Viper SD4 RTC Flight Manual HA-BEW-sn21737

1.8 Typical Airplane Weights......................................................... 6 1.9 Specific Loadings .................................................................... 7 1.10 Cabin Dimensions ................................................................... 7 1.11 Baggage Space....................................................................... 7 1.12 Symbols, Abbreviations and Terminology ............................... 7 1.13 Warnings, Cautions and Notes ............................................. 12 SECTION 1 Aircraft Flight Manual General 1 - 2 22.MAR 2016 1.1 Introduction In case of occurrences and technical support contact: TOMARK, s.r.o Strojnícka 5 08001 Prešov Slovakia tomarkaero@tomarkaero.com (+421)51-77480-561 1.1.1 Certification Base The airplane Viper SD-4 RTC has been approved in accordance with the CS-LSA Amendment1 certification specification of the European Aviation Safety Agency (EASA.A.606). 1.1.2 General The content of this Aircraft Flight Manual covers all instructions for carrying out a safe flight with the Viper SD-4 RTC airplane. Each pilot and maintenance technician of the Viper SD-4 RTC airplane is obliged to get acquainted with this Manual. The Viper SD-4 RTC airplane is operated upon its user’s own responsibility. The Viper SD-4 RTC is designed for sporting and recreational purposes. The manufacturer of the Viper SD-4 RTC airplane does not bear responsibility for damage to the airplane caused by the use of the airplane in breach of individual provisions of the operation, control or maintenance documentation of the airplane. THIS MANUAL INCLUDES THE MATERIAL REQUIRED TO BE FURNISHED TO THE PILOT BY THE EUROPEAN AVIATION SAFETY AGENCY REGULATIONS AND ADDITIONAL INFORMATION PROVIDED BY THE MANUFACTURER AND CONSTITUTES THE EASA APPROVED AIRPLANE FLIGHT MANUAL Aircraft Flight Manual SECTION 1 General 22.MAR 2016 1 - 3 Further documentation for the operation, control and maintenance of Viper SD-4 RTC refer to latest approved revisions of (supplied by TOMARK): Aircraft Maintenance Manual TOM-TC-01-AMM Rotax Engine Operation Manual 912S/ULS Neuform Propeller Operation Manual f.u.n.k.e. ATR-833 transceiver Pilot’s Guide f.u.n.k.e. TRT-800H transponder Pilot’s Guide Model E-04 ELT Installation manual Operation manual Galaxy Ballistic Rescue System user guide GRS 6/600 SD S-LSA DYNON SkyView User Guide Garmin Aera 500 GPS manual SECTION 1 Aircraft Flight Manual General 1 - 4 22.MAR 2016 1.2 Three View Drawing Aircraft Flight Manual SECTION 1 General 22.MAR 2016 1 - 5 1.3 Engine NOTE For 912 ULS variants of the Viper - do not install any Service Bulletin / Service Instruction / Technical Note or other publication released by Rotax without written confirmation by TOMARK. Number of Engines: 1 Engine Manufacturer: BRP-Power train Engine Model Number: 912 ULS / S Engine type: Reciprocating Normally aspirated Geared 2,43:1 Air cooled cylinders Liquid cooled cylinder heads 4 cylinders Power Ratings (kW(HP)) / Engine Rotational Speeds (RPM) (1) Take-off Power 73,5 (100) / 5 800 (2) Maximum Continuous Power 69 (90) / 5 500 (3) Operating Power = 75% 51 (68) / 5 000 Operating Power = 65% 44,6 (60) / 4 800 Operating Power = 55% 38 (50) / 4 300 Engine Speed over 5 500 RPM is restricted to 5 min. 1.4 Propeller NOTE Do not install any Service Bulletin / Service Instruction / Technical Note or other publication released by Neuform without written confirmation by TOMARK. Number of Propellers: 1 Propeller Manufacturer: Neuform Propeller Model Name: CR3-65-(IP)-47-101.6 Number of Blades: 3 Propeller Diameter: 1,65 m SECTION 1 Aircraft Flight Manual General 1 - 6 22.MAR 2016 1.5 Fuel Usable capacity: 90 litres Total capacity of fuel tanks: 100 litres Fuel specification: Knock resistance: min. RON 95 (min. AKI 91) European standard (MOGAS): EN 228 Super, EN 228 Super Plus AVGAS - unleaded UL91 (ASTM D7547) AVGAS - leaded AVGAS 100 LL (ASTM D910) US standard ASTM D4814 1.6 Oil Description: For the selection of suitable lubricants refer to SI-912-016 latest edition Brand: SHELL AeroShell Sport Plus 4 (recommended) Specification: Min. API SG Viscosity: SAE 5W-30 ÷ 15W-50 (depends on oil temperature operation Total oil Capacity: 3,5 litres (with oil cooler) Refill Quantity 3 litres Oil Quantity Operating Range: 2,5 ÷ 3 litres (in sump; oil level between min. and max. mark) 1.7 Maximum Certificated Weights Maximum Takeoff Weight 600kg Maximum Landing Weight 600kg Maximum Baggage Weight 7,5kg per Compartment 15kg TOTAL 1.8 Typical Airplane Weights Empty Weight: 369 kg 410 kg maximum Minimum Crew Weight 55kg Aircraft Flight Manual SECTION 1 General 22.MAR 2016 1 - 7 1.9 Specific Loadings Wing Loading: 57,4 kg / m2 Power Loading: 8,16 kg / kW (6 kg / HP) 1.10 Cabin Dimensions Cabin Width: 1000/1100 mm Cabin Length: 850/1350 mm Cabin Height 950/1050 mm 1.11 Baggage Space Compartment Width: 420 mm Compartment Length: 230 mm Compartment Height: 310 mm Compartment Volume: 40 dm3 1.12 Symbols, Abbreviations and Terminology General Airspeed Terminology and Symbols AFM Aircraft Flight Manual AMM Aircraft Maintenance Manual AMO Approved Maintenance Organisation CAS Calibrated Airspeed, airspeed corrected by the error of the speed measuring system GS Ground Speed IAS Indicated Airspeed is the speed of an aircraft as shown in the airspeed indicator when corrected for instrument error. TAS True Airspeed VA Maneuvering Speed is the maximum speed at which application of full available aerodynamic control will not overstress the airplane. VFE Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position SECTION 1 Aircraft Flight Manual General 1 - 8 22.MAR 2016 VO Operating Maneuvering Speed: No full or abrupt single pitch control input above this speed. VNE Never Exceed Speed is the speed limit that may not be exceeded at any time VS Stalling Speed or the minimum steady flight speed at which the airplane is controllable.( in clean configuration) VS1 Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the take-off configuration VS0 Stalling Speed or the minimum steady flight speed at which the airplane is controllable in the landing configuration VX Best Angle-of-Climb Speed is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance. VY Best Rate-of-Climb Speed is the airspeed which delivers the greatest gain in altitude in the shortest possible time. Meteorological Terminology bar. bar - unit of pressure, 1 bar = 1 000 mbar Indicated Pressure Altitude The number actually read from an altimeter when the barometric subscale has been set to 1013.25 hPa (29.92” Hg). Pressure Altitude Altitude measured from standard sea level pressure (1013.25 hPa (29.92” Hg)) by a pressure or barometric altimeter. It is the indicated pressure altitude corrected for position and instrument error. Station Pressure An actual atmospheric pressure at field elevation. Wind The wind velocities recorded as the headwind or tailwind components of the reported wind. ISA International Standard Atmosphere in which (1) The air is a dry perfect gas; (2) The temperature at sea level is 15° C (59° F); (3) The pressure at sea level is 1013.25 hPa (29.92” Hg); (4) The temperature gradient from sea level to the altitude at which the temperature is -56,5°C (-69,7°F) is -0,0065° C (-0,0117° F) /m and 0°/m above that altitude. Aircraft Flight Manual SECTION 1 General 22.MAR 2016 1 - 9 OAT Outside Air Temperature is the free air static temperature, obtained either from in flight temperature indications or ground meteorological sources, adjusted for instrument error and compressibility effects. Power Terminology Note: Maximum Power for the combination of the engine and propeller is determined by engine speed“ Takeoff Power The maximum power permissible for takeoff (may be time limited) Maximum Continuous Power (MCP) Continuous The maximum power for abnormal or emergency operations. Maximum Normal Operating Power (MNOP) The maximum power for all normal operations (except Take-off). This power may be the same as Maximum Continuous Power Cruising Climb Power The power (not to exceed MNOP) recommended to operate the airplane in a cruise climb (a continuous, gradual climb) Ground Idle Power The power required to run an engine on the ground, as slowly as possible, yet sufficient to ensure satisfactory engine, engine accessory, and airplane operation with a minimum of thrust. RPM Revolutions Per Minute kW Kilo-Watt- unit of power, 1 kW = 1 000 W HP Horse-Power - unit of power, 1 HP = 0,735 kW Engine Controls and Instruments THROTTLE LEVER The lever used to control engine power, from the lowest through the highest power, by engine speed. EGT Gauge The exhaust gas temperature indicator, on piston engine powered airplanes, Tachometer An instrument that indicates rotational speed of engine as RPM 3 Main Switches “INSTR” + “MASTR” + “GENRTR” SECTION 1 Aircraft Flight Manual General 1 - 10 22.MAR 2016 Section Switches Switches/Automatic Circuit Breakers to control of electric/electronic onboard equipment Airplane Performance, Flight Planning and Navigation Terminology Climb Gradient The demonstrated ratio of the change in height during a portion of a climb, to the horizontal distance traversed in the same time interval Demonstrated Crosswind Velocity The demonstrated crosswind velocity is the velocity of the crosswind component for which adequate control of the airplane during takeoff and landing was actually demonstrated during certification tests. GPS Global Positioning System IFR Instrument Flight Rules IMC Instrument Metrological Conditions RWY Runway TWR Tower TXY Taxi Way VFR Visual Flight Rules VMC Visual Meteorological Conditions Weight & Balance Reference Datum An imaginary vertical plane from which all horizontal distances are measured for balance purposes. Station A location along the airplane fuselage usually given in terms of distance from the reference datum. Arm The horizontal distance from the reference datum to the centre of gravity (C.G.) of an item Moment The product of the weight of item multiplied by its arm. (Moment divided by a constant is used to simplify balance calculations by reducing the number of digits.) Centre of Gravity (C.G.) The point at which an airplane would balance if suspended. Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane C.G. Arm The arm obtained by adding the airplane's individual moments and dividing the sum by the total weight. Aircraft Flight Manual SECTION 1 General 22.MAR 2016 1 - 11 C.G. Limits The extreme centre of gravity locations within which the airplane must be operated at a given weight Usable Fuel Fuel available for flight planning Unusable Fuel Fuel remaining after a run out test has been completed in accordance with governmental regulations Standard Empty Weight Weight of a standard airplane including unusable fuel, full operating fluids and full oil. Basic Empty Weight Standard empty weight plus optional equipment Payload Weight of crew and baggage. Useful Load Difference between takeoff weight and basic empty weight. Maximum Takeoff Weight Maximum weight approved for the start of the take-off run Maximum Landing Weight Maximum weight approved for the landing touchdown. Maximum Zero Fuel Weight Maximum weight exclusive of usable fuel MAC Mean Aerodynamic Chord SECTION 1 Aircraft Flight Manual General 1 - 12 22.MAR 2016 1.13 Warnings, Cautions and Notes Definitions of Warning, Caution and Note used in text of the Aircraft Flight Manual are listed below: W A R N I N G It means that the failure to observe the specified procedures will lead to an immediate or substantial decrease of the flight safety. Information that may prevent danger to life and crew C A U T I O N It means that the failure to observe the specified procedures will lead to a smaller or longer-term decreased flight safety. Information that may prevent damage to the aircraft and its equipment NOTE Focuses attention to a special step, which is not related directly with the flight safety but which is important or unusual. Information of special importance to the pilot. Aircraft Flight Manual SECTION 2 Limitations 22.MAR 2016 2 - 1 Section 2 LIMITATIONS Table of Contents Section 2 LIMITATIONS ......................................................................... 1 2.1 Airspeed Limitations ................................................................ 2 2.2 Airspeed Indicator Markings.................................................... 3 2.3 Minimum instruments and equipment list ................................ 3 2.4 Power plant Limitations ........................................................... 4 2.4.1 Propeller Limitations............................................................ 4 2.4.2 Engine Limitations ............................................................... 4 2.4.3 Power Plant Instruments Markings ..................................... 5 2.5 Weight Limits........................................................................... 5 2.6 Centre of Gravity Limits........................................................... 6 2.7 Maneuver Limits ...................................................................... 6 2.8 Kinds of Operation Limits ........................................................ 6 2.9 Flight Load Factor Limits ......................................................... 6 2.10 Fuel Limitations ....................................................................... 6 2.11 Outside Air Temperature Limits .............................................. 7 2.12 System and Equipment Limits................................................. 7 2.13 Miscellaneous Limits ............................................................... 7 2.14 Placards .................................................................................. 8 SECTION 2 Aircraft Flight Manual Limitations 2 - 2 22.MAR 2016 2.1 Airspeed Limitations Air- Speed Description KIAS KCAS Remarks VNE Never-exceed speed 126 130 Do not exceed this speed in any flight mode! VC Design Cruise speed 102 105 VO operating Maneuvering speed 88 90 No full or abrupt single pitch control input above this speed. VA Design maneuvering speed 88 90 VFE Maximum flap extended speed 79 81 It must not be exceeded with extended flaps in any position. VS Stalling speed in clean configuration 49 50 Soiling of the wing, rain and frost on the wing increase the airplane’s stalling speed. VS1 Stalling speed in configuration Flaps – pos. II 43 44 Aircraft Flight Manual SECTION 2 Limitations 22.MAR 2016 2 - 3 2.2 Airspeed Indicator Markings Marking KIAS value or range Meaning White band 43-79 Flap operating range. The lower limit is VS1 at the maximum weight in the landing configuration. The upper limit is the maximum flap extended speed. Green band 49-102 Normal operating range. The lower limit is VS1 at the maximum weight and the front-most CG position with retracted flaps. The upper limit is the maximum structural cruising speed. Yellow band 102-126 Caution range. Turns must be made with care and in calm air. Red line 126 Never-Exceed speed for any flight mode. 2.3 Minimum instruments and equipment list Instrument optional required x-station1 Airspeed indicator X -200 Altimeter X -200 Magnetic compass X -250 Skyview - EFIS X -200 Skyview - EMS X -200 Trim indication (pitch and roll) X -200 Safety harness for every used seat X -200 Garmin GPS X -200 Radio X -200 Transponder X -200 ELT X2 1248 1 mm aft of wing leading edge 2 depending on national regulations SECTION 2 Aircraft Flight Manual Limitations 2 - 4 22.MAR 2016 2.4 Power plant Limitations 2.4.1 Propeller Limitations Number of Propellers: 1 Propeller Type: Ground adjustable Blade angle 22°±°0.5°Measured at distance 425 mm from the root of the blade Propeller Manufacturer: Neuform Propeller Model Name: CR3-65 (IP) 47-101,6 Number of Blades: 3 Propeller Diameter: 1.65 m Propeller Speed: Max.: 2 600 RPM (equals 6320 engine RPM; exceeds engine Max RPM 2.4.2 Engine Limitations Number of Engines: 1 Engine Manufacturer: BRP-Power train Engine Model Number: 912 S / ULS Max. Power: 73.5 kW (100 HP) Speed: Max.: 5800 RPM Speed over 5 500 RPM is restricted to 5 min. Min.: 1 400 RPM Engine operation at zero gravity Max.: 5 second at max. -0,5g Coolant Temperature: Max.: 120° C (248° F) Oil Pressure: Max.: 7 bar (102 psi); For a short period admissible at cold start Min.: 0,8 bar (12 psi) Below 3 500 RPM Oil Temperature: Max.: 130° C (266° F) Min.: 50° C (120° F) Fuel Pressure: Max.: 0.50 bar Min.: 0.15 bar Exhaust Gas Temperature (EGT): Max.: 880° C (1616° F) /take-off/ Engine Start Operating Max.: 50° C (120° F) / ambient / Aircraft Flight Manual SECTION 2 Limitations 22.MAR 2016 2 - 5 Temperature: Min.: -25° C (-16° F) / oil / 2.4.3 Power Plant Instruments Markings Instrument Red line Lower limit Yellow band Warning range Green band Normal operation Yellow band Warning range Red line Upper limit Tachometer 0÷220 RPM 220÷1350 RPM 1 350÷ 5 500 RPM 5 500÷ 5 800 RPM 5 800÷ 5900 RPM Manifold Pressure ----- ----- 600÷926 mbar 926÷1 014 mbar 1 014 mbar Exhaust Gas Temperature ----- 0÷800 °C 800÷850 °C 850÷880 °C 880÷900 °C Coolant Temperature ----- 50÷75 °C 75÷110 °C 110÷120 °C 120÷135 °C Oil Temperature 0÷50 °C 50÷90 °C 90÷110 °C 110÷130 °C 130÷150 °C Oil Pressure 0÷0.8 bar ----- 0.8÷5.0 bar 5.0÷7.0 bar 7.0÷8.0 bar Fuel Pressure 0.15 bar ----- 0.15÷0.50 bar ----- 0.5÷0,7 bar Fuel Flow ----- ----- 0÷25 l/h 25÷30 l/h 30÷35 l/h Ammeter -15÷-14 A -14÷-12 A -12÷+23 A +23÷+24 A +24÷+25 A Voltmeter 10÷11 V 11÷12.4 V 12.4÷14.6 V 14.6÷15.6 V 15.6÷16 V Fuel Capacity 0÷5 litres 5÷10 litres 10÷45+ litres ----- ----- 2.5 Weight Limits Maximum Takeoff Weight 600 kg Maximum Landing Weight 600 kg Minimum Weight of Crew 55 kg Maximum Baggage Weight 7.5kg per Compartment/15kg Total Maximum Empty Weight 410 kg SECTION 2 Aircraft Flight Manual Limitations 2 - 6 22.MAR 2016 2.6 Centre of Gravity Limits CG range: Forward: 24 %MAC Aft: 32 %MAC 2.7 Maneuver Limits Viper SD-4 RTC airplane is designed only for non-aerobatic operation! Aerobatic flights and intentional spins with the Viper SD - 4 are strictly forbidden. 2.8 Kinds of Operation Limits Viper SD-4 RTC may only be used for flights during the day, under VMC conditions, according to the day-VFR rules. Flights in icing conditions, flight into IMC conditions are prohibited. Intentional spinning and aerobatic maneuvers are prohibited. Maximum demonstrated components of wind for Take-off and Landing Cross Max.: 15 kts (7.5 m/s) Tail Max.: 5 kts (2,5 m/s) 2.9 Flight Load Factor Limits In normal operations: Maximum Positive g-load: +4 g Maximum Negative g-load: -2 g With Flaps out max pos. g-load +2 g With Flaps out max neg. g-load 0 g 2.10 Fuel Limitations Fuel Capacity in Each Fuel Tank: 50 litres Total Fuel Capacity: 100 litres Unusable Fuel in Each Tank: 5 litres Total Usable Fuel Capacity: 90 litres Aircraft Flight Manual SECTION 2 Limitations 22.MAR 2016 2 - 7 2.11 Outside Air Temperature Limits Maximum outside temperature +40 °C Minimum outside temperature -15 °C (at ground) 2.12 System and Equipment Limits Starter Starter activation without interruption Max.: 10 seconds Cooling period after 10 seconds starter use Min.: 2 minutes Ballistic Parachute Rescue System Allowed never exceed speed KTAS for use VNE Max.: 170 kts Temperature range Max.: +60° C Min.: - 40° C On-board electric socket Power consumption 12V Max.: 1 A (12 W) 2.13 Miscellaneous Limits Flap position III (40deg) is only to be used for emergency and precautionary short field landings as described in section 3. At this flap setting, full trimmability is not possible. Pilot in command seat is the left hand seat. No smoking on board of Viper SD-4 RTC aircraft. SECTION 2 Aircraft Flight Manual Limitations 2 - 8 22.MAR 2016 2.14 Placards Location Placard Inside the Cabin The Left Instruments Panel Above the push button starter START Above the generator switch/circuit breaker GENRTR Above the master switch/circuit breaker MASTR Above the instrument switch/circuit breaker INSTR Above left RED warning indicator light GENRTR WARNING Above GREEN indicator light FUEL PUMP Above middle RED indicator light ALARM EMS Above right RED indicator light STARTER PROCESS Above the EFIS screen USB interface connector USB SkyView ONLY At the top in the right corner near centre panel KIAS LIMITS Above the BRS activation handle in the centre at the bottom TO ACTIVATE PARACHUTE PULL HANDLE Left at the bottom POH/AMM Centre Instrument Panel At the top in the centre (Call sign) At the left side in line with switches/circuit breakers ON OFF Above the EMS switch/circuit breaker/ EMS Above the Inter COMM switch/circuit breaker INTRCM Above the COMM Transceiver switch/circuit breaker RADIO Above the EFIS switch/circuit breaker EFIS Above the Fuel Pump switch/circuit breaker FUEL PUMP Above the Start Power switch/circuit breaker STARTER POWER Above the Flaps switch/circuit breaker FLAPS Aircraft Flight Manual SECTION 2 Limitations 22.MAR 2016 2 - 9 Location Placard At the left side in line with switches/circuit breakers ON OFF Centre Instrument Panel Above the Trim switch/circuit breaker TRIM Above the GPS Navigation receiver switch/circuit breaker GPS Above the Transponder SSR ATC switch/circuit breaker XPDR Above the Navigation Lights switch/circuit breaker NAV LIGHTS Above the Strobe Lights switch/circuit breaker STROBE Above the Socket 12V/1A switch/circuit breaker SOCKET 12V/1A Above position of blended opening for reserve switch/circuit breaker RES. Left at the bottom Do not exceed MTOM 600kg! In the centre at the bottom AEROBATICS and intentional spins are PROHIBITED ! Right at the bottom This aircraft has been approved only for VFR day flights under no icing conditions and must be operated within limitations defined in AFM Right Instrument Panel Above the EMS screen USB interface connector USB SkyView ONLY Above the SOCKET 12V (Cigarette Lighter Connector) SOCKET 12V Above the Cabin Heating control handle CABIN HEAT Above the Carburettor Heating control handle CARB. HEAT Above the Cylinder Heating control handle CYLINDER AIR SECTION 2 Aircraft Flight Manual Limitations 2 - 10 22.MAR 2016 Location Placard Cylinder Air lever head PULL ON Cabin Heat and Carb. Heat lever heads PULL CLOSE Above instrument Panel Inside of cockpit on the upper left/right cover of instrument panel WARNING This aircraft is equipped with ballistically-deployed emergency parachute system Front part of the centre console between the seats Under/In back of the THROTTLE LEVER THROTTLE Under the Choke control handle Ý CHOKE PULL & HOLD ON On top of the Brake Lever BRAKE Under the Brake Lever head Viper SD-4 RTC (logo) Behind the Seats Baggage compartment (2x) Baggage 7,5kg Behind the baggage compartment NOT FOR BAGGAGE Storage Compartment Storage compartment for Pilot Operation Handbook / Aircraft Maintenance Manual ê POH/AMM Air Valve Informative direction at each air valve on canopy CLOSE ó OPEN OPEN ó CLOSE Aircraft Flight Manual SECTION 2 Limitations 22.MAR 2016 2 - 11 Figure 2-1 Cabin placards preview SECTION 2 Aircraft Flight Manual Limitations 2 - 12 22.MAR 2016 Location Placard Outer airplane surfaces Under the oil dipstick cover located at the right side of the upper part of the engine cowl in front of the canopy edge RON 424 / SAE 10W-40 API min. SG or higher (see also SI-912-016 ch. 3 the latest issue) The right side of the fuselage in front of the leading edge of the right wing and in front of the lower edge of the edge (BRS rocket cover) DANGER - EXPLOSIVE - EGRESS triangle + pictogram The right side of the fuselage in front of the leading edge of the right wing and in front of the lower edge of the edge under the warning triangle (BRS rocket cover) STAY CLEAR Front part of the fuselage (2 x, left side + right side; under the upper edge and in front of the aft edge of the lower engine cowl) SD-4 (logo) Fuel tank (edgewise fuselage) NO STEP Near the tank filler cap of the fuel tank (2x) MAX 50L, Usable Fuel 45L, Min RON 95 Ailerons, Flaps, Elevator, Elevator up-float tab, Rudder (trailing edge) NO PUSH Flaps (edgewise fuselage) RED RECTANGLE + RED CROSS + NO STEP (written on red cross) Canopy (2 x, left side + right side; in front of the lower front edge of the ventilation window, nearby lock handles) OPEN - CLOSE (PICTOGRAM) Vertical stabilizer (2x, left side + right side) Viper SD-4 RTC (logo) The wheel fairing of the front landing gear – at the left side of just above the wheel axis seat TYRE 120 + 10kPa Aircraft Flight Manual SECTION 2 Limitations 22.MAR 2016 2 - 13 Location Placard The wheel fairing at the left leg of the main landing gear - at the left side just above the wheel axis seat (1x) The wheel fairing at the right leg of the main landing gear - at the right side just above the wheel axis seat (1x) TYRE 220 + 10kPa Right side of fuselage near the location of the ELT in Baggage compartment White cross on green rectangle Left side of fuselage near the location of the First-aid kid in Baggage compartment White pictogram of fire extinguisher on red rectangle Left side of fuselage near the location of the Fire extinguisher in Baggage compartment Black ELT LOCATED HERE on yellow triangle The fuselage (2x, left and right side between wing trailing edge and vertical stabilizer leading edge at the upper half part of the fuselage The bottom part of the left wing (Registration) SECTION 2 Aircraft Flight Manual Limitations 2 - 14 22.MAR 2016 Figure 2-2 Outer airplane surface placards preview Aircraft Flight Manual SECTION 3 Emergency Procedures 22.MAR 2016 3 - 1 Section 3 EMERGENCY PROCEDURES Table of Contents Section 3 EMERGENCY PROCEDURES .............................................. 1 3.1 Airspeeds for Emergency Procedures .................................... 3 3.2 Engine Failure ......................................................................... 3 3.2.1 During Take-off run ............................................................. 3 3.2.2 After Take-off ...................................................................... 3 3.2.3 Engine Failure in-Flight, engine restart ............................... 4 3.2.4 Engine shut down after Failure in-Flight.............................. 5 3.3 Exceeding of Maximum Admissible Engine Speed ................. 5 3.4 Not possible power setting - Throttle lever linkage cables failure 5 3.5 Oil System Failures ................................................................. 5 3.5.1 Oil Pressure Below Minimum – During Flight...................... 5 3.5.2 Oil Pressure Over Maximum – On Ground ......................... 5 3.5.3 Oil Pressure Over Maximum – During Flight....................... 6 3.5.4 Exceeding of Maximum Admissible Oil Temperature – On Ground 6 3.5.5 Exceeding of Maximum Admissible Oil Temperature – During Flight .................................................................................... 6 3.6 Cooling System Failures ......................................................... 6 3.6.1 Exceeding of Maximum Admissible Coolant Temperature . 6 3.7 Propeller Failures During Flight............................................... 7 3.8 Glide ........................................................................................ 7 3.9 Landing Emergencies ............................................................. 7 3.9.1 Emergency Landing without Engine Power ........................ 7 SECTION 3 Aircraft Flight Manual Emergency procedures 3 - 2 22.MAR 2016 3.9.2 Precautionary Landing with Engine Power ......................... 8 3.9.3 Approach and Landing with Flaps Retracted ...................... 9 3.10 Landing Gear failures .............................................................. 9 3.11 Smoke and Fire ..................................................................... 10 3.11.1 Engine Fire During Take-off (On the Ground) ............... 10 3.11.2 Engine Fire After Take-off and During Flight ................. 10 3.11.3 Fire in the cockpit .......................................................... 11 3.12 System Emergencies ............................................................ 11 3.12.1 Electrical system failures ............................................... 11 3.13 Loss of EMS or EFIS functionality ......................................... 12 3.14 Loss of Flight Controls .......................................................... 13 3.15 Spin ....................................................................................... 13 3.16 Vibrations .............................................................................. 14 3.17 Activation of the rescue parachute ........................................ 14 3.18 List of EMS warning alerts .................................................... 15 3.19 List of EMS caution alerts ..................................................... 18 Aircraft Flight Manual SECTION 3 Emergency Procedures 22.MAR 2016 3 - 3 3.1 Airspeeds for Emergency Procedures Engine Failure After Take-off: Flaps UP .......................................................... 64 KIAS Flaps Down-Position I ...................................... 64 KIAS Air Start: ..................................................................... >70 KIAS Balked Landing: ......................................................... >53 KIAS Maximum Glide: ......................................................... 64 KIAS Landing Without Engine Power: Flaps Up .......................................................... 64 KIAS Flaps Down ...................................................... 64 KIAS 3.2 Engine Failure 3.2.1 During Take-off run THROTTLE LEVER .................. Pull to idle Brake ......................................... Brake until STOP Fuel Pump ................................. Switch OFF FUEL selector .......................... CLOSE IGNITION .................................. Switch OFF Section switches ....................... Switch OFF 3 Main switches ........................ Switch OFF 3.2.2 After Take-off Airspeed .................................... Maintain 65 KIAS Fuel Pump ................................. Switch OFF IGNITION .................................. Switch OFF 3 position FUEL LANE selector CLOSE Flaps ......................................... Extend as desire Carry out an Precautionary Landing Instruments ............................... Switch OFF after landing Section switches ....................... Switch OFF 3 Main switches ........................ Switch OFF SECTION 3 Aircraft Flight Manual Emergency procedures 3 - 4 22.MAR 2016 C A U T I O N If the engine fails at low altitudes, carry out landing in the direction of the flight (with diverting, if there are obstacles in the direction of the flight). 3.2.3 Engine Failure in-Flight, engine restart Airspeed .................................... Maintain 70 KIAS Carburettor Heat ....................... ON Landing field .............................. Chosen All unnecessary equipment ....... Switch OFF 3 position FUEL LANE selector Switch to the tank with more fuel FUEL pump ............................... Switch ON Fuel Pressure ............................ Confirm IGNITION .................................. Switch OFF than to BOTH If engine is not windmilling STARTER POWER ................... Check if it is ON or switch ON START button ........................... Press until engine starts If starter is inoperative and propeller is not windmilling: AIRSPEED ................................ 115KIAS Engine is running ...................... Switch ON all necessary equipment THROTTLE LEVER ................. Adjust Carburettor Heat ....................... Check Note: The carburettor heat control should never be used in intermediate position. A gradually reducing power might be caused by carburettor icing – this however is not always noticed; therefore carburettor icing must also be considered as potential reason for complete engine shut down. Note: In case of engine failure maintain speed at best glide and do not reduce speed unnecessary to avoid the propeller stopping. C A U T I O N After starting the engine land as soon as practical. If you fail starting the engine proceed with emergency landing according to the point 3.9.1 Aircraft Flight Manual SECTION 3 Emergency Procedures 22.MAR 2016 3 - 5 3.2.4 Engine shut down after Failure in-Flight Airspeed .................................... Maintain 65 KIAS IGNITION .................................. Switch OFF Fuel Pump ................................. Switch OFF 3 position FUEL LANE selector Switch OFF Carry out Emergency Landing according to the point 3.9.1 3.3 Exceeding of Maximum Admissible Engine Speed Engine Speed ........................... Reduce engine speed 3.4 Not possible power setting - Throttle lever linkage cables failure Air speed ................................... Appropriate to power setting Altitude ...................................... Control by switching ignition ON/OFF as required Airspeed while engine OFF ....... > 70 KIAS Landing ..................................... As soon as practical 3.5 Oil System Failures Oil Pressure Below Minimum – On Ground Engine Speed ........................... Stop the engine immediately Oil system ................................. Check 3.5.1 Oil Pressure Below Minimum – During Flight THROTTLE LEVER .................. Reduce engine power setting to the minimum necessary to maintain flight Oil Temperature ........................ Monitor Landing ..................................... Land as soon as practical / prepare for emergency landing 3.5.2 Oil Pressure Over Maximum – On Ground Engine Speed ........................... Stop the engine immediately Oil system ................................. Check SECTION 3 Aircraft Flight Manual Emergency procedures 3 - 6 22.MAR 2016 3.5.3 Oil Pressure Over Maximum – During Flight THROTTLE LEVER .................. Reduce engine power setting to the minimum necessary to maintain flight Oil Temperature ........................ Monitor Landing ..................................... Land as soon as practical / prepare for emergency landing 3.5.4 Exceeding of Maximum Admissible Oil Temperature – On Ground Engine Speed ........................... Stop the engine immediately Oil system ................................. Check 3.5.5 Exceeding of Maximum Admissible Oil Temperature – During Flight THROTTLE LEVER .................. Reduce engine power setting to the minimum necessary to maintain flight Oil Temperature ........................ Monitor Landing ..................................... Land as soon as practical / prepare for emergency landing 3.6 Cooling System Failures 3.6.1 Exceeding of Maximum Admissible Coolant Temperature THROTTLE LEVER .................. Reduce engine power setting to the minimum necessary to maintain flight Oil Temperature ........................ Monitor Landing ..................................... Land as soon as practical / prepare for emergency landing