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Diamond DA20-C1 Manual

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Download this manual See also: Maintenance Manual, Flight Manual
AIRCRAFT FLIGHT MANUAL
DA20-C1
DIAMOND AIRCRAFT INDUSTRIES INC.
1560 CRUMLIN SIDEROAD, LONDON, ONTARIO
CANADA N5V 1S2
All rights reserved. No part of this manual may be reproduced or copied
in any form or by any means without written permission
of
DIAMOND AIRCRAFT INDUSTRIES INC.
Copyright © 2007 by DIAMOND AIRCRAFT INDUSTRIES INC., London, Ontario
INITIAL ISSUE: December 19, 1997
REV 25
April 06, 2010

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  • Page 1 All rights reserved. No part of this manual may be reproduced or copied in any form or by any means without written permission DIAMOND AIRCRAFT INDUSTRIES INC. Copyright © 2007 by DIAMOND AIRCRAFT INDUSTRIES INC., London, Ontario INITIAL ISSUE: December 19, 1997 REV 25...
  • Page 2 DA20-C1 AIRCRAFT FLIGHT MANUAL This manual contains the maintenance information required by JAR-VLA. Contents and revision status can be found in the TABLE OF CONTENTS and the RECORD OF REVISIONS. DIAMOND AIRCRAFT INDUSTRIES INC. 1560 CRUMLIN SIDEROAD London, Ontario, Canada N5V 1S2 http://www.diamondair.com/...
  • Page 3 DIAMOND AIRCRAFT INDUSTRIES INC. FLIGHT MANUAL DA20-C1 Category of Airworthiness : UTILITY Applicable Airworthiness Requirements : AWM Chapter 523-VLA Serial No. Registration Date of Issue : 19 December 1997 Document No. : DA202-C1 This manual must be carried in the aircraft at all times! Scope and revision status can be found in the List of Effective Pages and in the Record of Revisions.
  • Page 4 DA20-C1 Flight Manual PREFACE Congratulations on your choice of the DA20-C1. Safe handling of an airplane increases and ensures your safety and provides you with many hours of enjoyment. For this reason you should take the time to familiarize yourself with your new airplane.
  • Page 5 DA20-C1 Flight Manual TABLE OF CONTENTS Chapter GENERAL OPERATING LIMITATIONS EMERGENCY PROCEDURES NORMAL OPERATING PROCEDURES PERFORMANCE WEIGHT AND BALANCE / EQUIPMENT LIST DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS HANDLING, PREVENTIVE AND CORRECTIVE MAINTENANCE SUPPLEMENTS Doc # DA202-C1 April 16, 2009...
  • Page 6 DA20-C1 Flight Manual INTENTIONALLY LEFT BLANK Doc # DA202-C1 April 16, 2009 Page 0 - 4 Revision 24...
  • Page 7 DA20-C1 Flight Manual LIST OF EFFECTIVE PAGES Chapter Page Date Chapter Page Date DOT-appr 2-12 April 06, 2010 Cover Page April 06, 2010 DOT-appr 2-13 April 06, 2010 DOT-appr 2-14 April 06, 2010 DOT-appr 2-15 April 06, 2010 April 06, 2010...
  • Page 8 DA20-C1 Flight Manual LIST OF EFFECTIVE PAGES (continued) Chapter Page Date Chapter Page Date DOT-appr April 16, 2009 April 06, 2010 DOT-appr April 16, 2009 April 06, 2010 DOT-appr April 16, 2009 April 16, 2009 DOT-appr April 16, 2009 April 16, 2009...
  • Page 9 DA20-C1 Flight Manual SUPPLEMENTS LIST OF EFFECTIVE PAGES NOTE It is only necessary to maintain those supplements which pertain to optional equipment that may be installed in your airplane. Refer to Page 9-2 for index of supplements. Supp Page Date...
  • Page 10 DA20-C1 Flight Manual SUPPLEMENTS LIST OF EFFECTIVE PAGES (continued) Supp Page Date Supp Page Date DOT-appr S12-1 April 06, 2010 DOT-appr S12-2 April 06, 2010 DOT-appr S12-3 April 06, 2010 DOT-appr S12-4 April 06, 2010 DOT-appr S12-5 April 06, 2010...
  • Page 11 DA20-C1 Flight Manual RECORD OF REVISIONS Revisions to this manual, with the exception of actual weighing data, are recorded in the following table. Revisions of approved sections must be endorsed by the responsible airworthiness authority. The new or amended text will be indicated by a bold black vertical line in the left hand margin of a revised page.
  • Page 12 DA20-C1 Flight Manual RECORD OF REVISIONS (continued) Affected Pages Rev. No Approved Date Name 0-4, 0-5, 0-8, 0-9, 0-10, 2-3, 2-5, Rev 7 June 21, 1999 W. Jupp 2-14, 3-3, 3-4, 3-5, 3-6, 3-8, 3-9, Chief, Flight Test 4-10, 4-11, 4-12, 4-13, 4-14, for Director, Aircraft Certification 4-15, 4-16, 4-17, 4-18, 7-6, 7-17.
  • Page 13 DA20-C1 Flight Manual RECORD OF REVISIONS (continued) Affected Pages Rev. No Approved Date Name 0-4, 0-5, 0-6, 0-7, 0-8, 0-9, 0-10, Rev 14 August 9, 2001 W. Jupp 0-11, 1-3, 1-5, 2-4, 2-5, 2-10, Chief, Flight Test 2-15, 4-1, 4-18, 5-5, 5-9, 5-11,...
  • Page 14 DA20-C1 Flight Manual RECORD OF REVISIONS (continued) Affected Pages Rev. No Approved Date Name 0-10, 2-5 TR-1 October 2, 2007 W. Jupp Chief, Flight Test For Director, Aircraft Certification Transport Canada Rev 22 0-4, 0-5, 0-6, 0-10, 2-4, 2-7, 2-17, November 2, 2007 W.
  • Page 16 DA20-C1 Flight Manual INTENTIONALLY LEFT BLANK Doc # DA202-C1 April 06, 2010 Page 0 - 14 Revision 25...
  • Page 17 DA20-C1 Flight Manual REVISION LOG This log should be used to record all revisions issued and inserted in this manual. The affected pages of any revision must be inserted into the manual as well as the Record of Revisions upon receipt. The pages superseded by the revision must be removed and destroyed.
  • Page 18 DA20-C1 Flight Manual INTENTIONALLY LEFT BLANK Doc # DA202-C1 April 06, 2010 Page 0 - 16 Revision 25...
  • Page 19 Pages Highlights Cover page Cover Page revised to show Revision 25, Dated April 06, 2010. DA 20-C1 changed to DA20-C1 on the header of each page. 0-1, 0-2 DIAMOND AIRCRAFT INDUSTRIES changed to DIAMOND AIRCRAFT INDUSTRIES INC. List of Effective Pages revised. Rev bars inserted adjacent to the 0-5 thru 0-8 changed pages.
  • Page 20 First two “Approval pages” removed. Supp S12 Supp S13 S13-1 thru S13-22 New Supplement added. Garmin G500 Integrated Display System. DA 20-C1 changed to DA20-C1 on the header of each page. Doc # DA202-C1 April 06, 2010 Page 0 - 18 Revision 25...
  • Page 21 SUBSCRIPTION SERVICE Diamond Aircraft Publications Revision Subscription Contacts To ensure safe operation and maintenance of the DA20-C1 aircraft, it is recommended that operators verify that their documentation is at the correct issue/revision levels. For revision and subscription service please contact the following: DA20-C1 related manuals and publications.
  • Page 22 DA20-C1 Flight Manual INTENTIONALLY LEFT BLANK Doc # DA202-C1 April 06, 2010 Page 0 - 20 Revision 25...

  • Page 23: General

    DA20-C1 Flight Manual General CHAPTER 1 GENERAL 1.1. INTRODUCTION....................... 2 1.2. CERTIFICATION BASIS ....................2 1.3. WARNINGS, CAUTIONS, AND NOTES ................2 1.4. THREE-VIEW-DRAWING OF AIRPLANE ................ 3 1.5. DIMENSIONS ........................4 1.5.1. Overall Dimensions ..................4 1.5.2. Wing ........................ 4 1.5.3.
  • Page 24 Manual (AWM) Chapter 523-VLA. It also contains supplemental data supplied by the airplane manufacturer which can be useful to the pilot. The Flight Manual conforms to a standard equipped DA20-C1 airplane. Any optional equipment installed on request of the customer (COMM, NAV, etc.) is not considered.
  • Page 25 DA20-C1 Flight Manual DA20-C1 Flight Manual General General 1.4. THREE-VIEW-DRAWING OF AIRPLANE Doc # DA202-C1 Doc # DA202-C1 April 06, 2010 April 06, 2010 Page 1 - 3 Page 1 - 3 Revision 25 Revision 25...
  • Page 26 DA20-C1 Flight Manual General 1.5. DIMENSIONS 1.5.1. Overall Dimensions Span: 35 ft 8 in (10.87 m) Length: 23 ft 6 in (7.17 m) Height: 7 ft 2 in (2.19 m) 1.5.2. Wing Airfoil: Wortmann FX 63-137/20 HOAC Wing Area: 125 sq ft (11.6 m2) Mean Aerodynamic Chord (MAC): 3 ft 6.9 in (1.09 m)
  • Page 27 DA20-C1 Flight Manual General 1.6. ENGINE Continental IO 240, naturally aspirated, 4 cylinder, 4 stroke-engine, fuel injected, horizontally opposed, air cooled. Propeller drive direct from engine crankshaft. Displacement: 239.8 cu.in. (3.9 liters) Output Power: 125 hp (93.2 kW) 2800 RPM 1.7.
  • Page 28 DA20-C1 Flight Manual General 1.9. LUBRICANT AND COOLANT 1.9.1. Lubricant Use only lubricating oils conforming to TCM specification MHS24. See Table 1 below for approved brands. Table 1 SUPPLIER BRAND (if applicable) TYPE (if applicable) BP Oil Corporation BP Aero Oil...
  • Page 29 DA20-C1 Flight Manual General Table 2 The viscosity should be selected according to the various climatic conditions using Table 2. Use only the oils specified TCM specification MHS 24 Oil Capacity: Maximum : 6.0 US qt (5.68 liters) Minimum : 4.0 US qt (3.78 liters)
  • Page 30 DA20-C1 Flight Manual General 1.10. WEIGHT Maximum Ramp Weight : 1660 lbs (753 kg) Maximum Take-off Weight : 1653 lbs (750 kg) Maximum Landing Weight : 1653 lbs (750 kg) Empty Weight : See Chapter 6 Maximum Weight in Baggage Compartment...
  • Page 31 DA20-C1 Flight Manual General 1.11. LIST OF DEFINITIONS AND ABBREVIATIONS 1.11.1. Speed AGL: Above Ground Level CAS: Calibrated airspeed; Indicated speed corrected for installation and instrument errors. CAS is equal to TAS at standard atmospheric conditions at MSL. KCAS: CAS in knots.
  • Page 32 DA20-C1 Flight Manual General 1.11.2. Meteorological Terms ISA: International Standard Atmosphere at which air is identified as a dry gas. The temperature at mean sea level is 15° C (59° F), the air pressure at sea level is 1013.25 mbar (29.92 inHg), the temperature gradient up to the altitude at which the temperature reaches -56.5°...
  • Page 33 DA20-C1 Flight Manual General 1.11.4. Flight Performance and Flight Planning Demonstrated Crosswind Component: The maximum speed of the crosswind component at which the manoeuvrability of the airplane during take-off and landing has been demonstrated during type certification test flights. Service Ceiling: The altitude at which the maximum rate of climb is 0.5 m/s (100 ft/min.).
  • Page 34 DA20-C1 Flight Manual General CG position: Distance from the reference datum to the CG. It is determined by dividing the total moment (sum of the individual moments) by the total weight. Center of Gravity Limits: The CG range which an airplane with a given weight must be operated within.
  • Page 35 DA20-C1 Flight Manual General 1.12. CONVERSION FACTORS 1.12.1. Length or Altitude 1 [ft.] = 0.3048 [m] 1 [in.] = 25.4 [mm] 1.12.2. Speed 1 [kts] = 1.852 [km/h] 1 [mph] = 1.609 [km/h] 1.12.3. Pressure 1 [hPa] = 100 [N/m2] = 1 [mbar] 1 [in.
  • Page 36 DA20-C1 Flight Manual General INTENTIONALLY LEFT BLANK Doc # DA202-C1 April 06, 2010 Page 1 - 14 Revision 25...

  • Page 37: Operating Limitations

    DA20-C1 Flight Manual Limitations CHAPTER 2 OPERATING LIMITATIONS 2.1. INTRODUCTION....................... 2 2.2. AIRSPEED LIMITATIONS ....................2 2.3. AIRSPEED INDICATOR MARKINGS ................2 2.4. POWER PLANT LIMITATIONS ..................3 2.4.1. Engine ........................3 2.4.2. Additional for aircraft equipped with altitude compensating fuel system..................4 2.4.3.
  • Page 38 DA20-C1 Flight Manual Limitations 2.1. INTRODUCTION Chapter 2 of this Flight Manual comprises of the operating limitations, instrument markings, airspeed indicator markings, and the limitation placards which are necessary for the safe operation of the airplane, its engine, and standard systems and equipment.
  • Page 39 DA20-C1 Flight Manual Limitations 2.4. POWER PLANT LIMITATIONS 2.4.1. Engine Engine Manufacturer : Teledyne Continental Motors Engine Type Designation : IO-240-B Engine Operating Limitations Max. T/O Power (5 min.) : 125 BHP / 93.2 kW Max. Permissible T/O RPM : 2800 RPM Max.
  • Page 40 DA20-C1 Flight Manual Limitations Cylinder Head Temperature Maximum : 460°F (238°C) Minimum : 240°F (115°C) takeoff and descent Fuel Specifications Approved Fuel Grades : AVGAS 100LL or 100 Oil Grades : Reference TCM IO-240-B operator and installation manual (form X30620) or TCM specification MHS-24.
  • Page 41 DA20-C1 Flight Manual Limitations 2.5. POWERPLANT INSTRUMENT MARKINGS Powerplant instrument markings and their color code significance are shown below: Instrument Red Line/ Green Arc/ Yellow Arc/ Red Line/ Lower Limit Normal Operating Caution Range Upper Limit Range Tachometer 700 - 2800 RPM...
  • Page 42 DA20-C1 Flight Manual Limitations 2.7. WEIGHT Maximum Ramp Weight : 1660 (753 kg) Maximum Take-Off Weight : 1653 lbs (750 kg) Maximum Landing Weight : 1653 lbs (750 kg) Maximum permissible weight : 44 lbs (20 kg) only permissible in the baggage compartment...
  • Page 43 DA20-C1 Flight Manual Limitations 2.9. APPROVED MANEUVERS This airplane is certified in the UTILITY Category in accordance with Canadian Airworthiness Manual Chapter 523-VLA. Permissible Utility Category Maneuvers: All normal flight maneuvers The following maneuvers in which the angle of bank is not more than 60°:...
  • Page 44 DA20-C1 Flight Manual Limitations 2.10. MANEUVERING LOAD FACTORS Table of structural maximum permissible load factors: at v at v with flaps in T/O or LDG position Positive + 4.4 + 4.4 + 2.0 Negative - 2.2 - 2.2 WARNING EXCEEDING THE MAXIMUM LOAD FACTORS WILL RESULT IN OVERSTRESSING OF THE AIRPLANE.
  • Page 45 DA20-C1 Flight Manual Limitations 2.11. MAXIMUM PASSENGER SEATING Maximum Passenger Seating: one passenger. 2.12. FLIGHT CREW Minimum Flight Crew: one pilot. 2.13. KINDS OF OPERATION Flights are permissible in accordance with visual flight rules. Minimum Equipment, Flight and Navigation Instruments:...
  • Page 46 DA20-C1 Flight Manual Limitations On the upper instrument panel 2.14. FUEL surround. Fuel Capacity Total Fuel Quantity: : 24.5 US gal. (93.0 liters) Usable Fuel: : 24.0 US gal. (91.0 liters) On the instrument panel below the Unusable Fuel: : 0.5 US airspeed indicator.
  • Page 47 DA20-C1 Flight Manual Limitations On the lower left side of the instrument panel above the switches. With Aspen Avionics Doc # DA202-C1 April 06, 2010 Page 2 - 11 Revision 25 DOT Approved...
  • Page 48 DA20-C1 Flight Manual Limitations On the instrument panel above the individual circuit breakers. (a) Placard information will vary depending on installed equipment On the lower left side of the instrument panel. (a) With Aspen installed. On the upper left corner of the instrument panel.
  • Page 49 DA20-C1 Flight Manual Limitations On the exterior of the canopy frame on On the exterior of the canopy frame on the L/H side. And on the interior of the the L/H side. canopy frame on the R/H side. (If equipped with an outside handle)
  • Page 50 DA20-C1 Flight Manual Limitations On the interior of the canopy frame On the R/H side of the canopy sill. on the L/H side and R/H side. (On S/N C0150 and subs) On the R/H upper fuselage behind the canopy, if an ELT is installed.
  • Page 51 DA20-C1 Flight Manual Limitations On the fuselage (belly), near the On the underside of the fuselage center line between the wings. (belly) near the L/H wing trailing edge. On the underside of the fuselage (belly) to the left just forward of the On the L/H side of the fuselage wing trailing edge.
  • Page 52 DA20-C1 Flight Manual Limitations On the upper engine cowling behind For ME406 - On the side of the ELT Bracket the propeller spinner. Around the stall warning hole in the left wing. On the L/H side of the baggage compartment.
  • Page 53 DA20-C1 Flight Manual DA20-C1 Flight Manual Limitations Limitations On the engine controls on the center console. On the engine controls on the center console. On the center console on the heating and parking brake controls. On the center console on the heating and parking brake controls.
  • Page 54 DA20-C1 Flight Manual Limitations On the left side of the instrument On the instrument panel on Aircraft panel near the top. equipped with supplemental lighting (MOD 32). On the engine controls for aircraft On fuel shut-off handle on R/H side with center console mounted Fuel of the center console.
  • Page 55 DA20-C1 Flight Manual Limitations Around the ignition switch on the On the instrument panel. If instrument panel. equipped with altitude compensating fuel pump. On the back-rest on the right side. On the instrument panel. If equipped with altitude compensating fuel pump.
  • Page 56 DA20-C1 Flight Manual Limitations On the instrument panel. If equipped with altitude compensating fuel pump. 2.16. DEMONSTRATED CROSSWIND COMPONENT The maximum demonstrated crosswind component is 20 kts. (37 km/h). 2.17. TEMPERATURE LIMITS CAUTION FOR AIRCRAFT WITH OTHER THAN WHITE UNDERSIDES.

  • Page 57: Emergency Procedures

    DA20-C1 Flight Manual Emergency Procedures CHAPTER 3 EMERGENCY PROCEDURES 3.1. INTRODUCTION....................... 2 3.2. AIRSPEEDS DURING EMERGENCY PROCEDURES ............ 2 3.3. EMERGENCY PROCEDURES - CHECKLISTS ............... 3 3.3.1. Engine Failures....................3 3.3.2. Gliding ......................6 3.3.3. Emergency Landing..................6 3.3.4. Fire ........................8 3.3.5.
  • Page 58 DA20-C1 Flight Manual Emergency Procedures 3.1. INTRODUCTION The following chapter contains check-lists as well as descriptions of the recommended procedures in case of an emergency. However, engine failure or other airplane related emergency situations will most likely never occur if the mandatory pre-flight check and maintenance are performed properly.
  • Page 59 DA20-C1 Flight Manual Emergency Procedures 3.3. EMERGENCY PROCEDURES - CHECKLISTS 3.3.1. Engine Failures A. Engine Failure during Take-off Run Throttle IDLE Brakes as required Flaps CRUISE Mixture IDLE CUT-OFF Ignition Switch GEN/BAT Master Switch B. Engine Failure after Take-Off INSUFFICIENT ENGINE POWER...
  • Page 60 DA20-C1 Flight Manual Emergency Procedures C. Engine Failure during Flight ENGINE RUNNING ROUGHLY Mixture FULL RICH Alternate Air OPEN Fuel Shut-off OPEN Fuel Pump Ignition Switch cycle L - BOTH - R - BOTH Throttle at present position No Improvement reduce throttle to minimum required power, land as soon as possible.
  • Page 61 DA20-C1 Flight Manual Emergency Procedures CAUTION DO NOT ENGAGE STARTER IF PROPELLER IS WINDMILLING. ENGINE DAMAGE MAY RESULT. The propeller will continue to windmill as long as the airspeed is at least 60 KIAS. RESTARTING THE ENGINE WITH PROPELLER WINDMILLING...
  • Page 62 DA20-C1 Flight Manual Emergency Procedures 3.3.2. Gliding Wing Flaps CRUISE Airspeed at 1653 lbs (750 kg) 73 KIAS Glide Ratio 11:1 Example: For every 1000 feet of altitude the aircraft can move forward 11,000 feet or 1.8 NM (3.4 km).
  • Page 63 DA20-C1 Flight Manual Emergency Procedures Over fly selected landing area (not below 500 ft / 150 m above ground) to confirm suitability and that approach route is free of obstacles. Climb up to pattern altitude. Low pass over flight at a safe altitude to observe any possible obstacles, such as cables, fences, ditches.
  • Page 64 DA20-C1 Flight Manual Emergency Procedures 3.3.4. Fire A. Engine Fire during Engine-Start-Up on the Ground Fuel Shut-off Valve CLOSED Cabin Heat CLOSED Mixture IDLE CUTOFF GEN/BAT Master Switch Ignition Switch Evacuate Airplane immediately B. Engine Fire during Flight Fuel Shut-off Valve...
  • Page 65 DA20-C1 Flight Manual Emergency Procedures NOTE Restore electrical power systematically allowing time to monitor the system voltmeter and amp meter between the reconnection of loads. Watch carefully for smoke. Circuit Breakers Pull all circuit breakers. Circuit Breakers Push BATTERY GEN/BAT Master Switch...
  • Page 66 DA20-C1 Flight Manual Emergency Procedures 3.3.5. Icing Unintentional Flight Into Icing Area Leave icing area (through change of altitude or change of flight direction to reach area with higher outside air temp.). Continue to move control surfaces to maintain their moveability.
  • Page 67 DA20-C1 Flight Manual Emergency Procedures 3.3.7. Landing with Defective Tire on Main Landing Gear Final approach with wing flaps in landing position. Land airplane on the side of runway opposite to the side with the defective tire to compensate for change in direction which is to be expected during final rolling.
  • Page 68 DA20-C1 Flight Manual Emergency Procedures LOW VOLTAGE INDICATION (NEEDLE IN YELLOW ARC) DURING FLIGHT All non-flight essential electrical Switch OFF consumers If needle is remaining in the yellow arc Generator Failure: and the ammeter is indicating to the left Refer to paragraph 3.3.8.C.
  • Page 69 DA20-C1 Flight Manual Emergency Procedures 3.3.9. Flap System Failure Flap Position Indicator Failure visual check of the flap position select airspeed within the range of the white arc marked on the airspeed indicator check all positions of the flap toggle switch (flap stops are fail-safe) modify approach and landing as follows: •...
  • Page 70 DA20-C1 Flight Manual Emergency Procedures 3.3.11. Avionics System Failure TOTAL AVIONICS FAILURE: Check Avionics Master Circuit If popped, press and monitor status, Breaker If it pops again, land at the nearest suitable airport. Check Avionics Master Switch Toggle avionics master switch, if...
  • Page 71 DA20-C1 Flight Manual Emergency Procedures 3.3.12. Trim System Failure STUCK TRIM: Circuit breaker check, press if breaker is tripped Rocker switch depress in both directions, wait 5 minutes, try again NOTE Full range of travel is available for elevator, but expect higher forces on control stick.
  • Page 72 DA20-C1 Flight Manual Emergency Procedures 3.3.13. Instrument Panel Lighting Failure Rocker Switch, map light Rocker Switch, I-panel lighting Cycle Rocker Switch OFF - ON Dimming Control Turn fully clockwise Internal Lighting Circuit Breaker If tripped, reset If NOT Successful Use flashlight Expect electrical power failure.

  • Page 73: Normal Operating Procedures

    DA20-C1 Flight Manual Normal Operating Procedures CHAPTER 4 NORMAL OPERATING PROCEDURES 4.1. INTRODUCTION....................... 2 4.2. AIRSPEEDS FOR NORMAL FLIGHT OPERATION............2 4.3. STRUCTURAL TEMPERATURE INDICATOR ..............3 4.4. NORMAL OPERATION CHECKLIST ................5 4.4.1. Preflight Inspection...................... 5 4.4.2. Before Starting Engine ....................9 4.4.3.
  • Page 74 DA20-C1 Flight Manual Normal Operating Procedures 4.1. INTRODUCTION Chapter 4 provides checklist and amplified procedures for the normal operation. 4.2. AIRSPEEDS FOR NORMAL FLIGHT OPERATION Unless stated otherwise, the following table contains the applicable airspeeds for maximum take-off and landing weight. The airspeeds may also be used for lower flight weights.
  • Page 75 DA20-C1 Flight Manual Normal Operating Procedures 4.3. STRUCTURAL TEMPERATURE INDICATOR A structural temperature indicator, installed on the spar bridge, indicates when the structural temperature limitation is exceeded (refer to Section 2.17). The indicator need only be checked if the OAT exceeds 38º C (100º F).
  • Page 76 DA20-C1 Flight Manual Normal Operating Procedures INTENTIONALLY LEFT BLANK Doc # DA202-C1 April 16, 2009 Page 4 - 4 Revision 24 DOT Approved...
  • Page 77 DA20-C1 Flight Manual Normal Operating Procedures 4.4. NORMAL OPERATION CHECKLIST 4.4.1. Preflight Inspection A. In-Cabin Check Structural Temperature Indicator check that Structural Temperature (if OAT exceeds 38º C (100º F)) does not exceed 55º C (131º F) Airplane Documents check...
  • Page 78 DA20-C1 Flight Manual Normal Operating Procedures B. Walk Around Check and Visual Inspection Doc # DA202-C1 April 16, 2009 Page 4 - 6 Revision 24 DOT Approved...
  • Page 79 DA20-C1 Flight Manual Normal Operating Procedures CAUTION VISUALLY INSPECT FOR THE FOLLOWING CONDITIONS: DEFECTS, CONTAMINATION, CRACKS, DELAMINATIONS, EXCESSIVE PLAY, INSECURE OR IMPROPER MOUNTING AND GENERAL CONDITION. ADDITIONALLY, CHECK THE CONTROL SURFACES FOR FREEDOM OF MOVEMENT. CAUTION SET PARKING BRAKE PRIOR TO REMOVING WHEEL CHOCKS.
  • Page 80 DA20-C1 Flight Manual Normal Operating Procedures Empennage Stabilizers and Control Surfaces visual inspection Tie down remove Fixed Tab on Rudder visual inspection Right Wing Entire Wing visual inspection Wing Flap including Inspection Panel visual inspection Aileron including Inspection Panel visual inspection...
  • Page 81 DA20-C1 Flight Manual Normal Operating Procedures 4.4.2. Before Starting Engine CAUTION BEFORE STARTING THE ENGINE, THE CANOPY MUST BE CLOSED AND LATCHED. THE RED HANDLES MUST BE MOVED FULLY FORWARD. AFTER STARTING THE ENGINE THE CANOPY MUST BE CLOSED AND LATCHED AND STAY CLOSED AND LATCHED UNTIL THE ENGINE IS SHUT DOWN.
  • Page 82 DA20-C1 Flight Manual Normal Operating Procedures 4.4.3. Starting Engine A. Starting Engine Cold NOTE It is recommended that the engine be preheated if it has been cold soaked for 2 hours or more at temperatures of -4º C (25º F) or less.
  • Page 83 DA20-C1 Flight Manual Normal Operating Procedures NOTE Activate starter for maximum of 30 seconds only, followed by a cooling period of 3-5 minutes. Throttle 800 to 1000 RPM CAUTION DO NOT OPERATE ENGINE ABOVE 1000 RPM UNTIL AN OIL TEMPERATURE INDICATION IS REGISTERED.
  • Page 84 DA20-C1 Flight Manual Normal Operating Procedures CAUTION DO NOT ENGAGE STARTER IF THE PROPELLER IS MOVING. SERIOUS DAMAGE CAN RESULT. NOTE Steps 5, 6, 7, 8, 9, and 10 are to be performed without delay between steps. Fuel Pump Fuel Prime...
  • Page 85 DA20-C1 Flight Manual Normal Operating Procedures CAUTION IF OIL PRESSURE IS BELOW 10 PSI, SHUT DOWN ENGINE IMMEDIATELY (MAXIMUM 30 SECONDS DELAY). NOTE Oil Pressure may advance above the green arc until Oil Temp. reaches normal operating temperatures. Regulate warm up RPM to maintain pressure below 100 psi limit.
  • Page 86 DA20-C1 Flight Manual Normal Operating Procedures 4.4.6. Before Take-off (Engine Run-up) NOTE For OAT’s less than -5º F (-20º C) turn cabin heat on for at least 10 minutes prior to take-off. Brakes apply Safety Belts fastened Canopy closed and locked...
  • Page 87 DA20-C1 Flight Manual Normal Operating Procedures 4.4.7. Take-off Fuel Prime check OFF Fuel Pump check ON Mixture check FULL RICH GEN/BAT Master Switch check ON Ignition Switch check BOTH Wing Flaps check T/O Trim NEUTRAL Throttle FULL Check RPM min 2000 RPM...

  • Page 88: Performance

    DA20-C1 Flight Manual Normal Operating Procedures 4.4.8. Climb Mixture FULL RICH NOTE For aircraft without the altitude compensating fuel pump, at full throttle settings with power less than 75%, it is necessary to lean the engine with the mixture control. It should be noted that with the engine set to full throttle, it can produce less than 75% power, depending on pressure altitude.
  • Page 89 DA20-C1 Flight Manual Normal Operating Procedures 4.4.10. Descent Flight Instruments and Avionics adjust Fuel Pump Mixture FULL RICH Throttle as required CAUTION CHT NOT BELOW 300º F FOR MORE THAN 5 MINUTES. 240º F MIN. NOTE To achieve a fast descent:...
  • Page 90 DA20-C1 Flight Manual Normal Operating Procedures 4.4.12. Balked Landing Throttle FULL Mixture FULL RICH Wing Flaps Airspeed 58 KIAS 4.4.13. After Landing Throttle as required Mixture FULL RICH Wing Flaps CRUISE Avionics as required Exterior Lights as required 4.4.14. Engine Shut-down...
  • Page 91 DA20-C1 Flight Manual Normal Operating Procedures 4.4.16. Spinning A. Spin Entry Loose Items stowed Seat Belts fastened Altitude and Airspace check Fuel Pump Wing Flaps CRUISE Mixture FULL RICH Throttle IDLE Entry Speed trim to 58 KIAS Reduce speed with elevator...
  • Page 92 DA20-C1 Flight Manual Normal Operating Procedures 4.4.17. Idle Power Operations NOTE Turn fuel pump on for all low throttle operations, including taxiing and all flight operations when engine speed could fall below 1400 RPM (eg. stalls, descents, spins, landings, etc.).
  • Page 93 DA20-C1 Flight Manual Performance CHAPTER 5 PERFORMANCE 5.1. INTRODUCTION....................... 2 5.2. USE OF PERFORMANCE TABLES AND DIAGRAMS ............ 2 5.3. PERFORMANCE TABLE AND DIAGRAMS ..............3 5.3.1. Airspeed System Calibration ..................3 5.3.2. Cruising Performance....................4 5.3.3. Stall Speeds ......................5 5.3.4.
  • Page 94 DA20-C1 Flight Manual Performance 5.1. INTRODUCTION This chapter contains the performance data required by the basis of certification. This data which has been approved by Transport Canada is marked ‘DOT Approved’ in the footer of the page. Where additional performance data has been provided, beyond the basis for certification, it has not been reviewed or approved by Transport Canada.
  • Page 95 DA20-C1 Flight Manual Performance 5.3. PERFORMANCE TABLE AND DIAGRAMS 5.3.1. Airspeed System Calibration Assumes zero indicator error Flaps Cruise KIAS KCAS Flaps T/O KIAS KCAS Flaps LDG KIAS KCAS Example: CRUISE Flap KIAS = 90 kts therfore KCAS = 92 kts from chart Figure 5.1.
  • Page 96 DA20-C1 Flight Manual Performance 5.3.2. Cruising Performance Maximum RPM is 2800 Example: OAT: 70º F Pressure Altitude: 5000 ft Desired Power setting: Result: Set RPM: 2560 Figure 5.2. Cruising Performance Doc # DA202-C1 April 16, 2009 Page 5 - 4...
  • Page 97 DA20-C1 Flight Manual Performance 5.3.3. Stall Speeds Configuration: Idle, most forward center of gravity, max. weight (this is the most adverse configuration) Bank Angle 0º 30º 45º 60º Flaps CRUISE NOTE: Stall speeds in kts Figure 5.3. Stall Speeds Doc # DA202-C1...
  • Page 98 DA20-C1 Flight Manual Performance 5.3.4. Wind Components Maximum demonstrated crosswind component: 20 kts (37 km/h) xample: Wind speed: 11 kts (20 km/h) Angle between wind direction and flight direction: 30° Headwind component: 9.5 kts (18 km/h) Crosswind component: 5.5 kts (10 km/h) Figure 5.4.
  • Page 99 DA20-C1 Flight Manual Performance 5.3.5. Take-off Distance Figure 5.5. Take-off Distance Doc # DA202-C1 April 16, 2009 Page 5 - 7 Revision 24 DOT Approved...
  • Page 100 DA20-C1 Flight Manual Performance 5.3.6. Climb Performance / Cruising Altitudes Max. Cruising Altitude (in standard conditions): 13120 ft (4000 m) Best Rate-of-Climb Speed with Wing Flaps CRUISE 75 KIAS CAUTION IN AIRPLANE OPERATIONS WITHOUT THE OPTIONAL WH FAIRINGS INSTALLED, CLIMB PERFORMANCE REDUCED BY APPROXIMATELY 3%.
  • Page 101 DA20-C1 Flight Manual Performance 5.3.7. Climb Performance / Take off Best Rate-of-Climb Speed with Wing Flaps T/O 68 KIAS Example: Pressure Altitude: 2000 ft OAT: 65° F Weight : 1653 lbs Result: Climb performance: 775 ft/min Figure 5.7. Climb Performance / Take off...
  • Page 102 DA20-C1 Flight Manual Performance 5.3.8. Cruising Speed (True Airspeed Diagram for true airspeed (TAS) calculation at se lec d pow er level. CAUTION IN AIRPLANE OPERATIONS WITHOUT THE OPTIONAL WHEEL FAIRINGS INSTALLED, THE MAXIMUM CRUISING SPEED IS REDUCED BY APPROXIMATELY 5%.
  • Page 103 DA 20-C1 Flight Manual Performance 5.3.9. Maximum Flight Duration Table for calculation of the maximum flight duration depending on fue l availability. Table 1. Flight Manual Cruise Performance Table 20º C Below Standard Standard 10º C Above Standard Temp Tempe rature Temp Press Alt...
  • Page 104 DA 20-C1 Flight Manual Performance .3.10. Climb Performance / Balked Landing onditions: Speed = 52 KIAS Wing Flaps in Landing Position (LDG) max take-off power CAUTION IN AIRPLANE OPERATIONS WITHOUT THE OPTIONAL WHEEL FAIRINGS INSTALLED, CLIMB PERFORMANCE REDUCED BY APPROXIMATELY 3%. Example: Pressure altitude: 2000 ft...
  • Page 105 DA 20-C1 Flight Manual Performance 5.3.11. Landing Distance Conditions: - Throttle: Idle - Maximu m T/O Weight - Ap ach Speed 2 KIA - Level Runway, paved Flap s in Landing position (L - St Settin g, M Landing distance over a 50 ft (15 m) obstacle: ox.
  • Page 106 DA 20-C1 Flight Manual Performance INTENTIONALLY LEFT BLANK Doc # DA202-C1 April 16, 2009 Page 5 - 14 Revision 24 DOT Approved...

  • Page 107: Weight And Balance / Equipment List

    DA20-C1 Flight Manual Weight and Balance CHAPTER 6 WEIGHT AND BALANCE / EQUIPMENT LIST 6.1. INTRODUCTION....................... 2 6.2. AIRPLANE WEIGHING ..................... 3 6.3. WEIGHT AND BALANCE REPORT ................. 6 6.4. FLIGHT WEIGHT AND CENTER OF GRAVITY ............... 8 6.5. EQUIPMENT LIST ......................12...
  • Page 108 DA20-C1 Flight Manual Weight and Balance 6.1. INTRODUCTION To obtain the performance, flight characteristics and safe operation described in this Flight Manual, the airplane must be operated within the permissible weight and balance envelope as described in Chapter 2. It is the pilot's responsibility to adhere to the weight and balance limitations and to take into consideration the change of the center of gravity (CG) position due to fuel consumption.
  • Page 109 DA20-C1 Flight Manual Weight and Balance 6.2. AIRPLANE WEIGHING Pre-weighing conditions: - equipment must be in accordance with the airplane equipment list - brake fluid, lubricant (6 US qt / 5.7 liters) and - unusable fuel, included (2 liters unusable, 3.18 lbs/1.44 Kg)
  • Page 110 DA20-C1 Flight Manual Weight and Balance Figure 6.1. Longitudinal Leveling Diagram Legend: Arm - Datum to center line nose wheel Arm - Datum to C/L main wheels (LH and RH) Net weight - Nose wheel Net weight - Main wheels (LH and RH)
  • Page 111 DA20-C1 Flight Manual Weight and Balance Model: DA20-C1 Serial Number Registration Data with reference to the Type Certificate Data Sheet and the Flight Manual Reference Datum: Leading edge of wing at root rib. Horizontal reference line: Wedge 1000:55.84, 2000mm (78.7 in) aft of the step in the fuselage...
  • Page 112 DA20-C1 Flight Manual Weight and Balance 6.3. WEIGHT AND BALANCE REPORT The empty weight and Empty Weight CG position data determined prior to delivery of the airplane is the first entry in the Weight and Balance Report. Each change of the installed...
  • Page 113 DA20-C1 Flight Manual Weight and Balance Doc # DA202-C1 April 16, 2009 Page 6 - 7 Revision 24 DOT Approved...
  • Page 114 DA20-C1 Flight Manual Weight and Balance 6.4. FLIGHT WEIGHT AND CENTER OF GRAVITY The followin g data enables the pilot to operate the DA20-C1 within the required weight and center of gr avity limitations. The followin g diagrams, Figure 6.5...
  • Page 115 DA20-C1 Flight Manual Weight and Balance Example: Pilot and Passenger: 359 lbs. (163 kg) Fuel 14.0 US gal. / 52.9 liters: 93 lbs. (42 kg) (6.01 lbs. per US gal./0.72 kg per liter) Result: Moment of Pilot and Passenger: 2021 in. lbs. (24.4 kgm) Moment of Fuel: 3017 in.
  • Page 116 DA20-C1 Flight Manual Weight and Balance DA20-C1 (Example) Your DA20-C1 Calculation of the Load Weight [lbs] Moment [in.lbs] Weight [lbs] Moment [in.lbs] Limits (Weight [kg]) ([kgm]) (Weight [kg]) ([kgm]) 1. Empty Weight (use the 1153 12562 data for your airplane (523) (144.740)
  • Page 117 DA20-C1 Flight Manual Weight and Balance See example calculat ion of loadin condition Figure .7. Change in center of gravity is due to fuel consumption Figure 6.8. Permissible Center of Gravity Range and Permissible Flight-Weight-Moment Doc # DA202-C1 April 16, 2009...
  • Page 118 DA20-C1 Flight Manual Weight and Balance EQUIPMENT LIST The following table lists all the equipment available for this airplane. An Equipment Record of items installed in your specific airplane is included in the back of this manual. The equipment list comprises the following data: •...
  • Page 119 (0.95) (-0.52) 24-001 Ammeter -16.4 VDO 190-031SB (0.1) (-0.42) 24-002 EPU Kit (S/N C0001-C0148, C0150) +45.6 Diamond Service Bulletin # DAC1-24-02 (2.0) (+1.16) 24-003 Battery, GIL G-35M 26.3 +57.5 Diamond Service Bulletin # DAC1-24-03 (11.9) (+1.46) Doc # DA202-C1 April 16, 2009...
  • Page 120 DA20-C1 Flight Manual Weight and Balance Equipment List Item Part Description, Weight Number Manufacturer Part/Model No. lbs (kg) in (m) 24-004 Battery, standard C0001-C0148, C0150 15.3 +57.5 Yuasa Y50N18L-A-CX (6.9) (+1.46) Battery, standard (S/N C01 49, C0151 onwards) 15.3 -35.0 Yuasa Y50N18L-A-CX (6.9)
  • Page 121 DA20-C1 Flight Manual Weight and Balance Equipment List Item Part Description, Weight Number Manufacturer Part/Model No. lbs (kg) in (m) 34-003 Nav Indicator -16.4 King KI 208 (0.5) (-0.42) 34-004 Outside Air Temperature Indicator (F) -15.5 Davtron 301F (0.2) (-0.39)
  • Page 122 Sensenich W69EK7-63 an d W69EK7-63G (5.7) (-1.54) 71-001 Heater +45.5 Tanis TAS100-29 (0.5) (+1.16) 71-002 Winter Kit -33.5 Diamond Service Bulletin # DAC1-71-01 (0.2) (-0.85) 73-001 Fuel Pressure Ind icator -15.5 22-7330-00-01 (0.1) (-0.39) 77-001 Cylinder Head Te mp. Indicator -16.4...
  • Page 123 DA20-C1 Flight Manual Weight and Balance Equipment List Item Part Description, Weight Number Manufacturer Part/Model No. lbs (kg) in (m) 77-007 Vision Microsystems VM-1000 -20.0 4010066 Data Pro cessing Unit (0.6) (-0.51) 77-008 Lighted RPM In dicator – Recording -16.4...
  • Page 124 DA20-C1 Flight Manual Weight and Balance INTENTIONALLY LEFT BLANK Doc # DA202-C1 April 16, 2009 Page 6 - 18 Revision 24 DOT Approved...
  • Page 125 DA20-C1 Flight Manual Description CHAPTER 7 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS 7.1. INTRODUCTION....................... 3 7.2. AIRFRAME ........................3 7.2.1. Fuselage......................3 7.2.2. Wings....................... 3 7.2.3. Empennage ..................... 3 7.3. FLIGHT CONTROLS ......................4 7.3.1. Trim System ....................4 7.3.2.
  • Page 126 DA20-C1 Flight Manual Description 7.10. FUEL SYSTEM ....................... 17 7.10.1. Fuel Shut-off Valve ..................19 7.10.2. Tank Drain ..................... 19 7.10.3. Fuel Filter Bowl....................19 7.10.4. Fuel Filter Bowl Drain ..................19 7.10.5. Fuel Dipstick ....................19 7.10.6. Electric Fuel Pump (Priming Pump) Operation..........20 7.11.
  • Page 127 DA20-C1 Flight Manual Description 7.1. INTRODUCTION This Chapter provides description and operation of the airplane and its systems. Refer to Chapter 9, Supplements, for details of optional systems and equipment. 7.2. AIRFRAME 7.2.1. Fuselage The GFRP-fuselage is of semi-monocoque construction. The fire protection cover on the fire wall is made from a special fire retarding ceramic fiber that is covered by a stainless steel plate on the engine side.
  • Page 128 DA20-C1 Flight Manual Description 7.3. FLIGHT CONTROLS The ailerons and elevator are actuated via push rods. The rudder is controlled using control cables. The flaps have three positions, CRUISE, T/O (take-off), LDG (landing), and are electrically operated. The switch is located on the instrument panel. The flap control circuit breaker can be manually ‘tripped’...
  • Page 129 DA20-C1 Flight Manual Description 7.3.3. Flap Position Indicator The current flap position is indicated by three control lights beside the flap operating switch. Wing Flap Position Light Degree CRUISE green 0° yellow 15° yellow 45° When two lights are illuminated at the same time, the flaps are in-between positions.
  • Page 130 DA20-C1 Flight Manual Description 7.3.5. Flight Control Lock A flight control lock, P/N 20-1000-01-00, is provided with each aircraft and should be installed whenever the aircraft is parked. See Figure 7.1, Installation and Removal of the Control Stick. NOTE Failure to install the flight control lock whenever the aircraft is parked may result in control system damage, due to gusts or turbulence.
  • Page 131 DA20-C1 Flight Manual Description 7.4. INSTRUMENT PANEL (See Figure 7.2) Item Description Item Description Item Description Item Description Vacuum Gauge Vertical Speed Ind. Throttle Lever Fuel Quantity Ind. Clock (optional) Fuel Mixture Lever EGT Indicator Magnetic Compass Air Vent Lever Friction Knob...
  • Page 132 DA20-C1 Flight Manual Description 7.4.1. Flight Instruments The flight instruments are installed on the pilot's side of the instrument panel. 7.4.2. Cabin Heat The cabin heat and defrost system, directs ram air through the exhaust heat shroud into the cabin heat valve. The warm air is then directed to the window defrosting vents and to the cabin floor as selected by the Floor/Defrost lever.
  • Page 133 DA20-C1 Flight Manual Description 7.5. LANDING GEAR SYSTEM The landing gear system consists of the two main landing gear wheels mounted to aluminum spring struts and a 60° castering nose wheel. The suspension of the nose wheel is provided by an elastomer spring.
  • Page 134 DA20-C1 Flight Manual Description Figure 7.3. Brake System Schematic Diagram Doc # DA202-C1 April 16, 2009 Page 7 - 10 Revision 24...
  • Page 135 DA20-C1 Flight Manual Description 7.6. SEATS AND SAFETY BELTS The seats are removable to facilitate the maintenance and inspection of the underlying controls. Covers on the control sticks prevent loose objects from entering the control area. The seats have removable cushions.
  • Page 136 DA20-C1 Flight Manual Description 7.8. CANOPY CAUTION BEFORE STARTING THE ENGINE, THE CANOPY MUST BE CLOSED AND LATCHED. THE RED HANDLES MUST BE MOVED FULLY FORWARD. AFTER STARTING THE ENGINE THE CANOPY MUST BE CLOSED AND LATCHED AND STAY CLOSED AND LATCHED UNTIL THE ENGINE IS SHUT DOWN.
  • Page 137 DA20-C1 Flight Manual Description Figure 7.4. Canopy Doc # DA202-C1 April 06, 2010 Page 7 - 13 Revision 25...
  • Page 138 The DA20-C1 may be equipped with an optional altitude compensating fuel pump. A placard on the instrument panel indicates if this system is installed. With this system it is not necessary to manually lean the mixture with altitude.
  • Page 139 DA20-C1 Flight Manual Description 7.9.3. Mixture Control A. Cruise The mixture control allows leaning of the fuel mixture to maximize fuel economy during cruise conditions. Teledyne Continental Motors specifies that above 75% of maximum rated power, the mixture must be set at FULL RICH. It should be noted that even with the throttle set at the full power position, actual power may be less than 75% of maximum rated power and then leaning is required (reference Section 5.3.2, Cruise...
  • Page 140 DA20-C1 Flight Manual Description 7.9.5. Lubricating CAUTION NEVER OPERATE THE ENGINE WITH THE OIL FILLER CAP REMOVED. OBSERVE NORMAL PROCEDURES LIMITATIONS WHILE RUNNING ENGINE. The engine has high pressure wet sump lubrication. The oil is pumped by a mechanical, engine driven pump.
  • Page 141 Fuel pressure is measured at the fuel distribution manifold and displayed on the fuel pressure indicator, which is calibrated in PSI. Some DA20-C1 aircraft also have a fuel vapor separator in the distribution manifold. These aircraft have a second vapor return line from the distribution manifold to the firewall.
  • Page 142 DA20-C1 Flight Manual Description Figure 7.6. Fuel System Schematic Diagram Doc # DA202-C1 April 06, 2010 Page 7 - 18 Revision 25...
  • Page 143 THE FUEL SHUT-OFF VALVE SHOULD ONLY BE CLOSED FOR EMERGENCIES OR FUEL SYSTEM MAINTENANCE. There are two different versions of fuel shut-off valves in the DA20-C1. Version 1 The fuel shut-off valve is located on the cabin side of the firewall and is controlled by a handle on the right side center pedestal.
  • Page 144 Several readings should be taken to confirm accuracy. 7.10.6. Electric Fuel Pump (Priming Pump) Operation The DA20-C1 is equipped with a DUKES constant flow, vane type, two speed, and electric fuel pump. This pump emits an audible whine when it is switched on.
  • Page 145 DA20-C1 Flight Manual Description 7.11. ELECTRICAL SYSTEM Simplified Schematic (see Figure 7.7) 7.11.1. Power Supply A 12 V battery is connected to the master bus via the battery circuit breaker (50 Amps). The 40 amp. generator is attached to the engine near the propeller hub. The generator feeds the main bus via the generator circuit breaker (50 Amps).
  • Page 146 DA20-C1 Flight Manual Description 7.11.3. Electrical Powered Equipment The individual consumers (e.g. Radio, Fuel Pump, Position Lights, etc.) are connected in series with their respective circuit breakers. See Figure 7.2 for an illustration of the instrument panel. 7.11.4. Voltmeter The voltmeter indicates the status of the electrical bus. It consists of a dial that is marked numerically from 8 - 16 volts in divisions of 2.
  • Page 147 Description 7.11.8. Internal Lighting The internal lighting of the DA20-C1 is provided by a lighting module located aft of the Pilot’s head and on the centerline of the aircraft. Included in this module are two panel illumination lights and one map light. The switches for the lights are located on the instrument panel. There is a dimming control located on the left side of the instrument panel for adjusting the intensity of the lighting.
  • Page 148 DA20-C1 Flight Manual Description 7.12. PITOT AND STATIC PRESSURE SYSTEMS The pitot pressure is measured on the leading edge of a calibrated probe below the left wing. The static pressure is measured by the same probe. For protection against water and humidity, water sumps are installed within the line.
  • Page 149 DA20-C1 Flight Manual Handling CHAPTER 8 HANDLING, PREVENTIVE AND CORRECTIVE MAINTENANCE 8.1. INTRODUCTION....................... 2 8.2. AIRPLANE INSPECTION PERIOD................... 2 8.3. AIRPLANE ALTERATIONS OR REPAIRS ............... 2 8.4. GROUND HANDLING / ROAD TRANSPORT ..............3 8.4.1. Ground Handling ..................... 3 8.4.2.
  • Page 150 It is essential that the responsible airworthiness authority be contacted prior to any alterations on the airplane to ensure that the airworthiness of the airplane is not affected. For repairs and painting refer to the applicable Maintenance Manual Doc. No. DA20-C1. Doc # DA202-C1...
  • Page 151 DA20-C1 Flight Manual Handling 8.4. GROUND HANDLING / ROAD TRANSPORT 8.4.1. Ground Handling A. Towing Forward The airplane is most easily and safely maneuvered by hand with the tow-bar attached to the nose wheel. See Figure 8.1 for installation of tow bar.
  • Page 152 DA20-C1 Flight Manual Handling B. Moving Backward By following a simple procedure it is very easy to move the airplane backwards. CAUTION Do not push or lift on Spinner! CAUTION Do not push on control surfaces! Push down with one hand on the aft section of the fuselage near the vertical stabilizer, to lift the nose wheel.
  • Page 153 DA20-C1 Flight Manual Handling 8.4.3. Mooring The tail skid of the airplane has a tie down hole which can be used to moor airplane. Tie-down rings are also installed near the midpoint on each wing for tie-down mooring ropes. See Figure 8.2.
  • Page 154 DA20-C1 Flight Manual Handling 8.4.4. Jacking The DA20-C1 can be jacked at the two jack points located on the lower side of the fuselage's root ribs and at the tail fin. See Figure 8.3. Figure 8.3. Jacking Point Location Doc # DA202-C1...
  • Page 155 DA20-C1 Flight Manual Handling 8.4.5. Road Transport When transporting the airplane on the road, it is recommended that you use an open trailer. All airplane components must be stored on a cushioned surface and secured to avoid any movement during transport.
  • Page 156 BONDING SURFACES IF THE AIRCRAFT WERE EVER IN NEED OF STRUCTURAL REPAIR. To achieve the best flight characteristics for the DA20-C1, a clean external surface is most important. For this reason it is highly recommended that the airplane, especially the leading edge of the wings are kept clean at all times.
  • Page 157 DA20-C1 Flight Manual Handling 8.5.3. Propeller Refer to Sensenich Propeller, W69EK7-63, W69EK7-63G and W69EK-63 Instruction Manual. 8.5.4. Engine See Operator's Manual for the Continental IO 240B aircraft engine Form # X30620. 8.5.5. Interior Surfaces, Seats and Carpets The interior should be cleaned using a vacuum cleaner. All loose items (pens, bags etc.) should be properly stored and secured.
  • Page 158 DA20-C1 Flight Manual Handling INTENTIONALLY LEFT BLANK Doc # DA202-C1 April 06, 2010 Page 8 - 10 Revision 25...
  • Page 159 DA20-C1 Flight Manual Supplements CHAPTER 9 SUPPLEMENTS 9.1. GENERAL ........................9-1 9.2. INDEX OF SUPPLEMENTS ..................9-2 Doc # DA202-C1 April 06, 2010 Page 9 - 1 Revision 25...

  • Page 160: Table Of Contents

    DA20-C1 Flight Manual Supplements 9.1. GENERAL This Chapter contains information regarding optional equipment which may be installed in your airplane. Individual supplements address each optional equipment installation. It is only necessary to maintain those supplements which pertain to your specific airplane’s configuration.

  • Page 161: External Power Operation

    DA20-C1 Flight Manual Supplement 1 CHAPTER 9 SUPPLEMENT 1 EXTERNAL POWER OPERATION GENERAL ........................S1-2 OPERATING LIMITATIONS ..................S1-4 EMERGENCY PROCEDURES................... S1-5 NORMAL PROCEDURES ..................S1-5 PERFORMANCE ...................... S1-10 WEIGHT AND BALANCE ..................S1-10 Doc # DA202-C1 April 16, 2009...
  • Page 162 Supplement 1 GENERAL This supplement addresses the operating procedure for a DA20-C1 aircraft equipped with an optional External Power Unit (EPU). The EPU receptacle and related circuits provide for the connection of an external power source for various ground operations, e.g. maintenance, battery charging, starting.
  • Page 163 DA20-C1 Flight Manual Supplement 1 Battery Breaker EPU Switch Battery Switch CANOPY Reverse Polarity Diode EPU Relay Current Limiter EPU Receptacle EPU Annunciator Reverse Current Diode Circuit Breaker EPU Plug Battery Relay *Installed on S/N C0001 up to C0148 Battery and C0150 Only Figure 1.2...
  • Page 164 DA20-C1 Flight Manual Supplement 1 OPERATING LIMITATIONS 2.1. Voltage supplied to the EPU receptacle should be 12-14 volts nominal. 2.15 . PLACARDS On the lower left side of the instrument panel above the switches. On the right side of the aircraft above the EPU receptacle.
  • Page 165 DA20-C1 Flight Manual Supplement 1 EMERGENCY PROCEDURES 3.3.4. Fire A. Engine Fire during Engine-Start-Up on the Ground (EPU power connected). Fuel Shut-off Valve CLOSED Cabin Heat CLOSED Mixture IDLE CUTOFF Throttle FULL GEN/BAT Master Switch Ignition Switch EPU Switch Evacuate Airplane immediately NORMAL PROCEDURES 4.1.
  • Page 166 DA20-C1 Flight Manual Supplement 1 4.4. Normal Operation Checklist In addition to those items contained in Section 4, Normal Operating Procedures, Preflight Inspection, check the following items if this supplement is applicable to the aircraft you are operating: A. In-Cabin Check...
  • Page 167 DA20-C1 Flight Manual Supplement 1 Starting Engine The Starting Engine checklist from Section 4.4.3 is repeated in this section and includes the steps for starting the engine with an external power source connected. 4.4.3. Starting Engine A. Starting Engine Cold...
  • Page 168 DA20-C1 Flight Manual Supplement 1 Throttle FULL for prime (prime for 3 seconds minimum before starting) Throttle Full IDLE to 1/4 inch OPEN as required Ignition Switch START, hold until engine starts or for 10 seconds maximum (if engine does not start, release ignition key,...
  • Page 169 DA20-C1 Flight Manual Supplement 1 B. Starting Engine Warm Throttle IDLE Mixture FULL RICH Toe Brakes hold Propeller Area clear WARNING ENSURE THAT PROPELLER AREA IS CLEAR! CAUTION DO NOT ENGAGE STARTER IF THE PROPELLER IS MOVING. SERIOUS DAMAGE CAN RESULT.
  • Page 170 DA20-C1 Flight Manual Supplement 1 CAUTION IF OIL PRESSURE IS BELOW 10 PSI, SHUT DOWN ENGINE IMMEDIATELY (MAXIMUM 30 SECONDS DELAY). NOTE Oil Pressure may advance above the green arc until Oil Temp. reaches normal operating temperatures. Regulate warm up RPM to maintain pressure below 100 psi limit.

  • Page 171: Description Of The Airplane And Its Systems

    DA20-C1 Flight Manual Supplement 2 CHAPTER 9 SUPPLEMENT 2 WINTERIZATION KIT GENERAL ........................S2-2 OPERATING LIMITATIONS ..................S2-2 EMERGENCY PROCEDURES................... S2-3 NORMAL PROCEDURES ..................S2-3 PERFORMANCE ......................S2-3 WEIGHT AND BALANCE ................... S2-3 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS ......... S2-4 HANDLING, PREVENTIVE AND CORRECTIVE MAINTENANCE......
  • Page 172 DA20-C1 Flight Manual Supplement 2 GENERAL The Winterization Kit consists of cowling inlet and outlet baffles. The inlet baffles are attached to the upper cowling with two winged 1/4-turn fasteners. The outlet baffles are attached to the lower cowling with screws.
  • Page 173 DA20-C1 Flight Manual Supplement 2 EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when the Winterization Kit is installed. NORMAL PROCEDURES 4.4.1. Preflight Inspection: [Insert after Item 7 (c) of the Walk-around inspection (refer to section 4.4.1 of the Airplane Flight...
  • Page 174 DA20-C1 Flight Manual Supplement 2 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS The Winterization Kit consists of: • left and right baffles installed in the forward cowling inlets, • left and right baffles installed in the aft outlet opening of the lower cowling, and •...

  • Page 175: Recognition Lights

    DA20-C1 Flight Manual Supplement 3 CHAPTER 9 SUPPLEMENT 3 RECOGNITION LIGHTS GENERAL ........................S3-2 OPERATING LIMITATIONS ..................S3-2 EMERGENCY PROCEDURES................... S3-2 NORMAL PROCEDURES ..................S3-2 PERFORMANCE ......................S3-2 WEIGHT AND BALANCE ................... S3-2 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS ......... S3-3 HANDLING, PREVENTIVE AND CORRECTIVE MAINTENANCE......
  • Page 176 DA20-C1 Flight Manual Supplement 3 GENERAL The installation is defined by Service Bulletin DAC1-33-01. OPERATING LIMITATIONS 2.15. PLACARDS On the instrument panel above the individual circuit breakers Figure 1. EMERGENCY PROCEDURES There are no changes to the airplane emergency procedures when the Recognition Lights are installed.

  • Page 177: Doc # Da202-C1 April 16, 2009 Page 0

    DA20-C1 Flight Manual Supplement 3 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS The Recognition Light System consists of 3, 35 watt lamps located in the left wing and the landing light. The lamps are aimed specifically to increase the aircraft's visibility on final approach and head on.
  • Page 178 DA20-C1 Flight Manual Supplement 3 HANDLING, PREVENTATIVE AND CORRECTIVE MAINTENANCE Service or replacement of bulbs shall be performed according to chapter 33-00 of your Diamond Aircraft Maintenance Manual (Document number DA201-C1). Doc # DA202-C1 April 16, 2009 Page S3 - 4...

  • Page 179: Doc # Da202-C1 Revision

    DA20-C1 Flight Manual Supplement 4 CHAPTER 9 SUPPLEMENT 4 GROSS WEIGHT INCREASE (800 kg) GENERAL ........................S4-2 OPERATING LIMITATIONS ..................S4-2 EMERGENCY PROCEDURES................... S4-5 NORMAL PROCEDURES ..................S4-6 PERFORMANCE ......................S4-6 WEIGHT AND BALANCE ..................S4-14 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS ........S4-16 HANDLING, PREVENTIVE AND CORRECTIVE MAINTENANCE......
  • Page 180 Supplement 4 GENERAL This supplement addresses the effects on the DA20-C1 of an increase in the gross weight from 750 kg (1653 lbs) to 800 kg (1764 lbs) and is applicable only to aircraft with the Sensenich propeller. This increase of 50 kg (110 lbs) imposes no significant change to the control and stability of the aircraft.
  • Page 181 DA20-C1 Flight Manual Supplement 4 2.8. CENTER OF GRAVITY Points Gross Weight Arm (aft of datum) (lbs) (kgs) (in) 1653 7.95 .202 1764 8.07 .205 1764 12.16 .309 1653 12.48 .317 WARNING EXCEEDING CENTER GRAVITY LIMITATIONS REDUCES THE MANOEUVRABILITY AND STABILITY OF THE AIRPLANE.
  • Page 182 DA20-C1 Flight Manual Supplement 4 2.9. APPROVED MANEUVERS This airplane is certified in the UTILITY Category in accordance with Canadian Airworthiness Manual Chapter 523-VLA. Permissible Utility Category Maneuvers: All normal flight maneuvers The following maneuvers in which the angle of bank is not more than 60°:...
  • Page 183 DA20-C1 Flight Manual Supplement 4 EMERGENCY PROCEDURES 3.2. AIRSPEEDS DURING EMERGENCY PROCEDURES AT 800 kg. KIAS Engine failure after take-off with flaps in T/O position Maneuvering Speed Airspeed for best glide angle Maximum Gross Weight Wing Flaps in CRUISE position...
  • Page 184 DA20-C1 Flight Manual Supplement 4 NORMAL PROCEDURES 4.2. AIRSPEEDS FOR NORMAL FLIGHT OPERATION LANDING KIAS Approach speed for normal landing. Wing Flaps LDG PERFORMANCE 5.3. PERFORMANCE TABLE AND DIAGRAMS 5.3.1. Airspeed System Calibration Assumes zero indicator error Flaps Cruise KIAS...
  • Page 185 DA20-C1 Flight Manual Supplement 4 5.3.3. Stall Speeds Configuration: Idle, most forward center of gravity, max. weight of 800 kg (this is the most adverse configuration) Stall speeds in kts Most Forward Center of Gravity Angle of Bank Flap 0°...
  • Page 186 DA20-C1 Flight Manual Supplement 4 SENSENICH PROPELLER W69EK7-63, W69EK7-63G and W69EK-63 Figure 5.5. Take-off Distance Doc # DA202-C1 April 16, 2009 Page S4 - 8 Revision 24 DOT Approved...
  • Page 187 DA20-C1 Flight Manual Supplement 4 SENSENICH PROPELLER W69EK7-63, W69EK7-63G and W69EK-63 Max. Cruising Altitude (in standard conditions): 13120 ft (4000 m) Best Rate-of-Climb Speed with Wing Flaps CRUISE 75 KIAS Example: Pressure Altitude: 2000 ft OAT: 65º F Weight :...
  • Page 188 DA20-C1 Flight Manual Supplement 4 SENSENICH PROPELLER W69EK7-63, W69EK7-63G and W69EK-63 Best Rate-of-Climb Speed with Wing Flaps T/O 68 KIAS Example: Pressure Altitude: 2000 ft OAT: 65º F Weight : 1764 lbs Result: Climb performance: 744 ft/min Figure 5.7. Climb Performance / Take off...
  • Page 189 DA20-C1 Flight Manual Supplement 4 SENSENICH PROPELLER W69EK7-63, W69EK7-63G and W69EK-63 Diagram for true airspeed (TAS) calculation at selected power level. Example: Pressure altitude: 6000 ft. Temperature: 70º F Power setting: Result: True airspeed (TAS): 121kts Figure 5.8. Cruising Speed (True Airspeed)
  • Page 190 DA20-C1 Flight Manual Supplement 4 SENSENICH PROPELLER W69EK7-63, W69EK7-63G and W69EK-63 Conditions: Speed = 52 KIAS Wing Flaps in Landing Position (LDG) max take-off power Example: Pressure altitude: 2000 ft Outside temperature: 70ºF Result: Climb performance during balked landing: 374 ft/min Figure 5.10.
  • Page 191 DA20-C1 Flight Manual Supplement 4 5.3.11. Landing Distance Conditions: - Throttle: Idle - Maximum T/O Weight - Approach Speed 55 KIAS - Level Runway, paved - Wing Flaps in Landing position (LDG) - Standard Setting, MSL Landing distance over a 50 ft (15 m) obstacle: approx.
  • Page 192 DA20-C1 Flight Manual Supplement 4 WEIGHT AND BALANCE Model: DA20-C1 Serial Number Registration Data with reference to the Type Certificate Data Sheet and the Flight Manual Reference Datum: Leading edge of wing at root rib. Horizontal reference line: Wedge 1000:55.84, 2000mm (78.7 in) aft of the step in the fuselage at the canopy...
  • Page 193 DA20-C1 Flight Manual Supplement 4 DA 20 (Example) Your DA 20 Weight [lbs] Moment Weight [lbs] Moment Calculation of the Load Limits [in.lbs] [in.lbs] (Weight [kg]) ([kgm]) (Weight [kg]) ([kgm]) 1. Empty Weight (use the data for your 1153 12562...
  • Page 194 DA20-C1 Flight Manual Supplement 4 See example calculation of loading condition Figure 6.6. Change in center of gravity is due to fuel consumption Figure 6.7. Permissible Center of Gravity Range and Permissible Flight-Weight-Moment DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS The gross weight increase to 800 kg.

  • Page 195: S-Tec Autopilot

    DA20-C1 Flight Manual Supplement 5 CHAPTER 9 SUPPLEMENT 5 S-Tec Autopilot GENERAL ........................S5-2 OPERATING LIMITATIONS ..................S5-2 EMERGENCY PROCEDURES................... S5-3 NORMAL PROCEDURES ..................S5-4 PERFORMANCE ......................S5-7 WEIGHT AND BALANCE ................... S5-7 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS ......... S5-7 HANDLING, PREVENTATIVE AND CORRECTIVE MAINTENANCE ......
  • Page 196 DA20-C1 Flight Manual Supplement 5 GENERAL This supplement addresses the optional installation of an S-TEC System 30 autopilot (Mod No. 30). Only the portions of the flight manual affected by this installation are included in this supplement. OPERATING LIMITATIONS NOTE Refer to all of the Operating Limitations with the following inserted into the appropriate place.
  • Page 197 DA20-C1 Flight Manual Supplement 5 EMERGENCY PROCEDURES 3.1. Autopilot Malfunction CAUTION IN THE EVENT OF AN AUTOPILOT MALFUNCTION, OR ANY TIME THE AUTOPILOT IS NOT PERFORMING AS EXPECTED OR COMMANDED, DO NOT ATTEMPT TO IDENTIFY THE SYSTEM PROBLEM. IMMEDIATELY REGAIN CONTROL OF THE AIRCRAFT BY OVERPOWERING THE AUTOPILOT AS NECESSARY AND THEN DISCONNECT THE AUTOPILOT.
  • Page 198 DA20-C1 Flight Manual Supplement 5 NORMAL OPERATING PROCEDURES NOTE Refer to all of the Normal Operating Procedures with the following inserted into the appropriate places. 4.4. NORMAL OPERATION CHECKLIST 4.4.1. Preflight Inspection B. Walk Around Check and Visual Inspection Left Wing...
  • Page 199 DA20-C1 Flight Manual Supplement 5 4.4.4. Before Taxiing AP Master Switch ON (if desired) Autopilot Mandatory Pre-flight Test COMPLETE Autopilot Mandatory Pre-flight Test A. Observe all lights and annunciators illuminate. B. Observe the following light sequence of the trim indicators: (Sequence requires 9 seconds).
  • Page 200 DA20-C1 Flight Manual Supplement 5 4.4.6. Before Take-off 22a. Autopilot Disengaged (AP DISC) 4.4.9. Cruise Insert after Engine Gauges check Autopilot Operation (if desired) NOTE A guide containing useful operating information is available from S-TEC Corporation, One S-TEC Way, Municipal Airport, Mineral Wells, Texas, 76067-9236, USA.
  • Page 201 DA20-C1 Flight Manual Supplement 5 PERFORMANCE There is no change in airplane performance with the autopilot system installed. WEIGHT AND BALANCE The installation adds 11.1 lbs (5.0 kg) of weight at a –24.6 in (–.62 m) arm. DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS 7.15.
  • Page 202 DA20-C1 Flight Manual Supplement 5 The following list describes the various features illustrated in Figure 1. Turn Coordinator – Provides basic flight information, autopilot mode switching and annunciation. Mode Annunciation window – displays mode in use. Green Ready (RDY) Light – Illuminates when autopilot is ready for engagement.
  • Page 203 DA20-C1 Flight Manual Supplement 5 Figure 1 Doc # DA202-C1 April 16, 2009 Page S5 - 9 Revision 24 DOT Approved...
  • Page 204 DA20-C1 Flight Manual Supplement 5 HANDLING, PREVENTATIVE AND CORRECTIVE MAINTENANCE There is no change in handling, preventative or corrective maintenance with the installation of S-TEC System 30 autopilot (Mod No. 30). Doc # DA202-C1 April 16, 2009 Page S5 - 10...
  • Page 205 DA20-C1 Flight Manual Supplement 6 CHAPTER 9 SUPPLEMENT 6 VM1000 Monitoring System GENERAL ........................S6-2 OPERATING LIMITATIONS ..................S6-2 EMERGENCY PROCEDURES................... S6-2 NORMAL PROCEDURES ..................S6-4 PERFORMANCE ......................S6-4 WEIGHT AND BALANCE ................... S6-4 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS ......... S6-4 HANDLING, PREVENTATIVE AND CORRECTIVE MAINTENANCE ......
  • Page 206 DA20-C1 Flight Manual Supplement 6 GENERAL This supplement addresses the optional installation of the Vision Microsystems VM1000 engine instrument package (Mod 31). Only portions of the flight manual affected by the installation are included in this supplement. OPERATING LIMITATIONS 2.1.
  • Page 207 DA20-C1 Flight Manual Supplement 6 NOTE There is 30 minutes of battery power at a discharge load of 20 amperes when the battery is fully charged and properly maintained. The amp meter monitors generator load which will indicate low amps when the generator is off or has malfunctioned.
  • Page 208 VM 1000 System General The following provides a general description for use of the VM 1000 as it pertains to the operation of the DA20-C1. Features such as “Autotrack” “Lean Mode” and “EC 100” are described in detail in the VISON MICRO SYSTEM owners manual P/N 5010002. Copies of the manual can be obtained through.
  • Page 209 7.6. Fuel Computer System The fuel computer portion of the VM 1000 is not operational on the DA20-C1 7.7. Electrical System Voltage is displayed both analog and digitally. Full color range marks provide a quick reference for fast analysis of voltage levels.
  • Page 210 DA20-C1 Flight Manual Supplement 6 7.8. Fuel Quantity Fuel quantity is displayed on a separate indicator but is controlled by the VM 1000 Data Processing Unit and EC 100 remote display. Display resolution is 1 US gallon. When 5 US gallons remain in the main tank the fuel system display is flashed an audible tone is heard and the EC 100 displays the warning.
  • Page 211 Supplement 6 HANDLING, PREVENTATIVE AND CORRECTIVE MAINTENANCE Service and maintenance of the VM 1000 / EC 100 system shall be performed according to the Diamond Aircraft Maintenance Manual (Document number DA201-C1). Doc # DA202-C1 April 16, 2009 Page S6 - 7...
  • Page 212 DA20-C1 Flight Manual Supplement 6 INTENTIONALLY LEFT BLANK Doc # DA202-C1 April 16, 2009 Page S6 - 8 Revision 24 DOT Approved...

  • Page 213: Auxiliary Fuel System

    DA20-C1 Flight Manual Supplement 7 CHAPTER 9 SUPPLEMENT 7 Auxiliary Fuel System GENERAL S7-2 OPERATING LIMITATIONS S7-2 EMERGENCY PROCEDURES S7-2 NORMAL PROCEDURES S7-3 PERFORMANCE S7-4 WEIGHT AND BALANCE S7-4 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS S7-5 HANDLING, PREVENTATIVE AND CORRECTIVE MAINTENANCE...
  • Page 214 60). The optional auxiliary fuel system installation provides extended range operation by increasing the total fuel capacity of the DA20-C1 by 5 US gallons. Only portions of the flight manual affected by the installation are included in this supplement. OPERATING LIMITATIONS...
  • Page 215 DA20-C1 Flight Manual Supplement 7 NORMAL PROCEDURES NOTE Refer to all of the Normal Operating Procedures with the following inserted into the appropriate places. CAUTION THE AIRCRAFT MUST BE GROUNDED PRIOR TO AND DURING FUELING. USE THE GROUND STUD, LOCATED UNDER THE TRAILING EDGE OF THE LEFT WING.
  • Page 216 DA20-C1 Flight Manual Supplement 7 4.4.18. Auxiliary Tank Fuel Transfer NOTE It is recommended to transfer fuel in level cruise flight. Main fuel tank. less than 3/4 full Auxiliary fuel tank indicator Full Fuel Transfer switch Transfer time 10 minutes...
  • Page 217 DA20-C1 Flight Manual Supplement 7 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS The auxiliary fuel tank is located in the fuselage, aft of the passenger compartment and underneath the baggage compartment floor, on the right hand side of the main fuel tank.
  • Page 218 DA20-C1 Flight Manual Supplement 7 HANDLING, PREVENTATIVE AND CORRECTIVE MAINTENANCE Service and maintenance of the Auxiliary Fuel Tank system shall be performed according to the Diamond Aircraft Maintenance Manual (Document number DA201-C1). Doc # DA202-C1 April 16, 2009 Page S7 - 6...

  • Page 219: Stick Mounted Trim Switches

    DA20-C1 Flight Manual Supplement 8 CHAPTER 9 SUPPLEMENT 8 Stick Mounted Trim Switches GENERAL S8-2 OPERATING LIMITATIONS S8-2 EMERGENCY PROCEDURES S8-2 NORMAL PROCEDURES S8-2 PERFORMANCE S8-2 WEIGHT AND BALANCE S8-2 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS S8-3 HANDLING, PREVENTATIVE AND CORRECTIVE MAINTENANCE...
  • Page 220 DA20-C1 Flight Manual Supplement 8 GENERAL This supplement addresses the optional installation of a stick mounted trim switch system. Only portions of the flight manual affected by the installation are included in this supplement. OPERATING LIMITATIONS There is no change in to the operating limitations with the stick mounted trim switch installed.
  • Page 221 Figure 1. Control Stick Grip (Left Hand Shown) HANDLING, PREVENTATIVE AND CORRECTIVE MAINTENANCE Service and maintenance of the Stick Mounted Trim Switches shall be performed according to the Diamond Aircraft Maintenance Manual (Document number DA201-C1). Doc # DA202-C1 April 16, 2009...
  • Page 222 DA20-C1 Flight Manual Supplement 8 INTENTIONALLY LEFT BLANK Doc # DA202-C1 April 16, 2009 Page S8 - 4 Revision 24 DOT Approved...

  • Page 223: Us Gallon Fuel Tank

    DA20-C1 Flight Manual Supplement 9 CHAPTER 9 SUPPLEMENT 9 20 US Gallon Fuel Tank GENERAL S9-2 OPERATING LIMITATIONS S9-2 EMERGENCY PROCEDURES S9-2 NORMAL PROCEDURES S9-2 PERFORMANCE S9-2 WEIGHT AND BALANCE S9-2 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS S9-3 HANDLING, PREVENTATIVE AND CORRECTIVE MAINTENANCE...
  • Page 224 DA20-C1 Flight Manual Supplement 9 GENERAL This supplement addresses the optional installation of a smaller 20.5 US gallon fuel tank in place of the standard 24.5 US gallon fuel tank. Only portions of the flight manual affected by the installation are included in this supplement.
  • Page 225 DA20-C1 Flight Manual Supplement 9 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS 7.10. Fuel System A 20.5 US Gal total / 20.5 US Gal usable fuel tank replaces the standard 24.5 US Gal total / 24.0 US Gal usable fuel tank. There are no other changes to the fuel system.
  • Page 226 DA20-C1 Flight Manual Supplement 9 INTENTIONALLY LEFT BLANK Doc # DA202-C1 April 16, 2009 Page S9 - 4 Revision 24 DOT Approved...

  • Page 227: Reversed Instrument Panel

    DA20-C1 Flight Manual Supplement 10 CHAPTER 9 SUPPLEMENT 10 Reversed Instrument Panel GENERAL S10-2 OPERATING LIMITATIONS S10-2 EMERGENCY PROCEDURES S10-2 NORMAL PROCEDURES S10-2 PERFORMANCE S10-2 WEIGHT AND BALANCE S10-2 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS S10-3 HANDLING, PREVENTATIVE AND CORRECTIVE MAINTENANCE...
  • Page 228 DA20-C1 Flight Manual Supplement 10 GENERAL This supplement addresses the optional installation of the navigation and powerplant instruments in a reversed configuration. The navigational instruments are located on the right hand side of the instrument panel. The powerplant instruments are located on the left hand side of the panel.
  • Page 229 DA20-C1 Flight Manual Supplement 10 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS 7.4. Instrument Panel Description Description Description Description Vertical Speed Ind. Fuel Quantity Ind. Clock/OAT EGT Indicator Magnetic Compass Air Vent CHT Indicator Trim Position Switch Panel Circuit Breakers...
  • Page 230 DA20-C1 Flight Manual Supplement 10 INTENTIONALLY LEFT BLANK Doc # DA202-C1 April 16, 2009 Page S10 - 4 Revision 24 DOT Approved...

  • Page 231: Pitot Heat Operation

    DA20-C1 Flight Manual Supplement 11 CHAPTER 9 SUPPLEMENT 11 Pitot Heat Operation GENERAL S11-2 OPERATING LIMITATIONS S11-3 EMERGENCY PROCEDURES S11-4 NORMAL PROCEDURES S11-4 PERFORMANCE S11-5 WEIGHT AND BALANCE S11-6 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS S11-6 HANDLING, PREVENTATIVE AND CORRECTIVE MAINTENANCE...
  • Page 232 DA20-C1 Flight Manual Supplement 11 GENERAL Ice build up on the Pitot Static Probe can cause the airspeed, altimeter and vertical speed indicators to display incorrect data. The “Pitot Heat” system provides protection against ice build up on the Pitot Static Probe.
  • Page 233 DA20-C1 Flight Manual Supplement 11 OPERATING LIMITATIONS 2.15. PLACARDS On the lower left side of the instrument panel above the switches. Doc # DA202-C1 April 06, 2010 Page S11 - 3 Revision 25 DOT Approved...
  • Page 234 DA20-C1 Flight Manual Supplement 11 EMERGENCY PROCEDURES Icing: Unintentional Flight into Icing Area Checklist has been repeated in this section to include operations with pitot heat system installed. 3.3.5. Icing Unintentional Flight into Icing Area Pitot Heat Leave icing area (through change of altitude or change of flight direction to reach area with higher outside air temp.).
  • Page 235 DA20-C1 Flight Manual Supplement 11 4.4.4. Normal Operation Checklist Before Taxiing: The Before Taxiing Checklist has been repeated in this section to include operations with “Pitot Heat” system installed. Before Taxiing Avionics Master Switch Flight Instruments and Avionics Engine Gauges...
  • Page 236 DA20-C1 Flight Manual Supplement 11 WEIGHT AND BALANCE The weight and balance of the aircraft is not affected by operation. DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS 7.12.1. Pitot Heat The “Pitot Heat” system consists of heating elements imbedded in the Pitot Static Probe, a 15 amp circuit breaker, a control relay, thermal limit switches (HIGH and LOW), OFF/ON switch, and a GREEN LED monitor.

  • Page 237: Brazilian Placards And Markings

    DA20-C1 Flight Manual Supplement 12 CHAPTER 9 SUPPLEMENT 12 Brazilian Placards and Markings GENERAL S12-2 OPERATING LIMITATIONS S12-2 EMERGENCY PROCEDURES S12-8 NORMAL PROCEDURES S12-8 PERFORMANCE S12-8 WEIGHT AND BALANCE S12-8 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS S12-8 HANDLING, PREVENTATIVE AND CORRECTIVE MAINTENANCE...
  • Page 238 DA20-C1 Flight Manual Supplement 12 GENERAL This supplement addresses the placards and markings for the Brazilian airplane. Only portions of the flight manual affected by the installation are included in this supplement. OPERATING LIMITATIONS 2.15. Placards On the exterior of the canopy frame on the L/H side (If equipped with outside handle).
  • Page 239 DA20-C1 Flight Manual Supplement 12 On the interior of the canopy frame on the L/H side (If equipped with outside handle). On the interior of the canopy frame on the R/H side (If equipped with outside handle). On the exterior of the canopy frame on the L/H side (If equipped with lock).
  • Page 240 DA20-C1 Flight Manual Supplement 12 On the L/H side of the canopy sill. On the R/H side of the canopy sill. On the R/H upper fuselage behind the canopy, if an ELT is installed. Doc # DA202-C1 April 06, 2010...
  • Page 241 DA20-C1 Flight Manual Supplement 12 Next to the fuel filler cap. Next to the fuel filler cap. On the inside of the oil filler door. On the upper L/H fuselage near the wing trailer edge. Doc # DA202-C1 April 06, 2010...
  • Page 242 DA20-C1 Flight Manual Supplement 12 Under each wing and on the tail skid. On the underside of the fuselage (belly) near the L/H wing trailing edge. On the upper engine cowling behind the propeller spinner. On the L/H side of the baggage compartment.
  • Page 243 DA20-C1 Flight Manual Supplement 12 On the back-rest on the right side. On the right side of the aircraft above the EPU receptacle. On the instrument panel above the GPS. Doc # DA202-C1 April 06, 2010 Page S12 - 7...
  • Page 244 DA20-C1 Flight Manual Supplement 12 EMERGENCY PROCEDURES There is no change in the emergency procedures with the Brazilian placards and markings installed. NORMAL PROCEDURES There is no change in the normal procedures with the Brazilian placards and markings installed. PERFORMANCE There is no change in airplane performance with the Brazilian placards and markings installed.

  • Page 245: Garmin G500 Integrated Display System

    DA20-C1 Flight Manual Supplement 13 CHAPTER 9 SUPPLEMENT 13 GARMIN G500 INTEGRATED DISPLAY SYSTEM GENERAL .....................S13-2 OPERATING LIMITATIONS ................S13-3 EMERGENCY PROCEDURES ..............S13-9 NORMAL OPERATING PROCEDURES .............S13-13 PERFORMANCE..................S13-17 MASS AND BALANCE ................S13-17 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS ......S13-18 AIRPLANE HANDLING, CARE AND MAINTENANCE........S13-23...
  • Page 246 This Supplement to the AFM is provided to acquaint the pilot with the limitations as well as normal, abnormal and emergency operating procedures of the Garmin G500. The limitations presented are pertinent to the operation of the G500 System as installed in the DA20-C1 airplane. Garmin provides a detailed Pilot’s Guide Document Number 190-01102-02, Rev B.
  • Page 247 DA20-C1 Flight Manual Supplement 13 OPERATING LIMITATIONS Cockpit Reference Guide The Garmin G500 Cockpit Reference Guide, Document Number 190-01102-03, Rev B dated June 2009 or later appropriate revision must be immediately available to the flight crew. System Software Requirements The G500 must utilize the following or later TCCA/FAA approved software versions for...
  • Page 248 DA20-C1 Flight Manual Supplement 13 AHRS Operational Area The AHRS used in the G500 is limited in its operational area. Operations are prohibited north of 72 degrees North and south of 70 degrees South latitudes and in the following four regions:...
  • Page 249 DA20-C1 Flight Manual Supplement 13 Placards The placards shown below pertain only to the instrument panel with Garmin G500 Integrated Display and must be installed: Switches on the instrument panel below the GDU 620 display On the flap controller Power setting below the instrument panel...
  • Page 250 DA20-C1 Flight Manual Supplement 13 Limitations on the right upper corner of the instrument panel For aircraft operated in European Aviation Safety Agency (EASA) member countries only. Doc # DA202-C1 April 06, 2010 Page S13 - 6 Revision 25 DOT Approved...
  • Page 251 DA20-C1 Flight Manual Supplement 13 Circuit breaker on the right side of the instrument panel Doc # DA202-C1 April 06, 2010 Page S13 - 7 Revision 25 DOT Approved...
  • Page 252 DA20-C1 Flight Manual Supplement 13 Maneuvering speed on the left side of the instrument panel Trim placard on the upper left corner of the instrument panel Doc # DA202-C1 April 06, 2010 Page S13 - 8 Revision 25 DOT Approved...
  • Page 253 DA20-C1 Flight Manual Supplement 13 EMERGENCY PROCEDURES Emergency Procedures No change. Abnormal Procedures These procedures supersede those presented as markings or placards, or documented in the aircraft’s TCCA/FAA approved AFM as a result of the installation of the G500 PFD/MFD system. All other emergency procedures remain in effect.
  • Page 254 DA20-C1 Flight Manual Supplement 13 Abnormal Indications 3.3.1 Heading Failure A magnetometer failure is indicated by a HDG with a red X over it just to the left of the heading display. If the GDU620 is still receiving valid GPS ground track from the GNS navigator, the heading will be replaced with GPS ground track in magenta.
  • Page 255 DA20-C1 Flight Manual Supplement 13 WARNINGS, CAUTIONS, and Advisories The following tables show the color and significance of the warning, caution, and advisory messages which may appear on the G500 displays. NOTE The G500 cockpit reference guide and the G500 pilot's guide contain detailed descriptions of the annunciator system and all warnings, cautions and advisories.
  • Page 256 DA20-C1 Flight Manual Supplement 13 CAUTION annunciations - Yellow Annunciation Pilot Action Cause AHRS Aligning – Limit aircraft banking as AHRS is aligning. Keep wings level Keep wings level AHRS aligns – OK to taxi. using standby attitude indicator. AHRS will align even if you must bank, but the alignment time may be slightly longer if maneuvering.
  • Page 257 DA20-C1 Flight Manual Supplement 13 NORMAL OPERATING PROCEDURES Detailed operating procedures are described in the Garmin G500 Cockpit Reference Guide, Document No. 190-01102-03, Rev B or later appropriate revision and in the Garmin G500 Pilot’s Guide, Document No. 190-01102-02, Rev B, dated June 2009 or later appropriate revision.
  • Page 258 DA20-C1 Flight Manual Supplement 13 The Jeppesen ChartView electronic charts database contains procedure charts for the coverage area purchased. An own-ship position icon will be displayed on these charts. This database is updated on a 14-day cycle. If not updated within 70 days of the expiration date, ChartView will no longer function.
  • Page 259 DA20-C1 Flight Manual Supplement 13 PFD Soft Keys The soft keys are located along the bottoms of the displays below the soft key labels. The soft key labels shown depend on the soft key level or page being displayed. The soft keys can be used to select the appropriate soft key function.
  • Page 260 DA20-C1 Flight Manual Supplement 13 MFD Knobs The MFD knobs are for navigating and selecting information on the MFD pages. Small (Inner) Knob Selects a specific page within a page group. Pressing the small MFD knob turns the selection cursor ON and OFF.
  • Page 261 DA20-C1 Flight Manual Supplement 13 Course Pointer Auto Slewing The G500 HSI will auto slew, i.e. automatically rotate the GPS course pointer to the desired course defined by each GPS leg. The system will also auto slew the VHFNAV course pointer when the CDl transitions to a LOC setting if an ILS, LOC, LOC BC, LDA, or SDF approach is activated in the GPS/WAAS navigator.
  • Page 262 DA20-C1 Flight Manual Supplement 13 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS Instrument Panel Figure 1 – Instrument Panel Doc # DA202-C1 April 06, 2010 Page S13 - 18 Revision 25 DOT Approved...
  • Page 263 DA20-C1 Flight Manual Supplement 13 Major Instruments and Controls Flap Speeds Engine RPM Master Switch Panel Air Speed Indicator - AVIONICS MASTER Auto Selector - FUEL PUMP Switch NAV/COM GPS - GEN/BAT Switch Altimeter Fuel Prime VHF COM Ignition Switch...
  • Page 264 DA20-C1 Flight Manual Supplement 13 Avionics – General The G500 system consists of: • Garmin Display Unit (GDU) 620 (PFD/MFD) • Garmin data Computer (GDC) 74A [Air Data Computer (ADC)] • Garmin Reference System (GRS) 77 [Attitude and Heading Reference System (AHRS)] •...
  • Page 265 DA20-C1 Flight Manual Supplement 13 GMU 44 Magnetometer The GMU 44 magnetometer senses magnetic field information. Data is sent to the GRS 77 AHRS for processing to determine aircraft magnetic heading. This unit receives power directly from the GRS 77 and communicates with the GRS 77 using an RS-485 digital interface.
  • Page 266 DA20-C1 Flight Manual Supplement 13 Figure 2 – G500 System Overview with Optional and Required Equipment Doc # DA202-C1 April 06, 2010 Page S13 - 22 Revision 25 DOT Approved...
  • Page 267 DA20-C1 Flight Manual Supplement 13 AIRPLANE HANDLING, CARE AND MAINTENANCE No change. Doc # DA202-C1 April 06, 2010 Page S13 - 23 Revision 25 DOT Approved...
  • Page 268 DA20-C1 Flight Manual Supplement 13 Intentionally Left Blank Doc # DA202-C1 April 06, 2010 Page S13 - 24 Revision 25 DOT Approved...

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