPTS TO SOLVE THE CURRENT PROBLEM ("FIRST FLY THE AIRCRAFT") NOTE As long as there is no major mechanical engine defect, the propeller will continue to windmill.
  • Page 111 AFM DA 50 C If the engine power could not be restored by this procedure, prepare for 03-18 - Engine Failure in Flight - Emergency operation procedure and land as soon as possible. Doc No.: 9.01.01-E Page 03-32 Issue : 011...
  • Page 112 AFM DA 50 C LANDING GEAR SYSTEM FAILURES Doc No.: 9.01.01-E Page 03-33 Issue : 011 14-Dec-2022...
  • Page 113 AFM DA 50 C 03-23 Emergency Gear Extension Emergency operation procedure 1 Emergency Gear Extension 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 102 KIAS. The manual extension of the landing gear may take up to 20 sec.
  • Page 114 AFM DA 50 C 03-24 Landing with A Defective Tire on the MLG Emergency operation procedure 1 Landing with a Defective Tire on the MLG 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.
  • Page 115 AFM DA 50 C 03-25 Landing with Defective Brakes Emergency operation procedure 1 Landing with Defective Brakes In general, a landing on grass is recommended in order to reduce the landing run due to the greater rolling resistance. WARNING IF SUFFICIENT TIME IS REMAINING, THE RISK OF FIRE IN THE...
  • Page 116 AFM DA 50 C 03-26 Landing Gear Unsafe Warning Emergency operation procedure 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 117 AFM DA 50 C 03-27 Landing with Gear Up Emergency operation procedure 1 Landing with Gear Up NOTE This procedure applies, if the landing gear is completely retracted. Approach................with power at normal approach airspeeds and flap settings Sun visors (if installed)................locked in fully upward position PFD/MFD control unit (keypad) (if installed)..................stowed...
  • Page 118 AFM DA 50 C FAILURES IN THE ELECTRICAL SYSTEM Doc No.: 9.01.01-E Page 03-39 Issue : 011 14-Dec-2022...
  • Page 119 AFM DA 50 C 03-28 Complete Failure of the Electrical System Emergency operation procedure 1 Complete Failure of the Electrical System Circuit breakers..........................all in ESSENTIAL BUS..........................ON Electrical equipment............switch OFF all equipment which is not needed Land on the nearest suitable airfield.
  • Page 120 AFM DA 50 C SMOKE AND FIRE Doc No.: 9.01.01-E Page 03-41 Issue : 011 14-Dec-2022...
  • Page 121 AFM DA 50 C 03-29 Engine Fire on Ground Emergency operation procedure 1 Engine Fire on Ground ENGINE MASTER..........................OFF FUEL valve............................OFF ELECT. MASTER..........................OFF After Standstill Door..............................open Airplane .........................evacuate immediately Doc No.: 9.01.01-E Page 03-42 Issue : 011 14-Dec-2022 DA50-A-15-43-00-00A-141A-D...
  • Page 122 AFM DA 50 C 03-30 Electrical Fire with Smoke on Ground Emergency operation procedure 1 Electrical Fire with Smoke on Ground ELECT. MASTER..........................OFF If the Engine Is Running POWER lever.........................Ground Idle (GI) ENGINE MASTER..........................OFF FUEL valve........................OFF (lift and turn) When the Engine Has Stopped Door..............................open...
  • Page 123 AFM DA 50 C 03-31 If Take-Off Can Be Aborted Emergency operation procedure 1 Smoke and Fire During Take-Off If Take-Off Can Still Be Aborted POWER lever.........................Ground Idle (GI) ECS shut-off............................PULL Brakes....................apply - bring the airplane to a stop ENGINE MASTER..........................OFF FUEL valve........................OFF (lift and turn)
  • Page 124 AFM DA 50 C 03-32 If Take-Off CANNOT Be Aborted Emergency operation procedure 1 Smoke and Fire During Take-Off If Take-Off CANNOT Be Aborted WARNING IF, IN THE EVENT OF AN ENGINE PROBLEM OCCURRING DURING TAKE-OFF, THE TAKE-OFF CAN NO LONGER BE...
  • Page 125 AFM DA 50 C 03-33 Engine Fire in Flight Emergency operation procedure 1 Engine Fire in Flight WARNING IN THE EVENT OF SMOKE OR FIRE, PREPARE TO LAND THE AIRPLANE WITHOUT DELAY WHILE COMPLETING FIRE SUPPRESSION AND/OR SMOKE EVACUATION PROCEDURES. IF...
  • Page 126 AFM DA 50 C 03-34 Electrical Fire with Smoke in Flight Emergency operation procedure 1 Electrical Fire in Flight WARNING IN THE EVENT OF SMOKE OR FIRE, PREPARE TO LAND THE AIRPLANE WITHOUT DELAY WHILE COMPLETING FIRE SUPPRESSION AND/OR SMOKE EVACUATION PROCEDURES. IF...
  • Page 127 AFM DA 50 C OTHER EMERGENCIES Doc No.: 9.01.01-E Page 03-48 Issue : 011 14-Dec-2022...
  • Page 128 AFM DA 50 C 03-35 Unintentional Flight Into Icing Conditions Emergency operation procedure 1 Unintentional Flight Into Icing Conditions Unintentional Flight Into Icing Conditions Leave the icing area (by changing altitude or turning back in order to reach zones with a higher ambient temperature).
  • Page 129 AFM DA 50 C 03-36 Suspicion of Carbon Monoxide Contamination in the Cabin Emergency operation procedure 1 Suspicion of Carbon Monoxide Contamination in the Cabin Carbon monoxide (CO) is a gas which is developed during the combustion process. It is poisonous and without smell.
  • Page 130 AFM DA 50 C 03-37 Recovery from Spin Emergency operation procedure 1 Recovery from Spin CAUTION STEPS A TO D MUST BE CARRIED OUT IMMEDIATELY AND SIMULTANEOUSLY. POWER lever........................Flight Idle (FI) Ailerons............................neutral Rudder..................full deflection against direction of spin Elevator (control stick)........................forward When rotation has stopped: Rudder............................neutral...
  • Page 131 AFM DA 50 C 03-38 Gliding Emergency operation procedure 1 Gliding NOTE The glide ratio is 10; i.e., for every 1000 ft (~300 m) of altitude loss the maximum horizontal distance traveled in still air is 1.6 NM (~ 3.0 km). During this the propeller will continue to windmill.
  • Page 132 AFM DA 50 C 03-39 Emergency Descent Emergency operation procedure 1 Emergency Descent FLAPS..............................UP WARNING MAX. LANDING GEAR EXTENDED SPEED V = 162 KIAS. Airspeed........................not above 162 KIAS Gear...............................DOWN POWER lever........................Flight Idle (FI) Doc No.: 9.01.01-E Page 03-53 Issue : 011...
  • Page 133 AFM DA 50 C 03-40 Emergency Exit Emergency operation procedure 1 Emergency Exit In case of a roll over of the airplane on ground, the emergency exit is at the RH side of the PAX row. The red release belt is located at the upper rear corner of the emergency exit window. For activation follow instructions as placarded.
  • Page 134 AFM DA 50 C 03-41 Emergency Landing with Engine Off Emergency operation procedure 1 Emergency Landing with Engine Off POWER lever........................Flight Idle (FI) ENGINE MASTER..........................OFF PFD/MFD control unit (keypad) (if installed)..................stowed FUEL valve............................OFF Airspeed, Landing Gear, Flaps....................as required Before touchdown Belts and Harnesses........................fasten...
  • Page 135 AFM DA 50 C 03-42 Autopilot or Electric Trim Malfunction / Failure Emergency operation procedure 1 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 136 AFM DA 50 C ABNORMAL OPERATING PROCEDURES Doc No.: 9.01.01-E Page 03A-1 Issue : 011 14-Dec-2022...
  • Page 137 AFM DA 50 C AIRPLANE RELATED CAS CAUTIONS Doc No.: 9.01.01-E Page 03A-2 Issue : 011 14-Dec-2022...
  • Page 138 AFM DA 50 C 03A-01 Airplane related G1000 Caution Messages Emergency operation procedure 1 Crew Alert System (CAS) Caution Messages CAS Message Cause Corrective Action Engine alternator 1 has failed. 03A-02 - ALTN 1 FAIL - Spe- ALTN 1 FAIL cial operation.
  • Page 139 AFM DA 50 C CAS Message Cause Corrective Action Stall warning heat has failed. 03A-10 - STALL HT FAIL / STALL HT FAIL STALL HT OFF - Special opera- tion. Stall warning heat is off. 03A-10 - STALL HT FAIL /...
  • Page 140 AFM DA 50 C 03A-02 ALTN 1 FAIL Special operation 1 Alternator 1 Failure ALTN 1 FAIL Engine alternator 1 has failed. Circuit breakers....................check if all OK (pressed in) Alternator 1 switch..........................OFF NOTE By switching the essential bus ON, alternator 2 supplies electrical power to the main and essential bus and charges the main battery.
  • Page 141 AFM DA 50 C 03A-03 ALTN 2 FAIL Special operation 1 Alternator 2 Failure ALTN 2 FAIL Engine alternator 2 has failed. Circuit breakers....................check if all OK (pressed in) Alternator 2 switch..........................OFF Bus voltage...........................monitor NVFR or IFR operation............terminate, land on the next suitable airfield Doc No.: 9.01.01-E...
  • Page 142 AFM DA 50 C 03A-04 CHECK GEAR Special operation 1 CHECK GEAR CHECK GEAR Landing gear retracted. NOTE The CHECK GEAR caution message is displayed when either the flaps are in LDG position or the POWER lever is set to less than approx. 20% and the landing gear is not down and locked.
  • Page 143 AFM DA 50 C 03A-05 COOLANT LVL Special operation 1 COOLANT LVL COOLANT LVL Coolant level is low. A low coolant caution alert may indicate a loss of coolant. This will subsequently lead to decreased engine cooling capability / loss of engine power due to engine failure.
  • Page 144 AFM DA 50 C 03A-06 ECU A FAIL Special operation 1 ECU A FAIL ECU A FAIL Engine ECU A has detected a failure. On Ground Terminate flight preparation. In Flight ALTERNATE AIR..........................OPEN EMERGENCY FUEL PUMP switch.....................ON Circuit breakers....................check / reset if necessary...
  • Page 145 AFM DA 50 C 03A-07 ECU B FAIL Special operation 1 ECU B FAIL ECU B FAIL Engine ECU B has detected a failure. On Ground Terminate flight preparation. In Flight ALTERNATE AIR..........................OPEN EMERGENCY FUEL PUMP switch.....................ON Circuit breakers....................check / reset if necessary FADEC TEST button................press for more than 2 seconds...
  • Page 146 AFM DA 50 C 03A-08 FUEL LOW Special operation 1 FUEL LOW FUEL LOW Main tank fuel quantity is low. WARNING WHEN THE FUEL PUMP TAKES IN AIR (E.G. WHEN THE EMERGENCY FUEL VALVE IS NOT SWITCHED BACK AND THE AUXILIARY TANK IS EMPTY), AN INSPECTION OF THE PUMP IS NECESSARY PRIOR TO NEXT FLIGHT.
  • Page 147 AFM DA 50 C 03A-09 PITOT HEAT FAIL / PITOT HEAT OFF Special operation 1 PITOT FAIL / PITOT HT OFF PITOT FAIL PITOT HT OFF Pitot heat has failed. / Pitot heat is off. PITOT/STALL HEAT....................check ON / as required...
  • Page 148 AFM DA 50 C 03A-10 STALL HT FAIL / STALL HT OFF Special operation 1 STALL HT FAIL / STALL HT OFF STALL HT FAIL STALL HT OFF Stall warning heat has failed. / Stall warning heat is off. PITOT/STALL HEAT....................check ON / as required...
  • Page 149 AFM DA 50 C 03A-11 VOLTS LOW Special operation 1 VOLTS LOW VOLTS LOW Essential bus voltage is below 25 V. Possible reasons are: a fault in the power supply RPM too low. On Ground Circuit breakers..........................check POWER lever........................increase RPM If the caution light does not extinguish Terminate flight preparation.
  • Page 150 AFM DA 50 C 03A-12 STALL WARN FAIL Special operation 1 STALL WARN FAIL STALL WARN FAIL Stall warning system has failed. NOTE The STALL WARN FAIL caution message is displayed when the stall warning computer detects a failure of the stall warning system.
  • Page 151 AFM DA 50 C 03A-13 ENG INTAKE Special operation 1 Engine Air Intake Temperature High ENG INTAKE Engine air intake temperature is high (above 70 °C) for more than 30 seconds. High engine intake temperatures leads to reduces power output.
  • Page 152 AFM DA 50 C ABNORMAL PROCEDURES Doc No.: 9.01.01-E Page 03A-17 Issue : 011 14-Dec-2022...
  • Page 153 AFM DA 50 C 03A-14 Failure in the Electrical Rudder Trim System Special operation Failure in Electrical Rudder Trim Indication or Function Rudder trim movement............check via indication on PFD and actuation In case of indication failure Rudder trim........................adjust as required In case of functional failure Airplane attitude..................maintain/regain airplane control,...
  • Page 154 AFM DA 50 C 03A-15 Failure in Flap Operating System Special operation 1 FAILURE IN FLAP OPERATING SYSTEM Failure in Position Indication or Function FLAPS position........................check visually Airspeed..................keep in white sector (max. 121 KIAS) FLAPS switch......................re-check all positions Modified Approach Procedure Depending on the Available Flap Setting...

  • Page 155: Table Of Contents

    AFM DA 50 C 03A-16 Before Starting Engine with External Power Special operation 1 Before Starting Engine with External Power Pre-flight inspection........................complete Rudder pedals......................adjusted and locked Passengers..........................instructed Safety harnesses........................all fastened Doors...........................closed and locked Door locks......................unlocked, key removed Parking brake............................set Flight controls........................free movement Gear lever...........................check DOWN...
  • Page 156 AFM DA 50 C Press ENT on MFD to acknowledge COOLANT LVL caution......................check OFF Fuel temperature..........................check WARNING NEVER ROTATE THE PROPELLER BY HAND. Doc No.: 9.01.01-E Page 03A-21 Issue : 011 14-Dec-2022 DA50-A-15-50-01-01A-161A-D...
  • Page 157 AFM DA 50 C 03A-17 Starting Engine with External Power Special operation 1 Starting Engine with External Power WARNING IF THE OIL PRESSURE HAS NOT MOVED FROM THE RED RANGE WITHIN 3 SECONDS AFTER STARTING, SET THE ENGINE MASTER SWITCH TO OFF AND INVESTIGATE PROBLEM.
  • Page 158 AFM DA 50 C Circuit breakers........................check all IN Ground Idle (GI) RPM.....................check, 660 RPM (Ground Idle (GI) RPM might be higher in certain environmental conditions) External power.........................disconnect External power unit..........check disconnected and moved clear of the airplane Warm up..............Ground Idle (GI) for 2 min, then increase Propeller RPM to 1100 until engine temperatures are within green range.
  • Page 159 AFM DA 50 C 03A-18 Lightning Strike Special operation 1 LIGHTNING STRIKE CAUTION DUE TO POSSIBLE DAMAGE TO THE AIRPLANE OBEY THE FOLLOWING INSTRUCTIONS: - AVOID ABRUPT OR FULL CONTROL SURFACE MOVEMENTS. - AVOID HIGH G-LOADS ON THE AIRFRAME. - AVOID HIGH YAW ANGLES.
  • Page 160 AFM DA 50 C 03A-19 Defective Fuel Transfer System Emergency operation procedure 1 Defective Fuel Transfer System When switching on the fuel transfer pump, and the fuel transfer status light is not illuminated, monitor the fuel quantities. The transfer rate is 1 US gal per minute. If the fuel amount of the main tank is less than 17 US gal the fuel transfer can be activated.
  • Page 161 AFM DA 50 C AUTOPILOT FAILURES Doc No.: 9.01.01-E Page 03A-26 Issue : 011 14-Dec-2022...
  • Page 162 AFM DA 50 C 03A-20 Autopilot Diconnect Emergency operation procedure 1 AUTOPILOT DISCONNECT (yellow AP flashing on PFD) AP DISC switch......................depress and release (to cancel disconnect tone) Pitch trim......................retrim if necessary, using the trim wheel NOTE The autopilot disconnect may be accompanied by a red boxed PTCH (pitch) or ROL on the PFD, indicating the axis which has failed.
  • Page 163 AFM DA 50 C 03A-21 Autopilot Overspeed Recovery Emergency operation procedure 1 AUTOPILOT OVERSPEED RECOVERY (yellow MAXSPD on PFD) POWER lever........................reduce power When overspeed condition is corrected: Autopilot...................reselect vertical mode (if necessary) NOTE Overspeed recovery mode provides a pitch up command to decelerate the airplane at or below the maximum autopilot operating speed (185 KIAS).
  • Page 164 AFM DA 50 C 03A-22 Loss of Navigation Information Emergency operation procedure 1 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 165 AFM DA 50 C 03A-23 Autopilot Out Of Trim Emergency operation procedure 1 AUTOPILOT OUT OF TRIM (Yellow ←AIL, AIL→, ↑ELE, ↓ELE, ←RUD or RUD→ on PFD) For ↑ELE, or ↓ELE Indication: If the annunciation remains: WARNING DO NOT ATTEMPT TO OVERPOWER THE AUTOPILOT IN THE EVENT OF A PITCH MISTRIM.
  • Page 166 AFM DA 50 C For ←AIL, AIL→ or ←RUD, RUD→ Indication: Rudder trim..................verify slip / skid indicator is centered, trim is necessary NOTE Observe the maximum fuel imbalance limitation. If the annunciation remains: Control stick....................grasp firmly with both hands CAUTION BE PREPARED FOR SUSTAINED CONTROL FORCES IN THE DIRECTION OF THE ANNUNCIATION ARROW.
  • Page 167 AFM DA 50 C 03A-24 Flashing Yellow Mode Annunciation Emergency operation procedure 1 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.
  • Page 168 AFM DA 50 C 03A-25 Effects Of G1000 NXi Losses Upon Autopilot Operation Description EFFECTS OF G1000 NXi LOSSES UPON AUTOPILOT OPERATION G1000 NXi System Loss Effect upon Autopilot Operation AHRS The autopilot disconnects and autopilot, yaw damper and flight director are inoperative. Manual electric trim is available.
  • Page 169 AFM DA 50 C NORMAL OPERATING PROCEDURES Doc No.: 9.01.01-E Page 04-1 Issue : 011 14-Dec-2022...
  • Page 170 AFM DA 50 C NORMAL OPERATING PROCEDURES GENERAL Doc No.: 9.01.01-E Page 04-2 Issue : 011 14-Dec-2022...
  • Page 171 Normal operating procedures for GFC 700 are described in the Garmin G1000 NXi Cockpit Reference Guide, P/N 190-02800-( ) and the Garmin G1000 NXi Pilot’s Guide for the Diamond DA 50 C, P/N 190-02799-( ). Doc No.: 9.01.01-E Page 04-3...
  • Page 172 Description Flight Characteristics The DA 50 C 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 applied, the airplane will easily recover from sideslip if the trim is set to neutral (normal procedure), otherwise it may require corrective action with a moderate amount of rudder input.
  • Page 173 AFM DA 50 C 04-03 Airspeeds for Normal Operation Description Airspeeds for Normal Operating Procedures For all airspeed tables in the following Sections apply linear variations between weights. above 1600 kg up to 1600 kg (3527 lb) above 1800 kg...
  • Page 174 AFM DA 50 C DAILY CHECK Doc No.: 9.01.01-E Page 04-6 Issue : 011 14-Dec-2022...
  • Page 175 AFM DA 50 C 04-04 Daily Checks Pre-operation procedure 1 Daily Check Before the first flight of a day it must be ensured that the following checks are performed: On-condition check of the LH and RH pilot door and the passenger door for cracks and major scratches.
  • Page 176 AFM DA 50 C CHECKLISTS FOR NORMAL OPERATING PROCEDURES Doc No.: 9.01.01-E Page 04-8 Issue : 011 14-Dec-2022...
  • Page 177 AFM DA 50 C 04-05 Pre-Flight Inspection - Cabin Check Pre-operation procedure 1 Pre-Flight Inspection - Cabin Check Preparation Pitot Cover..........................removed Parking brake..........................set ON MET, NAV, mass and balance................flight planning completed Airplane documents....................complete and up to date LH and RH Pilot doors and passenger door..clean, undamaged, check locking mechanism function Baggage........................stowed and secured...
  • Page 178 AFM DA 50 C PFD/MFD control unit (keypad) (if installed)..................stowed Below instrument panel in front of left seat Alternate Static Source......................check closed Emergency gear extension lever..................check pushed in ECS shut-off......................check pushed in / OPEN Below instrument panel in front of right seat Alternate Air.........................check closed...
  • Page 179 AFM DA 50 C CAUTION WHEN SWITCHING ELECT. MASTER ELECTRICALLY DRIVEN HYDRAULIC GEAR PUMP 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 PREPARATION. THERE IS A MALFUNCTION IN THE LANDING GEAR SYSTEM.
  • Page 180 AFM DA 50 C check aileron centering and elevator pull spring (stick should move to aileron neutral, elevator at back stop position) Elevator trim..................check free and correct movement up to full deflection Doc No.: 9.01.01-E Page 04-12 Issue : 011...
  • Page 181 AFM DA 50 C 04-06 Pre-Flight Inspection - Walk Around Check Pre-operation procedure 1 Pre-Flight Inspection - Walk Around Check, Visual Inspection CAUTION A VISUAL INSPECTION MEANS: EXAMINATION FOR DAMAGE, CRACKS, DELAMINATION, EXCESSIVE PLAY, LOAD TRANSMISSION, CORRECT ATTACHMENT AND GENERAL CONDITION.
  • Page 182 AFM DA 50 C Down and uplock switches....................Visual inspection Wear, tread depth of tire....................Visual inspection Tire, wheel, brake......................Visual inspection Check discs for cracks and scoring Check brake pad condition Check callipers for free movement Brake line connection......................Check for leaks Slip marks........................Check alignment Landing gear door......................Visual inspection...
  • Page 183 AFM DA 50 C Passenger door and window..................Visual inspection Fuselage skin.........................Visual inspection Antennas........................Visual inspection Fuselage................Check for contamination (hydraulic fluid, fuel) Drain holes fuselage.................Check for liquids (water, TKS) Trim weight container....................Visual inspection Trim weight container attachment screws..............Visual inspection Empennage Stabilizers and control surfaces, elevator tips...............Visual inspection Hinges..........................Visual inspection...
  • Page 184 AFM DA 50 C Wear, tread depth of tire....................Visual inspection Tire, wheel, brake......................Visual inspection Check discs for cracks and scoring Check brake pad condition Check callipers for free movement Brake line connection......................Check for leaks Slip marks........................Check alignment Landing gear door......................Visual inspection Right Wing Step......................Visual inspection of attachment...
  • Page 185 AFM DA 50 C RH pilot door........................Visual inspection EPU connector..........................Check Cowling..........................Visual inspection Compart. ventilation small NACA air intake...........Clear (LH/RH rear cowling) Exhaust..........................Visual inspection COWL FLAP and linkages.....................Visual inspection Nose landing gear strut and lock............Visual inspection, sufficient height (at least 5 cm (2.0 in)) Down and uplock switches....................Visual inspection...

  • Page 186: Passengers

    AFM DA 50 C 04-07 Before Starting Engine Pre-operation procedure 1 Before Starting the Engine Pre-flight inspection........................complete Passengers..........................instructed Ensure all the passengers have been fully briefed on the location, operation and use of the seat belts, doors and backrest folding mechanism,...
  • Page 187 AFM DA 50 C CAUTION IF THE PROVISIONS FOR TABLET MOUNTS ARE INSTALLED ON THE LH AND RH A-COLUMN (OÄM-50-020 IS INSTALLED) AND A TABLET COMPUTER IS USED, THE PILOT MUST ENSURE THAT THE MOUNT IS ADJUSTED NOT TO INTERFERE WITH THE...
  • Page 188 AFM DA 50 C 04-08 Starting Engine Pre-operation procedure 1 Starting Engine CAUTION STARTER CRANKING ALLOWED FOR MAX. 3 SECONDS CONTINUOUS. WAIT AT LEAST 30 SECONDS BEFORE NEW ATTEMPT. AFTER 6 UNSUCCESSFUL RESTARTS, ALLOW 30 MINUTES FOR STARTER MOTOR COOLING.
  • Page 189 AFM DA 50 C CAUTION DO NOT OVERHEAT THE STARTER MOTOR. DO NOT OPERATE THE STARTER MOTOR FOR MORE THAN 3 SECONDS. AT LOW AMBIENT TEMPERATURES IT IS POSSIBLE THAT THE ENGINE WILL NOT START AT THE FIRST ATTEMPT. IN THIS CASE WAIT 30 SECONDS BETWEEN THE START ATTEMPTS.
  • Page 190 AFM DA 50 C 04-09 Before Taxiing Pre-operation procedure 1 BEFORE TAXIING AVIONIC MASTER..........................ON Warm up....................Ground Idle (GI) for 2 min, then increase Propeller RPM to 1100 until engine temperatures are within green range Electrical equipment......................ON as required Flight instruments and avionics..................set as required Flood light....................ON, test function, as required...
  • Page 191 AFM DA 50 C autopilot....................engage by pressing AP button AP DISC switch..............press. verify that the autopilot disconnects TRIM.......................set to take-off position manually Doc No.: 9.01.01-E Page 04-23 Issue : 011 14-Dec-2022 DA50-A-15-33-00-06A-121A-D...
  • Page 192 AFM DA 50 C 04-10 Taxiing Pre-operation procedure 1 Taxiing CAUTION WHEN TAXIING ON A POOR SURFACE SELECT THE LOWEST POSSIBLE RPM TO AVOID DAMAGE TO THE PROPELLER FROM STONES OR SIMILAR ITEMS. CAUTION AVOID PROLONGED PERMANENT BRAKING WHILE TAXIING.
  • Page 193 AFM DA 50 C 04-11 Before Take-Off Pre-operation procedure 1 Before Take-Off Before Take-Off Check Position airplane into wind if possible. Parking brake............................set CAUTION FOR TAKE-OFF THE ADJUSTABLE BACKRESTS MUST BE FIXED IN THE UPRIGHT POSITION. Adjustable backrests..............verify upright position and proper fixation Safety harnesses....................CHECK on and fastened...

  • Page 194: Fadec

    AFM DA 50 C POWER lever.........................Ground Idle (GI) FLAPS....................check function & indicator / set T/O NOTE For maximum service life minimize heater operation during ground operation. PITOT/STALL HEAT......................ON, if required EMERGENCY FUEL PUMP switch..................check OFF FADEC..........................check AUTO Landing light........................ON, if required Flight controls................unrestricted free movement, correct sense...
  • Page 195 AFM DA 50 C FADEC TEST button.............RELEASE when test sequence completed FADEC............................Force B Engine.....................check running without a change CAUTION RUNNING THE ENGINE WITH THE FADEC ON FORCE B, OTHER THAN FOR THIS TEST OR IN AN EMERGENCY, IS PROHIBITED. THE ENGINE CONTROL SYSTEM REDUNDANCY IS ONLY GIVEN WITH THE FADEC SET ON AUTO.

  • Page 196: Emergency Fuel Pump Switch

    AFM DA 50 C Altitude -35°C -20°C -10°C 0°C 10°C 20°C 30°C 40°C 50°C [ft] -31°F -4°F 14°F 32°F 50°F 68°F 86°F 104°F 122°F 10000 Table 1 Load Indication POWER lever.........................Ground Idle (GI) NOTE With the POWER lever in Ground Idle (GI) the oil pressure may be in the low yellow range.
  • Page 197 AFM DA 50 C 04-12 Take-Off Normal operation procedure 1 Take-Off POWER lever............MAX (take-off power apply smoothly, for max. 5 min.) RPM...................check 2340 RPM reached during take-off roll Elevator............................neutral 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.
  • Page 198 AFM DA 50 C FLAPS..............................UP LOAD..................latest after 5 min reduce to 90% (MCP) COWL FLAP...........................as required ALTERNATE AIR.................OPEN in rain, snow or visible moisture Doc No.: 9.01.01-E Page 04-30 Issue : 011 14-Dec-2022 DA50-A-15-34-00-01A-131A-D...
  • Page 199 AFM DA 50 C 04-13 Climb Normal operation procedure 1 Climb CAUTION IF THE OIL TEMPERATURE AND/OR COOLANT TEMPERATURE REACHES THE YELLOW RANGE DURING CLIMB, FLIGHT SHOULD BE CONTINUED WITH AN AIRSPEED INCREASED BY 5 KT AND POWER REDUCED BY 10% (REDUCED CLIMB RATE) FOR BETTER ENGINE COOLING.
  • Page 200 AFM DA 50 C 04-14 Climb Autopilot Normal operation procedure 1 Autopilot Operation During Climb NOTE The NOSE UP and NOSE DN buttons on the mode controller on the MFD are referenced to airplane movement. The NOSE UP button will increase the reference pitch attitude, increase the reference vertical speed and decrease the reference airspeed.
  • Page 201 AFM DA 50 C White ALT (altitude preselect armed)...................note on PFD Green ALT.....................verify upon altitude capture 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 202 AFM DA 50 C NOTE If the Course Deviation Indicator (CDI) is greater than one dot from center, the autopilot will arm the NAV mode and indicate VOR or GPS in white on the PFD. The pilot must ensure that the current heading will result in a capture of the selected course.
  • Page 203 AFM DA 50 C 04-15 Cruise Normal operation procedure 1 Cruise CAUTION WHEN OPERATING THE FUEL TRANSFER PUMP, MAKE SURE NOT TO EXCEED THE FUEL IMBALANCE LIMITATIONS GIVEN 02-14 - FUEL - DESCRIPTION. NOTE The recommended cruise power setting is 75%.
  • Page 204 AFM DA 50 C 04-16 Cruise Autopilot Normal operation procedure 1 Autopilot Operation During Cruise NOTE The NOSE UP and NOSE DN buttons on the mode controller on the MFD are referenced to airplane movement. The NOSE UP button will increase the reference pitch attitude, increase the reference vertical speed and decrease the reference airspeed.
  • Page 205 AFM DA 50 C 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 206 AFM DA 50 C Course bearing pointer (CRS)................set using course knob Intercept heading..................establish in HDG or ROL mode (if required) Mode controller..................select NAV on mode controller Green or white VOR or GPS annunciation................note on PFD Vertical mode and reference................select on mode controller...
  • Page 207 AFM DA 50 C 04-17 Fuel Transfer Normal operation procedure 1 Fuel Transfer CAUTION DURING NORMAL OPERATION FUEL IS TAKEN FROM THE MAIN TANK ONLY. THEREFORE FUEL MUST BE TRANSFERRED FROM THE AUXILIARY TANK TO THE MAIN TANK BY ACTIVATING THE...
  • Page 208 AFM DA 50 C 04-18 Descent Normal operation procedure 1 Descent POWER lever................as required (at or above flight idle, FI) Airspeed..........................as required Trim............................as required PEDs......................OFF, for low visibilty approach NOTE Definition of the switched-off status for PEDs: Many PEDs are not completely disconnected from the internal power source when switched off.
  • Page 209 AFM DA 50 C 04-19 Descent Autopilot Normal operation procedure 1 Autopilot Operation During Descent NOTE The NOSE UP and NOSE DN buttons on the mode controller on the MFD are referenced to airplane movement. The NOSE UP button will increase the reference pitch attitude, increase the reference vertical speed and decrease the reference airspeed.
  • Page 210 AFM DA 50 C 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 211 AFM DA 50 C NOTE If the Course Deviation Indicator (CDI) offset is greater than one dot from center, the autopilot will arm the NAV mode and indicate VOR or GPS in white on the PFD. The pilot must ensure that the current heading will result in a capture of the selected course.
  • Page 212 AFM DA 50 C 04-20 Approach and Landing Normal operation procedure 1 Approach and Landing CAUTION FOR LANDING THE ADJUSTABLE BACKRESTS MUST BE FIXED IN THE UPRIGHT POSITION. NOTE If LOI annunciation is displayed and GPS based navigation is aborted while on the final approach segment, the missed approach procedure must be executed.
  • Page 213 AFM DA 50 C above 1600 kg up to 1600 kg (3527 lb) above 1800 kg Flight Mass (3527 lb) up to 1800 kg (3968 lb) (3968 lb) - Flaps UP 84 KIAS 90 KIAS 94 KIAS - Flaps T/O...
  • Page 214 AFM DA 50 C 04-21 Approach and Landing Autopilot Normal operation procedure 1 Autopilot Operation During Approach and Landing Navigation source....................select VOR using CDI button on PFD Course bearing pointer (CRS)................set using course knob Intercept heading..................establish in HDG or ROL mode (if required) Mode controller..................select APR on mode controller...
  • Page 215 AFM DA 50 C NOTE When the selected navigation source is a valid ILS, glideslope coupling is automatically armed when tracking the localizer. The glideslope cannot be captured until the localizer is captured. The autopilot can capture the glideslope from above or below the glideslope.
  • Page 216 AFM DA 50 C 04-22 Go Around Normal operation procedure 1 Go-Around POWER lever......................MAX (max. 5 min) FLAPS..............................T/O Airspeed....................77 KIAS up to 1600 kg (3527 lb) 79 KIAS above 1600 kg (3527 lb) up to 1800 kg (3968 lb) 85 KIAS above 1800 kg (3968 lb) COWL FLAP.......................OPEN, as required...
  • Page 217 AFM DA 50 C 04-23 Go Around Autopilot Normal operation procedure 1 Autopilot Operation During Go Around Control Stick...........................grasp firmly GA button.....................push - verify GA/GA on PFD in lateral and vertical mode fields NOTE After the GA button is pressed, the autopilot disconnects and the flight director indicates a 6°...
  • Page 218 AFM DA 50 C 04-24 After Landing Post-operation procedure 1 After Landing POWER lever.........................Ground Idle (GI) Brakes.............................as required ALTERNATE AIR........................CLOSED Lights............................as required Avionics..........................as required EMERGENCY FUEL PUMP switch....................OFF PITOT/STALL HEAT..........................OFF FLAPS..............................UP Doc No.: 9.01.01-E Page 04-50 Issue : 011 14-Dec-2022...
  • Page 219 AFM DA 50 C 04-25 Engine Shut Down Post-operation procedure 1 Engine Shut-Down CAUTION DO NOT SHUT DOWN AN ENGINE WITH THE FUEL VALVE. THE HIGH PRESSURE FUEL PUMP CAN BE DAMAGED OTHERWISE. Parking brake............................set POWER lever..................Ground Idle (GI) at least 2 minutes FLAPS............................check UP...
  • Page 220 AFM DA 50 C 04-26 Exit Airplane Post-operation procedure 1 Exit Airplane Exit the airplane to the aft on designated areas on the wing LH or RH. Doc No.: 9.01.01-E Page 04-52 Issue : 011 14-Dec-2022 DA50-A-15-35-00-03A-151A-D...
  • Page 221 AFM DA 50 C 04-27 Post Flight Inspection Post-operation procedure 1 Post Flight Inspection Record any problem found in flight and during the post-flight check in the log book. Park the airplane. If necessary, moor the airplane. Doc No.: 9.01.01-E...
  • Page 222 AFM DA 50 C 04-28 Parking Post-operation procedure 1 Parking Parking brake......................release, use chocks Map light..........................check OFF Airplane...................moor, if unsupervised for extended period WARNING THE PITOT PROBE BECOMES VERY HOT DURING OPERATION. BE CAREFULL TO AVOID BURNS. THIS CAN CAUSE INJURIES TO PERSONS.
  • Page 223 AFM DA 50 C 04-29 Flight in Rain Normal operation procedure 1 Flight in Rain, Snow or Visible Moisture CAUTION DURING OPERATION ON GROUND ALTERNATE AIR MUST BE CLOSED. NOTE Performance deteriorates in rain; this applies particularly to the take-off distance and to the maximum horizontal speed.
  • Page 224 AFM DA 50 C 04-30 Refueling Description Refueling CAUTION BEFORE REFUELING, THE AIRPLANE MUST BE CONNECTED ELECTRICAL GROUND. GROUNDING POINTS: UNPAINTED AREAS ON STEPS, LEFT AND RIGHT. ONLY APPROVED FUEL ADDITIVES NOT EXCEEDING THE APPROVED CONCENTRATIONS MAY BE USED; REFER TO 02-14 - FUEL - DESCRIPTION.
  • Page 225 AFM DA 50 C PRIST Hi-Flash Fuel Quantity Fuel Additive *, ** PRIST Hi-Flash (1500 ppm) Liter US gal 13.2 40.2 88.68 58.9 1.99 26.4 80.4 177.37 117.9 3.99 39.6 120.6 266.05 176.8 5.98 * Densities used for calculation: Fuel: 0.804 kg/l, PRIST Hi-Flash: 1.05 kg/l...
  • Page 226 AFM DA 50 C 04-31 Flight at High Altitude Description 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. Doc No.: 9.01.01-E...
  • Page 227 AFM DA 50 C PERFORMANCE Doc No.: 9.01.01-E Page 05-1 Issue : 011 14-Dec-2022...
  • Page 228 AFM DA 50 C PERFORMANCE GENERAL Doc No.: 9.01.01-E Page 05-2 Issue : 011 14-Dec-2022...
  • Page 229 AFM DA 50 C 05-01 Performance data Description 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.
  • Page 230 AFM DA 50 C 05-02 Use Of Performance Tables and Diagrams Description Use of the Performance Tables and Diagrams In order to illustrate the influence of a number of different variables, the performance data is reproduced in the form of tables or diagrams. These contain sufficiently detailed information so that conservative values can be selected and used for the determination of adequate performance data for the planned flight.
  • Page 231 AFM DA 50 C 05-03 Airspeed Calibration Description Airspeed Calibration Airspeed Calibration - Flaps TO / LDG Indicated Airspeed [KIAS] Calibrated Airspeed [KCAS] Table 1 Airspeed Calibration - Flaps TO / LDG Doc No.: 9.01.01-E Page 05-5 Issue : 011...
  • Page 232 AFM DA 50 C Airspeed Calibration - Flaps UP Indicated Airspeed [KIAS] Calibrated Airspeed [KCAS] Table 2 Airspeed Calibration - Flaps UP Doc No.: 9.01.01-E Page 05-6 Issue : 011 14-Dec-2022 DA50-A-15-61-00-00A-040A-D...
  • Page 233 AFM DA 50 C 05-04 International Standard Atmosphere Description International Standard Atmosphere Figure 1 - International Standard Atmosphere Doc No.: 9.01.01-E Page 05-7 Issue : 011 14-Dec-2022 DA50-A-15-61-02-00A-040A-D...
  • Page 234 AFM DA 50 C 05-05 Stalling Speeds Description Stalling Speeds Stalling Speed at Various Flight Masses. Airspeeds, most forward CG, Flight Idle (FI): Bank Angle 1600 kg (3527 lb) 0° 30° 45° 60° Gear Flaps KIAS KCAS KIAS KCAS KIAS...
  • Page 235 AFM DA 50 C 05-06 Wind Components Description Wind Components Flight Direction 0° 10° 20° 30° 40° 50° 60° 70° 80° 90° 100° 110° 180° 160° 140° 130° 120° Crosswind Component [kts] Figure 2 - Wind Components Max. demonstrated crosswind component: 15 kts Example: Flight direction: 360°...
  • Page 236 AFM DA 50 C TAKE OFF DISTANCE Doc No.: 9.01.01-E Page 05-10 Issue : 011 14-Dec-2022...
  • Page 237 AFM DA 50 C 05-07 Take-Off Distance Description Take-Off Distance Conditions Power lever Flaps Runway dry, paved, level Nose wheel lift-off Airspeed for initial climb 50ft The following factors are to be applied to the computed take-off distance for the noted condition: Headwind Decrease by 4% for each 5 kt (2.6 m/s) headwind.
  • Page 238 AFM DA 50 C CAUTION THE FACTORS IN THE ABOVE CORRECTIONS ARE TYPICAL VALUES. ON WET GROUND OR WET SOFT GRASS COVERED RUNWAYS THE TAKE-OFF ROLL MAY BECOME SIGNIFICANTLY LONGER THAN STATED ABOVE. IN ANY CASE THE PILOT MUST ALLOW FOR THE CONDITION OF THE RUNWAY TO ENSURE A SAFE TAKE-OFF.
  • Page 239 AFM DA 50 C 05-08 Take-Off Distance 1999 kg Description Doc No.: 9.01.01-E Page 05-13 Issue : 011 14-Dec-2022 DA50-A-15-62-00-01A-040A-D...
  • Page 240 AFM DA 50 C Take-Off Distance - Normal Procedure - 1999 kg / 4407 lb - [SI-units] Weight: 1999 kg / 4407 lb Flaps: 68 KIAS Power: 79 KIAS Runway: dry, paved, level 50ft Distances are given in meter [m] Press.
  • Page 241 AFM DA 50 C Take-Off Distance - Normal Procedure - 1999 kg / 4407 lb - [imperial units] Weight: 1999 kg / 4407 lb Flaps: 68 KIAS Power: 79 KIAS Runway: dry, paved, level 50ft Distances are given in feet [ft] Press.
  • Page 242 AFM DA 50 C 05-09 Take-Off Distance 1800 kg Description Doc No.: 9.01.01-E Page 05-16 Issue : 011 14-Dec-2022 DA50-A-15-62-00-02A-040A-D...
  • Page 243 AFM DA 50 C Take-Off Distance - Normal Procedure - 1800 kg / 3968 lb - [SI-units] Weight: 1800 kg / 3968 lb Flaps: 64 KIAS Power: 73 KIAS Runway: dry, paved, level 50ft Distances are given in meter [m] Press.
  • Page 244 AFM DA 50 C Take-Off Distance - Normal Procedure - 1800 kg / 3968 lb - [imperial units] Weight: 1800 kg / 3968 lb Flaps: 64 KIAS Power: 73 KIAS Runway: dry, paved, level 50ft Distances are given in feet [ft] Press.
  • Page 245 AFM DA 50 C 05-10 Take-Off Distance 1600 kg Description Doc No.: 9.01.01-E Page 05-19 Issue : 011 14-Dec-2022 DA50-A-15-62-00-03A-040A-D...
  • Page 246 AFM DA 50 C Take-Off Distance - Normal Procedure - 1600 kg / 3527 lb - [SI-units] Weight: 1600 kg / 3527 lb Flaps: 59 KIAS Power: 69 KIAS Runway: dry, paved, level 50ft Distances are given in meter [m] Press.
  • Page 247 AFM DA 50 C Take-Off Distance - Normal Procedure - 1600 kg / 3527 lb - [imperial units] Weight: 1600 kg / 3527 lb Flaps: 59 KIAS Power: 69 KIAS Runway: dry, paved, level 50ft Distances are given in feet [ft] Press.
  • Page 248 AFM DA 50 C CLIMB PERFORMANCE TAKE OFF CLIMB Doc No.: 9.01.01-E Page 05-22 Issue : 011 14-Dec-2022...
  • Page 249 AFM DA 50 C 05-11 Climb Performance - Take-Off Climb Description Climb Performance - Take-Off Climb Conditions: Power lever 90% or maximum 2300 RPM Flaps Landing gear retracted Airspeed The climb performance tables show the rate of climb. The gradient of climb can be calculated using the...
  • Page 250 AFM DA 50 C 05-12 Climb Performance - Take-Off Climb 1999 kg Description Take-Off Climb - Flaps T/O - 1999 kg / 4407 lb Flaps: Power: 90%, max. 2300 RPM Airspeed: 79 KIAS Gear: retracted Rate of Climb [ft/min] Press.
  • Page 251 AFM DA 50 C 05-13 Climb Performance - Take-Off Climb 1800 kg Description Take-Off Climb - Flaps T/O - 1800 kg / 3968 lb Flaps: Power: 90%, max. 2300 RPM Airspeed: 79 KIAS Gear: retracted Rate of Climb [ft/min] Press.
  • Page 252 AFM DA 50 C 05-14 Climb Performance - Take-Off Climb 1600 kg Description Take-Off Climb - Flaps T/O - 1600 kg / 3527 lb Flaps: Power: 90%, max. 2300 RPM Airspeed: 79 KIAS Gear: retracted Rate of Climb [ft/min] Press.
  • Page 253 AFM DA 50 C CLIMB PERFORMANCE CRUISE CLIMB Doc No.: 9.01.01-E Page 05-27 Issue : 011 14-Dec-2022...
  • Page 254 AFM DA 50 C 05-15 Climb Performance - Cruise Climb Description Climb Performance - Cruise Climb Conditions: Power lever 90% or maximum 2300 RPM Flaps Landing gear retracted Airspeed 94 KIAS The climb performance tables show the rate of climb. The gradient of climb can be calculated using the...
  • Page 255 AFM DA 50 C 05-16 Climb Performance - Cruise Climb 1999 kg Description Cruise Climb - 1999 kg / 4407 lb Flaps: Power: 90%, max. 2300 RPM Airspeed: 94 KIAS Gear: retracted Rate of Climb [ft/min] Press. Alt. Outside Air Temperature - [°C] / [°F]...
  • Page 256 AFM DA 50 C 05-17 Climb Performance - Cruise Climb 1800 kg Description Cruise Climb - 1800 kg / 3968 lb Flaps: Power: 90%, max. 2300 RPM Airspeed: 94 KIAS Gear: retracted Rate of Climb [ft/min] Press. Alt. Outside Air Temperature - [°C] / [°F]...
  • Page 257 AFM DA 50 C 05-18 Climb Performance - Cruise Climb 1600 kg Description Cruise Climb - 1600 kg / 3527 lb Flaps: Power: 90%, max. 2300 RPM Airspeed: 94 KIAS Gear: retracted Rate of Climb [ft/min] Press. Alt. Outside Air Temperature - [°C] / [°F]...
  • Page 258 AFM DA 50 C TIME, FUEL DISTANCE TO CLIMB Doc No.: 9.01.01-E Page 05-32 Issue : 011 14-Dec-2022...
  • Page 259 AFM DA 50 C 05-19 Time, Fuel and Distance to Climb 1999 kg Description Time, Fuel and Distance to Climb - 1999 kg / 4407 lb Flaps: Power: 90%, max. 2300 RPM Airspeed: 94 KIAS Gear: retracted Time Fuel Distance Press.
  • Page 260 AFM DA 50 C 05-20 Time, Fuel and Distance to Climb 1800 kg Description Time, Fuel and Distance to Climb - 1800 kg / 3968 lb Flaps: Power: 90%, max. 2300 RPM Airspeed: 94 KIAS Gear: retracted Time Fuel Distance Press.
  • Page 261 AFM DA 50 C 05-21 Time, Fuel and Distance to Climb 1600 kg Description Time, Fuel and Distance to Climb - 1600 kg / 3527 lb Flaps: Power: 90%, max. 2300 RPM Airspeed: 94 KIAS Gear: retracted Time Fuel Distance Press.
  • Page 262 AFM DA 50 C CRUISE PERFORMANCE Doc No.: 9.01.01-E Page 05-36 Issue : 011 14-Dec-2022...
  • Page 263 AFM DA 50 C 05-22 Cruise Performance Description Cruise Performance Conditions: Flaps Landing gear retracted For conversion of OAT to delta-ISA temperatures refer to Chapter 5 05-04 - International Standard Atmosphere - Description. Doc No.: 9.01.01-E Page 05-37 Issue : 011...
  • Page 264 AFM DA 50 C 05-23 Cruise Performance 1999 kg Description Cruise Performance up to 1999 kg (4407 lb) Press Alt. Pwr [%] FF [gph] KTAS [ft] / [m] ISA-10 ISA+10 ISA+20 ISA+30 15.3 2000 12.4 10.1 15.3 4000 12.4 1219 10.1...
  • Page 265 AFM DA 50 C Cruise Performance up to 1999 kg (4407 lb) Press Alt. Pwr [%] FF [gph] KTAS [ft] / [m] ISA-10 ISA+10 ISA+20 ISA+30 12.9 16000 10.7 4877 12.1 18000 5486 20000 6096 Table 1 Cruise Performance up to 1999 kg (4407 lb) Doc No.: 9.01.01-E...
  • Page 266 AFM DA 50 C LANDING DISTANCES Doc No.: 9.01.01-E Page 05-40 Issue : 011 14-Dec-2022...
  • Page 267 AFM DA 50 C 05-24 Landing Distances Description Landing Distances Conditions Power lever Flight Idle (FI) Flaps LDG, T/O or UP Runway dry, paved, level Approach speed The following factors are to be applied to the computed landing distance for the noted condition: Headwind Decrease by 10% for each 20 kt (10.3 m/s) headwind.
  • Page 268 AFM DA 50 C CAUTION THE FACTORS IN THE ABOVE CORRECTIONS ARE TYPICAL VALUES. ON WET GROUND OR WET SOFT GRASS COVERED RUNWAYS LANDING DISTANCE BECOME SIGNIFICANTLY LONGER THAN STATED ABOVE. IN ANY CASE THE PILOT MUST ALLOW FOR THE CONDITION OF THE RUNWAY TO ENSURE A SAFE LANDING.
  • Page 269 AFM DA 50 C 05-25 Landing Distances 1999 kg Description Landing Distance - Flaps LDG - 1999 kg / 4407 lb - [SI-units] Weight: 1999 kg / 4407 lb Flaps: 77 KIAS Power: Flight Idle (FI) Runway: dry, paved, level Distances are given in meter [m] Press.
  • Page 270 AFM DA 50 C Landing Distance - Flaps LDG - 1999 kg / 4407 lb - [imperial units] Weight: 1999 kg / 4407 lb Flaps: 77 KIAS Power: Flight Idle (FI) Runway: dry, paved, level Distances are given in feet [ft] Press.
  • Page 271 AFM DA 50 C 05-26 Landing Distances 1800 kg Description Landing Distance - Flaps LDG - 1800 kg / 3968 lb - [SI-units] Weight: 1800 kg / 3968 lb Flaps: 75 KIAS Power: Flight Idle (FI) Runway: dry, paved, level Distances are given in meter [m] Press.
  • Page 272 AFM DA 50 C Landing Distance - Flaps LDG - 1800 kg / 3968 lb - [imperial units] Weight: 1800 kg / 3968 lb Flaps: 75 KIAS Power: Flight Idle (FI) Runway: dry, paved, level Distances are given in feet [ft] Press.
  • Page 273 AFM DA 50 C 05-27 Landing Distances 1600 kg Description Landing Distance - Flaps LDG - 1600 kg / 3527 lb - [SI-units] Weight: 1600 kg / 3527 lb Flaps: 73 KIAS Power: Flight Idle (FI) Runway: dry, paved, level Distances are given in meter [m] Press.
  • Page 274 AFM DA 50 C Landing Distance - Flaps LDG - 1600 kg / 3527 lb - [imperial units] Weight: 1600 kg / 3527 lb Flaps: 73 KIAS Power: Flight Idle (FI) Runway: dry, paved, level Distances are given in feet [ft] Press.
  • Page 275 AFM DA 50 C LANDING DISTANCE ABNORMAL FLAP POSITION Doc No.: 9.01.01-E Page 05-49 Issue : 011 14-Dec-2022...
  • Page 276 AFM DA 50 C 05-28 Landing Distances - Abnormal Flap Position 1999 kg Description Landing Distance - Abnormal Flap Position - 1999 kg / 4407 lb - [SI-units] Weight: 1999 kg / 4407 lb Flaps: T/O or UP 85 KIAS (Flaps T/O)
  • Page 277 AFM DA 50 C Landing Distance - Abnormal Flap Position - 1999 kg / 4407 lb - [imperial units] Weight: 1999 kg / 4407 lb Flaps: T/O or UP 85 KIAS (Flaps T/O) Power: Flight Idle (FI) 94 KIAS (Flaps UP)
  • Page 278 AFM DA 50 C 05-29 Landing Distances - Abnormal Flap Position 1800 kg Description Landing Distance - Abnormal Flap Position - 1800 kg / 3968 lb - [SI-units] Weight: 1800 kg / 3968 lb Flaps: T/O or UP 79 KIAS (Flaps T/O)
  • Page 279 AFM DA 50 C Landing Distance - Abnormal Flap Position - 1800 kg / 3968 lb - [imperial units] Weight: 1800 kg / 3968 lb Flaps: T/O or UP 79 KIAS (Flaps T/O) Power: Flight Idle (FI) 90 KIAS (Flaps UP)
  • Page 280 AFM DA 50 C 05-30 Landing Distances - Abnormal Flap Position 1600 kg Description Landing Distance - Abnormal Flap Position - 1600 kg / 3527 lb - [SI-units] Weight: 1600 kg / 3527 lb Flaps: T/O or UP 77 KIAS (Flaps T/O)
  • Page 281 AFM DA 50 C Landing Distance - Abnormal Flap Position - 1600 kg / 3527 lb - [imperial units] Weight: 1600 kg / 3527 lb Flaps: T/O or UP 77 KIAS (Flaps T/O) Power: Flight Idle (FI) 84 KIAS (Flaps UP)
  • Page 282 AFM DA 50 C GO AROUND CLIMB PERFORMANCE Doc No.: 9.01.01-E Page 05-56 Issue : 011 14-Dec-2022...
  • Page 283 AFM DA 50 C 05-31 Go-Around Climb Performance Description Go Around Climb Performance Conditions: Power lever Flaps Landing gear extended Airspeed The climb performance tables show the rate of climb. The gradient an angle of climb can be calculated using the following formula:...
  • Page 284 AFM DA 50 C 05-32 Go-Around Climb Performance 1999 kg Description Go-Around Climb Performance - 1999 kg / 4407 lb Flaps: Power: Airspeed: 77 KIAS Gear: extended Rate of Climb [ft/min] Press. Alt. Outside Air Temperature - [°C] / [°F]...
  • Page 285 AFM DA 50 C 05-33 Go-Around Climb Performance 1800 kg Description Go-Around Climb Performance - 1800 kg / 3968 lb Flaps: Power: Airspeed: 75 KIAS Gear: extended Rate of Climb [ft/min] Press. Alt. Outside Air Temperature - [°C] / [°F]...
  • Page 286 AFM DA 50 C 05-34 Go-Around Climb Performance 1600 kg Description Go-Around Climb Performance - 1600 kg / 3527 lb Flaps: Power: Airspeed: 73 KIAS Gear: extended Rate of Climb [ft/min] Press. Alt. Outside Air Temperature - [°C] / [°F]...
  • Page 287 AFM DA 50 C GLIDE Doc No.: 9.01.01-E Page 05-61 Issue : 011 14-Dec-2022...
  • Page 288 AFM DA 50 C 05-35 Glide Description Glide CAUTION THE PROPELLER WILL KEEP WINDMILLING UNDER ALL EXPECTED CONDITIONS. DO NOT ATTEMPT TO STOP THE PROPELLER INTENTIONALLY. The following table shows the glide ratio and the resulting maximum horizontal distance in nautical miles per 1000 ft (~300 m) of altitude loss in a glide traveled in still air.
  • Page 289 AFM DA 50 C APPROVED NOISE DATA Doc No.: 9.01.01-E Page 05-63 Issue : 011 14-Dec-2022...
  • Page 290 AFM DA 50 C 05-36 Approved Noise Data Description Approved Noise Data Maximum Flight Mass 1999 kg (4407 lb) ICAO Annex 16 Chapter X 85.0 dB(A) CS-36 Subpart C 85.0 dB(A) No determination has been made by the Federal Aviation Administration that the noise levels of this aircraft are or should be acceptable or unacceptable for operation at, into, or out of, any airport.
  • Page 291 AFM DA 50 C MASS AND BALANCE / EQUIPMENT Doc No.: 9.01.01-E Page 06-1 Issue : 011 14-Dec-2022...
  • Page 292 AFM DA 50 C MASS AND BALANCE Doc No.: 9.01.01-E Page 06-2 Issue : 011 14-Dec-2022...
  • Page 293 AFM DA 50 C 06-01 General Description 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 294 AFM DA 50 C 06-02 Datum Plane Description Datum Plane The Datum Plane (DP) is a plane which is normal to the airplane’s longitudinal axis and in front of the nose landing gear as seen from the direction of flight. When the airplane is aligned horizontally by means of the weighing tool, the Datum Plane is vertical.
  • Page 295 AFM DA 50 C 06-03 Mass and Balance Report Description Mass and Balance Report Mass and Balance Report Conditions 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 296 AFM DA 50 C Doc No.: 9.01.01-E Page 06-6 Issue : 011 14-Dec-2022 DA50-A-15-81-00-00A-040A-D...
  • Page 297 Flight Mass and Center of Gravity The following information enables you to operate your DA 50 C within the permissible mass and balance limits. For the calculation of the flight mass and the corresponding CG position the following tables and...
  • Page 298 AFM DA 50 C 06-05 Moment Arms Description Moment Arms Table 1 shows the most important lever arms aft of the Datum Plane: Lever Arm Item [in] Occupants on front seats 2.24 88.2 Occupants on rear seats 3.13 123.2 Fuel 2.63...
  • Page 299 AFM DA 50 C 06-06 Loading Diagram Description Loading Diagram Figure 2 shows the loading diagram. Load Mass [kg] [lb] Front Seats Fuel Quantity [US gal] [liters] Rear Seats Fuel LH (Main Tank) Fuel RH (Aux Tank) [kgm] [in.lb] 10,000 20,000 30,000 40,000 50,000 Load Moment Figure 2 - Loading Diagram Doc No.: 9.01.01-E...
  • Page 300 AFM DA 50 C 06-07 Calculation of Loading Condition Description Calculation of Loading Condition Complete one of the following forms. (Either in metric or imperial dimensions). Divide the total moments from rows 8 and 10 by the related total mass to obtain the CG positions.
  • Page 301 AFM DA 50 C Your DA 50 C CALCULATION OF LOADING CONDITION - Metric Mass Moment [kg] [kgm] Empty mass (from Mass and Balance Report) Front seats Lever arm: 2.24 m Passenger seats Lever arm: 3.13 m Baggage in Area A Lever arm: 3.98 m...
  • Page 302 AFM DA 50 C Your DA 50 C CALCULATION OF LOADING CONDITION - Impe- Mass Moment rial [lb] [in.lb] Empty mass (from Mass and Balance Report) Front seats Lever arm: 88.2 in Passenger seats row Lever arm: 123.2 in Baggage in Area A Lever arm: 156.7 in...
  • Page 303 AFM DA 50 C Example DA 50 C Mass Moment EXAMPLE CALCULATION OF LOADING CONDI- TION - Metric and Imperial [kg] [kgm] [lb] [in.lb] Empty mass (from Mass and Balance Report) 1480 kg 3560.9 kgm 3263 lb 309,073 in.lb Front seats 160 kg 358.4 kgm...
  • Page 304 AFM DA 50 C 06-08 Permissible Center of Gravity Range Description Permissible Center of Gravity Range Figure 3 shows the permissible center of gravity range. The flight CG position must be within the following limits: Most forward flight CG: 2.315 m aft of datum plane at 1480 kg to 1750 kg 2.315 m aft of datum plane at 1750, increasing linearly to (see next row)
  • Page 305 AFM DA 50 C 06-09 Permissible Moment Range Description Permissible Moment Range Figure 4 shows the permissible moment range. Flight Mass Moment [in lb] 2100 4 00 2 50 2000 4 00 1950 4 00 1900 1850 4 00 1800 1750 3800 1 00...
  • Page 306 AFM DA 50 C EQUIPMENT LIST Doc No.: 9.01.01-E Page 06-16 Issue : 011 14-Dec-2022...
  • Page 307 06-10 Equipment Description Equipment List and Equipment Inventory All equipment that is approved for installation in the DA 50 C is shown in the Equipment List below. NOTE The equipment listed below cannot be installed in any arbitrary combination. The airplane manufacturer must be contacted before removing or installing equipment, with the exception of replacing a unit by an identical unit.
  • Page 308 AFM DA 50 C Doc No.: 9.01.01-E Page 06-18 Issue : 011 14-Dec-2022 DA50-A-15-82-00-00A-040A-D...
  • Page 309 AFM DA 50 C Doc No.: 9.01.01-E Page 06-19 Issue : 011 14-Dec-2022 DA50-A-15-82-00-00A-040A-D...
  • Page 310 AFM DA 50 C Doc No.: 9.01.01-E Page 06-20 Issue : 011 14-Dec-2022 DA50-A-15-82-00-00A-040A-D...
  • Page 311 AFM DA 50 C Doc No.: 9.01.01-E Page 06-21 Issue : 011 14-Dec-2022 DA50-A-15-82-00-00A-040A-D...
  • Page 312 AFM DA 50 C Doc No.: 9.01.01-E Page 06-22 Issue : 011 14-Dec-2022 DA50-A-15-82-00-00A-040A-D...
  • Page 313 AFM DA 50 C Doc No.: 9.01.01-E Page 06-23 Issue : 011 14-Dec-2022 DA50-A-15-82-00-00A-040A-D...
  • Page 314 AFM DA 50 C Doc No.: 9.01.01-E Page 06-24 Issue : 011 14-Dec-2022 DA50-A-15-82-00-00A-040A-D...
  • Page 315 AFM DA 50 C Doc No.: 9.01.01-E Page 06-25 Issue : 011 14-Dec-2022 DA50-A-15-82-00-00A-040A-D...
  • Page 316 AFM DA 50 C DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS Doc No.: 9.01.01-E Page 07-1 Issue : 011 14-Dec-2022...
  • Page 317 AFM DA 50 C 07-01 Airframe Description Airframe Fuselage The CFRP fuselage is of semi monocoque molded construction. The center wing is attached to the fuselage with bolts. The two main spars are part of the center wing. The two main spars are CFRP items.
  • Page 318 AFM DA 50 C FLIGHT CONTROLS Doc No.: 9.01.01-E Page 07-3 Issue : 011 14-Dec-2022...
  • Page 319 AFM DA 50 C 07-02 Flight Controls Description Flight Controls The ailerons, elevator and wing flaps are operated through control rods, while the rudder is controlled by cables. The flaps are electrically operated. Elevator forces can be balanced by a trim tab on the elevator, which is operated by a Bowden cable.
  • Page 320 AFM DA 50 C 07-03 Ailerons Description Ailerons Construction: GFRP/CFRP composite sandwich. Hinges: There are 4 hinges, which are hinge pins mounted in an aluminum bracket. They are secured in position by a roll pin. The absence of this roll pin can lead to the loss of the hinge pin and a consequent loss of flight safety.
  • Page 321 AFM DA 50 C 07-04 Flaps 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 322 AFM DA 50 C 07-05 Rudder Description 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.
  • Page 323 AFM DA 50 C 07-06 Elevator Description Elevator Construction: GFRP sandwich. Hinges: 5 hinges. Operation: Steel pushrods; 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 324 AFM DA 50 C 07-07 Elevator Trim 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 325 AFM DA 50 C 07-08 Rudder Trim Description Rudder Trim The rudder trim control are integrated push buttons on the lower side of the power lever. An indication on the G1000 NXi MFD shows the center position, the bold area and the direction of movement.
  • Page 326 AFM DA 50 C 07-09 Rudder Pedal Description 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 327 AFM DA 50 C INSTRUMENT PANEL Doc No.: 9.01.01-E Page 07-12 Issue : 011 14-Dec-2022...
  • Page 328 AFM DA 50 C 07-10 Instrument Panel Description Instrument Panel CAUTION DO NOT INADVERTENTLY OPERATE THE FADEC SWITCH WHEN ADJUSTING INSTRUMENT PANEL VENTILATION NOZZLE. IN CASE OF INADVERTENT SWITCH OPERATION, BRING THE SWITCH BACK TO THE DESIRED POSITION, TYPICALLY AUTO.
  • Page 329 AFM DA 50 C Figure 1 - Instrument Panel Doc No.: 9.01.01-E Page 07-14 Issue : 011 14-Dec-2022 DA50-A-31-10-00-99A-040A-D...
  • Page 330 AFM DA 50 C LANDING GEAR Doc No.: 9.01.01-E Page 07-15 Issue : 011 14-Dec-2022...
  • Page 331 AFM DA 50 C 07-11 Landing Gear Description Landing Gear System Overview The landing gear is a fully retractable, hydraulically operated, tricycle landing gear.The nose wheel is able to caster through an angular range of ±42°. The desgin and sizing of the landing gear and brake system allows a maximum take-off mass (MTOM) of 1999 kg.
  • Page 332 AFM DA 50 C The landing gear is designed to be manually operated in the event of failure. Since the gear is held in the retracted position by hydraulic pressure, gravity will allow the gear to extend if the system fails for any reason.
  • Page 333 07-12 Hydraulic Gear Extension System Schematic Description Hydraulic Gear Extension System Schematic The landing gear of the DA 50 C is extended with three hydraulic cylinders. The following schematic figures show the system conditions for each operating mode. Figure 1 the extension of the landing gear is shown.
  • Page 334 AFM DA 50 C Extending LG Cylinders Zero Current Zero Current Emergency Extension Valve Pressure Switch Pump Tank Figure 1 - Extension of the Landing Gear Doc No.: 9.01.01-E Page 07-19 Issue : 011 14-Dec-2022 DA50-A-32-30-00-99A-040A-D...
  • Page 335 AFM DA 50 C Extended LG Cylinders Zero Current Zero Current Emergency Extension Valve Pressure Switch Pump Tank Figure 2 - Landing Gear Extended Doc No.: 9.01.01-E Page 07-20 Issue : 011 14-Dec-2022 DA50-A-32-30-00-99A-040A-D...
  • Page 336 AFM DA 50 C Retracting LG Cylinders Zero Current Energized Emergency Extension Valve Pressure Switch Pump Tank Figure 3 - Retraction of the Landing Gear Doc No.: 9.01.01-E Page 07-21 Issue : 011 14-Dec-2022 DA50-A-32-30-00-99A-040A-D...
  • Page 337 AFM DA 50 C Retracted LG Cylinders Energized Energized Emergency Extension Valve Pressure Switch Pump Tank Figure 4 - Landing Gear Retracted Doc No.: 9.01.01-E Page 07-22 Issue : 011 14-Dec-2022 DA50-A-32-30-00-99A-040A-D...
  • Page 338 AFM DA 50 C Extending LG Cylinders Emergency Extension Valve Pressure Switch Pump Tank Figure 5 - Emergency Extension of the Landing Gear Doc No.: 9.01.01-E Page 07-23 Issue : 011 14-Dec-2022 DA50-A-32-30-00-99A-040A-D...
  • Page 339 AFM DA 50 C 07-13 Brake System Description Brake System DA50-A-32-40-00-00A-040A-D shows the brake system functional diagram. 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.
  • Page 340 AFM DA 50 C SEATS AND SAFETY HARNESSES Doc No.: 9.01.01-E Page 07-25 Issue : 011 14-Dec-2022...
  • Page 341 AFM DA 50 C 07-14 Crew Seat Description Seats and Safety Harnesses CAUTION BEFORE ADJUSTING THE ANGLE, LEAN AGAINST THE BACKREST COUNTERACT SPRING LOAD; OTHERWISE THE BACKREST MAY SLAP FORWARD. CAUTION DO NOT APPLY A LOAD OF MORE THAN 90 DECANEWTONS (202 POUND FORCE) TO THE TOP OF THE BACKREST.
  • Page 342 AFM DA 50 C Lumbar Support Inboard Hinge Bowden Cable Outboard Hinge Lumbar Support Lever Release Button Figure 1 - Pilots Seat Doc No.: 9.01.01-E Page 07-27 Issue : 011 14-Dec-2022 DA50-A-25-10-00-01A-040A-D...
  • Page 343 AFM DA 50 C DOORS AND INTERIOR Doc No.: 9.01.01-E Page 07-28 Issue : 011 14-Dec-2022...
  • Page 344 AFM DA 50 C 07-15 LH/RH Pilot Door Description LH and RH Pilot Door The LH and 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. On locking, steel bolts lock into mating holes in polyethylene blocks.
  • Page 345 AFM DA 50 C 07-16 Passenger Door Description Passenger Door WARNING DO NOT BLOCK THE DOOR WITH THE LOCKING KEY BEFORE FLIGHT IN ORDER TO ASSURE EMERGENCY ACCESS FROM OUTSIDE. The passenger door is closed in the same way as the pilot doors by pulling down on the handle and locking it with the lever.
  • Page 346 AFM DA 50 C 07-17 Emergency Exit Window Description Emergency Exit Window The emergency exit is integrated in the window structure (composite frame with mechanical system bonded to the window and covered by an interior panel from the inside). The emergency exit window is secured with a pin against unauthorized access from the outside when parked.
  • Page 347 AFM DA 50 C Figure 1 - Emergency Exit Window Doc No.: 9.01.01-E Page 07-32 Issue : 011 14-Dec-2022 DA50-A-56-10-00-99A-040A-D...
  • Page 348 AFM DA 50 C Legend [1, Fig.1] Activation Handle Cover [2, Fig.1] Activation Handle [3, Fig.1] Window Attachments (7x) [4, Fig.1] Activation Rope [5, Fig.1] Activation Handle Doc No.: 9.01.01-E Page 07-33 Issue : 011 14-Dec-2022 DA50-A-56-10-00-99A-040A-D...
  • Page 349 AFM DA 50 C 07-18 Egress Hammer Description Egress Hammer WARNING MAKE SURE NOT TO HARM OTHER PERSONS BY USING THE EGRESS HAMMER. WARNING BEWARE OF SHARP EDGES AND FRAGMENTS OF THE BROKEN WINDOW. An egress hammer is installed on the floor panel behind the co-pilot’s seat.
  • Page 350 AFM DA 50 C 07-19 Heating and Ventilation Description Heating and Ventilation System CAUTION DO NOT INADVERTENTLY OPERATE THE FADEC SWITCH WHEN ADJUSTING INSTRUMENT PANEL VENTILATION NOZZLE. IN CASE OF INADVERTENT SWITCH OPERATION, BRING SWITCH BACK TO THE DESIRED POSITION, TYPICALLY AUTO.
  • Page 351 AFM DA 50 C nozzles allow a change of the jet direction of each cone and the jet intensity can be regulated by rotation of the nozzle. In emergency cases the cabin can be isolated at the main bulkhead by pulling the knob of the ECS shut- off valve.
  • Page 352 AFM DA 50 C POWERPLANT Doc No.: 9.01.01-E Page 07-37 Issue : 011 14-Dec-2022...
  • Page 353 AFM DA 50 C 07-20 Engine, General Description Engine The airplane is powered with a Centurion 3.0 engine. The sales name is Continental CD-300. The CD-300 is a liquid cooled V6-cylinder-four-stroke Diesel engine with double overhead camshafts. The direct fuel-injection engine operates based on the common-rail technology and is turbocharged by two turbochargers.
  • Page 354 Description Propeller The DA 50 C with the CD 300 Diesel engine has a variable pitch three-bladed propeller, type MTV-12-D/ 210-56 from mt-Propeller. The blades are made from wood and are covered with GFRP, with an acryl lacquer painted finish. A stainless-steel sheath protects the outboard leading-edges of the blades from erosion.
  • Page 355 AFM DA 50 C 07-22 Propeller Control Description Propeller Control The propeller pitch control system is part of the Engine. The pitch is set by the FADEC via an electro- mechanical control valve. Depending on the power lever setting, the propeller pitch is adjusted such that the most efficient RPM will be obtained.
  • Page 356 AFM DA 50 C 07-23 Engine Operating Controls Description Engine Operating Controls POWER LEVER WARNING IT IS POSSIBLE THAT THE PROPELLER BLADES REMAIN IN THE POSITION OF FINE PITCH IN CASE OF A MALFUNCTION OF THE ENGINE CONTROL UNIT. IN THIS CASE THE REDUCED ENGINE PERFORMANCE SHOULD BE TAKEN INTO CONSIDERATION.
  • Page 357 AFM DA 50 C A ECU controls manifold pressure, injected fuel quantity and propeller speed according to the desired engine power preselected with the power lever. If the power lever is in a low power position - as for a landing approach - while the landing gear is retracted, an aural warning alerts the pilot to the retracted landing gear.
  • Page 358 AFM DA 50 C 07-24 Engine Instruments Description Engine Instruments The engine instruments are displayed on the Garmin G1000 NXi. See Figure Display when pushing the ENGINE button see Figure Designation Indication Unit Load % Aviailable power Oil Pres Oil pressure...
  • Page 359 AFM DA 50 C Figure 2 - G1000 NXi Engine page Doc No.: 9.01.01-E Page 07-44 Issue : 011 14-Dec-2022 DA50-A-77-00-00-99A-040A-D...
  • Page 360 AFM DA 50 C Figure 3 - G1000 NXi Full Engine Page Doc No.: 9.01.01-E Page 07-45 Issue : 011 14-Dec-2022 DA50-A-77-00-00-99A-040A-D...
  • Page 361 AFM DA 50 C 07-25 Cooling System Description Cooling System The engine is liquid cooled. The liquid cooling system consists of a short, an external and a bybass cooling circuit. The bybass cooling circuit (cabin heat exchanger) is always active. The short cooling circuit is active at low cooling temperatures.
  • Page 362 AFM DA 50 C Figure 4 - Liquid Cooling System Schematic Diagram Doc No.: 9.01.01-E Page 07-47 Issue : 011 14-Dec-2022 DA50-A-75-20-00-99A-040A-D...
  • Page 363 AFM DA 50 C 07-26 Turbo-Charger System Description 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 LH and RH cowlings to the exterior of the airplane.
  • Page 364 AFM DA 50 C Air Filter Box RH Intercooler RH Solenoid Valve RH Air Filter RH Turbine RH RH Cylinders Alternate Air Valve RH Turbo Charger RH Waste Gate RH Exhaust RH Engine Exhaust LH Waste Gate LH Turbo Charger LH Alternate Air Valve LH LH Cylinders Turbine LH Air Filter LH Solenoid Valve LH Intercooler LH Air Filter Box LH Figure 5 - Turbo-Charger System Schematic Doc No.: 9.01.01-E...
  • Page 365 Description FADEC System The 4-stroke Diesel engine installed in the DA 50 C is electronically controlled by a 32-bit microprocessor engine management system (FADEC). As a result, all aspects of engine operation are based on the load level (lever position) selected by the pilot. For redundancy two independent and identical management systems are installed and continuously monitor each other;...
  • Page 366 AFM DA 50 C FUEL SYSTEM Doc No.: 9.01.01-E Page 07-51 Issue : 011 14-Dec-2022...
  • Page 367 AFM DA 50 C 07-28 Fuel System Description Fuel System In normal operation fuel is taken out of the LH wing fuel tank via the fuel trap pickup line. From there it passes through the fuel valve and gascolator to the electrically driven low pressure fuel supply pumps to...
  • Page 368 AFM DA 50 C Engine Low Pressure Pump Fuel Return Line High Pressure Pump Fuel Supply Line Firewall Fuel Fine Filter Check Valve Main Fuel Pumps Fuel Selector Valve Solenoid Valve Fuel Cooler Gascolator Drain Transfer Line Transfer Pump Filter Electrical Middle Section Transfer Pump Low Level Transfer Pump Outboard Outboard High Level Shut Off Switch Chamber Chamber Transfer Pump Fuel Aux Tank Main Tank Shut Off Switch Temperature Fuel Inboard Fuel...
  • Page 369 AFM DA 50 C 07-29 Fuel Pumps Description Fuel Pumps The feeder pumps to the engine are electrically driven fuel pumps with an internal mechanical adjusted pressure regulating valve (adjusted to 7 psi). The minimum pumping capacity of 180 l/h is provided.
  • Page 370 AFM DA 50 C 07-30 Fuel Valve Description Fuel Valve The fuel valve handle is located in the personnel compartment centre console, behind the trim wheel. It is connected with a mechanical linkage to the fuel valve. Each of the three positions is secured, through a distinct lifting of the handle that is required to change the position, to avoid inadvertent operation.
  • Page 371 AFM DA 50 C Figure 2 - Schematic Normal Fuel Supply Doc No.: 9.01.01-E Page 07-56 Issue : 011 14-Dec-2022 DA50-A-28-00-99-02A-040A-D...
  • Page 372 AFM DA 50 C Figure 3 - Schematic Emergency Fuel Supply Doc No.: 9.01.01-E Page 07-57 Issue : 011 14-Dec-2022 DA50-A-28-00-99-02A-040A-D...
  • Page 373 AFM DA 50 C 07-31 Fuel Tanks Description Fuel Tanks Both main (LH) and auxiliary (RH) fuel tanks are made of aluminium. The fuel tanks are located in the left and right wing, between the two main spars, and are supported by the wing ribs. Pads made of non- absorbent material are installed to prevent chafing.
  • Page 374 AFM DA 50 C 07-32 Fuel Level Check Tool Description Alternate Means for Fuel Quantity Indication for the Fuel Tank for Ground Use The alternate means for fuel quantity indication allows the fuel quantity in the tank to be determined on ground.
  • Page 375 AFM DA 50 C Fuel Quantity Indicator: Pitch Angle Reading Usable Fuel Quantity 2° 3° 4° 5° 6° US gal Liter 68.1 71.9 75.7 79.5 83.3 87.1 90.8 Table 1 Main Tank (LH) Fuel Quantity Indicator: Pitch Angle Reading Usable Fuel Quantity 2°...
  • Page 376 AFM DA 50 C Fuel Quantity Indicator: Pitch Angle Reading Usable Fuel Quantity 2° 3° 4° 5° 6° US gal Liter 23.5 89.0 Table 2 Auxiliary Tank (RH) Doc No.: 9.01.01-E Page 07-61 Issue : 011 14-Dec-2022 DA50-A-28-40-00-99A-040A-D...
  • Page 377 AFM DA 50 C Fuel Quantity Indicator Scale D I A 0 -0 7 -9 0 -2 o :  rt  N   F O D   L T   U   N O   A N T I O D I R  ...
  • Page 378 AFM DA 50 C Fuel Quantity Indicator 90mm Center Wing Main Tank Figure 5 - Fuel Level Check Tool on Wing Doc No.: 9.01.01-E Page 07-63 Issue : 011 14-Dec-2022 DA50-A-28-40-00-99A-040A-D...
  • Page 379 AFM DA 50 C ELECTRICAL SYSTEMS Doc No.: 9.01.01-E Page 07-64 Issue : 011 14-Dec-2022...
  • Page 380 AFM DA 50 C 07-33 Electrical System Description Electrical System Refer to Figure 1 for the electrical system schematic. Power Generation Power generation is provided by two 70 Ampère alternators which are mounted aft of the engine. The alternators are driven by a flat belt.
  • Page 381 AFM DA 50 C 3.1 HOT BUS: The HOT BUS is connected to the main battery and cannot be disconnected from the main battery. The HOT BUS provides power to the pilot map/reading light which is protected by its own fuse.
  • Page 382 AFM DA 50 C Figure 1 - Electrical System Doc No.: 9.01.01-E Page 07-67 Issue : 011 14-Dec-2022 DA50-A-24-00-99-00A-040A-D...
  • Page 383 The MD302 Standby Attitude Module is not connected to an external ARINC 429 source (Garmin G1000 NXi), thus heading information and automatic BARO synchronization is not available in the DA 50 C. Doc No.: 9.01.01-E...
  • Page 384 AFM DA 50 C 07-35 Crew Alerting System (CAS) Description Crew Alerting System (CAS) The G1000 NXi 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 385 AFM DA 50 C Warning Alerts on the G1000 NXi Refer to 03-04 - Airplane related G1000 Warning Messages - Emergency operation procedure warning alerts on the G1000 NXi. Caution Alerts on the G1000 NXi Refer to 03A-01 - Airplane related G1000 Caution Messages - Emergency operation procedure warning alerts on the G1000 NXi.
  • Page 386 AFM DA 50 C GARMIN G1000 NXI Doc No.: 9.01.01-E Page 07-71 Issue : 011 14-Dec-2022...
  • Page 387 Refer to the Garmin G1000 NXi Cockpit Reference Guide and Garmin G1000 NXi Pilot's Guide for the Diamond DA 50 C for complete descriptions of the G1000 NXi system and operating' procedures. 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".
  • Page 388 AFM DA 50 C 07-37 Primary Flight Display (PFD) Description Primary Flight Display (PFD) The primary flight display (PFD Figure 1) 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 389 AFM DA 50 C Figure 1 - Primary Flight Display Doc No.: 9.01.01-E Page 07-74 Issue : 011 14-Dec-2022 DA50-A-31-40-99-01A-040A-D...
  • Page 390 AFM DA 50 C 07-38 Multi-Function Display (MFD) Description Multi-Function Display (MFD) The multi-function display (MFD) typically displays engine data, maps, terrain, traffic and topography displays, and flight planning and progress information. The display unit is nearly identical to the PFD and contains the same controls as previously listed.
  • Page 391 AFM DA 50 C 07-39 Audio Panel Description 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...
  • Page 392 AFM DA 50 C 07-40 Attitude and Heading Reference System (AHRS) Description Attitude and Heading Reference System (AHRS) The attitude and heading reference system (AHRS) uses GPS, rate sensors, air data, and magnetic variation to determine pitch and roll attitude, sideslip and heading. Operation is possible in a degraded mode if the system loses any of these inputs.
  • Page 393 AFM DA 50 C 07-41 Air Data Computer (ADC) Description Air Data Computer (ADC) The air data computer (ADC) provides airspeed, altitude, vertical speed, and air temperature to the display system. In addition to the primary displays, this information is used by the FMS and TIS systems.
  • Page 394 AFM DA 50 C 07-42 PFD / MFD Control Unit (KEYPAD) Description PFD / MFD Control Unit (Keypad) The optional PFD / MFD control unit (if OÄM-50-018 is installed) is a user interface allowing for ease of data entry, PFD / MFD operation and NAV / COM tuning. The PFD / MFD control unit is installed in the center armrest.
  • Page 395 AFM DA 50 C AUTOPILOT Doc No.: 9.01.01-E Page 07-80 Issue : 011 14-Dec-2022...
  • Page 396 AFM DA 50 C 07-43 Autopilot GFC700 Description AUTOPILOT SYSTEM General The GFC 700 automatic flight control system (AFCS) if OÄM 50-031 is installed, is a 3 axis autopilot and flight director system which provides the pilot with the following features: altitude preselect and altitude hold (ALT);...
  • Page 397 HDG mode, then reselecting NAV mode. The GFC 700 automatic flight control system (AFCS) installed in the Diamond DA 50 C consists of the following components: One GDU which contains the following mode control buttons:...
  • Page 398 Refer to the Garmin G1000 NXi Cockpit Reference Guide, P/N 190-02800-( ) and Garmin G1000 NXi Pilot's Guide for the Diamond DA 50 C, P/N 190-02799-( ) for complete descriptions of the G1000 NXi system and operating procedures.
  • Page 399 AFM DA 50 C 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 400 AFM DA 50 C Advisory Alerts Meaning / Cause PREFLIGHT TEST - Performing preflight sys- tem test; aural alert sounds at completion. Do not press the AP DISC switch during servo pow- er-up and preflight system tests as this may cause the preflight system test to fail or never to start (if servos fail their power-up tests).
  • Page 401 AFM DA 50 C PITOT STATIC SYSTEM Doc No.: 9.01.01-E Page 07-86 Issue : 011 14-Dec-2022...
  • Page 402 AFM DA 50 C 07-44 Pitot-Static System Description Pitot-Static System Total pressure is measured at the leading edge of a Pitot probe installed at the LH winglet root rib. The static pressure is measured through the static ports also on that probe. To protect against dirt and condensation there are filters in the system.
  • Page 403 AFM DA 50 C STALL WARNING SYSTEM Doc No.: 9.01.01-E Page 07-88 Issue : 011 14-Dec-2022...
  • Page 404 Stall Warning System The lift transducer of the DA 50 C is located on the leading 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 405 AFM DA 50 C BAGGAGE COMPARTMENT Doc No.: 9.01.01-E Page 07-90 Issue : 011 14-Dec-2022...
  • Page 406 AFM DA 50 C 07-46 Baggage Compartment Description Baggage Compartment There is a baggage compartment aft of the passenger seat row. The baggage compartment is accessible via the passenger door on the LH side of the airplane. The compartment is divided into 2 main areas, A and B, and 2 compartments below floor level, compartments C and D, as described on limitation placard.
  • Page 407 AFM DA 50 C Figure 1 - Baggage Compartment I Doc No.: 9.01.01-E Page 07-92 Issue : 011 14-Dec-2022 DA50-A-25-50-00-99A-040A-D...
  • Page 408 AFM DA 50 C Figure 2 - Baggage Compartment II Doc No.: 9.01.01-E Page 07-93 Issue : 011 14-Dec-2022 DA50-A-25-50-00-99A-040A-D...
  • Page 409 AFM DA 50 C Figure 3 - Baggage Compartment III Doc No.: 9.01.01-E Page 07-94 Issue : 011 14-Dec-2022 DA50-A-25-50-00-99A-040A-D...
  • Page 410 AFM DA 50 C Figure 4 - Front Barrier and Baggage Tray Step Doc No.: 9.01.01-E Page 07-95 Issue : 011 14-Dec-2022 DA50-A-25-50-00-99A-040A-D...
  • Page 411 AFM DA 50 C 07-47 Trim Weight Description TRIM WEIGHT To adjust the airplanes CG, it is possible to install a trim weight in the lower vertical tail. The trim weight can be varied from 1.0 kg (2.2 lb) to a maximum of 20 kg (44.1 lb) in increments of 1 kg (2.2 lb) by installing the required number of steel plates.
  • Page 412 AFM DA 50 C AIRPLANE HANDLING, CARE AND MAINTENANCE Doc No.: 9.01.01-E Page 08-1 Issue : 011 14-Dec-2022...
  • Page 413 AFM DA 50 C GENERAL Doc No.: 9.01.01-E Page 08-2 Issue : 011 14-Dec-2022...
  • Page 414 AFM DA 50 C 08-01 General Description Introduction This Chapter contains the manufacturer's recommended procedures for proper ground handling and servicing of the airplane. The Airplane Maintenance Manual lists certain inspection and maintenance requirements which must be followed if the airplane is to retain a new plane performance and reliability.
  • Page 415 AFM DA 50 C 08-02 Airplane Inspection Intervals Description Airplane Inspection Intervals Inspections are scheduled every 100, 200, 1000 and 2000 hours. Independent of the flight hours an annual inspection must be performed every year. A non-recurring engine inspection must be performed on new engines after 3 to 6 hours.
  • Page 416 AFM DA 50 C 08-03 Airplane Alterations or Repairs Description Airplane Alterations or Repairs Alterations or repairs to the airplane may be carried out only according to the Airplane Maintenance Manual and only by authorized personnel. Doc No.: 9.01.01-E Page 08-5...
  • Page 417 AFM DA 50 C SERVICING Doc No.: 9.01.01-E Page 08-6 Issue : 011 14-Dec-2022...
  • Page 418 AFM DA 50 C 08-04 Refueling Handling References None Preliminary Requirements Required Conditions Not applicable Required Persons Not applicable Fixtures, Tools and Support Equipment Not applicable Consumable Materials Not applicable Expendable Parts Not applicable Safety Conditions WARNING DO NOT GET FUEL ON YOUR SKIN. FUEL CAN CAUSE SKIN DISEASE.
  • Page 419 AFM DA 50 C CAUTION USE ONLY APPROVED FUEL TYPES GIVEN IN 02-14 - FUEL - DESCRIPTION Main Procedure Refueling Ground the airplane and the fuel supply vehicle electrically. Remove the fuel filler cap (located on top of the outer wing). Check cap retaining cable for damage.
  • Page 420 AFM DA 50 C 08-05 Engine Oil Level Check Handling References None Preliminary Requirements Required Conditions Not applicable Required Persons Not applicable Fixtures, Tools and Support Equipment Not applicable Consumable Materials Not applicable Expendable Parts Not applicable Safety Conditions Not applicable...
  • Page 421 AFM DA 50 C 08-06 Gearbox Oil Level Check Handling References None Preliminary Requirements Required Conditions Not applicable Required Persons Not applicable Fixtures, Tools and Support Equipment Not applicable Consumable Materials Not applicable Expendable Parts Not applicable Safety Conditions Not applicable...
  • Page 422 AFM DA 50 C 08-07 Tire Inflation Pressure Check Handling References None Preliminary Requirements Required Conditions Not applicable Required Persons Not applicable Fixtures, Tools and Support Equipment Not applicable Consumable Materials Not applicable Expendable Parts Not applicable Safety Conditions Not applicable...
  • Page 423 AFM DA 50 C GROUND HANDLING Doc No.: 9.01.01-E Page 08-12 Issue : 011 14-Dec-2022...
  • Page 424 AFM DA 50 C 08-08 Ground Handling Description Ground Handling To move the airplane on ground, it can be pushed or pulled by hand on the inner section of the propeller blades near the spinner or pushed on the rough surface of the center wing. Do not push on the spinner, as you may damage the spinner which can cause vibration and damage to the engine.
  • Page 425 AFM DA 50 C Max. 42° Max. 42° Figure 1 - Steering Bar Legend [1, Fig.1] Nose Wheel Doc No.: 9.01.01-E Page 08-14 Issue : 011 14-Dec-2022 DA50-A-15-37-02-00A-040A-D...
  • Page 426 AFM DA 50 C 08-09 Parking Description 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 moored to the ground or placed in a hangar.
  • Page 427 AFM DA 50 C Figure 2 - Gust Lock Installation Doc No.: 9.01.01-E Page 08-16 Issue : 011 14-Dec-2022 DA50-A-15-37-02-01A-040A-D...
  • Page 428 AFM DA 50 C 08-10 Mooring Description 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 429 AFM DA 50 C 08-11 Jacking Description Jacking The airplane can be jacked at the two jackpoints located on the lower side of the center wing's LH and RH root ribs as well as at the tail fin. Doc No.: 9.01.01-E...
  • Page 430 AFM DA 50 C 08-12 Cleaning and Care Description Cleaning and Care Painted Surfaces The entire surface of the airplane is painted with a weatherproof two component paint. Nevertheless, it is recommended to protect the airplane against moisture and dampness. It is also recommended not to store the airplane outside for long periods of time.
  • Page 431 AFM DA 50 C 08-13 Cleaning the Aircraft from Ice and Snow Description Cleaning from Ice and Snow Approved fluids for cleaning the aircraft from ice and snow are: Manufacturer Name Kilfrost TKS 80 Aeroshell Compound 07 AL-5 (DTD 406B) Table 1 Fluids for cleaning the aircraft from ice and snow Remove any snow from the airplane using a soft brush.
  • Page 432 AFM DA 50 C Supplements SUPPLEMENTS Doc No.: 9.01.01-E Page 09-1 Issue : 011 14-Dec-2022...
  • Page 433 Description Introduction Chapter 9 contains information concerning additional (optional) equipment of the DA 50 C. 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.