PILOT´S OPERATING HANDBOOK

8-10 Initial issue 8-11 Initial issue 8-12 Initial issue 8-13 Initial issue 8-14 Initial issue 8-15 Initial issue 8-16 Initial issue 8-17 Initial issue 8-18 Initial issue 8-19 Initial issue 8-20 Initial issue 9 9-1 Initial issue 9-2 Initial issue 9-3 Initial issue 9-4 Initial issue 9-5 Initial issue 9-6 Initial issue Page F Initial issue Chapter Page Date Chapter Page Date Initial issue Page G TABLE OF CONTENTS Chapter Chapter Name 0 ...................................................................................................................INTRODUCTION 1 ............................................................................................. GENERAL INFORMATION 2 ......................................................................................................................... LIMITATIONS 3 ........................................................................................ EMERGENCY PROCEDURES 4 ................................................................................................. NORMAL PROCEDURES 5 ................................................................................................................... PERFORMANCE 6 ......................................... WEIGHT AND BALANCE, AND EQUIPMENT LIST 7 .................................................... DESCRIPTION OF AIRCRAFT AND SYSTEMS 8 ....................................................................................... HANDLING AND SERVICING 9 ..................................................................................................................... SUPPLEMENTS Page H Initial issue This page is left blank intentionally Initial issue Page 0-1 0 INTRODUCTION TABLE OF CONTENTS 0.1 GENERAL ............................................................................................................... 0-2 0.2 LIST OF STANDARDS............................................................................................... 0-2 0.3 CONTINUED AIRWORTHINESS ................................................................................ 0-2 0.4 AIRCRAFT MANUFACTURER CONTACT INFORMATION ............................................ 0-2 0.5 DATA LOCATION AND CONTACT INFORMATION FOR RECOVERY OF APPROVAL DOCUMENTATION ................................................................................................. 0-2 0.6 SYMBOLS, ABBREVIATIONS AND TERMINOLOGY .................................................... 0-3 Speed .............................................................................................................................. 0-3 Meteorological Terms .................................................................................................... 0-3 Power Plant .................................................................................................................... 0-4 Flight Performance and Flight Planning ......................................................................... 0-4 Weight and Balance ....................................................................................................... 0-4 Equipment ...................................................................................................................... 0-5 Miscellaneous................................................................................................................. 0-5 0.7 CONVERSION FACTORS .......................................................................................... 0-6 Length or Altitude .......................................................................................................... 0-6 Speed .............................................................................................................................. 0-6 Pressure .......................................................................................................................... 0-6 Weight ............................................................................................................................ 0-6 Volume ........................................................................................................................... 0-6 Area ................................................................................................................................ 0-6 Page 0-2 Initial issue 0.1 General This Pilot´s Operating Handbook (POH) has been prepared to provide pilots and instructors with all information needed for the safe and efficient operation of this aircraft. This manual contains supplementary data supplied by the manufacturer. Before using the aircraft, read this handbook carefully: an in depth knowledge of aircraft features and limitations will allow you to operate the aircraft safely. 0.2 List of Standards EASA Approval Basis was Standard Specification for Design and Performance of a Light Sport Airplane ASTM F2245- 10c. This aircraft is not type certified and is accepted for EASA Permit to Fly. See the related EASA Flight Conditions for the operational limitations and airworthiness conditions. The noise requirements are shown according to Certification Specifications and Acceptable Means of Compliance for Aircraft Noise CS-36, Amendment 3 dated 20th January 2013. 0.3 Continued Airworthiness Technical publications for continued airworthiness are released on the Aerospool website www.aerospool.sk and they may be downloaded free of charge. Rotax Aircraft Engines releases technical publications on their website www.flyrotax.com from which they may be downloaded free of charge. Documentation updates for the propeller may be downloaded on www.helices-evra.com. Documentation updates for avionics may be downloaded on the avionics manufacturer’s website. It is the responsibility of the owner/operator of the aircraft to keep the aircraft and its documentation up to date and to comply with all technical publications. The owner/operator is responsible for keeping a current POH onboard every flight. 0.4 Aircraft Manufacturer Contact Information Aerospool spol. s r. o. Letisková 10 971 03 Prievidza Slovak republic Web: www.aerospool.sk E-mail: dynamic@aerospool.sk 0.5 Data Location and Contact Information for Recovery of Approval Documentation European Aviation Safety Agency (EASA) Postfach 10 12 53 50452 Koeln Germany Web: www.easa.europa.eu E-mail: info@easa.europa.eu Initial issue Page 0-3 0.6 Symbols, Abbreviations and Terminology Speed CAS Calibrated airspeed; Indicated speed in kilometers per hour corrected for installation and instrument errors. CAS is equal to TAS in standard atmospheric conditions at MSL. KCAS CAS indicated in knots. IAS Indicated airspeed in kilometers per hour as shown on the airspeed indicator. KIAS IAS indicated in knots. GS Ground Speed. Speed of the aircraft relative to the ground. TAS True airspeed. Speed of the aircraft relative to the air. TAS is CAS corrected for altitude and temperature errors. vA Maneuvering airspeed. Maximum speed at which the aircraft is not overstressed at full deflection of control surfaces. vFE Maximum airspeed with flaps extended. vLOF Airspeed at liftoff. vNE Airspeed which must never be exceeded in any operation. vNO Normal operating airspeed (cruise speed). vRA Maximum rough airspeed. vS The power-off stall airspeed with the aircraft in its standard configuration. vSO The power-off stall airspeed with the aircraft in landing configuration. vX Best angle-of-climb airspeed. vY Best rate-of-climb airspeed. v50 Airspeed at height 15m (50 ft). Meteorological Terms AGL Above Ground Level MSL Above Mean Sea Level 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. 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. Page 0-4 Initial issue Power Plant hp Horsepower kW Kilowatt Takeoff Power Maximum engine power for takeoff. Maximum Continuous Power Maximum permissible continuous engine output power during flight. Flight Performance and Flight Planning Demonstrated Crosswind Component The maximum speed of the crosswind component at which the maneuverability of the aircraft during takeoff and landing has been demonstrated during type certification test flights. Service Ceiling The altitude at which the maximum rate of climb is 100 fpm / 0.5 m/s. Weight and Balance Reference Datum (RD) An imaginary vertical plane from which all horizontal distances for the center of gravity calculations are measured. The Reference Datum is located 1.975 m / 77.76 in forward direction from inner surface of the firewall, perpendicular to the longitudinal axis of the aircraft. 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 aircraft 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. Center of Gravity Limits The CG range which an aircraft with a given weight must be operated within. MAC Mean Aerodynamic Chord 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 aircraft including all operating fluids and maximum oil amount without unusable fuel. Basic Empty Weight Weight of the aircraft including all operating fluids and maximum oil amount with unusable fuel. Useful Load The difference between takeoff weight and empty weight. Maximum Takeoff Weight Maximum weight permissible for takeoff. Initial issue Page 0-5 Equipment ALT Altitude or Altimeter ASI Airspeed Indicator CDI Course Deviation Indicator COMM Communication Transceiver CRS Course EFIS Electronic Flight Information System ELT Emergency Locator Transmitter EMS Engine Monitoring System EPS Emergency Parachute System GPS Global Positioning System HDG Heading MFD Multi-function Display OEM Original Equipment Manufacturer, company that controls the engineering and design rights for the LSA or an assembly, subassembly, accessory, or part installed in the aircraft, the consumable material, tools, fixtures, and test equipment used to service or maintain the aircraft. VSI Vertical Speed Indicator Miscellaneous ATC Air Traffic Control CS-LSA Certification Specification for Light Sport Aeroplanes EASA European Aviation Safety Agency IFR Instrument Flight Rules PIC Pilot in Command POH Pilot’s Operating Handbook VFR Visual Flight Rules RWY Runway Page 0-6 Initial issue 0.7 Conversion Factors Length or Altitude 1 [m] = 3.281 [ft] 1 [ft] = 0.305 [m] 1 [m] = 39.37 [in] 1 [in] = 0.0254 [m] 1 [km] = 0.5399 [nm] 1 [nm] = 1.852 [km] Speed 1 [km/h] = 0.54 [knots] 1 [knots] = 1.852 [km/h] 1 [m/s] = 1.9425 [knots] 1 [knots] = 0.5148 [m/s] 1 [m/s] = 196.86 [fpm] 1 [fpm] = 0.00508 [m/s] Pressure 1 [atm] = 1013.25 [mbar] = 101325 [Pa] = 29.92 [inHg] 1 [inHg] = 0.03342 [atm] = 33.865 [mbar] = 3386.5 [Pa] Weight 1 [kg] = 2.205 [lb] 1 [lb] = 0.454 [kg] Volume 1 [liter] = 0.2642 [U. S. gallon] 1 [U. S. gallon] = 3.785 [liter] Area 1 [m2] = 10.76 [ft2] 1 [ft2] = 0.0929 [m2] Initial issue Page 1-1 1 GENERAL INFORMATION TABLE OF CONTENTS 1.1 GENERAL ............................................................................................................... 1-2 1.2 INTRODUCTION TO THE POH.................................................................................. 1-2 Warnings, Cautions and Notes ....................................................................................... 1-2 Procedures ..................................................................................................................... 1-2 1.3 INTRODUCTION TO THE AIRCRAFT ......................................................................... 1-3 Dimensions ..................................................................................................................... 1-3 Engine ............................................................................................................................. 1-3 Propeller ......................................................................................................................... 1-3 Three View Drawing ....................................................................................................... 1-4 Ground Turning Clearance ............................................................................................. 1-5 1.4 SUMMARY OF PERFORMANCE ............................................................................... 1-6 Weights .......................................................................................................................... 1-6 Top and Cruise Speeds ................................................................................................... 1-6 1.4.2.1 Top Speeds at Sea Level ................................................................................................. 1-6 1.4.2.2 Cruise Speeds at Altitudes and Power Setting ............................................................... 1-6 Fuel Operating Ranges ................................................................................................... 1-7 Rate of Climb .................................................................................................................. 1-7 Stall Speeds .................................................................................................................... 1-7 Approved Fuel Types and Fuel Capacity ........................................................................ 1-8 Maximum Engine Power Output.................................................................................... 1-8 Specific Loadings ............................................................................................................ 1-8 Page 1-2 Initial issue 1.1 General This chapter contains information of general interest to pilots and owners. You will find useful information to familiarize yourself with the aircraft, such as dimensions, ground turning clearance, loading, fuelling and summary of performance. 1.2 Introduction to the POH Warnings, Cautions and Notes The following highlighting styles are used in this handbook to focus attention on particular information that is important. WARNING Warnings are used to call attention to operating procedures that if not strictly observed, may result in personal injury or loss of life! CAUTION Cautions are used to call attention to operating procedures that if not strictly observed, may result in damage of equipment! NOTE Notes are used to call attention to any special item, not directly related to safety, but which is important or unusual. Procedures The procedures, listed in this POH are formed into tables with three columns as shown in the example below: Column A Column B Column C a. Item 1 OFF b. ITEM 2 As required c. ITEM 3 handle OPEN, carefully Column A contains letters in the alphabetical order, defining the order of the actions in the procedure. Plain text in Column B defines the item, which is not marked by a placard in the cabin, but is generally identifiable; or supplements the other text. Bold capital text in column B defines the item, which is marked by a placard with the identical expression in the cabin. Plain text in Column C defines the setting or action which is generally understandable; or supplements the other text. Capital text in Column C defines the setting or action, which usually changes the state of the item from one setting to another; and/or emphasizes the importance of the setting or action. Bold capital text in Column C defines the setting or action, which is marked by a placard with the identical expression in the cabin. Initial issue Page 1-3 1.3 Introduction to the Aircraft Dimensions Wing area 10.500 m2 112.98 ft2 Wing span 8.926 m 29.28 ft Overall length 6.460 m 21.19 ft Maximum height 1.850 m 6.07 ft Wheel base 1.400 m 4.59 ft Main landing gear track 2.240 m 7.35 ft Maximum propeller diameter 1.750 m 68.90 in Mean aerodynamic chord (MAC) 1.172 m 3.84 ft Engine Number of engines 1 Number of cylinders 4 Engine manufacturer BRP-Rotax GmbH & Co KG Engine model number Rotax 912 ULS2 Engine type Horizontally opposed, geared, normally aspirated, spark ignition Cooling Combined liquid and air Maximum takeoff power at 5800 rpm (max. 5 min.) 73.5 kW / 100 hp Maximum continuous power at 5500 rpm 69.0 kW / 92.5 hp Propeller Number of propellers 1 Propeller manufacturer PRODUCTION EVRA, Creil, France Propeller model number EVRA PerformanceLine 175/xxx/805.5 Number of blades 3 Propeller diameter 1.750 m (68.90 in) Propeller type Fixed pitch, ground adjustable Pitch setting (measured 200 mm from blade tip) 23° Page 1-4 Initial issue Three View Drawing Fig. 1-1 Three view drawing Initial issue Page 1-5 Ground Turning Clearance Fig. 1-2 Ground turning clearance A Wing tip radius 9.850 m 32.32 ft B Outside main gear radius 6.500 m 21.32 ft C Nose gear radius 5.380 m 17.65 ft D Inside main gear radius 4.260 m 13.98 ft CAUTION The data are valid for dry paved surface, fully turned nose gear and minimum taxi speed! Expect greater turning radius on unpaved, wet and/or slippery surfaces! Page 1-6 Initial issue 1.4 Summary of Performance NOTE All airspeeds shown in the POH are IAS / KIAS, unless not stated otherwise. Weights Maximum takeoff weight 600.0 kg 1323 lb Maximum landing weight 600.0 kg 1323 lb Empty weight Max. 410.8 kg Max. 906 lb Maximum load per seat 120.0 kg 265 lb Maximum total baggage weight 2 x 20.0 kg 2 x 44 lb Top and Cruise Speeds 1.4.2.1 Top Speeds at Sea Level IAS KIAS Top speeds at sea level At 5800 rpm 240 130 At 5500 rpm 230 124 1.4.2.2 Cruise Speeds at Altitudes and Power Setting Pressure altitude Engine speed MAP Cruise speeds ft rpm inHg IAS KIAS 2000 5 500 24.2 223 120 4000 5 500 24.4 216 117 6000 5 500 22.6 211 114 8000 5 500 21.4 201 109 10000 5 500 19.9 192 104 NOTE For more details see Chapter 5.6. Initial issue Page 1-7 Fuel Operating Ranges Endurances and ranges at altitude 2000 ft ISA Engine speed rpm 4 300 4 500 4 800 5 000 5 500 Fuel consumption l/h 14.5 15.5 17.2 18.5 21.3 IAS km/h 165 175 190 200 223 KIAS knots 89 94 103 108 120 CAS km/h 163 172 185 194 215 KCAS knots 88 93 100 105 116 TAS km/h 172 183 196 206 228 KTAS knots 93 99 106 111 123 Usable fuel (l) 119 hh:mm 8:12 7:40 6:55 6:25 5:35 km 1411 1404 1356 1325 1273 nm 762 758 732 715 687 100 hh:mm 6:53 6:27 5:48 5:24 4:41 km 1186 1180 1139 1113 1070 nm 640 637 615 601 578 80 hh:mm 5:31 5:09 4:39 4:19 3:45 km 948 944 911 890 856 nm 512 510 492 481 462 60 hh:mm 4:08 3:52 3:29 3:14 2:49 km 711 708 683 668 642 nm 384 382 369 361 347 40 hh:mm 2:45 2:34 2:19 2:09 1:52 km 474 472 455 445 428 nm 256 255 246 240 231 20 hh:mm 1:22 1:17 1:09 1:04 0:56 km 237 236 227 222 214 nm 128 127 123 120 116 Rate of Climb IAS KIAS Best angle of climb airspeed VX (at SL) 100 IAS 54 KIAS Rate of climb at VX (at SL) 985 fpm (5.0 m/s) Best rate of climb airspeed VY (at SL) 127 IAS 69 KIAS Rate of climb at VY (at SL) 1085 fpm (5.5 m/s) Stall Speeds IAS KIAS Cruise, FLAPS 0 (0°) 78 42 Takeoff, FLAPS 1 (15°) 68 37 Landing – normal, FLAPS 2 (24°) 64 35 Landing – emergency, FLAPS 3 (35°) 61 33 Page 1-8 Initial issue Approved Fuel Types and Fuel Capacity Approved types of fuel (Min. RON 95) EN 228 Super EN 228 Super Plus AVGAS 100 LL Total capacity of fuel tanks 126.0 l 33.29 U. S. gal 90.7 kg 200 lb Total usable fuel 119.0 l 31.44 U. S. gal 85.7 kg 189 lb Total unusable fuel 7.0 l 1.85 U. S. gal 5.0 kg 11 lb Maximum Engine Power Output Maximum takeoff power at 5800 rpm (max. 5 min.) 73.5 kW 100.0 hp Maximum continuous power at 5500 rpm 69.0 kW 92.5 hp Specific Loadings Wing loading 57.14 kg/m2 11.71 lb/ft2 Power loading 8.16 kg/kW 18.00 lb/kW 6.00 kg/hp 13.23 lb/hp Initial issue EASA Approved Page 2-1 2 LIMITATIONS TABLE OF CONTENTS 2.1 GENERAL ............................................................................................................... 2-3 2.2 AIRSPEED LIMITATIONS ......................................................................................... 2-3 Airspeed Indicator Marking............................................................................................ 2-3 Stalling Speeds at Maximum Takeoff Weight (VS and VS0) ............................................ 2-3 Flap Extended Speed Range (VS0 – VFE) .......................................................................... 2-3 Operating Maneuvering Speed (VO)............................................................................... 2-4 Never Exceed Speed (VNE) .............................................................................................. 2-4 Rough Air Speed (VRA) .................................................................................................... 2-4 2.3 POWER PLANT LIMITATIONS .................................................................................. 2-5 Engine Limitations .......................................................................................................... 2-5 Power Plant Instrument Markings ................................................................................. 2-6 Taxi Power ...................................................................................................................... 2-6 2.4 WEIGHT LIMITS ...................................................................................................... 2-7 2.5 CENTER OF GRAVITY LIMITS ................................................................................... 2-7 2.6 APPROVED MANEUVERS ........................................................................................ 2-8 2.7 FLIGHT LOAD FACTOR LIMITS ................................................................................. 2-8 2.8 FLIGHT CREW LIMITATIONS.................................................................................... 2-8 2.9 FLUIDS ................................................................................................................... 2-9 Fuel ................................................................................................................................. 2-9 Oil ................................................................................................................................. 2-10 Coolant ......................................................................................................................... 2-10 2.10 ENVIRONMENTAL LIMITATIONS ........................................................................... 2-11 2.11 KIND OF OPERATION............................................................................................ 2-11 2.12 SERVICE CEILING .................................................................................................. 2-11 2.13 SYSTEMS AND EQUIPMENT LIMITATIONS............................................................. 2-12 Flap Limitations ............................................................................................................ 2-12 Emergency Parachute System ...................................................................................... 2-12 Minimum Equipment for Flight Operation .................................................................. 2-13 Page 2-2 EASA Approved Initial issue 2.14 OTHER LIMITATIONS ............................................................................................ 2-13 Smoking ........................................................................................................................ 2-13 Dynon SkyView System Limitations ............................................................................. 2-13 External Power Source and Battery ............................................................................. 2-13 2.15 PLACARDS ........................................................................................................... 2-14 Interior Placards ........................................................................................................... 2-14 Exterior Placards .......................................................................................................... 2-15 Initial issue EASA Approved Page 2-3 2.1 General The limitations included in this section are approved by the European Aviation Safety Agency. Chapter 2 includes operating limitations, instrument markings, and basic placards necessary for safe operation of the aircraft, its standard systems and equipment. WARNING Aircraft must be operated within the limitations stated in this chapter! 2.2 Airspeed Limitations Airspeed Indicator Marking Color code Significance Airspeed or airspeed range White arc Operating range with extended flaps. Lower limit is maximum weight stalling speed in landing configuration VS0. Upper limit is maximum speed permissible with flaps extended VFE. 61 – 140 IAS 33 – 76 KIAS Green arc Normal operating range. Lower limit is maximum weight stalling speed with flaps retracted VS. Upper limit is maximum cruising speed VNO. 78 – 218 IAS 42 – 118 KIAS Yellow arc Maneuvers must be conducted with caution and only in smooth air. (Lower limit is VNO. Upper limit is VNE) 218 – 275 IAS 118 – 148 KIAS Red line Maximum speed for all operations VNE 275 IAS 148 KIAS Stalling Speeds at Maximum Takeoff Weight (VS and VS0) Configuration Flaps positions Airspeed Cruise FLAPS 0 (0°) 78 IAS 42 KIAS Takeoff FLAPS 1 (15°) 68 IAS 37 KIAS Landing – Normal FLAPS 2 (24°) 64 IAS 35 KIAS Landing – Emergency FLAPS 3 (35°) 61 IAS 33 KIAS Flap Extended Speed Range (VS0 – VFE) VS0 - VFE Speed range from stalling airspeed (flaps fully extended) to maximum airspeed with flaps extended 61 – 140 IAS 33 – 76 KIAS Page 2-4 EASA Approved Initial issue Operating Maneuvering Speed (VO) VO at maximum takeoff weight Do not make full or abrupt control movements above this airspeed, because under certain conditions the aircraft may be overstressed by full control deflections. 180 IAS 97 KIAS VO at minimum flying weight 140 IAS 76 KIAS Never Exceed Speed (VNE) VNE Do not exceed this airspeed in any operation. 275 IAS 148 KIAS Rough Air Speed (VRA) VRA Do not exceed this airspeed except in smooth air and then only with caution. Air movements in lee-wave rotors, thunderclouds, visible whirlwind, or over mountain crests are to be understood as rough air. 218 IAS 118 KIAS Initial issue EASA Approved Page 2-5 2.3 Power Plant Limitations Engine Limitations Engine manufacturer BRP-Powertrain GmbH&Co.KG Engine model number Rotax 912 ULS2 Engine power Max. takeoff 73.5 kW / 100.0 hp at 5800 rpm (max. 5 min.) Max. continuous 69.0 kW / 92.5 hp at 5500 rpm Engine speed Takeoff 5800 rpm (max. 5 min.) Continuous 5500 rpm Idle 1400 rpm (minimum) Manifold pressure Maximum 29.5 inHg Coolant temperature Maximum 120 °C Oil temperature Minimum 50 °C Maximum 130 °C Oil pressure Minimum 0.8 bar Maximum 7.0 bar Exhaust gas temperature Maximum 880 °C Fuel pressure Minimum 0.15 bar Maximum 0.50 bar Engine start operating temperature Minimum -25 °C Maximum 50 °C Engine zero/negative load condition Maximum -0.5 g (max. 5 seconds) NOTE For complete performance data and limitations see OPERATORS MANUAL FOR ROTAX ENGINE TYPE 912 SERIES, Doc. No. OM-912, latest edition. Page 2-6 EASA Approved Initial issue Power Plant Instrument Markings Digital power plant instrument SkyView SV D1000 for monitoring of engine parameters complemented with analogue engine speed indicator and fuel pressure indicator are marked with following color code significance: Dynon SkyView SV-D1000 Unit Red Line Minimum Limit Green Arc Normal Operating Yellow Arc Caution Range Red Line Maximum Limit Engine speed rpm – 1400 – 5500 0 – 1400 5500 – 5800 5800 Manifold pressure inHg – 0.0 – 28.0 28.0 – 29.5 29.5 Coolant temperature oC – 50 – 120 – 120 Oil temperature oC 50 90 – 110 50 – 90 110 – 130 130 Oil pressure bar 0.8 2.0 – 5.0 0.8 – 2.0 5.0 – 7.0 7.0 Exhaust gas temperature oC – 200 – 880 – 880 Fuel pressure bar 0.15 0.15 – 0.50 – 0.50 Fuel flow meter l/h – 0.0 – 30.0 – over 30.0 Fuel level l 0 - 16 16 – 45 45+ – – CAUTION Illumination of the fuel reserve warning lamp signals that in the appropriate tank is 16 liters / 4.23 U. S. gal of fuel remaining, of which 3.5 liters / 0.92 U. S. gal is unusable fuel! This fuel is sufficient for half-hour flight at maximum continuous power! Taxi Power Use the minimum power settings for taxiing. Power settings for taxiing on flat, smooth, hard surfaces is idle (min. 1400 rpm). Power settings for grassy, inclined, soft surfaces or when start motion is slightly above idle (1400 rpm). Initial issue EASA Approved Page 2-7 2.4 Weight Limits Maximum takeoff weight 600.0 kg 1323 lb Maximum landing weight 600.0 kg 1323 lb Minimum flying weight 405.0 kg 893 lb Maximum load per seat 120.0 kg 265 lb Maximum total baggage weight 2x 20.0 kg 2x 44 lb WARNING Do not exceed maximum takeoff weight 600.0 kg! WARNING Do not place any baggage or objects to the compartment below your legs! It is not a baggage compartment! NOTE Actual aircraft empty weight is mentioned in Chapter 6. 2.5 Center of Gravity Limits Metric Units U. S. Standard Units Reference Datum 1.975 m forward from inner surface of the firewall 77.76 in forward from inner surface of the firewall Forward CG 2.704 m (18.3 %MAC) at 542.5 kg with straight line taper to 2.748 m (22.0 %MAC) at 600.0 kg 106.48 in (18.3 %MAC) at 1196 lb with straight line taper to 108.18 in (22.0 %MAC) at 1323 lb Rearward CG 2.824 m (28.5 %MAC) 111.18 in (28.5 %MAC) Center of gravity limits charts are shown at Fig. 6-2 (Metric Units) and Fig. 6-3 (U. S. Standard Units). Rearward center of gravity limit is obtained at maximum crew weight and minimum fuel amount. Forward center of gravity limit is obtained at minimum pilot weight and maximum fuel amount. For more details see the Chapter 6. WARNING A flight shall not be commenced until the pilot-in-command is satisfied that the mass of the aircraft and CG location are within the allowed limits for takeoff and landing! Fuel consumption moves the CG rearwards, therefore the CG location must be calculated for empty tanks as well! The mass of the baggage must be taken into account for every CG calculation! Page 2-8 EASA Approved Initial issue 2.6 Approved Maneuvers Aerobatic maneuvers, including spins are prohibited. The aircraft is not approved for pitch attitudes greater than 30°. The aircraft is not designed for aerobatic operations. Only those operations incidental to normal flight are approved. These operations include normal stalls (except whip stalls), chandelles, lazy eights and turns in which the bank angle does not exceeding 60°. WARNING Aerobatic maneuvers and intentional spins are prohibited! 2.7 Flight Load Factor Limits Flaps Load Factor Flaps retracted: FLAPS 0 (0°) +4 / -2* Flaps extended: FLAPS 1 (15°), FLAPS 2 (24°), FLAPS 3 (35°) +2 / 0 * Rotax 912 ULS2 limit is -0.5 for no more than 5 seconds. WARNING Exceeding of the maximum allowed load factor may result in overstressing of the aircraft! Simultaneous full deflection of control surfaces around more than one axis may result in overstressing of the aircraft, even at speeds below VA! Rapid pull / push of the control stick (pitch control) may result in exceeding the operating envelope limits! 2.8 Flight Crew Limitations Minimum flight crew 1 pilot Pilot in command (PIC) Left seat only Initial issue EASA Approved Page 2-9 2.9 Fluids Fuel The electric fuel pump must be ON for takeoff and landing. The electric fuel pump is connected to LH fuel tank only. Approved types of fuel (min. RON 95) EN 228 Super EN 228 Super Plus AVGAS 100 LL Total capacity of fuel tanks 126.0 l 33.29 U. S. gal 90.7 kg 200 lb Total usable fuel 119.0 l 31.44 U. S. gal 85.7 kg 189 lb Total unusable fuel 7.0 l 1.85 U. S. gal 5.0 kg 11 lb WARNING Fuelling must be done with respect to the allowed CG range and MTOW, see Chapter 6! Use of unapproved fuel may result in damage of engine and fuel system and eventually can lead to the engine failure! WARNING The electric fuel pump must be ON for takeoff and landing! LH fuel tank must be selected for takeoff and landing! NOTE Use of AVGAS 100 LL is not recommended, as it increases the engine wear. Use AVGAS 100 LL only when no other approved type of fuel is available. For complete fuel specifications see OPERATORS MANUAL FOR ROTAX ENGINE TYPE 912 SERIES, Doc. No. OM-912 and Rotax Service Instructions SI-912-016, latest edition. Page 2-10 EASA Approved Initial issue Oil Oil capacity is 3.0 – 3.5 l (oil system + oil tank). CAUTION Use only suitable oil according to the specification stated at placard in the engine compartment! CAUTION Never use AVGAS, LB 95 with fully synthetic engine oils! NOTE For complete oil specifications see OPERATORS MANUAL FOR ROTAX ENGINE TYPE 912 SERIES, Doc. No. OM-912 and Rotax Service Instructions SI-912-016, latest edition. Coolant Coolant capacity is approximately 2.5 l (cooling system + overflow bottle). CAUTION Use only suitable conventional coolant according to the specification stated on placard in the engine compartment! Never mix different types of coolants! Do not use waterless coolant! NOTE For complete conventional coolant specifications see OPERATORS MANUAL FOR ROTAX ENGINE TYPE 912 SERIES, Doc. No. OM-912 and Rotax Service Instructions SI-912-016, latest edition. Initial issue EASA Approved Page 2-11 2.10 Environmental Limitations Before starting preheat the engine and oil if outside temperature falls below +5 °C. Do not operate the aircraft below outside temperature -25 °C and above +50 °C. Flights in icing conditions are not allowed. WARNING Flights in icing conditions are prohibited! NOTE Cabin heating may be insufficient, when the outside temperature is below zero and the engine loading is low. 2.11 Kind of Operation WT9 Dynamic LSA is equipped and approved for VFR day operations only. VFR night, IFR day and IFR night operation is prohibited. WARNING VFR night and IFR operations are prohibited! 2.12 Service Ceiling Service ceiling is 15 000 ft. Page 2-12 EASA Approved Initial issue 2.13 Systems and Equipment Limitations Flap Limitations Normal takeoff FLAPS 1 Normal landing FLAPS 2 Emergency landing FLAPS 3 Emergency Parachute System The emergency parachute system must be operative. Maximum airspeed 290 CAS 157 KCAS 303 IAS 164 KIAS Minimum height above terrain 660 ft (200 m) WARNING The emergency parachute system must be operative, otherwise the aircraft is not airworthy! WARNING Minimum recommended height for EPS activation is 660 ft (200 m) AGL and maximum airspeed is 303 IAS / 164 KIAS! Activation of EPS in a height less than 660 ft (200 m) may alleviate the consequences of an accident! Initial issue EASA Approved Page 2-13 Minimum Equipment for Flight Operation a. Flight indications: a.1 Airspeed a.2 Altitude a.3 Magnetic compass b. Engine indications: b.1 Engine RPM b.2 Fuel pressure b.3 Manifold pressure b.4 Oil pressure b.5 Oil temperature b.6 Coolant temperature b.7 Exhaust gas temperature b.8 Airbox temperature b.9 Fuel quantity c. ATC equipment (radio, XPDR) d. Stall Warning System (buzzer, warning light) e. Safety harness for each occupied seat. f. Operative emergency parachute system. WARNING A flight shall not be commenced if the minimum equipment for flight operation is not serviceable! CAUTION Failure of any indication not listed in the minimum equipment for flight operation should be inspected and repaired as soon as practical. Continuous operation of the aircraft with indications available only from backup instruments is not recommended! 2.14 Other Limitations Smoking Smoking on board is prohibited! Dynon SkyView System Limitations a. Using of the Synthetic Vision information for primary terrain and obstacle avoidance is prohibited. The terrain map is intended only to enhance the situational awareness. It is the pilot’s responsibility to provide terrain clearance at all time. b. Use of the MAP screen for pilotage navigation is prohibited. The navigation map is intended only to enhance the situational awareness. c. It is allowed to use autopilot in cruise only. External Power Source and Battery Max. power source output connected to the external power socket for engine starting is limited to 12 V / 90 A DC! Do not use external power to start the engine with a “dead” battery. Page 2-14 EASA Approved Initial issue 2.15 Placards NOTE If any placard is found missing or unreadable it should be replaced. List of all placards is given in the Aircraft Maintenance Manual AS-AMM-10-000, Chapter 11. Interior Placards a. Placards on the left part of instrument panel. b. Placards on the left side of cabin. c. Placards on the LH / RH side of the baggage compartment bulkhead. Initial issue EASA Approved Page 2-15 d. Placards on the L / R side in the baggage compartment on the flap’s torsion tube cover. Exterior Placards a. Placards on the wing center section, wing flaps. b. Placards near fuel tank caps LH / RH. c. Placard on the upper engine cowling near door for oil level check. d. Placards on the outer part of the main landing gear legs. e. Placard on the left part of the nose landing gear leg. f. Placards on the trailing edge of the control surfaces. g. Placards near jack points on the fuselage / wing center section bottom part. Page 2-16 EASA Approved Initial issue h. Placards near drain valves on the wing bottom part. i. Placards are located on the both sides of fuselage under the windows in baggage compartment. j. Placard is located on the emergency parachute system cover.