DIAMOND AIRCRAFT DA 20/100 Flight Manual

pages of any revision as well as the Record of Revisions must be inserted into the manual upon receipt. The pages superseded by the revision must be removed and destroyed. The Revision Log should be updated by hand. Changes are identified on those pages affected by a revision bar. Rev. No. Date Issued: Inserted On: Inserted By: Issue 1 20 Dec., 2000 20 Dec., 2000 Diamond Aircraft DIAMOND AIRCRAFT DA 20/100 Flight Manual Doc # DA202-100-VLA November 18, 2003 Page Revision 2 0 - 9 SUBSCRIPTION SERVICE Diamond Aircraft Publications Revision Subscription Contacts To ensure safe operation and maintenance of the DA20/100 Katana 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. DA20/100 Katana related manuals and publications. North America, Australia, South Africa: Europe, Other: Diamond Aircraft Industries Inc. Customer Support 1560 Crumlin Sideroad London, Ontario Canada N5V 1S2 www.diamondair.com Diamond Aircraft Industries GmbH Customer Support N.A. Otto-Strasse 5 A-2700 Wiener Neustadt Austria www.diamond-air.at Phone: Fax: 519-457-4041 519-457-4045 Phone: Fax: 011-43-2622-26700 011-43-2622-26780 2. Rotax 912 Engine related manuals and publications. North America: Rotech Research Canada LTD. 6235 Okanagan Landing Road Vernon, British Columbia Canada V1H 1M5 www.rotec.com HB- FLUGTECHNIK GES.M.B.H. Dr. Adolf Scharf Str. 44 A-4053HAID www.rotax.bombardier.com Phone: Fax: 250-260-6299 250-260-6269 Phone: Fax: 07229 / 79104/79117 07229 / 79104 15 OR Contact your authorized Rotax Engine distributor as listed in the back of the 912 Operators Manual. 3. Hoffmann Propeller Model HO-V352 related manuals and publications. North America, Australia, South Africa: Europe, Other: Diamond Aircraft Industries Inc. Customer Support 1560 Crumlin Sideroad London, Ontario Canada N5V 1S2 www.diamondair.com Hoffmann Propeller GmbH. & Co. Customer Support Kupferlingstr. 9 D-83022 Rosenheim Germany Phone: Fax: 519-457-4041 519-457-4045 Phone: Fax: 011-49-8031-1878-0 011-49-8031-1878-78 DIAMOND AIRCRAFT DA 20/100 Flight Manual General Doc # DA202-100-VLA 9 March, 2001 Page Revision 1 1 - 1 CHAPTER 1 GENERAL 1.1. INTRODUCTION 1- 1 1.2. CERTIFICATION BASIS 1- 2 1.3. WARNINGS, CAUTIONS, AND NOTES 1- 2 1.4. THREE-VIEW-DRAWING OF AIRPLANE 1- 3 1.5. DIMENSIONS 1- 4 1.6. ENGINE 1- 5 1.7. PROPELLER 1- 5 1.8. FUEL 1- 6 1.9. LUBRICANT AND COOLANT 1- 7 1.10. WEIGHT 1- 9 1.11. LIST OF DEFINITIONS AND ABBREVIATIONS 1-10 1.12. CONVERSION FACTORS 1-14 1.1. INTRODUCTION The Airplane Flight Manual has been prepared to provide pilots and instructors with information for the safe and efficient operation of this airplane. This Manual includes the material required by JAR-VLA including amendment VLA/92/1. It also contains supplemental data supplied by the airplane manufacturer that can be useful to the pilot. The Flight Manual conforms to a standard equipped DA 20/100 KATANA. Any optional equipment installed on request of the customer (COMM, NAV, etc.) is not considered. For the operation of optional equipment the Operation Manual of the respective vendor must be used. For permissible accessories refer to the equipment list, Section 6.5. DIAMOND AIRCRAFT DA 20/100 Flight Manual General Doc # DA202-100-VLA 9 March, 2001 Page Revision 1 1 - 2 1.2. CERTIFICATION BASIS The DA 20/100 has been approved by Transport Canada as meeting the requirements of JAR-VLA and amendment VLA/92/1. The Type Certificate No. A-191, originally issued on July 29th, 1994, has been revised to include the DA20/100. Category of Airworthiness: NORMAL Noise Certification Basis: a) Canadian Airworthiness Manual Chapter 516 b) FAA Part 36 c) LBA: LSL Chapter X of 1.01.1991 For others, refer to the national type certificate data sheets, as applicable. 1.3. WARNINGS, CAUTIONS, AND NOTES The following definitions apply to warnings, cautions, and notes used in the Flight Manual: WARNING means that the non-observation of the corresponding procedure leads to an immediate or important degradation of the flight safety. CAUTION means that the non-observation of the corresponding procedure leads to a minor or to a more or less long term degradation of flight safety. NOTE draws the attention to any special item not directly related to safety but which is important or unusual. DIAMOND AIRCRAFT DA 20/100 Flight Manual General Doc # DA202-100-VLA 9 March, 2001 Page Revision 1 1 - 3 1.4. THREE-VIEW-DRAWING OF AIRPLANE DIAMOND AIRCRAFT DA 20/100 Flight Manual General Doc # DA202-100-VLA 9 March, 2001 Page Revision 1 1 - 4 1.5. DIMENSIONS 1.5.1 Overall Dimensions Span: 35 ft 7 in (10.84 m) Length: 23 ft 6.0 in ( 7.17 m) Height: 6 ft 11.0 in ( 2.10m) 1.5.2 Wing Airfoil: Wortmann FX 63-137/20 HOAC Wing Area: 125 sq.ft. (11.6 m 2 ) Mean Aerodynamic Chord (MAC): 3 ft 6.9 in ( 1.09 m) Aspect Ratio: 10.0 Dihedral: +4° nominal Sweep of Leading Edge: +1° nominal 1.5.3 Horizontal Stabilizer Angle of Incidence : -2.5° ±0.5° Span: 8 ft 8 in (2.65 m) 1.5.4 Landing Gear Track: 6 ft 3 in (1.90 m) Wheel Base: 5 ft 9 in (1.75 m) Tire Size: Nose: 4.00-4 (TOST) 5.00-4 (GOODYEAR) Main:* 15 x 6.00-5 (GOODYEAR) or 5.00 x 5, 6 Ply (TSO C62) Tire Pressure: Nose: 26 psi (1.8 bar) Main: 33 psi (2.3 bar) * Main tires must be same brand, model and size. DIAMOND AIRCRAFT DA 20/100 Flight Manual General Doc # DA202-100-VLA 9 March, 2001 Page Revision 1 1 - 5 1.6. ENGINE Rotax 912S, 4 Cylinder, 4 Stroke-Engine, horizontally opposed, liquid cooled cylinder heads, air-cooled cylinders. Propeller drive via integrated reduction gear. Reduction Ratio: 2.43 : 1 Displacement: 82.5 cu.in. (1.352 liters) Output Power: 100 hp (73.5 kW) at 2385 RPM 1.7. PROPELLER Two-bladed variable pitch propeller, manufactured by HOFFMANN, Constant speed, hydraulic pitch control model HO-V352F/170FQ OR model HO-V352F/C170FQ Range of Pitch Angle: 10° - 35° Diameter: 5 ft 6.9 in (1.70 m) DIAMOND AIRCRAFT DA 20/100 Flight Manual General Doc # DA202-100-VLA 9 March, 2001 Page Revision 1 1 - 6 1.8. FUEL Approved Fuel Grades: AVGAS 100LL Automotive Gasoline, Unleaded, Minimum 95 RON or 91 AKI RON = Research Octane Number MON = Motor Octane Number AKI = Anti Knock Index = Total Fuel Capacity: Specifications: Europe - EN 228 USA - ASTM D4814 Canada – CAN/CGSB-3.5-94 (or more current issue) 20.1 US gal. (76 liters) Usable Fuel: 19.5 US gal. (74 liters) Unusable Fuel: 0.6 US gal. ( 2 liters) CAUTION Use of automotive gasoline containing alcohol (e.g.: methanol or ethanol) other than specified in the above listed specifications, is not permitted. NOTE Petroleum suppliers provide automotive gasoline of varying volatilities, depending on the season and climatic zone. Fuels with higher volatility (“cold weather” grade fuels) are more susceptible to fuel vapour formation than fuels with lower volatility (“hot weather” grade fuels), at equal temperatures. Use of fuels dispensed in winter or in colder climatic zones, under high ambient temperature conditions, increases the risk of vapor formation and subsequent possible engine malfunction. MON + RON 2 DIAMOND AIRCRAFT DA 20/100 Flight Manual General Doc # DA202-100-VLA November 18, 2003 Page Revision 2 1 - 7 1.9. LUBRICANT AND COOLANT 1.9.1. Lubricant Use only motor oil with API classification SF or SG or higher. Due to high stresses in the reduction gears, a 4 stroke motorcycle oil of a registered brand with gear additives that meets API classification SF or SG are highly recommended. The viscosity should be selected according to the various climatic conditions using the following table. CAUTION Do not use aviation lubricant! When operating with AVGAS100LL fuel do not use synthetic oil. Oil Capacity: Minimum : 3.0 liters (3.2 US qt.) Maximum : 3.4 liters (3.6 US qt.) DIAMOND AIRCRAFT DA 20/100 Flight Manual General Doc # DA202-100-VLA August 22, 2006 Page Revision 4 1 - 8 1.9.2. Coolant EVANS NPG+ waterless coolant or a comparable coolant must be used without water or other additives. WARNING Water or water-containing coolant must not be added in any case to the cooling system. CAUTION The coolant manufacturer’s data for change/replacement, usage, and operation are to be observed. (a) Coolant Capacity: Minimum : 2.5 US qt. (2.4 liters) Maximum : 2.6 US qt. (2.5 liters) (b) Reservoir Capacity: Minimum : 0.11 US qt. (0.1 liters) Maximum : 0.21 US qt. (0.2 liters) NOTE The level in the reservoir can be checked using the coolant dipstick. Excessive overfilling of the reservoir can result in overflow during operation. In the event of a completely empty reservoir, the coolant level in the dispatcher vessel on top of the engine must also be checked. DIAMOND AIRCRAFT DA 20/100 Flight Manual General Doc # DA202-100-VLA 9 March, 2001 Page Revision 1 1 - 9 1.10. WEIGHT Maximum Take-off Weight : 750 kg (1653 lbs) Maximum Landing Weight : 750 kg (1653 lbs) Empty Weight : See Chapter 6 Maximum Weight in Baggage Compartment : 20 kg (44 lbs) only if restraining devices available Wing Loading At Maximum Take-off Weight : 64.61 kg/m 2 (13.23 lbs/sq.ft.) Performance Load at Max. Take-off Weight : 7.50 kg/hp (16.53 lbs/hp.) DIAMOND AIRCRAFT DA 20/100 Flight Manual General Doc # DA202-100-VLA 20 December, 2000 Page Issue 1 1 - 10 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. IAS: Indicated airspeed as shown on the airspeed indicator. KIAS: IAS indicated in knots. GS: Ground Speed. Speed of the airplane relative to the ground. TAS: True airspeed. Speed of the airplane relative to air. TAS is CAS corrected for altitude and temperature errors. vA : Maneuvering speed. Maximum speed at which the airplane is not overstressed at full deflection of control surfaces. vFE : Maximum speed with flaps extended. vNE : Speed which must never be exceeded in any operation. vNO: Maximum structural cruising speed which should only be exceeded in calm air, and then only with caution. vS : The power-off stall speed with the airplane in its standard configuration. vSO: The power-off stall speed with the airplane in landing configuration. vX : Best angle-of-climb speed. vY: Best rate-of-climb speed. DIAMOND AIRCRAFT DA 20/100 Flight Manual General Doc # DA202-100-VLA 20 December, 2000 Page Issue 1 1 - 11 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° C (-67.9° F) is -0.0065° C/m (-0.0036° F/ft) and 0° C/m (0° F/ft) above. OAT: Outside air temperature. AGL: Above Ground Level Indicated Pressure Altitude: Altitude reading with altimeter set to 1013.25 mbar (29.92 inHg) air pressure. Pressure Altitude: Altitude measured at standard pressure at MSL (1013.25 mbar / 29.92 inHg) using a barometric altimeter. Pressure altitude is the indicated altitude corrected for installation and instrument errors. Within this manual the instrument errors are assumed to be zero. Aerodrome/Airport Pressure: Actual atmospheric pressure at the aerodrome/airport altitude. Wind: The wind speeds used in the diagrams in this manual should be referred to as headwind or tailwind components of the measured wind. 1.11.3. Powerplant Take-off Power: Maximum engine power for take-off. Maximum Continuous Power: Maximum permissible continuous engine output power during flight. DIAMOND AIRCRAFT DA 20/100 Flight Manual General Doc # DA202-100-VLA 20 December, 2000 Page Issue 1 1 - 12 1.11.4. Flight Performance and Flight Planning Demonstrated Crosswind Component: The maximum speed of the crosswind component at which the maneuvrability 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.). 1.11.5. Weight and Balance Reference Datum (RD): An imaginary vertical plane from which all horizontal distances for the center of gravity calculations are measured. It is the plane through the leading edge of the wing root rib, perpendicular to the longitudinal axis of the airplane. Station: A defined point along the longitudinal axis which is generally presented as a specific distance from the reference datum. Lever Arm: The horizontal distance from the reference datum to the center of gravity (of a component). Moment: The weight of a component multiplied by its lever arm. Center of Gravity (CG): Point of equilibrium for the airplane weight. 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. DIAMOND AIRCRAFT DA 20/100 Flight Manual General Doc # DA202-100-VLA 20 December, 2000 Page Issue 1 1 - 13 Center of Gravity Limits: The CG range which an airplane with a given weight must be operated within. Usable Fuel: The amount of fuel available for the flight plan calculation. Unusable Fuel: The amount of fuel remaining in the tank, which cannot be safely used in flight. Empty Weight: Weight of the airplane including unusable fuel, all operating fluids and maximum oil amount. Useful Load: The difference between take-off weight and empty weight. Maximum Take-off Weight: Maximum weight permissible for take-off. 1.11.6. Equipment ACL: Anti collision light 1.11.7 Miscellaneous GFRP - Glass Fibre Reinforced Plastic CFRP - Carbon Fibre Reinforced Plastic DIAMOND AIRCRAFT DA 20/100 Flight Manual General Doc # DA202-100-VLA 20 December, 2000 Page Issue 1 1 - 14 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/m 2] = 1 [mbar] 1 [in. Hg] = 33.865 [hPa] 1 [psi] = 68.97 [mbar] 1.12.4 Weight 1 [lbs] = 0.454 [kg] 1.12.5 Volume 1 [US gallon] = 3.785 [liters] 1 [Imperial gallon] = 4.546 [liters] DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 2 - 1 CHAPTER 2 OPERATING LIMITATIONS 2.1 INTRODUCTION 2-1 2.2 AIRSPEED LIMITATIONS 2-2 2.3 AIRSPEED INDICATOR MARKINGS 2-2 2.4 POWERPLANT LIMITATIONS 2-3 2.5 POWERPLANT INSTRUMENT MARKINGS 2-5 2.6 MISCELLANEOUS INSTRUMENT MARKINGS 2-5 2.7 WEIGHT 2-6 2.8 CENTER OF GRAVITY 2-6 2.9 APPROVED MANEUVERS 2-7 2.10 MANEUVERING LOAD FACTORS 2-7 2.11 MAXIMUM PASSENGER SEATING 2-8 2.12 FLIGHT CREW 2-8 2.13 KINDS OF OPERATION 2-8 2.14 FUEL 2-9 2.15 PLACARDS 2-9 2.16 DEMONSTRATED CROSSWIND COMPONENT 2-17 2.17 TEMPERATURE LIMITS 2-17 2.1. INTRODUCTION Chapter 2 of this Flight Manual comprises 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. The operating limitations in this Chapter and Chapter 9 have been approved by the Department of Transport (DOT), and must be complied with for all operations. WARNING These limitations must be complied with for all operations. DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 2 - 2 2.2. AIRSPEED LIMITATIONS IAS Speed kts mph km/h Remarks vA Maneuvering Speed 104 120 193 Do not make full or abrupt control movement above this speed, because under certain conditions the airplane may be overstressed by full control movement. vFE Maximum Flap Extended Speed 81 93 150 Do not exceed this speed with flaps extended vNO Maximum Structural Cruising Speed 118 135 218 Do not exceed this speed except in smooth air, and then only with caution vNE Never Exceed Speed 161 185 298 Do not exceed this speed in any operation 2.3. AIRSPEED INDICATOR MARKINGS IAS Marking kts mph km/h Explanation White Arc 37-81 43-93 69-150 Operating range with extended flaps Green Arc 41-118 47-135 76-218 Normal operating range Yellow Arc 118-161 135-185 218-298 Maneuvers must be conducted with caution and only in smooth air. Red Line 161 185 298 Maximum permissible speed for all operating modes DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 2 - 3 2.4. POWER PLANT LIMITATIONS 2.4.1. Engine (a) Engine Manufacturer : Bombardier Rotax, Gunskirchen/Austria (b) Engine Type Designation : 912 S3 NOTE The propeller is driven by the engine via a reduction gear with a ratio of 2.43:1. The RPM indicator indicates the propeller speed. For that reason, all speed references within this manual - contrary to the engine manual - are propeller speeds. (c) Engine Operating Limitations Max. T/O Power (5 min.) : 100 hp / 73.5 kW Max. Permissible T/O RPM : 2385 RPM Max. Continuous Power : 93 hp / 69 kW Max. Permissible Continuous RPM : 2260 RPM (d) Oil Pressure Minimum Normal : 12 psi (.8 bar) Below 1440 RPM : 29 psi – 73 psi (2.0-5.0 bar) Above 1440 RPM Max. in case of Cold-start (short-term) : 102 psi (7.0 bar) (e) Fuel Pressure Minimum : 2.2 psi (0.15 bar) Maximum : 5.8 psi (0.40 bar) (f) Oil Temperature Minimum : 122°F ( 50°C) Maximum : 266°F (130°C) DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 2 - 4 (g) Cylinder Head Temperature Maximum : 275°F (135°C) (h) Fuel Specifications Approved Fuel Grades : AVGAS 100LL Unleaded Automotive Fuel 95 RON /91 AKI (refer also to page 1-6) (i) Oil Grades : 4 stroke motorcycle oil of a registered brand with gear additives that meets or exceedes API classification SF or SG are highly recommended. (also see Page 1-7 for additional information on the selection of suitable lubricants) 2.4.2. Propeller (a) Propeller Manufacturer : Hoffmann Propeller, Rosenheim/Germany (b) Propeller Type : HO-V352F/170FQ OR HO-V352F/C170FQ (c) Propeller Diameter : 5 ft 6.9 in (1.70 m) (d) Propeller Pitch (at 3/4 radius) : 10° - 35° (e) Propeller Speed Limitations Max. T/O RPM (max. 5 min.) : 2385 RPM Max. Continuous RPM : 2260 RPM DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations Doc # 202-100-VLA November 18, 2003 Page Revision 2 2 - 5 2.5. POWERPLANT INSTRUMENT MARKINGS Powerplant instrument markings and their color code significance are shown below: Instrument Red Line = Lower Limit Green Arc = Normal Operating Range Yellow Arc = Caution Range Red Line = Upper Limit Tachometer - *600 - 2260 RPM 2260 - 2385 RPM 2385 RPM Oil Temperature Indicator 122° F 50° C 122- 266° F 50 - 130° C - 266° F 130° C Cylinder Head Temperature Indicator - - - 275° F 135° C Oil Pressure Indicator 12 psi 0.8 bar 29 - 73 psi 2 - 5 bar ABOVE 1440 RPM 12 – 29 psi 0.8 – 2 bar BELOW 1440 RPM 73 - 102 psi 5 - 7 bar 102 psi 7 bar * Recommended nominal idle speed = 950 RPM 2.6. MISCELLANEOUS INSTRUMENT MARKINGS Instrument Red Line = Lower Limit Green Arc = Normal Operating Range Yellow Arc = Caution Range Red Line = Upper Limit Voltmeter 8-11 Volts 12.5 - 16 Volts 11 - 12.5 Volts 16.1 Volts DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 2 - 6 2.7. WEIGHT Maximum permissible weight : 750 kg (1653 lbs) Maximum permissible weight in the baggage compartment : 20 kg (44 lbs) only permissible with baggage harness WARNING Exceeding the weight limitations may lead to overloading of the airplane, as well as degrading of the handling characteristics and flight performance. 2.8. CENTER OF GRAVITY The reference datum (RD) for the center of gravity (CG) calculation is tangent to the leading edge of the wing at the root rib. This plane is vertical when the fuselage is horizontal. Procedures for horizontal alignment, as well as particulars with regard to the empty weight center of gravity, refer to Chapter 6. Most forward CG (all weights) : 250 mm (9.84 in) aft of RD Most rearward CG (all weights) : 390 mm (15.35 in) aft of RD WARNING Exceeding the center of gravity limitations reduces the maneuverability and stability of the airplane. The procedure used to determine the center of gravity is described in Chapter 6. DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations Doc # 202-100-VLA November 18, 2003 Page Revision 2 2 - 7 2.9. APPROVED MANEUVRES This airplane is certified in the NORMAL Category in accordance with JAR-VLA. Permissible Normal Category Maneuvres: a) All normal flight maneuvres b) Stalls (except WHIP stalls) c) Lazy Eight’s Entry speed: 116 kts (215 km/h) Chandelles: Entry speed: 116 kts (215 km/h) Steep turns in which the angle of bank does not exceed 60° NOTE Aerobatics are prohibited. 2.10. MANEUVERING LOAD FACTORS Table of structural maximum permissible load factors: at vA: at vNE: with fully extended flaps Positive + 4.4 + 4.4 + 2.0 Negative - 2.2 - 2.2 0 WARNING Exceeding the maximum load factors will result in overstressing of the airplane. Simultaneous full deflection of more than one control surface can result in overstressing of the structure, even at speeds below the maneuvering speed. DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 2 - 8 2.11. MAXIMUM PASSENGER SEATING Maximum Passenger Seating: one passenger. 2.12. FLIGHT CREW Minimum Flight Crew: one pilot, aircraft to be flown solo from left seat only 2.13. KINDS OF OPERATION Flights are permissible in accordance with day visual flight rules. Minimum Equipment, Flight and Navigation Instruments: Airspeed Indicator Altimeter Magnetic Compass Minimum Equipment, Powerplant Instruments: Fuel Quantity Indicator Oil Pressure Indicator Oil Temperature Indicator Manifold Pressure Indicator Cylinder Head Temperature Indicator Tachometer Fuel Pressure Warning Light Voltmeter Ammeter Generator Warning Light Note: Additional equipment may be required for compliance with specific operational or specific national requirements. It is the operators responsibility to ensure compliance with any such specific equipment requirements. DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 2 - 9 2.14. FUEL Fuel Capacity Total Fuel Quantity: : 20.1 US gal. (76 liters) Usable Fuel: : 19.5 US gal. (74 liters ) Unusable Fuel: : 0.53 US gal. ( 2 liters) 2.15. PLACARDS The following placards must be installed: 1. On the instrument panel next to airspeed indicator Effective for all aircraft operated strictly under JAR-VLA regulations This airplane is classified as a very light airplane approved for day VFR only, in non-icing conditions. All aerobatic maneuvres, including intentional spinning, are prohibited. See Flight Manual for other limitations. DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 2 - 10 3. Next to the switches 4. On the flap control 2. On the instrument panel under the airspeed 5. On the dimming switch for trim display, flap control and GPS (if installed) 6. Next to dimming potentiometer for cabin and fuel shut-off valve light DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 2 - 11 7. On the instrument panel next to the individual circuit breakers  Depending on aircraft specific avionic equipment configuration. OR OR DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 2 - 12 8. On top of the instrument panel under the compass 9. Around Trim Display on top of the instrument panel 15. On the fuel quantity gauge 16. Next to GPS (if installed) 10. On top the instrument panel within pilot’s direct line of vision 11. On DME channeling switch on the RH side of the radio stack (optional) 12. Above RH air vent on the instrument panel (optional) 13. Above the OAT indicator 14. Below Microphone jack on LH side of the instrument panel DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 2 - 13 17. Under the instrument panel next to the individual knobs 18. On the centre console between throttle and propeller levers 19. On the side of the throttle quadrant next to tension adjustment knob 20. Next to trim switch on the centre console 21. Next to instrument and map light switches on the centre console 22. Next to fuel shut-off valve in correct position DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 2 - 14 23. Next to canopy release handles Inside Left (partially coloured red) Inside Right (partially coloured red) Outside Left Outside Right 24. Next to ELT (if installed) to indicate switch position for EBC 102A ELT model for EBC 502 ELT model 25. Next to Headset Jacks on the Back Rest Pilot side (LH) Co-pilot side (RH) DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations Doc # 202-100-VLA 22 August, 2006 Page Revision 4 2 - 15 26. On the LH side of baggage compartment 27. On the brake fluid reservoirs (rudder pedals) 30. On coolant equalizing reservoir 32. Next to fuel filler cap 28. On inside of oil filler door (coloured red) 29. On oil filler cap 31. On coolant dispatcher vessel Hydraulic Fluid MIL-H-5606 DO NOT ADD WATER TO THIS SYSTEM STOP! EVANS NPG+ WATERLESS COOLANT ONLY DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 2 - 16 33. On fuselage upper skin behind cockpit (only if ELT is installed), coloured yellow 35. Under each wing and tail skid plate 36. Around Stall Warning Hole in left wing 37. On Nose Landing Gear Strut 38. On Main Landing Gear Strut 34. On fuselage underside (belly), by left wing DIAMOND AIRCRAFT DA 20/100 Flight Manual Limitations Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 2 - 17 2.16. DEMONSTRATED CROSSWIND COMPONENT The maximum demonstrated crosswind component is 15 kts. (27 km/h). 2.17. TEMPERATURE LIMITS Limits for outside air temperature and temperature of the structure for the operation of the airplane: Maximum T/O Temperature : 131°F (55°C) Structural Temperature limit For Indicator see pg.4-3 DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures Doc # 202-100-VLA November 18, 2003 Page Revision 2 3 - 1 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 I. Insufficient Engine Power 3- 3 II. Engine Inoperative 3- 4 (c) Engine Failure during Flight I. Engine Running Roughly 3- 4 II. Loss of Oil Pressure 3- 4 III. Loss of Fuel Pressure 3- 4 IV. Restarting the Engine with Propeller Windmilling 3- 5 V. Restarting the Engine with Propeller at Full Stop 3- 6 3.3.2. Emergency Landing (a) Emergency Landing with Engine Off 3- 7 (b) Precautionary Landing with Engine Power Available 3- 7 3.3.3. Fire (a) Engine Fire during Start on the Ground 3- 9 (b) Engine Fire during Flight 3- 9 (c) Electrical Fire including Smoke during Flight 3- 9 (d) Electrical Fire including Smoke on the Ground 3-10 (e) Cabin Fire during Flight 3-10 3.3.4. Icing Unintentional Flight into Icing Area 3-11 3.3.5. Recovery from Unintentional Spin 3-11 3.3.6. Landing with Defective Tire on Main Landing Gear 3-12 3.3.7. [Intentionally left blank] 3-12 3.3.8. Gliding 3-13 3.3.9. Electrical Power Failure 3-13 3.3.10. Flap System Failure 3-15 3.3.11. Starter Failure 3-15 3.3.12. Avionics System Failure 3-16 3.3.13. Trim System Failure 3-17 3.3.14. Instrument Panel Lighting Failure 3-18 3.3.15. Tachometer failure 3-18 DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 2 3.1. INTRODUCTION The following chapter contains check-lists as well as descriptions of the recommended procedures in case of an emergency. Since it is impossible to present in the Flight Manual all emergency situations which may occur, knowledge of the airplane and experience of the pilot are essential in rectifying such problems. 3.2. AIRSPEEDS DURING EMERGENCY PROCEDURES vIAS kts mph km/h Engine failure after take-off with flaps in T/O position 60 68 110 Manoeuvring Speed 104 120 193 Airspeed for best glide angle Wing Flaps in T/O Position 1653 lbs (750 kg) 73 84 135 Wing Flaps in T/O-Position 1322 lbs (600 kg) 66 76 121 Precautionary Landing (with power and Wing Flaps in landing position) 57 66 106 Emergency landing with engine off (Wing Flaps in T/O or LDG position) 57 66 106 Emergency landing with engine off (Wing Flaps UP) 65 75 120 DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 3 3.3. EMERGENCY PROCEDURES - CHECKLISTS 3.3.1. Engine Failures (a) Engine Failure during Take-off Run 1. Throttle IDLE 2. Brakes as required (b) Engine Failure after Take-Off I. INSUFFICIENT ENGINE POWER 1. Airspeed (vIAS ) 60 kts / 68 mph / 110 km/h 2. Throttle FULL 3. Carburetor Heat ON 4. Choke OFF 5. Fuel Shut-off Valve OPEN 6. Ignition Switch BOTH 7. Electric Fuel Pump ON 8. Propeller Speed Control Lever max. RPM WARNING If adequate engine performance cannot be restored immediately, prepare for an emergency landing. If possible, land straight ahead, avoiding obstacles. Shortly before landing: 9. Fuel Shut-off Valve CLOSED 10. Ignition Switch OFF 11. Master Switch (Battery) OFF DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 4 II. ENGINE INOPERATIVE Perform emergency landing according to paragraph 3.3.2. (c) Engine Failure during Flight I. ENGINE RUNNING ROUGHLY 1. Carburetor Heat ON 2. Electric Fuel Pump ON 3. Choke check OFF 4. Fuel Shut-off Valve check OPEN 5. Ignition Switch cycle L - BOTH - R - BOTH 6. Throttle at present position 7. No Improvement reduce throttle to minimum required power, land as soon as possible. II. LOSS OF OIL PRESSURE 1. Oil Temperature check 2. If Oil Pressure drops below Green Arc but Oil Temperature is normal land at nearest airfield If Oil Pressure drops below Green Arc and Oil Temperature is rising reduce throttle to minimum required power; land as soon as possible. Be prepared for engine failure and emergency landing III. LOSS OF FUEL PRESSURE 1. Electric Fuel Pump ON, and land at nearest suitable airport 2. If Fuel Pressure Warning Light does not extinguish Land at nearest suitable airport. Be prepared for engine failure and emergency landing. DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 5 IV. RESTARTING THE ENGINE WITH PROPELLER WINDMILLING As long as the airspeed (vIAS ) is at least 54 kts / 62 mph / 100 km/h, the propeller will continue to windmill. 1. Airspeed (vIAS ) 70 kts / 81 mph / 130 km/h 2. Wing Flaps T/O Position 3. Propeller Speed Control Lever max. RPM 4. Fuel Shut-off Valve OPEN 5. Ignition Switch BOTH 6. Electric Fuel Pump ON 7. Throttle 3/4 in (2 cm) forward If the engine does not start within 10 seconds: Cold Start 8. Throttle IDLE 9. Choke ON (Pulled) 10. Ignition Switch START DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 6 V. RESTARTING THE ENGINE WITH PROPELLER AT FULL STOP 1. Electrically Powered Equipment OFF 2. Master Switch (Battery) ON 3. Propeller Speed Control Lever max. RPM 4. Fuel shut off valve OPEN 5. Electric Fuel Pump ON 6. Throttle Cold Start: Warm Start: IDLE 3/4 in (2 cm) forward 7. Choke Cold Start: Warm Start: ON (pulled) OFF 8. Ignition Switch START NOTE The engine may also be re-started by increasing the airspeed by pushing the airplane into a descent and accelerating to approx. (v IAS ) 120 kts / 138 mph / 222 km/h. A loss of 1000 ft / 300 m altitude must be taken into account. After successful re-start: 9. Oil Pressure check 10. Choke OFF 11. Electrically Powered Equipment ON if required 12. Oil Temperature check DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 7 3.3.2. Emergency Landing (a) Emergency Landing Approach with Engine off 1. Airspeed (vIAS ) (Flaps in T/O and LDG position) 57 kts / 66 mph / 106 km/h Airspeed (vIAS ) (Flaps UP) 65 kts / 75 mph / 120 km/h 2. Fuel Shut-off Valve CLOSED 3. Ignition Switch OFF 4. Safety Belts secured 5. Radio Transmit, giving location and intentions 6. Master Switch (Battery) OFF (b) Precautionary Landing with Engine Power Available NOTE A precautionary landing would be required if continuing the flight would endanger the aircraft or its occupants. Such circumstances could include mechanical defects, low fuel quantity or deteriorating weather conditions. 1. Search for a suitable place to land. Special attention must be given to wind direction and obstacles in the approach path 2. Safety Belts secured 3. Initiate Descent 4. Throttle as required 5. Trim as required 6. Wing Flaps (observe permissible speed) as required DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 8 7. Overfly selected landing area (not below 500 ft / 150 m above ground) to confirm suitability and that approach route is free of obstacles 8. Climb up to 1000 ft AGL (if possible) 9. Low pass over flight (around 100 feet) to observe any possible obstacles, such as cables, fences, ditches 10. Climb up to 1000 ft AGL (if possible) 11. Radio Transmit, giving location and intentions 12. Final Approach Throttle as required Propeller Speed Control Lever max. RPM Carburetor Heat ON Electric Fuel Pump ON Wing Flaps LDG Airspeed (vIAS ) 57 kts / 66 mph / 106 km/h 13. Touch-down is to be made with minimum airspeed, nose wheel should be kept above ground as long as possible 14. After Touch-down: Brake as required Fuel Shut-off Valve CLOSED Ignition Switch OFF Master Switch (Battery) OFF NOTE If no suitable level landing area can be found, an up-hill landing should be performed, if possible. DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 9 3.3.3. Fire (a) Engine Fire during Engine-Start-Up on the Ground 1. Fuel Shut-off Valve CLOSED 2. Throttle FULL 3. Master Switch (Battery) OFF 4. Ignition Switch OFF 5. Evacuate Airplane immediately (b) Engine Fire during Flight 1. Fuel Shut-off Valve CLOSED 2. Airspeed (vIAS ) 70 kts / 81 mph / 130 km/h 3. Flaps T/O 4. Throttle FULL 5. Electric Fuel Pump OFF 6. Cabin Heat CLOSED 7. Perform emergency landing with engine off according to paragraph 3.3.2 (c) Electrical Fire including Smoke during Flight 1. Master Switch (Battery) OFF 2. Cabin Air OPEN 3. Fire Extinguisher use only if smoke development continues. CAUTION If fire extinguisher is used, the cabin must be aerated. DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 10 In case the fire is extinguished and electric power is required for continuation of the flight: 4. Avionics Master Switch OFF 5. Electrically Powered Equipment OFF 6. Master Switch (Battery) ON 7. Avionics Master Switch ON 8. Radio ON 9. Land as soon as possible. (d) Electrical Fire including Smoke on the Ground 1. Master Switch (Battery) OFF If engine running: 2. Throttle IDLE 3. Fuel Shut-off Valve CLOSED 4. Ignition Switch OFF 5. Canopy open 6. Fire Extinguisher deploy as required (e) Cabin Fire during Flight 1. Master Switch (Battery) OFF 2. Cabin Air OPEN 3. Cabin Heat CLOSED 4. Fire Extinguisher deploy as required 5. Land as soon as possible CAUTION If fire extinguisher is used, the cabin must be aerated. DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 11 3.3.4. Icing Unintentional Flight into Icing Area 1. Leave icing area (through change of altitude or change of flight direction to reach area with higher outside air temp.). 2. Continue to move control surfaces to maintain their moveability. 3. Carburetor Heat ON 4. Increase RPM to avoid icing of propeller blades (observe maximum RPM) 5. Cabin Heat OPEN CAUTION In case of icing on the leading edge of the wing, the stall speed will increase. CAUTION In case of icing on wing leading edge, erroneous indicating of the airspeed, altimeter, rate of climb and stall warning should be expected. 3.3.5. Recovery from Unintentional Spin 1. Throttle IDLE 2. Rudder fully applied opposite to direction of spin 3. Control Stick ease forward 4. Rudder neutral, after rotation has stopped 5. Wing Flaps UP 6. Elevator pull cautiously Bring airplane from descent into level flight position. Do not exceed maximum permissible speed (vNE ) DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 12 3.3.6. Landing with Defective Tire on Main Landing Gear 1. Final approach with wing flaps in landing position. 2. 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. 3. Land with wing slightly tipped in the direction of the non-defective tire. To increase the maneuvrability during rolling, the nose-wheel should be brought to the ground as soon as possible after touch-down. 4. To ease the load on the defective tire, the aileron should be fully applied in the direction of the non-defective tire. 3.3.7. [Intentionally left blank] DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 13 3.3.8. Gliding 1. Wing Flaps T/O 2. Airspeed at 1653 lbs (750 kg) (vIAS ) 73 kts / 84 mph / 135 km/h 3. Glide Ratio 14, which means at 1000 ft/305m above ground, and with no wind the distance of glide is 2.3 NM (4.25 km) NOTE The glide distance from 1000 ft altitude increases for each 10 kts tail wind by 1968 ft (0.6 km). The glide distance from 1000 ft altitude decreases for each 10 kts head wind by 2296 ft (0.7 km). 3.3.9. Electrical Power Failure a) Total Electrical Power Failure 1. Battery Circuit Breaker If tripped, reset 2. Master Switch (Generator/Battery) check ON 3. If Unsuccessful Land at nearest suitable airport b) Generator Failure GEN. Annunciator Illuminated 1. Master Switch (Generator) Cycle Generator Master Switch OFF - ON 2. Generator Circuit Breaker If tripped, reset 3. Generator CONTROL Circuit Breaker If tripped, reset 4. If Generator can not be brought on-line Switch OFF all non-flight essential electrical consumers. Monitor Ammeter and Voltmeter. Land at nearest suitable airport. NOTE There are 30 minutes of battery life remaining at a discharge load of 20 amperes. DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 14 c) Low Voltage Indication (needle in yellow Arc) I. LOW VOLTAGE INDICATION (NEEDLE IN YELLOW ARC) WHILE AIRPLANE ON GROUND 1. Propeller RPM Increase RPM until needle is in the Green Arc. This should occur before exceeding 1350 RPM. 2. Non-flight essential electrical consumers Switch OFF consumers until needle is in the Green Arc. 3. If needle remains in the yellow arc and the ammeter is indicating to the left of centre (discharge) Discontinue any planned flight activity II. LOW VOLTAGE INDICATION (NEEDLE IN YELLOW ARC) DURING FLIGHT 1. All non-flight essential electrical consumers Switch OFF 2. If needle is remaining in the yellow arc and the ammeter is indicating to the left of centre (discharge): Generator Failure: Refer to paragraph 3.3.9 (b) III. LOW VOLTAGE INDICATION (NEEDLE IN YELLOW ARC) DURING LANDING: 1. After landing proceed in accordance with paragraph 3.3.9 (c). WARNING If at any time the Voltmeter needle indicates in the red arc, you should land at the nearest suitable airfield and service the aircraft accordingly before continuing the flight. DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 15 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: • only UP available: - raise approach speed by 5 kts - throttle as required - flat approach angle • only T/O available: - normal approach speed - throttle as required - flat approach angle • only LDG available: - normal landing 3.3.11. Starter Failure Starter does not disengage after starting the engine (continuous whining sound audible). 1. Throttle IDLE 2. Ignition Switch OFF discontinue any planned flight DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 16 3.3.12 Avionics System Failure Total Avionic Failure: 1. Check Avionic Master Circuit Breaker If tripped, re-engage and monitor status, If it trips again, land at nearest suitable airport 2. Check Avionic Master Switch Toggle avionic master switch, if avionic system remains off-line, pull avionic master control circuit breaker and land at nearest suitable airport Radio System Operative, no reception: 1. Microphone Key check for stuck Microphone Key on transceiver display 2. Headphones check, deactivate SQUELCH for a few moments, if SQUELCH not heard, check headset connection Radio System Operative, transmitting not possible: 1. Selected Frequency check if correct 2. Microphone check, if available use different one (headset) Problem cannot be resolved: switch transponder (if available) to "COMM FAILURE" code if required by the situation and permitted by applicable national regulations. DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 17 3.3.13 Trim System Failure Stuck Trim: 1. Circuit breaker check, reset if breaker is tripped 2. Rocker switch depress in both directions, wait 5 minutes, try again NOTE Full range of travel is available for elevator, but expect forces up to 20 lbs. on control stick. 3. Land at nearest suitable airport Runaway of Trim: 1. Control Stick Grip stick and maintain control of airplane 2. Trim motor circuit breaker Pull circuit breaker 3. Rocker Switch Check if depressed If reason for runaway condition is obvious and has been resolved, push in (engage) circuit breaker. NOTE Full travel of the elevator trim system will take approximately 10 seconds. DIAMOND AIRCRAFT DA 20/100 Flight Manual Emergency Procedures Doc # 202-100-VLA 9 March, 2001 Page DOT Approved 3 - 18 3.3.14 Instrument Panel Lighting Failure 1. Rocker Switch, map light ON 2. Rocker Switch, I-panel lighting Cycle Rocker Switch OFF - ON 3. Dimming Control Turn fully clockwise 4. Internal Lighting Circuit Breaker. If tripped, reset 5. If NOT Successful Expect electrical power failure. Use Flashlight Ref. 3.3.9 3.3.15 Tachometer failure Operation at T/O (5 minute) power: 1. Airspeed Do not exceed 110 KIAS Operation at maximum continuous power: 1. Propeller Speed Control Lever Ensure lever is at least ½ inch (10mm) (measured at slot) aft of full forward position. Engine will now be operating at, or below, maximum continuous power. NOTE With propeller speed control lever at least ½ inch (10mm) aft of full forward position, the Max. Permissible Continuous RPM (2260 RPM) cannot be exceeded at any throttle setting and airspeed. However, maximum engine power may not be available. DIAMOND AIRCRAFT DA 20/100 Flight Manual Normal Operating Procedures Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 4 - 1 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. Walk-Around Check 4- 6 4.4.2. Before Starting Engine 4- 9 4.4.3. Starting Engine 4-10 4.4.4. Before Taxiing 4-11 4.4.5. Taxiing 4-11 4.4.6. Before Take-off (Engine Run-up) 4-12 4.4.7. Take-off 4-13 4.4.8. Climb 4-14 4.4.9. Cruise 4-14 4.4.10. Descent 4-15 4.4.11. Landing Approach 4-15 4.4.12. Balked Landing 4-16 4.4.13. After Landing 4-16 4.4.14. Engine Shut-down 4-16 4.4.15. Flight in Rain 4-17 DIAMOND AIRCRAFT DA 20/100 Flight Manual Normal Operating Procedures Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 4 - 2 4.1. INTRODUCTION Chapter 4 provides checklist and amplified procedures for the normal operation. For normal procedures and supplementary information associated with optional systems refer to Chapter 9. 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. vIAS TAKE-OFF kts mph km/h Climb Speed during normal take-off for 15 m (50 ft) obstacle 57 66 106 Best Rate-of-Climb speed at sea level vy (Wing Flaps T/O) 65 75 120 Best Angle-of-Climb speed at sea level vx (Wing Flaps T/O) 57 66 106 vIAS LANDING kts mph km/h Approach speed for normal landing. Wing Flaps in landing position 57 66 106 Balked landing climb speed, Wing Flaps in landing position 57 66 106 Maximum demonstrated crosswind speed during take-off and landing 15 17 27 vIAS CRUISE kts mph km/h Maximum permissible speed in rough air vNO 118 135 218 Maximum permissible speed with full control surface deflections vA 104 120 193 Maximum permissible speed with Wing Flaps extended vFE 81 93 150 DIAMOND AIRCRAFT DA 20/100 Flight Manual Normal Operating Procedures Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 4 - 3 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°F). The indicator is accessed by lifting the flap between the two seatback cushions. The indicator is visible through the cut out in the seat shell backs (ref. fig. 2). At temperatures below the 55°C (131°F) limit, the indicator appears all red with a faint indication of “55” (°C). At temperatures exceeding the 55°C (131° F) limit, the indicator displays a clearly contrasting red “55”(°C) on a black background (ref. fig.1). NOTE At temperatures approaching the limit, the background will progressively darken prior to turning black; this indicates acceptable temperatures. Red “55”on black background indicates that structural temperature limit is exceeded. Flight is prohibited. All red indicates that structural temperature is below limit. Flight is permitted. Figure 1 Figure 2 DIAMOND AIRCRAFT DA 20/100 Flight Manual Normal Operating Procedures Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 4 - 4 [ INTENTIONALLY LEFT BLANK ] DIAMOND AIRCRAFT DA 20/100 Flight Manual Normal Operating Procedures Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 4 - 5 4.4. NORMAL OPERATION CHECKLIST 4.4.1. Preflight Inspection I. In-Cabin Check 1. Structural Temperature Indicator (if OAT exceeds 38°C (100°F)) check that Structural Temperature does not exceed 55°C (131°F) 2. Airplane Documents check 3. Flight Control Lock removed 4. Flight Controls check for proper direction of movement 5. Ignition Key pulled out 6. Carburetor Heat free, OFF 7. Cabin Heat free 8. Choke free, self-resetting 9. Parking Brake free 10. Throttle free, IDLE 11. Propeller Speed Control Lever free, max. RPM 12. Master Switch (Battery) ON 13. Warning Lights (Gen., Fuel Press., and Canopy) illuminated 14. Fuel Quantity sufficient 15. Engine Gauges, Ammeter and Voltmeter check 16. Circuit Breakers pressed in 17. Map Light operational 18. Instrument Lights operational and dimmable 19. Trim NEUTRAL 20. Wing Flaps (Indicator- and Flap Actuation) check, extend and retract fully 21. Trim and Flap Indicator Lights operational and dimmable 22. Exterior Lights operational as required 23. Master Switch (Battery) OFF 24. Foreign Object Inspection done 25. Emergency Locator Transmitter (ELT): EBC Model 502 - ARM EBC Model 102A - OFF 26. Fire Extinguisher check 27. Baggage stowed, baggage net attached 28. Canopy clean, undamaged DIAMOND AIRCRAFT DA 20/100 Flight Manual Normal Operating Procedures Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 4 - 6 II. Walk Around Check and Visual Inspection DIAMOND AIRCRAFT DA 20/100 Flight Manual Normal Operating Procedures Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 4 - 7 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. Left Main Landing Gear a) Landing Gear Strut visual inspection b) Wheel Fairing visual inspection c) Tire Pressure (33 psi / 2.3 bar) check d) Tire, Wheel, Brake visual inspection e) Wheel Chocks remove 2. Left Wing a) Entire Wing visual inspection b) Stall Warning check (suck on opening) c) Pitot-Static Probe clean, holes open d) Tie down remove e) Taxi and Landing Lights visual inspection f) Wing Tip, Position Lights and Strobe visual inspection g) Aileron Balancing Weight visual inspection h) Aileron including Inspection Panel visual inspection i) Wing Flap including Inspection Panel visual inspection 3. Fuselage a) Skin visual inspection b) Tank Vent check c) Tank Drain drain water d) Fuel Quantity visual inspection (use fuel pipette) e) Antennas visual inspection DIAMOND AIRCRAFT DA 20/100 Flight Manual Normal Operating Procedures Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 4 - 8 4. Empennage a) Stabilizers and Control Surfaces visual inspection b) Tie down remove c) Trim Tabs visual inspection 5. Right Wing a) Entire Wing visual inspection b) Wing Flap including Inspection Panel visual inspection c) Aileron including Inspection Panel visual inspection d) Aileron Balancing Weight visual inspection e) Wing Tip, Position Lights and Strobe visual inspection f) Tie down remove 6. Right Main Landing Gear a) Landing Gear Strut visual inspection b) Wheel Fairing visual inspection c) Tire Pressure (33 psi / 2.3 bar) check d) Tire, Wheel, Brake visual inspection e) Wheel Chocks remove 7. Nose a) - Oil check level by using dip-stick. min / max range is indicated by flat area of stick - Coolant Level must be between dip-stick markings, refill if required. b) Cowling visual inspection c) Air Intakes (five) free d) Propeller visual inspection, Ground Clearance; minimum: approx. 25 cm (10 in). e) Propeller Blades perform Pitch Check by Hand f) Spinner visual inspection g) Nose Gear visual inspection, towbar removed h) Wheel Fairing visual inspection i) Tire Pressure (26 psi / 1.8 bar) check j) Tire and Wheel visual inspection k) Wheel Chocks remove DIAMOND AIRCRAFT DA 20/100 Flight Manual Normal Operating Procedures Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 4 - 9 4.4.2. Before Starting Engine 1. Preflight Inspection performed 2. Pedals adjust, lock 3. Passenger Briefing performed 4. Safety Belts fasten 5. Parking Brake set 6. Controls free 7. Fuel Shut-off Valve OPEN 8. Carburetor Heat OFF 9. Throttle IDLE 10. Propeller Speed Control Lever max. RPM 11. Friction Device of Throttle Quadrant adjust 12. Avionics Master Switch OFF 13. Master Switch (Battery/Generator) ON 14. Generator Warning Light illuminated 15. Fuel Pressure Warning Light illuminated 16. Exterior Lights as required 17. Instrument Panel Lighting as required 18. Canopy Close and Secure 19. Canopy Locking Warning Light OFF NOTE Under certain circumstances, activation of the fuel pressure warning light might take as long as 10 minutes after shutting down the engine or switching off the electric fuel pump. DIAMOND AIRCRAFT DA 20/100 Flight Manual Normal Operating Procedures Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 4 - 10 4.4.3. Starting Engine NOTE Extreme low temperatures require that the engine be preheated prior to engine start. Satisfactory engine starts have been demonstrated at -31ºF (-35ºC) OAT after a 2 hour preheat with the Tannis TAS100-27 preheat system. 1. Electric Fuel Pump ON (noise of pump audible) 2. Fuel Pressure Warning Light OFF 3. Throttle - Cold Start - Warm Engine IDLE approximately 3/4 in (2 cm) forward 4. Choke - Cold Start - Warm Engine ON, fully pulled and hold OFF 5. Toe Brakes Hold 6. Propeller Area Clear WARNING Ensure that propeller area is clear! 7. Ignition Key START NOTE During extreme cold weather starts, hold the choke on until the engine starts to warm up. 8. Choke OFF 9. Throttle maximum 1500 RPM 10. Oil Pressure within green range after maximum of 10 seconds CAUTION If Oil Pressure is below 12 psi (0.8 bar) shut down engine immediately (max. 10 seconds delay). NOTE Oil Pressure may advance to the yellow arc until Oil Temp. reaches normal operating temperatures. NOTE Activate starter for max. 10 sec. only, followed by a cooling period of 2 min. 11. Generator Warning Light OFF 12. Exterior Lights as required 13. Electric Fuel Pump OFF DIAMOND AIRCRAFT DA 20/100 Flight Manual Normal Operating Procedures Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 4 - 11 4.4.4. Before Taxiing 1. Avionics Master Switch ON 2. Flight Instruments and Avionics set 3. Engine Gauges check 4. Voltmeter check, ensure needle is in the green arc. Increase RPM to achieve or turn OFF non-flight essential electrical consumers 5. Warning Lights (Gen., Fuel Press., Canopy) push to test 6. Parking Brake release CAUTION Warm-up engine to a minimum Oil Temperature of 122° F (50° C) at 1100 to 1500 RPM (also possible during taxi). 4.4.5. Taxiing 1. Brake check 2. Direction Control check 3. Flight Instruments and Avionics check 4. Compass check CAUTION At high Propeller RPM the propeller may be damaged by loose sand, gravel or water. DIAMOND AIRCRAFT DA 20/100 Flight Manual Normal Operating Procedures Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 4 - 12 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. 1. Toe Brakes hold 2. Safety Belts fastened 3. Canopy closed and locked 4. Fuel Pressure Warning Light OFF (If light illuminates, maintenance action is required and flight should not be initiated ) 5. Fuel Shut-off Valve check OPEN 6. Fuel Quantity Indicator check 7. Engine Gauges within green range 8. Trim NEUTRAL 9. Controls free 10. Throttle 1700-1800 RPM 11. Propeller Speed Control Lever Cycle 3 times (RPM drop: 50 - 250 RPM) 12. Ignition Switch Cycle L - BOTH - R - BOTH (Max. RPM drop: 150 RPM) (Max. RPM difference (L/R): 50 RPM) (Min. RPM difference (L/R): none, but RPM drop must be noticeable) 13. Throttle 1500 RPM 14. Carburetor Heat ON RPM drop: max. 50 RPM; 15. Throttle IDLE 16. Carburetor Heat OFF 17. Circuit Breakers check pressed IN 18. Electric Fuel Pump ON 19. Wing Flaps T/O 20. Parking Brake release DIAMOND AIRCRAFT DA 20/100 Flight Manual Normal Operating Procedures Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 4 - 13 4.4.7. Take-off 1. Electric Fuel Pump check ON 2. Master Switch (Battery/Generator) check ON 3. Ignition Switch check BOTH 4. Carburetor Heat check OFF 5. Wing Flaps check T/O 6. Propeller Speed Control Lever check max. RPM 7. Throttle Check RPM FULL 2260 RPM to 2385 RPM 8. Elevator - at beginning of rolling NEUTRAL 9. Directional Control maintain with rudder NOTE In crosswind conditions, directional control can be enhanced by using the single wheel brakes. Note that using the brakes for directional control increases the take-off roll distance. 10. Rotate (vIAS) 51 kts / 59 mph / 95 km/h 11. Climb Speed (vIAS) 57 kts / 66 mph / 106 km/h CAUTION For the shortest possible take-off distance to clear a 15 m (50 ft) obstacle: Lift-off Speed (vIAS) 54 kts / 62 mph / 100 km/h Climb Speed (vIAS) 57 kts / 66 mph / 106 km/h 12. Propeller Speed Control Lever 2260 RPM (after reaching safe height) 13. Electric Fuel Pump OFF NOTE In order to avoid excessive noise, the propeller speed should be reduced to 2260 RPM as soon as a safe flight altitude has been reached. DIAMOND AIRCRAFT DA 20/100 Flight Manual Normal Operating Procedures Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 4 - 14 4.4.8. Climb 1. Propeller Speed Control Lever 2260 RPM 2. Throttle FULL 3. Engine Gauges within green range 4. Wing Flaps T/O 5. Airspeed 65 kts / 75 mph / 120 km/h 6. Trim adjust NOTE The best rate of climb speed decreases with increasing altitude. NOTE Electric fuel pump ON above 13000 ft. Speeds [ vIAS ] Altitude flaps T/O flaps UP feet kts mph km/h kts mph km/h 0 - 4000 65 75 120 69 79 128 4000 - 7000 63 73 117 65 75 120 7000 -10000 62 71 115    above 10000 59 68 110    4.4.9. Cruise 1. Throttle as required 2. Propeller Speed Control Lever 1700 - 2260 RPM NOTE For favorable manifold pressure/RPM combinations refer to Chapter 5. NOTE Electric fuel pump ON above 13000 ft. 3. Wing Flaps UP 4. Trim as required 5. Engine Gauges check DIAMOND AIRCRAFT DA 20/100 Flight Manual Normal Operating Procedures Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 4 - 15 4.4.10. Descent 1. Flight Instruments and Avionics adjust 2. Throttle as required 3. Propeller Speed Control Lever 1700 - 2260 RPM 4. Carburetor Heat as required NOTE To achieve a fast descent: Propeller Speed Control Lever 2260 RPM Throttle IDLE Carburetor Heat ON NOTE If RPM drops and then rises, suspect carburetor icing and leave Carb Heat ON. Otherwise turn Carb Heat OFF. Wing Flaps UP Airspeed 118 kts / 135 mph / 218 km/h 4.4.11. Landing Approach 1. Seat Belts fastened 2. Electric Fuel Pump ON 3. Lights as required 4. Master Switch (Battery/Generator) check ON 5. Ignition Switch check BOTH 6. Carburetor Heat ON NOTE If RPM drops and then rises, suspect carburetor icing and leave Carb Heat ON. Otherwise turn Carb Heat OFF. 7. Throttle as required 8. Airspeed max. 81 kts / 93 mph / 150 km/h 9. Wing Flaps T/O 10. Trim as required DIAMOND AIRCRAFT DA 20/100 Flight Manual Normal Operating Procedures Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 4 - 16 11. Propeller Speed Control Lever max. RPM 12. Wing Flaps LDG 13. Approach Speed 57 kts / 66 mph / 106 km/h CAUTION For strong headwind, crosswind, danger of wind-shear or turbulence, a higher approach speed should be selected. 4.4.12. Balked Landing 1. Propeller Speed Control Lever max. RPM 2. Throttle FULL 3. Carburetor Heat OFF 4. Wing Flaps T/O 5. Airspeed 57 kts / 66 mph / 106 km/h 4.4.13. After Landing 1. Throttle as required 2. Wing Flaps UP 3. Carburetor Heat OFF 4. Exterior Lights as required 5. Electric Fuel Pump OFF 4.4.14. Engine Shut-down 1. Throttle IDLE 2. Parking Brake set 3. ELT Check (by listening to 121.5 MHZ for signal) 4. Avionics Master Switch OFF 5. Electric Consumers OFF 6. Ignition Switch OFF 7. Instrument Panel Lighting OFF DIAMOND AIRCRAFT DA 20/100 Flight Manual Normal Operating Procedures Doc # 202-100-VLA 20 December, 2000 Page DOT Approved 4 - 17 8. Master Switch (Battery) OFF 9. Tie Downs and Wheel Chocks as required NOTE In case of post ignition due to hot weather conditions, the ignition should be switched on, choke pulled and after approximately 3 seconds, ignition should be turned off again. 4.4.15. Flight in Rain NOTE Flight performance might be reduced, especially for the T/O-distance and the maximum horizontal air speed. The influence on flight characteristics of the airplane is negligible. Flights through heavy rain should be avoided due to the reduced visibility DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance Doc # DA202-100-VLA March 19, 2004 Page Revision 3 5 - 1 CHAPTER 5 PERFORMANCE 5.1 INTRODUCTION 5- 2 5.2 USE OF PERFORMANCE TABLES AND DIAGRAMS 5- 2 5.3 PERFORMANCE TABLES AND DIAGRAMS 5- 3 5.3.1 Figure 5.1: Airspeed Calibration 5- 3 5.3.2 Figure 5.2: Cruising Performance 5- 4 5.3.3 Figure 5.3: Stall Speeds 5- 5 5.3.4 Figure 5.4: Wind Data 5- 6 5.3.5 Figure 5.5: Take-Off Distances 5- 7 5.3.6 Figure 5.6: Climb Performance / Service Ceiling 5- 9 5.3.7 [INTENTIONALLY LEFT BLANK] 5-10 5.3.8 Figure 5.8: Cruising Speed (True Airspeed) 5-11 5.3.9 Figure 5.9: Maximum Flight Duration 5-12 5.3.10 Figure 5.10: Climb Performance during Balked Landing 5-13 5.3.11 Landing Distances 5-14 5.4 NOISE DATA 5-15 DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance Doc # 202-100-VLA 20 December, 2000 Page Issue 1 5 - 2 5.1. INTRODUCTION The performance tables and diagrams on the following pages have been prepared to illustrate the performance you may expect from your airplane as well as to assist you in precise flight planning. The data presented in these tables and diagrams has been derived from test-flights using an airplane and engine in good operating condition, and was corrected to standard atmospheric conditions [59° F (15° C) and 29.92 in. Hg (1013.25 mbar) at sea level ]. The performance tables do not take into account the expertise of the pilot or the maintenance condition of the airplane. The performance illustrated in the tables can be achieved if the indicated procedures are followed and the airplane is in good maintenance condition. Note that the flight duration data does not include a fuel reserve. The fuel consumption during cruise is based on propeller RPM and manifold pressure settings. Some undefined variables such as the operating condition of the engine, contamination of the aircrafts surface, or turbulence could have influences on flight distance and flight duration. For this reason, it is of utmost importance that all available data is used when calculating the required amount of fuel for a flight. For flight operation without wheel fairings the resulting performance variations is given in %. 5.2. USE OF PERFORMANCE TABLES AND DIAGRAMS The performance data is shown in the form of tables and diagrams to illustrate the influence of the different variables. These tables contain sufficiently detailed information to plan any flight with the necessary precision and safety on the conservative side. DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance Doc # 202-100-VLA 20 December, 2000 Page DOT-Approved 5 - 3 5.3. PERFORMANCE TABLE AND DIAGRAMS 5.3.1. Figure 5.1: Airspeed System Calibration Assumes zero indicator error Example: vIAS = 93 kts equals vCAS = 95 kts. 160 110 40 50 60 70 80 90 100 120 130 140 150 40 50 60 70 80 90 100 110 120 130 140 150 160 T/O, LDG UP VIAS [kts] VCAS [kts] DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance Doc # 202-100-VLA 20 December, 2000 Page Issue 1 5 - 4 5.3.2. Figure 5.2: Cruising Performance Engine power in % of maximum continuous power 55% 65% Pressure altitude Standard Temp. Fuel Flow Fuel Flow Ft. M °C °F Rpm X100 MP In.Hg L/hr Gal/hr Rpm X100 MP In.Hg L/hr Gal/hr 0 0 15 59 19 24.7 13.6 3.6 20 25.7 15.6 4.1 2000 600 11 52 19 24.0 14.4 3.8 20 24.7 16.0 4.2 4000 1200 7 45 19 23.3 15.6 4.1 21 23.3 16.8 4.4 6000 1800 3 38 20 22.0 16.8 4.4 22 22.7 19.6 5.2 8000 2400 -1 31 21 21.0 18.0 4.8 22 21.7 21.2 5.6 10000 3000 -5 24 22 19.7 19.2 5.1 22.6 20.3* 22.4* 5.9* 12000 3600 -8 17 22.6 18.0* 20.4* 5.4* 13000 4000 -11 12 22.6 17.0* 21.5* 5.7* 75% 85% Pressure altitude Standard Temp. Fuel Flow Fuel Flow Ft. M °C °F Rpm X100 MP In.Hg L/hr Gal/hr Rpm X100 MP In.Hg L/hr Gal/hr 0 0 15 59 21 27.0 18.0 4.8 22.6 27.7 22.0 5.8 2000 600 11 52 22 25.7 18.4 4.9 22.6 26.7 22.4 5.9 4000 1200 7 45 22.6 24.3 19.6 5.2 22.6 25.7* 25.2* 6.7* 6000 1800 3 38 22.6 23.3 23.2 6.1 8000 2400 -1 31 22.6 22.0* 23.6* 6.2* Maximum Continuous Power Maximum Take-Off Power Pressure altitude Standard Temp. Fuel Flow Fuel Flow Ft. M °C °F Rpm X100 MP In.Hg L/hr Gal/hr Rpm X100 MP In.Hg L/hr Gal/hr 0 0 15 59 22.6 28.3 26.0 6.9 23.8 29.7* 30.0 7.9* 2000 600 11 52 22.6 27.7* 26.8* 7.1* 4000 1200 7 45 22.6 25.7* 25.2* 6.7* 6000 1800 3 38 Fuel flow is given in US-gal. Data labelled * give a basis for interpolation. These values may not be attained at the stated altitude. To maintain constant performance at non standard temperature gradient: Raise manifold pressure by 0.7 in.Hg at ISA + 18° F (10° C) Lower manifold pressure by 0.7 in.Hg at ISA - 18° F (10° C) NOTE To keep engine wear to a minimum, engine operation below 1900 RPM is not recommended. DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance Doc # 202-100-VLA 20 December, 2000 Page DOT-Approved 5 - 5 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° IAS CAS IAS CAS IAS CAS IAS CAS UP 41 50 46 53 55 59 69 70 T/O 39 46 44 49 51 54 63 65 LDG 37 44 41 47 49 52 59 62 Stall speeds in mph Bank Angle Flaps 0° 30° 45° 60° IAS CAS IAS CAS IAS CAS IAS CAS UP 47 57 53 62 63 68 79 81 T/O 45 52 51 56 59 62 72 75 LDG 43 50 47 54 56 60 68 72 Stall speeds in km/h Bank Angle Flaps 0° 30° 45° 60° IAS CAS IAS CAS IAS CAS IAS CAS UP 76 93 85 99 101 109 127 130 T/O 72 84 81 91 94 100 117 120 LDG 69 81 76 87 91 96 109 115 DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance Doc # 202-100-VLA 20 December, 2000 Page DOT-Approved 5 - 6 5.3.4. Figure 5.4: Wind Components Maximum demonstrated crosswind component: 15 kts (27 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) DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance Doc # DA202-100-VLA March 19, 2004 Page Revision 3 5 - 7 5.3.5. Figure 5.5: Take-off Distance Conditions: - maximum take-off power - lift-off speed 53 KIAS and speed for climb over obstacle 57 KIAS - level runway, paved - Wing Flaps in Take-Off Position (T/O) O u s id e A ir T e m p e ra tu re (° F ) Hp = -2000 ft Hp = 0 ft Hp = 2000 ft Hp = 4000 ft Hp = 6000 ft Hp = 8000 ft Hp = 10000 ft Hp = 12000 ft Std Temp -2 0 -1 0 0 1 0 2 0 3 0 4 0 O u s id e A ir T e m p e ra tu re (° C ) -4 1 4 3 2 5 0 6 8 8 6 1 0 4 A irc ra ft W e ig h t (lb s .) 6 0 0 6 2 5 6 5 0 6 7 5 7 0 0 7 2 5 7 5 0 A irc ra ft W e ig h t (k g ) 1 6 5 3 1 5 9 8 1 5 4 3 1 4 8 8 1 4 3 3 1 3 7 8 1 3 2 3 . 0 5 1 0 1 5 2 0 H e a d w in d C o m p o n e n t (k n o t) O b s ta c le H e ig ht (f e e t) 0 5 1 0 1 5 O b s tac le H e ig h t (m ) 0 1 6 3 3 4 9 5 0 0 7 0 0 9 0 0 1 1 0 0 1 3 0 0 1 5 0 0 1 7 0 0 1 9 0 0 2 1 0 0 2 3 0 0 2 5 0 0 2 7 0 0 2 9 0 0 3 1 0 0 3 3 0 0 3 5 0 0 . 1 5 2 2 5 2 3 5 2 4 5 2 5 5 2 6 5 2 7 5 2 8 5 2 9 5 2 1 0 5 2 Takeoff Distance (fe e t ) (m ) (fe e t ) (m ) Example: - Pressure altitude: 3000 ft - Outside temperature: 15° C (59° F) - Weight : 1598 lbs (725 kg) -Headwind: 10 kts Result: - Take-off roll distance: 1025ft (312.4 m) - Take-off distance to clear a 15 m (50 ft) obstacle: 1425 ft (434.3 m) NOTE Poor maintenance condition of the airplane, deviation from the given procedures as well as unfavourable outside conditions (high temperature, rain, unfavourable wind conditions, including cross-wind) could increase the take-off distance considerably. For take-off from dry, short-cut grass covered runways, the following corrections must be taken into account, compared to paved runways: DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance Doc # DA202-100-VLA March 19, 2004 Page Revision 3 5 - 8 • Grass up to 5cm (2in) deep: 10% increase in take-off roll distance; • Grass 5 to 10cm (2 to 4in) deep: 15% increase in take-off roll distance; • Grass deeper than 10cm (4in): 25% increase in take-off roll distance. On wet soft grass covered runways with grass deeper than 10cm (4in), the take-off roll distance might be increased by as much as 40%. This information is provided for guidance purposes only and has not been demonstrated. The dashed lines in the above diagram (wind component) represent tailwind. DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance Doc # DA202-100-VLA March 19, 2004 Page Revision 3 5 - 9 5.3.6. Figure 5.6 : Climb Performance / Service Ceiling Service Ceiling (in standard conditions): 17600 ft (5365 m) Best Rate-of-Climb Speed with Wing Flaps in Take-Off Position (T/O): 65 kts / 75 mph / 120 km/h -2000 0 2000 4000 6000 8000 10000 12000 14000 16000 18000 -20 -15 -10 -5 0 5 10 15 20 25 30 TEMPERATURE (°C) PRESSURE ALTITUDE (FEET) -4 5 14 23 32 41 50 59 68 77 86 TEMPERATURE (°F) 0 2000 4000 6000 8000 10000 12000 14000 16000 1 0 0 2 0 0 3 0 0 4 0 0 5 0 0 6 0 0 7 0 0 8 0 0 9 0 0 1 0 0 0 RO C (ft/m in ) 0 .5 1 .0 1 .5 2 .0 2 .5 3 .0 3 .6 4 .1 4 .6 5 .1 m /s e c 1 4 3 3 lb s / 6 5 0 kg 1 5 4 3 lb s / 7 0 0 kg 1 6 0 9 lb s / 7 3 0 kg 1 6 5 3 lb s / 7 5 0 kg Standard Temperature Example: Pressure Altitude: 5000 ft (1524 m) OAT: 46° F (8° C) Weight : 1477 lbs (670 kg) Result: Climb performance: 554 ft/min (2.82 m/s) CAUTION In case of operation without wheel fairings the climb performance is reduced by approximately 3%. DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance Doc # DA202-100-VLA March 19, 2004 Page Revision 3 5 - 10 5.3.7. [INTENTIONALLY LEFT BLANK] [ INTENTIONALLY LEFT BLANK ] DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance Doc # DA202-100-VLA March 19, 2004 Page Revision 3 5 - 11 5.3.8. Figure 5.8: Cruising Speed (True Airspeed) Diagram for true airspeed (TAS) calculation at selected power level. Flight mass 750 kg (1653 lbs) and Flaps UP. Temperature (°F) -4 +14 +32 +50 +68 +86 Temperature (°C) True Airspeed (knots) Example: Pressure altitude: 9500 ft Temperature: 57° F (14° C) power setting: 55 % Result: True airspeed (TAS): 116 kts (215 km/h) CAUTION In case of operation without wheel fairings the maximum cruising speed is reduced by approximately 5%. DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance Doc # DA202-100-VLA March 19, 2004 Page Revision 3 5 - 12 5.3.9. Figure 5.9: Maximum Flight Duration Diagram for calculation of the maximum flight duration depending on fuel availability. 600 m / 2000 ft. 600 m / 2000 ft. 1200 m / 4000 ft. 1800 m / 6000 ft. 1800 m / 6000 ft. 1200 m / 4000 ft. 600 m / 2000 ft. 0 10 20 30 40 50 60 70 80 0 1 2 3 4 5 6 Flight Time (hour), no reserve Fuel Quantity (litres) 0 2 4 6 8 10 12 14 16 18 20 - 3/4 1/4 1 1/4 2 1/4 3 1/4 4 1/4 5 1/4 Flight Time (hour), 45 minute reserve Fuel Quantity (US Gal) 55 % 75 % 95 % Example: Fuel quantity: 13.2 US gal (50 liters) Pressure Altitude 6000 ft Power Setting: 75% Result: Possible flight time without reserve: 2:11 h:min Possible flight time with reserve of 45 mins: 1:26 h:min DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance Doc # DA202-100-VLA March 19, 2004 Page Revision 3 5 - 13 5.3.10. Figure 5.10: Climb Performance during Balked Landing Conditions: Speed = 57 kts / 66 mph / 106 km/h Wing Flaps in Landing Position (LDG) Weight 750 kg (1653 lbs) most forward center of gravity max take-off power 0 100 200 300 400 500 600 700 800 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 ROC (ft/min) 0.00 0.51 1.02 1.52 2.03 2.54 3.05 3.56 4.06 ROC ( m/sec) Hp (ft) Hp (m) Example: Pressure altitude: 2250 ft (685 m) Outside temperature: 59° F (15° C) Result: Climb performance during balked landing: 320 ft/min. (1.63 m/sec) CAUTION In case of operation without wheel fairings the climb performance is reduced by approximately 3%. DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance Doc # DA202-100-VLA March 19, 2004 Page Revision 3 5 - 14 5.3.11. Landing Distance Conditions: - Throttle: Idle - Maximum T/O Weight - Propeller Speed Control Lever: max RPM - Approach Speed 57 kts / 66 mph / 106 km/h - Level Runway, paved - Wing Flaps in Landing position (LDG) - Standard Setting, MSL Landing distance over a 15 m (50 ft) obstacle: approx. 1532 ft (467 m) Landing roll distance: approx. 790 ft (241 m) Figure 5.11: Landing and Rolling Distances for Heights Above MSL Height above MSL ft. (m) 0 (0) 1000 (305) 2000 (610) 3000 (914) 4000 (1219) 5000 (1524) Landing Distance ft. (m) 1532 (467) 1593 (486) 1653 (504) 1714 (522) 1775 (541) 1836 (560) Landing Roll Distance ft. (m) 790 (241) 813 (248) 837 (255) 862 (263) 889 (271) 916 (279) NOTE Poor maintenance condition of the airplane, deviation from the given procedures as well as unfavourable outside conditions (high temperature, rain, unfavourable wind conditions, including cross-wind) could increase the landing distance considerably. For landings on dry, short-cut grass covered runways, the following corrections must be taken into account, compared to paved runways: • Grass up to 5cm (2in) deep: 5% increase in landing roll distance; • Grass 5 to 10cm (2 to 4in) deep: 15% increase in landing roll distance; • Grass deeper than 10cm (4in): 25% increase in landing roll distance. On wet soft grass covered runways with grass deeper than 10cm (4in), the landing roll distance might be increased by as much as 40%. This information is provided for guidance purposes only and has not been demonstrated. DIAMOND AIRCRAFT DA 20/100 Flight Manual Performance Doc # DA202-100-VLA March 19, 2004 Page Revision 3 5 - 15 5.4 NOISE DATA a) Noise limit according to FAR 36, Appendix G: 75.0 dB (A) Noise value measured: 63.8 dB (A) b) Noise limit according to ICAO Annex 16, Chapter 10: 79.1 dB (A) Noise value measured: 71.7 dB (A) DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance Doc # 202-100-VLA 20 December, 2000 Page DOT-Approved 6 - 1 CHAPTER 6 WEIGHT AND BALANCE / EQUIPMENT LIST 6.1 INTRODUCTION 6-2 6.2 AIRPLANE WEIGHING 6-3 - Figure 6.1 Weighing Report 6-4 6.3 WEIGHT AND BALANCE REPORT 6-5 - Figure 6.2 Weight & Balance Report 6-6 6.4 FLIGHT-WEIGHT AND CENTER OF GRAVITY 6-7 - Figure 6.3 Weight & Balance Diagram 6-8 - Figure 6.4 Calculation of Loading Condition 6-9 - Figure 6.5 Permissible Center of Gravity Range and permissible Flight Weight-Moment 6-10 6.5 EQUIPMENT LIST 6-11 AIRCRAFT SPECIFIC WEIGHT AND BALANCE DOCUMENTS (ENCLOSED AT THE END OF THIS CHAPTER) DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance Doc # 202-100-VLA 20 December, 2000 Page DOT-Approved 6 - 2 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 CG position due to fuel consumption. The procedure for weighing the airplane and calculating the empty weight CG position are given in this Chapter. The aircraft is weighed when new and should be reweighed in accordance with applicable air regulations. Empty weight and the center of gravity are recorded in a Weighing Report and Weight and Balance Report as illustrated in the samples in figure 6.1 and 6.2. The actual report for the aircraft is at the end of this chapter. In case of equipment changes, the new weight and empty weight CG position must be determined by calculation or by weighing and must be entered in the Weight & Balance Report. The following pages are sample forms which can be used for airplane weighing, calculation of the empty weight CG position, and for the determination of the useful load. NOTE After every repair, painting or change of equipment the new empty weight must be determined as required by applicable air regulations. Weight, empty weight CG position and useful load must be entered in the Weight & Balance Report by an authorized person. DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance Doc # 202-100-VLA 20 December, 2000 Page DOT-Approved 6 - 3 6.2. AIRPLANE WEIGHING Pre-weighing conditions: - equipment must be in accordance with the airplane equipment list - brake fluid, lubricant (3.17 US qt / 3 liters), coolant (2.64 US qt / 2,5 liters) and unusable fuel (0.53 US gal./ 2 liters), included 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. Ensure the aircraft is level longitudinally as illustrated on the weighing report (see figure 6.1). With the airplane correctly positioned, a plumb line is dropped from the leading edge of each wing at the root rib to the floor, join these two points to determine the reference datum (RD). From this line use a suspended plumb line aligned with each landing gear to measure the distances D N (nose gear), D L (left main gear) and D R (right main gear). The following formulas apply: Empty Weight: W T = W N + W L + W R lbs [kg] Empty Weight Moment: M = W N x D N + W L x D L + W R x D R in⋅lbs [m⋅kg] Empty Weight CG position : = Empty Weight Moment Empty Weight M WT = in [m] CAUTION Items ahead of RD are considered to have a negative lever arm. Items aft of RD are considered to have a positive lever arm. Record the data in the Weighing Report included at the end of this chapter. The following Sample Weighing Report figure 6.1 is for reference only. DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance Doc # 202-100-VLA 20 December, 2000 Page DOT-Approved 6 - 4 Figure 6.1: Sample Weighing Report (Aircraft Specific report at the end of this chapter.) Model: DA 20/100 S/N: Registration: Data in accordance with TCDS and Flight Manual Reason for Weighing: Reference Datum: Leading edge of wing at root rib Horizontal reference line: 24” Spirit Level placed on Fuselage Canopy Rail (L or R), supported at front by a 2 1/4” spacer as shown below Weighing Conditions: including brake fluid, lubricant, coolant and unusable fuel (3.31 lbs/1.5 kg) Equipment List dated: Support Gross [lbs] ([kg]) Tare [lbs] ([kg]) Net Weight [lbs] ([kg]) Lever Arm [in] ([m]) Nose WN = DN = Main Left WL = DL = Main Right WR = DR = Empty Weight WT = WN + WL + WR = lbs (kg) Empty Weight Moment M = W N x D N + W L x D L + W R x D R = _________________ in lbs [m kg] Empty Weight CG Position Empty Weight Moment Empty Weight M WT = = _________________ in [m] (Positive results indicate, that CG is located aft of RD) Maximum Permissible Useful Load: Maximum Weight [lbs] ([kg]) + Empty Weight [lbs] ([kg]) − Max useful Load [lbs] ([kg]) = Data to be entered into the Flight Manual: see page 6-6 Empty Weight [lbs] ([kg]) Empty- Weight-Moment [in⋅lbs] ([kg⋅m]) Place / Date Inspector’s Stamp Inspector’s Signature DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance Doc # 202-100-VLA 20 December, 2000 Page Issue 1 6 - 5 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 at the end of this chapter. The following Sample Weight and Balance Report figure 6.2. is for reference only. Ensure that you are using the latest weight and balance information when performing a weight and balance calculation DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance Doc # 202-100-VLA 20 December, 2000 Page Issue 1 6 - 6 figure 6.2: Sample Weight and Balance Report (Aircraft specific report at the end of this chapter) Date Description Changes of W eight Actual Signature of Part or Addition (+) Subtraction (-) Empty W eight IN OUT Modification W eight Arm Moment W eight Arm Moment W eight Arm Moment lbs in in.lbs lbs in in.lbs lbs in in.lbs (kg) (m) (kg.m) (kg) (m) (kg.m) (kg) (m) (kg.m) Original Issue Date: Registration: Aircraft Serial No.: Model: DA20-A1/100 KATANA Aircraft Specific Weight and Balance Report DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance Doc # 202-100-VLA 20 December, 2000 Page DOT approved 6 - 7 6.4. FLIGHT WEIGHT AND CENTER OF GRAVITY The following data enables the pilot to operate the DA 20/100 within the required weight and center of gravity limitations. The following diagrams, Figure 6.3 Weight & Balance Diagram Figure 6.4 Calculation of Loading Condition Figure 6.5 Permissible Center of Gravity Range and permissible Flight- Weight -Moment are to be used for calculations of the flight-weight and the center of gravity as follows: 1. The empty weight and the empty-weight-moment of the airplane should be taken from the weighing report or from the weight & balance report and entered into the form "Calculation of Loading Condition" (figure 6.4) in the columns identified with "Your DA 20". 2. Using the Weight & Balance Diagram (see figure 6.3) determine the moment for each part to be loaded, and enter it in the respective column in figure 6.4. 3. Add the weights and the moments of each column (point 4 and point 6 in figure 6.4) and enter the sum in figure 6.5 "Permissible CG Range and Permissible Flight-Weight-Moment" to check if the values are within the permissible limits of the loading range. DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance Doc # 202-100-VLA 9 March, 2001 Page DOT-Approved 6 - 8 Figure 6.3: Weight & Balance Diagram Example: Pilot and Passenger: 380 lbs. (172 kg) Fuel 19.5 US gal. / 74 liters: 117 lbs. ( 53 kg) (6.01 lbs. per US gal./0.72 kg per liter) Baggage 11lbs. (5 kg) Result: Moment of Pilot and Passenger: 2139 in.lbs. (24.60 kgm) Moment of Fuel: 3796 in.lbs. (43.76 kgm) Moment of Baggage 357 in.lbs. (4.12 kgm) DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance Doc # 202-100-VLA 9 March, 2001 Page DOT-Approved 6 - 9 Figure 6.4: Calculation of Loading Condition Calculation of the DA 20 (Example) Your DA 20 Load Limits Weight [lbs] Moment [in.lbs] Weight [lbs] Moment [in.lbs] (Weight [kg]) ([kgm]) (Weight [kg]) ([kgm]) 1. Empty Weight (use the data for your airplane recorded in the equipment list, including unusable fuel, lubricant and coolant). 1145 (520) 12880 (148.40) 2. Pilot and Passenger: Lever Arm: 0.143 m (5.63 in) 380 (172) 2139 (24.60) 3. Baggage: Lever Arm: 0.824 m (32.44 in) 11 (5) 357 (4.12) 4. Total Weight and Total Moment with empty fuel tank (sum of 1. - 3.) 1536 (697) 15376 (177.12) 5. Usable Fuel Load (6.01 lbs. per US gal./0.72 kg per liter) Lever Arm (32.44 in) (0.824 m) 117 (53) 3796 (43.76) 6. Total Weight and Total Moment, taking fuel into account (sum of 4. and 5.) 1653 (750) 19172 (220.88) 7. Find the values for the total weight (1536 lbs. and 1653 lbs.) and the total moment (15376 in lbs. and 19172 in.lbs.) in the center of gravity diagram. Since they are within the limitation range, the loading is permissible. DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance Doc # 202-100-VLA November 18, 2003 Page Revision 2 6 - 10 10.6" (270 mm) 11.4 " (290 mm) 12.2 ' (310 mm) 13.0" (330 mm) 13.8 " (350 mm) 14.5" (370 mm) 15.35" (390 mm) 9.8" (250 mm) 1235 1285 1335 1385 1435 1485 1535 1585 1635 12100 13428 14756 16084 17412 18740 20068 21396 22724 24052 25380 Flight Weight [lbs.] 560 585 610 635 660 685 710 735 Flight Weight [kg.] 1653 -- --750 Figure 6.5: Permissible Center of Gravity Range and permissible Flight-Weight-Moment Permissible Center of Gravity Range [mm/in] Permissable Flight-Weight-Moment DA 20 (Example of page 6-9) Changes during flight (due to fuel consumption) (in*lbs) (Kg*m) 1 1 DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance Doc # 202-100-VLA 20 December, 2000 Page Issue 1 6 - 11 6.5. EQUIPMENT LIST The following table lists the equipment available for this airplane. An Equipment Record of items installed in your specific airplane is included at the end of this chapter. The equipment list comprises the following data: • The item No. containing an alpha character for the equipment group and a sequential number. • Abbreviations: A Avionics I Instruments M Miscellaneous (any equipment other than avionics or instruments) Weight and lever arm of the equipment items are shown in the columns "Weight" and "Arm". NOTE Additional installation of equipment must be carried out in compliance with the specifications in the Maintenance Manual. The columns "Weight" and "Arm" show the weight and the CG position of the equipment with respect to the reference datum. A positive value shows the distance aft of the reference datum, a negative value shows the distance forward of the reference datum. DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance Doc # 202-100-VLA 20 December, 2000 Page Issue 1 6 - 12 Equipment List Seq. No.: Part Description, Manufacturer, Type Weight [lbs] (kg) Arm [in] (m) A 1 ADF King KR87 3.20 (1.45) -20.5 (-0.521) A 2 Slaving Amplifier Century 1D755 1.80 (0.82) +5.5 (+0.140) A 3 ADF ANTENNA King KA44B 2.80 (1.27) +38.5 (+.978) A 4 GPS / Com King KLX135A 4.4 (1.98 -20.5 (-0.521) A 5 DME Antenna King KA60 0.20 (0.09) +18.0 (+0.457) A 6 GPS Antenna Garmin GA56 0.25 (0.11) +16.0 (+0.407) A 7 GPS Antenna King KA91 0.6 (0.27) +16.0 (+0.407) A 8 Marker Beacon Antenna King KA26 0.50 (0.23) +59.0 (+1.499) A 9 Transponder Antenna Bendix/King, KA60 0.20 (0.09) +18.0 (+0.457) A 10 VHF-AM Antenna Comant CI122 0.50 (0.23) +43.5 (+1.105) A 11 Audio Panel King KMA24 1.7 (0.772) -20.5 (-0.521) A 12 Audio Panel Terra TMA350D 1.7 (0.772) -20.5 (-0.521) A 13 Diplexer Comant CI1125 0.25 (0.11) -18.0 (-0.457) A 14 Diplexer Comant CI505 0.20 (0.09) -18.0 (-0.457) A 15 DME King KN64 2.60 (1.18) -20.5 (-0.521) A 16 Encoder SSD120-20 0.80 (0.363) -22.5 (-.571) A 17 Flux Detector Century 1B495 0.40 (0.18) +14.0 (+0.356) A 18 GPS Garmin 155 2.14 (0.97) -20.5 (-0.521) A 19 GPS / Com King KLX135 4.4 (1.98) -20.5 (-0.521) A 20 ADF Indicator King KI227 0.70 (0.32) -15.5 (-0.394) DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance Doc # 202-100-VLA 20 December, 2000 Page Issue 1 6 - 13 Equipment List Seq. No.: Part Description, Manufacturer, Type Weight [lbs] (kg) A21 Hour Meter Hobbs 85000 0.50 (0.227) A22 HSI Indicator Century NSD1000 4.60 (2.09) A23 Nav Indicator King KI208 1.10 (0.499) A24 Nav Indicator King KI209 1.10 (0.499) A25 Outside Air Temperature Indicator Davtron 301F 0.50 (0.227) A26 Intercom PS Engineering PM501 0.53 (0.240) A27 Nav / Com #1 King KX125 3.88 (1.76) A28 Nav / Com #2 King KX125 3.88 (1.76) A29 † Nav / Com #1 King KX155 4.94 (2.24) A30 † Nav / Com #2 King KX155 4.94 (2.24) A31 Remote Switch NAT RS16 0.44 (0.20) A32 Transponder Bendix/King, KT76A 3.00 (1.36) A33 GPS Garmin, GPS150 2.14 (0.97) A34 Chronometer Davtron M800B 0.24 (0.11) A35 Audio Panel King KA134 TSO’d 0.8 (0.36) A36 GPS King KLN 35A 2.07 (0.94) A37 *Emergency Locator Transmitter EBC 502 2.75 (1.25) A38 Emergency Locator Transmitter EBC 102A 2.12 (0.96) * Not approved for use in all countries; check national regulations. † Not all serial numbers are approved in all countries; check national regulations. (KX 155 P/N 069-01024-0042 S/N 25000 and above comply with ICAO ANNEX 10. S/N 24999 and below require Mod 16 to comply with ICAO ANNEX 10.) DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance Doc # 202-100-VLA 20 December, 2000 Page Issue 1 6 - 14 Equipment List Seq. No.: Part Description, Manufacturer, Type Weight [lbs] (kg) Arm [in] (m) I1 Altimeter United, 5934PD3 0.86 (0.39) -16.35 (-0.415) I2 Compass Airpath C2300L4 0.75 (0.34) -15.0 (-0.381) I3 Compass IFR 31-12 0.64 (0.290) -16.35 (-0.415) I4 Turn Coordinator EGC 1394T100-7Z 1.2 (0.54) -16.35 (-0.415) I5 Ammeter VDO,190-031S3 0.18 (0.08) -16.35 (-0.415) I6 Cylinder Head Temp. Indicator VDO 20-3910-20-04 0.31 (0.14) -16.35 (-0.415) I7 Fuel Quantity Indicator VDO 301-035SB 0.20 (0.09) -16.35 (-0.415) I8 Manifold Pressure Indicator Uma 7-100-20 0.29 (0.13) -16.35 (-0.415) I9 Oil Pressure Indicator VDO 20-3910-20-03 0.31 (0.14) -16.35 (-0.415) I10 Oil Temperature Indicator VDO 20-3910-20-02 0.31 (0.14) -16.35 (-0.415) I11 Directional Gyro R.C.Allen, RCA15AK-2 2.45 (1.11) -16.35 (-0.415) I12 Artificial Horizon R.C.Allen, RCA26AK-1 2.43 (1.10) -16.35 (-0.415) I13 Airspeed Indicator United, 8000 0.66 (0.30) -16.35 (-0.415) I14 Turn and Slip Indicator RCA Allen 56-3BL 1.23 (0.56) -16.35 (-0.415) I15 Vertical Speed Indicator United, 7000 0.77 (0.35) -16.35 (-0.415) I16 RPM Indicator Superior Labs 20-3910-20-01 0.60 (0.27) -16.35 (-0.415) I17 Manifold Pressure Indicator Mitchel D1-111-5076 0.29 (0.13) -16.35 (-0.415) I18 Artificial Horizon B.F. Goodrich, 5040033943 2.5 (1.14) -16.35 (-0.415) I19 Directional Gyro B.F. Goodrich, 5050031927 3.0 (1.34) -16.35 (-0.415) DIAMOND AIRCRAFT DA 20/100 Flight Manual Weight & Balance Doc # 202-100-VLA 20 December, 2000 Page Issue 1 6 - 15 Equipment List Seq. No.: Part Description, Manufacturer, Type Weight [lbs] (kg) M1 Wheel Fairing, Main Gear DIAMOND left or right 2.65 (1.20) M2 Wheel Fairing, Nose Gear DIAMOND 2.65 (1.20) M3 Seat Cushion, standard DIAMOND, 2 pieces 4.50 (2.05) M4 Seat Cushion, leather DIAMOND, 2 pieces 5.63 (2.55) M5 *Fire Extinguisher AMEREX A 620 2.25 (1.02) M6 Tire 5.00x5,6Ply,Main Gear(TSOC62) (including inner tube) 4.51 (2.05) M7 Tire 15 x 6.00-5,Main Gear(Goodyear) (including inner tube) 7.70 (3.49) * Not approved for use in all countries; check national regulations. Refer to the Aircraft Specific Equipment list at the end of this chapter. DIAMOND AIRCRAFT DA 20/100 Flight Manual Description Doc # 202-100-VLA 20 December, 2000 Page Issue 1 7 - 1 CHAPTER 7 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS 7.1. INTRODUCTION 7- 2 7.2. AIRFRAME 7- 2 7.3. FLIGHT CONTROLS 7- 3 7.4. INSTRUMENT PANEL 7- 5 7.5. LANDING GEAR SYSTEM 7- 7 7.6. SEATS AND SAFETY BELTS 7- 8 7.7. BAGGAGE COMPARTMENT 7- 8 7.8. CANOPY 7- 9 7.9. POWERPLANT 7-10 7.10. FUEL SYSTEM 7-13 7.11. ELECTRICAL SYSTEM 7-14 7.12. PITOT AND STATIC PRESSURE SYSTEMS 7-17 7.13. STALL WARNING 7-17 7.14. AVIONICS 7-18 DIAMOND AIRCRAFT DA 20/100 Flight Manual Description Doc # 202-100-VLA 20 December, 2000 Page Issue 1 7 - 2 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 fleece, that is covered by a stainless steel plate on the engine side. The main bulkhead is of CFRP/GFRP construction. 7.2.2. Wings The GFRP-wings are of semi-monocoque sandwich construction, and contain a CFRP-spar. The ailerons and flaps are made from CFRP and are attached to the wings using aluminum hinges.