DA 20-C1 Flight Manual PREFACE Congratulations on your choice of the DA 20-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.
DA 20-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 December 19, 1997...
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DA 20-C1 Flight Manual LIST OF EFFECTIVE PAGES Chapter Page Date Chapter Page Date October 18, 2002 DOT-appr December 19, 1997 October 18, 2002 DOT-appr March 10, 1999 December 19, 1997 DOT-appr June 21, 1999 September 5, 2006 DOT-appr June 21, 1999...
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DA 20-C1 Flight Manual Chapter Page Date Chapter Page Date August 28, 1998 7-13 March 19, 2004 August 28, 1998 7-14 December 08, 1998 DOT-appr April 23, 2002 7-15 24 June, 2005 March 20, 2001 7-16 24 June, 2005 August 9, 2001...
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DA 20-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...
DA 20-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.
DA 20-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 The pages superseded by the revision must be removed and destroyed.
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DA 20-C1 Flight Manual 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: 1.
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(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 DA 20-C1 KATANA. Any optional equipment installed on request of the customer (COMM, NAV, etc.) is not considered.
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DA 20-C1 Flight Manual General 1.2. CERTIFICATION BASIS The DA 20-C1 has been approved by Transport Canada in accordance with the Canadian Airworthiness Manual (AWM) Chapter 523-VLA., Type Certificate No. A-191. Category of Airworthiness: UTILITY Noise Certification Basis: a) Canadian Airworthiness Manual Chapter 516...
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DA 20-C1 Flight Manual General 1.4. THREE-VIEW-DRAWING OF AIRPLANE SENSENICH PROPELLER W69EK7-63, W69EK7-63G, W69EK-63 DIAMETER 1752 (5'- 9") HOFFMANN PROPELLER HO14HM-175 157 DIAMETER 1750 (5'-9") DIMENSIONS ARE APPROXIMATE - FOR REFERENCE ONLY DIMENSIONS ARE IN mm (FEET - INCHES) Doc # DA202-C1...
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DA 20-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 m...
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DA 20-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.
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DA 20-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, SUPPLIER BRAND (if applicable) TYPE (if applicable) BP Oil Corporation BP Aero Oil...
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DA 20-C1 Flight Manual General Use only the oils specified TCM specification MHS 24 Table 2 Oil Capacity: Maximum : 6.0 US qt (5.68 liters.) Minimum : 4.0 US qt (3.78 liters.) Doc # DA202-C1 December 19, 1997 Page 1 - 7...
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DA 20-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...
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DA 20-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.
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DA 20-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° Celsius (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°...
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DA 20-C1 Flight Manual General 1.11.4. Flight Performance and Flight Planning Demonstrated Crosswind Component: The max. 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.
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DA 20-C1 Flight Manual General 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.
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DA 20-C1 Flight Manual Limitations AIRSPEED LIMITATIONS Speed KIAS Remarks Do not make full or abrupt control movement above this speed. Under certain conditions the Maneuvering Speed. airplane may be overstressed by full control movement. Maximum Flap Extended Speed. Do not exceed this speed with flaps in take-off (T/O) position.
DA 20-C1 Flight Manual Limitations (g) Cylinder Head Temperature Maximum : 460° F (238° C) Minimum : 240 F (115 C) takeoff and descent (h) Fuel Specifications Approved Fuel Grades : AVGAS 100LL or 100 (i) Oil Grades : Reference TCM IO-240-B operator and installation manual (form X30620) or TCM specification MHS-24.
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DA 20-C1 Flight Manual Limitations 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 = Caution Range = Upper Limit Operating Range...
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DA 20-C1 Flight Manual Limitations 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 in the baggage : 44 lbs ( 20 kg) only permissible with...
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DA 20-C1 Flight Manual Limitations Heading 1 inserted for proper page listing 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 Stalls (except whip stalls) Lazy Eight’s...
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DA 20-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:...
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DA 20-C1 Flight Manual Limitations 2.14 FUEL Fuel Capacity Total Fuel Quantity: : 24.5 US gal. ( 93.0 liters) Usable Fuel: : 24.0 US gal. ( 91.0 liters) Unusable Fuel: : 0.5 US gal. ( 2.0 liters) 2.15 PLACARDS The following placards must be installed: 1.
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DA 20-C1 Flight Manual Limitations 9. On the lower left side of instrument panel above the switches. 10. On the instrument panel above the individual circuit breakers Placard information will vary depending on (optional) installed equipment 12. On the upper left corner 11.
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DA 20-C1 Flight Manual Limitations 13. On the exterior of the canopy frame on 14.On the exterior of the canopy frame on the L/H side. And on the interior of the the R/H side. And on the interior of the canopy frame on the R/H side.
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DA 20-C1 Flight Manual Limitations 23. On the L/H side of the canopy sill. 24. On the R/H side of the canopy sill. 26. Next to the fuel filler cap 25. On the R/H upper fuselage behind the canopy, if an ELT is installed.
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DA 20-C1 Flight Manual Limitations 28. On the fuselage underside (belly), near 29. On the underside of the fuselage (belly), the center line between the wings. to the left just forward of the wing trailing edge. 31. On the upper L/H fuselage near the wing 30.
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DA 20-C1 Flight Manual Limitations 37. On the upper engine cowling behind the 38. Around the stall warning hole in the left propeller spinner. wing. 39. Around the co-pilot headset jacks on the 40. Around the pilot headset jacks on the back rest.
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DA 20-C1 Flight Manual Limitations 45a On the engine controls on 45b. 45c. the center console. 46a On the center console on the heating 46b. and parking brake controls. Doc # DA202-C1 August 9, 2001 Page 2–15 Revision 14 DOT Approved...
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DA 20-C1 Flight Manual Limitations 47 On the left side of the instrument 48 On the engine controls for panel near the top. aircraft with center console mounted Fuel Selector. 49 On the instrument panel on Aircraft equipped with supplemental lighting (MOD 32).
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DA 20-C1 Flight Manual Limitations 53. On the Instrument Panel. 54. Adjacent to the flap controller. (T/O) 100 KTS. (LDG) 78 KTS. 55. On the instrument panel if equipped with altitude compensating fuel pump. Doc # DA202-C1 March 19, 2004 Page 2–17...
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DA 20-C1 Flight Manual Limitations 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. Parking the aircraft over a light coloured or reflective surface in conditions of bright sunlight, particularly at high OAT, is not recommended.
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DA 20-C1 Flight Manual Emergency Procedures CHAPTER 3 EMERGENCY PROCEDURES 3.1. INTRODUCTION 3- 2 3.2. AIRSPEEDS DURING EMERGENCY PROCEDURES 3- 2 3.3. EMERGENCY PROCEDURES - CHECKLISTS 3.3.1. Engine Failures (a) Engine Failure during Take-off Run 3- 3 (b) Engine Failure after Take-off...
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DA 20-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.
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DA 20-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 Engine Failure after Take-Off INSUFFICIENT ENGINE POWER...
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DA 20-C1 Flight Manual Emergency Procedures ENGINE INOPERATIVE Perform emergency landing according to paragraph 3.3.3. 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...
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DA 20-C1 Flight Manual Emergency Procedures RESTARTING THE ENGINE WITH PROPELLER WINDMILLING CAUTION Do not engage starter if propeller is windmilling. Engine damage may result. With a Hoffmann propeller installed the propeller will continue to windmill as long as the airspeed is at least 46 KIAS.
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DA 20-C1 Flight Manual Emergency Procedures RESTARTING THE ENGINE WITH PROPELLER AT FULL STOP Airspeed 73 kts. Electrically Powered Equipment GEN/BAT Master Switch Mixture FULL RICH Fuel shut off valve OPEN Fuel Pump Fuel Prime Throttle 3/4 in (2 cm) forward...
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DA 20-C1 Flight Manual Emergency Procedures 3.3.3. Emergency Landing Emergency Landing with Engine off Airspeed (Flaps in T/O position) 58 KIAS Airspeed (Flaps in LDG position) 52 KIAS Airspeed (Flaps CRUISE) 62 KIAS Fuel Shut-off Valve CLOSED Mixture IDLE CUTOFF...
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DA 20-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.
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DA 20-C1 Flight Manual Emergency Procedures 3.3.4. Fire 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 Engine Fire during Flight Fuel Shut-off Valve...
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DA 20-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 ON BAT ½...
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DA 20-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.
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DA 20-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.
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DA 20-C1 Flight Manual Emergency Procedures 3.3.9. Electrical Power Failure a) Total Electrical Power Failure Battery Circuit Breaker If tripped, reset GEN/BAT Master Switch check ON Master Switch OFF if power not restored If Unsuccessful Land at nearest suitable airport b) Generator Failure GEN.
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DA 20-C1 Flight Manual Emergency Procedures II. 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: Refer to paragraph 3.3.9 (b) and the ammeter is indicating to the left of center (discharge): III.
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DA 20-C1 Flight Manual Emergency Procedures 3.3.10. 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: •...
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DA 20-C1 Flight Manual Emergency Procedures 3.3.12 Avionics System Failure Total Avionics Failure: Check Avionics Master Circuit If popped, press and monitor status, If it pops again, Breaker land at nearest suitable airport Check Avionics Master Switch Toggle avionics master switch, if avionics system remains off-line, pull avionics master control circuit breaker.
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DA 20-C1 Flight Manual Emergency Procedures 3.3.13 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.
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DA 20-C1 Flight Manual Emergency Procedures 3.3.14 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.
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DA 20-C1 Flight Manual Normal Operating Procedures CHAPTER 4 NORMAL OPERATING PROCEDURES 4.1. INTRODUCTION 4- 2 4.2. AIRSPEEDS FOR NORMAL FLIGHT OPERATION 4- 2 4.3. STRUCTURAL TEMPERATURE INDICATOR 4- 3 4.4. NORMAL OPERATION CHECKLIST 4- 5 4.4.1. Preflight Inspection I. In-Cabin Check 4- 5 II.
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DA 20-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.
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DA 20-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 (ref. section 2.17). The indicator need only be checked if the OAT exceeds 38° C (100°...
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DA 20-C1 Flight Manual Normal Operating Procedures [INTENTIONALLY LEFT BLANK] Doc # DA202-C1 December 19, 1997 Page 4 - 4 Issue 1 DOT Approved...
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DA 20-C1 Flight Manual Normal Operating Procedures 4.4. NORMAL OPERATION CHECKLIST 4.4.1. Preflight Inspection I. In-Cabin Check 1. Structural Temperature Indicator check that Structural Temperature (if OAT exceeds 38°C (100° F)) does not exceed 55° C (131° F) 2. Airplane Documents check 3.
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DA 20-C1 Flight Manual Normal Operating Procedures Walk Around Check and Visual Inspection Doc # DA202-C1 December 7, 1999 Page 4 - 6 Revision 8 DOTpproved...
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DA 20-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 1.
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DA 20-C1 Flight Manual Normal Operating Procedures 4. Empennage a) Stabilizers and Control Surfaces visual inspection b) Tie down remove c) Fixed Tab on Rudder visual inspection 5. Right Wing a) Entire Wing visual inspection b) Wing Flap including Inspection Panel...
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DA 20-C1 Flight Manual Normal Operating Procedures 4.4.2. Before Starting Engine Preflight Inspection performed Pedals adjust, lock Passenger Briefing performed Safety Belts fasten Parking Brake Flight Controls free Fuel Shut-off Valve OPEN Mixture FULL RICH Throttle IDLE Friction Device of Throttle Quadrant...
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DA 20-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 -4°C (25°F) or less.
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DA 20-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.
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DA 20-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 and 9 are to be performed without delay between steps. Fuel Pump Fuel Prime...
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DA 20-C1 Flight Manual Normal Operating Procedures 4.4.4. Before Taxiing Avionics Master Switch Flight Instruments and Avionics Engine Gauges check check, ensure needle is in the Voltmeter green arc. Increase RPM to achieve or turn OFF non-flight essential electrical consumers...
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DA 20-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...
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DA 20-C1 Flight Manual Normal Operating Procedures 4.4.7. Take-off 1. Fuel Prime check OFF 2. Fuel Pump check ON 3. Mixture check FULL RICH 4. GEN/BAT Master Switch check ON 5. Ignition Switch check BOTH 6. Wing Flaps check T/O 7.
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DA 20-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.
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DA 20-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 300°F for more than 5 minutes. 240°F Min. NOTE To achieve a fast descent:...
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DA 20-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.
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DA 20-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...
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DA 20-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 1000 RPM (eg. stalls, spins, descents, landings, etc.)
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DA 20-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 Figure 5.1: Airspeed System Calibration ..........3 5.3.2. Figure 5.2(a): Cruising Performance .............4 5.3.3. Figure 5.3: Stall Speeds................6 5.3.4.
DA 20-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.
DA 20-C1 Flight Manual PERFORMANCE 5.3. PERFORMANCE TABLE AND DIAGRAMS 5.3.1 Figure 5.1: 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...
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DA 20-C1 Flight Manual PERFORMANCE 5.3.2. Figure 5.2(a): Cruising Performance HOFFMANN PROPELLER HO-14HM-175-157 Maximum RPM is 2800 Example: OAT: 70 F Pressure Altitude: 5000 ft Desired Power setting: Result: Set RPM: 2625 DA202-C1 March 20, 2001 Page 5 - 4...
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DA 20-C1 Flight Manual PERFORMANCE Figure 5.2(b): Cruising Performance SENSENICH PROPELLER W69EK7-63, W69EK7-63G and W69EK-63 Maximum RPM is 2800 Example: OAT: 70 F Pressure Altitude: 5000 ft Desired Power setting: Result: Set RPM: 2560 DA202-C1 August 9, 2001 Page 5 - 5...
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DA 20-C1 Flight Manual PERFORMANCE 5.3.3. Figure 5.3: Stall Speeds Configuration: Idle, most forward center of gravity, max. weight (this is the most adverse configuration) Stall speeds in kts Bank Angle Flaps 0° 30° 45° 60° CRUISE DA202-C1 August 28, 1998...
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DA 20-C1 Flight Manual PERFORMANCE 5.3.4. Figure 5.4: Wind Components Maximum demonstrated crosswind component: 20 kts (37 km/h) Example: 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)
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DA 20-C1 Flight Manual PERFORMANCE Figure 5.5(b): Take-off Distance SENSENICH PROPELLER W69EK7-63, W69EK7-63G and W69EK-63 DA202-C1 August 9, 2001 Page 5 - 9 Revision 14 DOT Approved...
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DA 20-C1 Flight Manual PERFORMANCE 5.3.6. Figure 5.6(a): Climb Performance / Cruising Altitudes HOFFMANN PROPELLER HO-14HM-175-157 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...
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DA 20-C1 Flight Manual PERFORMANCE Figure 5.6(b) : Climb Performance / Cruising Altitudes 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:...
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DA 20-C1 Flight Manual PERFORMANCE 5.3.7. Figure 5.7(a): Climb Performance / Take off HOFFMANN PROPELLER HO-14HM-175-157 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:...
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DA 20-C1 Flight Manual PERFORMANCE Figure 5.7(b) : Climb Performance / Take off 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: 65° F Weight : 1653 lbs...
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DA 20-C1 Flight Manual PERFORMANCE 5.3.8 Figure 5.8(a): Cruising Speed (True Airspeed) HOFFMANN PROPELLER HO-14HM-175-157 Diagram for true airspeed (TAS) calculation at selected power level. Example: Pressure altitude: 6000 ft. Temperature: 70 F Power setting: Result: True airspeed (TAS): 124 kts...
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DA 20-C1 Flight Manual PERFORMANCE Figure 5.8(b): Cruising Speed (True Airspeed) 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: 70 F Power setting: Result: True airspeed (TAS):...
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DA 20-C1 Flight Manual PERFORMANCE 5.3.9. Figure 5.9(a): Maximum Flight Duration HOFFMANN PROPELLER HO-14HM-175-157 Diagram for calculation of the maximum flight duration depending on fuel availability. TO BE INSERTED Example: Fuel quantity: Power Setting: Result: Possible flight time without reserve:...
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DA 20-C1 Flight Manual PERFORMANCE Figure 5.9(b) : Maximum Flight Duration SENSENICH PROPELLER W69EK7-63, W69EK7-63G and W69EK-63 Table for calculation of the maximum flight duration depending on fuel availability. Figure 1: Flight Manual Cruise Performance Table, Sensenich Propeller Press 20 ° C Below Standard 20 °...
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DA 20-C1 Flight Manual PERFORMANCE 5.3.10. Figure 5.10(a): Climb Performance / Balked Landing HOFFMANN PROPELLER HO-14HM-175-157 Conditions: Speed = 52 KIAS Wing Flaps in Landing Position (LDG) max take-off power Example: Pressure altitude: 2000 ft Outside temperature: 65 F Result:...
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DA 20-C1 Flight Manual PERFORMANCE Figure 5.10(b): Climb Performance / Balked Landing 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: 70 F...
DA 20-C1 Flight Manual PERFORMANCE 5.3.11. Landing Distance Conditions: - Throttle: Idle - Maximum T/O Weight - Approach Speed 52 KIAS - Level Runway, paved - Wing Flaps in Landing position (LDG) - Standard Setting, MSL Landing distance over a 50 ft (15 m) obstacle: approx.
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DA 20-C1 Flight Manual Weight and Balance CHAPTER 6 WEIGHT AND BALANCE / EQUIPMENT LIST 6.1 INTRODUCTION 6.2 AIRPLANE WEIGHING - Figure 6.1 Leveling Diagram - Figure 6.2 Leveling Diagram - Figure 6.3 Sample Weighing Report 6.3 WEIGHT AND BALANCE REPORT - Figure 6.4 Sample Weight and Balance Report...
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DA 20-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.
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DA 20-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) To determine the empty weight and the empty weight CG position, the airplane is to be positioned in the above mentioned pre-weighing condition, with the nose gear and each main gear on a scale.
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DA 20-C1 Flight Manual Weight and Balance Figure 6.1 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)
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Aircraft Serial No.: Model: DA20-C1 KATANA Registration: Issue date: Aircraft Specific Weighing Report 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 edge.
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DA 20-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 equipment as well as each repair affecting the empty weight, the CG position of the empty weight or the empty weight moment must be entered in the Weight and Balance Report included at the back of this manual.The following Sample...
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Continuous report of structural changes or change of equipment Figure 6.7: Sample Weight and Balance Report DA 20-C1 Serial No.: Registration: Page No.: Changes of Weight Actual Signature Date Entry No. Description Addition (+) Subtraction (-) Empty Weight of Part or...
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DA 20-C1 Flight Manual Weight and Balance 6.4. FLIGHT WEIGHT AND CENTER OF GRAVITY The following data enables the pilot to operate the DA 20 within the required weight- and center of gravity limitations. The following diagrams, Figure 6.5 Loading Plan Figure 6.6...
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DA 20-C1 Flight Manual Weight and Balance Figure 6.6: Weight & Balance Diagram 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)
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DA 20-C1 Flight Manual Weight and Balance Figure 6.7: Calculation of Loading Condition Calculation of the DA 20 (Example) Your DA 20 Load Limits Weight [lbs] Moment Weight [lbs] Moment [in.lbs] [in.lbs] (Weight [kg]) ([kgm]) (Weight [kg]) ([kgm]) 1. Empty Weight (use the data for...
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Weight and Balance DA 20-C1 Flight Manual Figure 6.8: Permissible Center of Gravity Range and permissible Flight-Weight-Moment 1. See example calculation of loading condition Figure 6.7. Change in center of gravity is due to fuel consumption Doc # DA202-C1 April 23, 2002...
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DA 20-C1 Flight Manual Weight and Balance 6.5. 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: •...
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DA 20-C1 Flight Manual Weight and Balance Equipment List Item Part Description Weight Number Manufacturer Part/Model No. lbs (kg) in (m) 22-001 Autopilot Turn Coordinator/Roll Computer -16.4 S-TEC 01260-12-0-14 (1.0) (-0.42) 22-002 Autopilot Pitch Computer -27.4 S-TEC 01261-54-14 (0.5) (-0.68)
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DA 20-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/NC0149, C0151 onwards) 15.3 -35.0 Yuasa Y50N18L-A-CX (6.9)
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DA 20-C1 Flight Manual Weight and Balance Equipment List Item Part Description Weight Number Manufacturer Part/Model No. lbs (kg) in (m) 34-006 Transponder -20.5 Bendix/King KT 76A (1.4) (-0.52) 34-007 -20.5 Garmin GPS150 (1.0) (-0.52) 34-008 -20.5 Bendix/King KLN 35A (1.0)
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DA 20-C1 Flight Manual Weight and Balance Equipment List Item Part Description Weight Number Manufacturer Part/Model No. lbs (kg) in (m) 34-029 TCAD (Traffic Collision Alerting Device) -20.5 Ryan 8800 Gold (1.6) (-0.42) 34-030 -17.40 Garmin Gl106A (0.6) (-0.44) 34-031 GPS/Nav/Com -20.5...
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DA 20-C1 Flight Manual Description CHAPTER 7 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS INTRODUCTION 7–2 AIRFRAME 7–2 FLIGHT CONTROLS 7–3 INSTRUMENT PANEL 7–6 LANDING GEAR SYSTEM 7–8 SEATS AND SAFETY BELTS 7–10 BAGGAGE COMPARTMENT 7–10 CANOPY 7–11 POWERPLANT 7–12 7.10 FUEL SYSTEM...
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DA 20-C1 Flight Manual Description 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. 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.
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DA 20-C1 Flight Manual Description 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’ to disable the flap system.
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DA 20-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.
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DA 20-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. NOTE Failure to install the flight control lock whenever the aircraft is parked may result in control system damage, due to gusts or turbulence.
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DA 20-C1 Flight Manual Description INSTRUMENT PANEL Aircraft with ELT-200 Installed Aircraft with TAS600 Installed TRIM NO SE U P M80 0 CH RONO MET ER NE U TR AL 12:45 °F NO SE D OWN 360 420 This airplane is classified as a very light airplane approved for...
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DA 20-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.
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DA 20-C1 Flight Manual Description 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.
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DA 20-C1 Flight Manual Description Brake System Schematic Doc # DA202-C1 December 19, 1997 Page 7–9 Issue 1...
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DA 20-C1 Flight Manual Description 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.
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DA 20-C1 Flight Manual Description CANOPY Locking: The canopy is closed by pulling down on the forward handles on the canopy frame. Locking the canopy is accomplished by moving the two locking handles on the left and right side of the frame.
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DA 20-C1 Flight Manual Description POWERPLANT 7.9.1. Engine DA20-C1 aircraft are equipped with the Continental IO-240-B engine. The IO-240-B is a fuel injected, 4 cylinder, 4 stroke engine with horizontally opposed, air cooled cylinders and heads. The propeller drive is direct from the crankshaft.
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DA 20-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.
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DA 20-C1 Flight Manual Description 7.9.7. Lubricating The engine has a high pressure wet sump lubrication. The oil is pumped by a mechanical, engine driven pump. An oil dipstick indicates the level of oil in the tank. The dipstick is marked for US quarts.
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DA 20-C1 Flight Manual Description 7.10 FUEL SYSTEM The aluminum tank is located behind the seats, below the baggage compartment. The capacity is specified in Section 2 of this manual. The tank filler on the left side of the fuselage behind the canopy is connected to the tank with a rubber hose.
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DA 20-C1 Flight Manual Description Doc # DA202-C1 June 24, 2005 Page 7–16 Revision 19...
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DA 20-C1 Flight Manual Description 7.10.1. Fuel Shut-off Valve WARNING 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.
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DA 20-C1 Flight Manual Description To check the fuel level: 1. Insert the graduated end of the fuel dipstick into the tank through the fuel filler opening until the dipstick touches the bottom. 2. Withdraw the dipstick from the fuel tank.
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DA 20-C1 Flight Manual Description 7.11 ELECTRICAL SYSTEM 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).
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DA 20-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. Refer to Section 7.4 for a illustration of the instrument panel. 7.11.4. Voltmeter The voltmeter indicates the status of the electrical bus.
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7.11.8. Internal Lighting The internal lighting of the DA 20-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.
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DA 20-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.
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DA 20-C1 Flight Manual Handling CHAPTER 8 HANDLING, PREVENTIVE AND CORRECTIVE MAINTENANCE INTRODUCTION AIRPLANE INSPECTION PERIODS AIRPLANE ALTERATIONS OR REPAIRS GROUND HANDLING / ROAD TRANSPORT 8.4.1 Ground Handling 8.4.2 Parking 8.4.3 Mooring 8.4.4 Jacking 8.4.5 Road Transport CLEANING AND CARE 8.5.1...
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DA 20-C1 Flight Manual Handling 8.1. INTRODUCTION This Chapter contains factory-recommended procedures for proper ground handling and servicing of the airplane. It also identifies certain inspection and maintenance requirements which must be followed if the airplane is to retain its’ original performance and dependability. It is wise to follow a planned schedule of lubrication and preventive maintenance based on climatic and flying conditions encountered.
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DA 20-C1 Flight Manual Handling 8.4. GROUND HANDLING / ROAD TRANSPORT 8.4.1. Ground Handling I. Towing Forward The airplane is most easily and safely maneuvered by hand with the tow-bar attached to the nose wheel. If the aircraft is towed forward without using the tow-bar, the nose-wheel will follow the movement of the airplane.
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DA 20-C1 Flight Manual Handling 8.4.2. Parking For short time parking, the airplane must be positioned in a headwind direction, the parking brake must be engaged, the wing flaps must be in the retracted position and the wheels must be chocked.
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DA 20-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.
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DA 20-C1 Flight Manual Handling 8.5. CLEANING AND CARE CAUTION Excessive dirt deteriorates the flight performance. 8.5.1. Painted Surfaces To achieve the best flight characteristics for the DA20, 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.
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DA 20-C1 Flight Manual Handling 8.5.3. Propeller See Hoffmann Propeller Instruction Manual E 0110.74. 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.
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DA 20-C1 Flight Manual Supplements CHAPTER 9 SUPPLEMENTS GENERAL INDEX OF 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.
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DA 20-C1 Flight Manual Supplements 9.2 INDEX OF SUPPLEMENTS NOTE It is only necessary to maintain those supplements which pertain to optional equipment that may be installed in your airplane. Supplement No. Title Pages External Power Operation Winterization Kit Recognition Lights...
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DA 20-C1 Flight Manual Supplement 1 CHAPTER 9 SUPPLEMENT 1 EXTERNAL POWER OPERATION GENERAL S1-2 OPERATING LIMITATIONS S1-3 EMERGENCY PROCEDURES S1-4 NORMAL PROCEDURES S1-4 PERFORMANCE S1-9 WEIGHT AND BALANCE S1-9 Doc # DA202-C1 May 28, 2001 Page S1-1 Revision 13...
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DA 20-C1 Flight Manual Supplement 1 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, eg. maintenance, battery charging, starting.
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DA 20-C1 Flight Manual Supplement 1 Battery Breaker EPU Switch Battery Switch CANOPY Reverse Polarity Diode EPU Relay Current Limiter EPU Receptacle Current Limiter EPU Annunciator Reverse Current Diode Reverse Current Diode Circuit Breaker Circuit Breaker EPU Plug Battery Relay...
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DA 20-C1 Flight Manual Supplement 1 3. EMERGENCY PROCEDURES 3.3.4 FIRE 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 4.
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DA 20-C1 Flight Manual Supplement 1 4.4.1 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: I. In-Cabin Check...
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DA 20-C1 Flight Manual Supplement 1 GEN/BAT Master Switch Generator Warning Light illuminated Exterior Lights as required Instrument Panel Lighting as required Canopy close and secure Canopy Unlocking Warning Light 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.
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DA 20-C1 Flight Manual Supplement 1 Throttle FULL for prime (prime for 3 seconds minimum before starting) Throttle Full IDLE to ¼ inch OPEN as required Ignition Switch START, hold until engine starts or for 10 seconds maximum (if engine does not start, release ignition key,...
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DA 20-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.
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DA 20-C1 Flight Manual Supplement 1 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. At ambient temperatures below 32°F (0°C) DO NOT apply full power if oil pressure is above 70 psi.
DA 20-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...
DA 20-C1 Flight Manual Supplement 2 1. GENERAL The Winterization Kit consists of cowling inlet and outlet baffles. The inlet baffles are attached to the upper cowling with two winged ¼-turn fasteners. The outlet baffles are attached to the lower cowling with screws.
DA 20-C1 Flight Manual Supplement 2 3. EMERGENCY PROCEDURES There is no change to the airplane emergency procedures when the Winterization Kit is installed. 4. NORMAL PROCEDURES Preflight Inspection: [Insert after Item 7 (c) of the Walk-around inspection (ref. section 4.4.1 of the Airplane Flight Manual)] Install or remove winter kit baffles according to the following chart: 5.
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DA 20-C1 Flight Manual Supplement 2 7. 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 a placard located on the cowling below the oil door.
DA 20-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...
DA 20-C1 Flight Manual Supplement 3 1. GENERAL The installation is defined by Service Bulletin DAC1-33-01. 2. OPERATING LIMITATIONS 2.15. PLACARDS 1. On the instrument panel above the individual circuit breakers Figure 1. 3. EMERGENCY PROCEDURES There are no changes to the airplane emergency procedures when the Recognition Lights are installed.
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DA 20-C1 Flight Manual Supplement 3 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. One of the lamps is aimed to perform the function of the original taxi light.
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DA 20-C1 Flight Manual Supplement 3 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 March 10, 1999 Page S3 - 4 Revision 5 DOT Approved...
DA 20-C1 Flight Manual Supplement 4 CHAPTER 9 SUPPLEMENT 4 GROSS WEIGHT INCREASE (800 kg) GENERAL S4-2 OPERATING LIMITATIONS S4-2 EMERGENCY PROCEDURES S4-4 NORMAL PROCEDURES S4-5 PERFORMANCE S4-5 WEIGHT AND BALANCE S4-13 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS S4-15...
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Supplement 4 1. GENERAL This supplement addresses the effects on the DA 20-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.
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DA 20-C1 Flight Manual Supplement 4 CENTER OF GRAVITY MOMENT ARM (m) aft of datum 0.20 0.21 0.22 0.23 0.24 0.25 0.26 0.27 0.28 0.29 0.30 0.31 0.32 1764 1700 1600 1500 1400 1300 1200 10.5 11.5 12.5 MOMENT ARM (in) aft of datum...
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DA 20-C1 Flight Manual Supplement 4 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 Stalls (except whip stalls) Lazy Eight’s Entry speed: 116 KIAS...
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DA 20-C1 Flight Manual Supplement 4 4. NORMAL PROCEDURES 4.2 AIRSPEEDS FOR NORMAL FLIGHT OPERATION LANDING KIAS Approach speed for normal landing. Wing Flaps LDG 5. PERFORMANCE 5.3. PERFORMANCE TABLE AND DIAGRAMS 5.3.1 Figure 5.1: Airspeed System Calibration Assumes zero indicator error...
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DA 20-C1 Flight Manual Supplement 4 5.3.3. Figure 5.3: 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 Flap Angle of Bank Setting 0°...
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DA 20-C1 Flight Manual Supplement 4 Figure 5.5: Take-off Distance SENSENICH PROPELLER W69EK7-63, W69EK7-63G and W69EK-63 TAKE OFF DISTANCE NOTE THIS SUPPLEMENT IS APPLICABLE ONLY TO THOSE AIRCRAFT WHICH ARE REGISTERED IN THE UNITED STATES OF AMERICA OR CANADA. DA202-C1...
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DA 20-C1 Flight Manual Supplement 4 Figure 5.6 : Climb Performance / Cruising Altitudes 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 TEMPERATURE (°C) RATE OF CLIMB (m/min) -20°...
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DA 20-C1 Flight Manual Supplement 4 Figure 5.7 : Climb Performance / Take off SENSENICH PROPELLER W69EK7-63, W69EK7-63G and W69EK-63 Best Rate-of-Climb Speed with Wing Flaps T/O 68 KIAS TEMPERATURE (°C) RATE OF CLIMB (m/min) -20° -10° 0° +10° +20°...
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DA 20-C1 Flight Manual Supplement 4 Figure 5.8: Cruising Speed (True Airspeed) 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: 70° F Power setting: Result: True airspeed (TAS):...
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DA 20-C1 Flight Manual Supplement 4 Figure 5.10: Climb Performance / Balked Landing SENSENICH PROPELLER W69EK7-63, W69EK7-63G and W69EK-63 Conditions: Speed = 52 KIAS Wing Flaps in Landing Position (LDG) max take-off power TEMPERATURE (°C) RATE OF CLIMB (m/min) -20°...
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DA 20-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.
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DA 20-C1 Flight Manual Supplement 4 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 edge.
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DA 20-C1 Flight Manual Supplement 4 Figure 6.6: Calculation of Loading Condition Calculation of the DA 20 (Example) Your DA 20 Load Limits Weight [lbs] Moment Weight [lbs] Moment [in.lbs] [in.lbs] (Weight [kg]) ([kgm]) (Weight [kg]) ([kgm]) 1. Empty Weight (use the data for...
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DA 20-C1 Flight Manual Supplement 4 Figure 6.7: Permissible Center of Gravity Range and permissible Flight-Weight-Moment PERMISSIBLE FLIGHT - WEIGHT - MOMENT (kg m) 1764 1700 1600 1500 1400 1300 1200 9000 11000 13000 15000 17000 19000 21000 PERMISSIBLE FLIGHT - WEIGHT - MOMENT (in lbs) See example calculation of loading condition Figure 6.6.
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DA 20-C1 Flight Manual Supplement 5 1. 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. 2. OPERATING LIMITATIONS NOTE Refer to all of the Operating Limitations with the following inserted into the appropriate place.
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DA 20-C1 Flight Manual Supplement 5 3. 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.
DA 20-C1 Flight Manual Supplement 5 4. NORMAL OPERATING PROCEDURES NOTE Refer to all of the Normal Operating Procedures with the following inserted into the appropriate places. NORMAL OPERATION CHECKLIST 4.4. 4.4.1. Preflight Inspection II. Walk Around Check and Visual Inspection 2.
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DA 20-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).
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DA 20-C1 Flight Manual Supplement 5 5. Move control stick to level flight position – Engage ALT mode. Move control stick fore and aft to overpower pitch servo clutch. Overpower action should be smooth with no noise or jerky feel. If unusual sound or excessive play is detected, have the servo installation inspected prior to flight.
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DA 20-C1 Flight Manual Supplement 5 4.4.11. Landing Approach Autopilot Disengaged (AP DISC) 5. PERFORMANCE There is no change in airplane performance with the autopilot system installed. 6. WEIGHT AND BALANCE The installation adds 11.1 lbs (5.0 kg) of weight at a –24.6 in (–.62 m) arm.
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DA 20-C1 Flight Manual Supplement 5 2. Mode Annunciation window – displays mode in use. 3. Green ready (RDY) Light – Illuminates when autopilot is ready for engagement. When autopilot is disconnected, "RDY" will flash for five seconds accompanied by a beeping audio tone.
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DA 20-C1 Flight Manual Supplement 5 Trim Switch Press To Talk (PTT) Note: Left grip shown Right grip opposite Figure 1 Doc # DA202-C1 December 7, 1999 Page S5 - 9 Revision 8 DOT Approved...
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Supplement 5 8. HANDLING, PREVENTATIVE AND CORRECTIVE MAINTENANCE Service and maintenance of the System 30 Autopilot system shall be performed according to the Diamond Aircraft Maintenance Manual (Document number DA201-C1). Doc # DA202-C1 December 7, 1999 Page S5 - 10...
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DA 20-C1 Flight Manual Supplement 6 CHAPTER 9 SUPPLEMENT 6 VM1000 Monitoring System 1. GENERAL S6 -2 2. OPERATING LIMITATIONS S6 -2 3. EMERGENCY PROCEDURES S6 -2 4. NORMAL PROCEDURES S6 -4 5. PERFORMANCE S6 -4 6. WEIGHT AND BALANCE S6 -4 7.
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DA 20-C1 Flight Manual Supplement 6 1. 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. 2. OPERATING LIMITATIONS Placards 2.1.
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DA 20-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.
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DA 20-C1 Flight Manual Supplement 6 4. NORMAL PROCEDURES NOTE There is no change in the normal procedures with the VM 1000 and EC 100 monitoring system installed. Although there are no necessary changes to the normal procedures, Section 7 contains a description of some of the operating modes and functions that may be used, if desired by the pilot, as enhancements to the normal procedures.
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DA 20-C1 Flight Manual Supplement 6 Manifold Pressure 7.3. The manifold pressure system provides an analog display and a three place digital display. The full sweep analog display resolution is 1" Hg. The digital display resolution is 0.1" Hg. A warning alert activates when the manifold pressure redline is reached. The VM 1000 display will flash, if installed, the EC100 displays the warning and an audible tone is heard.
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DA 20-C1 Flight Manual Supplement 6 Fuel Quantity 7.8. 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.
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DA 20-C1 Flight Manual Supplement 6 8. 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 December 7, 1999...
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DA 20-C1 Flight Manual Supplement 7 CHAPTER 9 SUPPLEMENT 7 Auxiliary Fuel System 1. GENERAL S7- 2 2. OPERATING LIMITATIONS S7- 2 3. EMERGENCY PROCEDURES S7- 2 4. NORMAL PROCEDURES S7- 2 5. PERFORMANCE S7- 4 6. WEIGHT AND BALANCE S7- 4 7.
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DA 20-C1 Flight Manual Supplement 7 1. GENERAL This supplement addresses the optional installation of an auxiliary fuel tank system (Mod No 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.
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DA 20-C1 Flight Manual Supplement 7 CAUTION The aircraft must be grounded prior to and during fueling. Use the ground stud, located under the trailing edge of the left wing. NOTE It is recommended to fill the main tank first and to full capacity before filling the auxiliary tank.
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DA 20-C1 Flight Manual Supplement 7 Auxiliary fuel tank indicator Full Fuel Transfer switch Transfer time 10 minutes Auxiliary fuel tank indicator Empty Main fuel tank 1/5 capacity increase Fuel Transfer switch 5. PERFORMANCE There is no change in airplane performance with the Auxiliary Fuel Tank system installed.
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DA 20-C1 Flight Manual Supplement 7 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.
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Supplement 7 8. 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 December 7, 1999 Page S7 - 6...
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DA 20-C1 Flight Manual Supplement 8 CHAPTER 9 SUPPLEMENT 8 Stick Mounted Trim Switches 1. GENERAL S8- 2 2. OPERATING LIMITATIONS S8- 2 3. EMERGENCY PROCEDURES S8- 2 4. NORMAL PROCEDURES S8- 2 5. PERFORMANCE S8- 2 6. WEIGHT AND BALANCE S8- 2 7.
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DA 20-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.
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Control Stick Grip (Left-hand Shown) Figure 1 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 December 7, 1999 Page S8 - 3...
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DA 20-C1 Flight Manual Supplement 9 CHAPTER 9 SUPPLEMENT 9 20 US Gallon Fuel Tank 1. GENERAL S9- 2 2. OPERATING LIMITATIONS S9- 2 3. EMERGENCY PROCEDURES S9- 2 4. NORMAL PROCEDURES S9- 2 5. PERFORMANCE S9- 2 6. WEIGHT AND BALANCE S9- 2 7.
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DA 20-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.
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DA 20-C1 Flight Manual Supplement 9 7.10.5 Fuel Dipstick A fuel dipstick P/N 22-2550-18-00, is supplied with all aircraft with the 20 US gallon fuel tank installed. This dipstick permits direct measurement of the fuel level during the pre-flight check.
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DA 20-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. Only portions of the flight manual affected by this installation are included in this supplement.
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DA 20-C1 Flight Manual Supplement 10 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS 7.4 Instrument Panel ENGINE FUEL PRESS START TACH. OIL PRESS OIL TEMP Usable SYSTEM 75.4L/19.7 US gal. TURN FUEL QTY. FUEL PITOT FLAPS TRIM & O.A.T. PUMP...
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DA 20-C1 Flight Manual Supplement 11 CHAPTER 9 SUPPLEMENT 11 Pitot Heat Operation 1. GENERAL 2. OPERATING LIMITATIONS 3. EMERGENCY PROCEDURES 4. NORMAL PROCEDURES 5. PERFORMANCE 6. WEIGHT AND BALANCE 7. DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS 8. HANDLING, PREVENTATIVE AND CORRECTIVE MAINTENANCE...
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DA 20-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.
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DA 20-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.).
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DA 20-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. 4.4.4 Before Taxiing Avionics Master Switch Flight Instruments and Avionics...
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DA 20-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.
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