Flight Manual. Manufacturer : Tomark s.r.o, Strojnícka 5, Prešov 08001, Slovakia

Transcription

1 Flight Manual Manufacturer : Tomark s.r.o, Strojnícka 5, Prešov 08001, Slovakia Type : Viper SD - 4 Model : UL Serial number : 0042 Aircraft registration : Category : Manufacturer : Aircraft conforming to the Regulation (EC) No. 216/2008 of the European Parliament and Council, Annex II, Article 4, Section 4, letter e), (v), and the UL-2 / LTF-UL airworthiness requirements for ultra light aircraft Tomark s.r.o., Strojnícka 5, Prešov, Slovakia The aircraft must be operated in line with the information and limitations specified in this manual. Date of approval:

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3 Flight Manual Chapter 0 Technical Information 0. Technical information 0.1 Aircraft details Completed by the manufacturer of the plane. Type Manufacturer Serial number Year of manufacture Airframe Viper SD - 4 TOMARK s.r.o Engine ROTAX 912 ULS2 BRP-ROTAX GmbH Propeller Peszke AS 1730 Pezske s.c. 642/ 1929, 1930,

4 Chapter 0 Technical Information Flight Manual 0.2 Details of the owner of the aircraft The details of the owner of the aircraft are completed by the owner of the aircraft according to the details specified in the Certificate of the Registration of the Aircraft in the Civil Aircraft Register. Owner of the aircraft Name : NLA Sweden AB Address : Svenska vägen LUND From :... signature Change of the owner of the aircraft : Name : Address : From :... signature 0-4

5 Chapter 0 Flight Manual Technical Information Change of the owner of the aircraft : Name : Address : From :... signature Change of the owner of the aircraft : Name : Address : From :... signature 0-5

6 Chapter 0 Flight Manual Technical Information 0.3 List of changes Any change in the valid manual shall be recorded in the following table, and, in the case of approved sections, the change must be approved by the responsible authority that approves airworthiness. A new or modified text on corrected pages shall be marked by a vertical line on the left margin and the number of the change, with the date of approval, shall be specified on the bottom left margin. Change ordinal number Number of bulletin by which the change was made Numbers of the pages the change concerns Date of the issuing of new pages Date of the replacement of pages and signature 0-6

7 Flight Manual Chapter 0 Technical Information 0.4 List of valid pages Chapter Page Date Chapter Page Date

8 Chapter 0 Flight Manual Technical Information 0.5 Abbreviations C degree Celsius - unit of temperature Amp. ampere - unit of electric current bar. bar - unit of pressure calibrated airspeed, airspeed corrected by the error of CAS the speed measuring system FLAPS flaps FUEL PUMP fuel pump GPS global positioning system HP horse power - unit of power IAS indicated airspeed inhg English unit of atmospheric pressure kw kilowatt - unit of power mbar millibar - unit of atmospheric pressure ISA international standard atmosphere NACA National Advisory Committee for Aeronautics EASA European Aviation Safety Agency OFF switched off RADIO designation of a VHF communication device MAC mean aerodynamic chord STROBO designation of anti-collision lights of the aircraft TRIM trimming V volt - unit of potential difference V A design manoeuvring speed V FE maximum flap extended speed V NE never exceed speed V S stalling speed in clean configuration V SO stalling speed in landing configuration VFR visual flight rules 0-8

9 Flight Manual Chapter 0 Technical Information 0.6 Contents 1. General information 2. Limitations 3. Emergency procedures 4. Normal procedures 5. Performance 6. Weight and Balance 0-9

10 Chapter 0 Flight Manual Technical Information Left blank intentionally 0-10

11 Flight Manual Chapter 1 General Information 1. General Information 1.1 Regulatory base 1.2 Warnings, cautions and notes 1.3 Important information 1.4 Drawing of the aircraft 1.5 Description of the aircraft Fuselage Wing Empennage Cockpit Landing gear Control Fuel system Engine Propeller Orientation of the moments of control elements Basic technical specifications of the aircraft Controls and instruments in the cockpit Basic control of onboard instruments 1-1

12 Chapter 1 Flight Manual General Information 1.1 Regulatory base This aircraft has been built in conformity with the Regulation (EC) No. 216/2008 of the European Parliament and Council, Annex II, Article 4, Section4, letter e), (v), and the Czech UL-2 and German LTF-UL airworthiness requirements for ultra light aircraft. 1.2 Warnings, cautions and notes The warnings, cautions and notes contained in this manual have the following meanings WARNING It means that the failure to observe the specified procedures will lead to an immediate or substantial decrease of the flight safety. CAUTION It means that the failure to observe the specified procedures will lead to a smaller or longer-term decreased flight safety. NOTE Focuses attention to a special step, which is not related directly with the flight safety but which is important or unusual. 1-2

13 Flight Manual Chapter 1 General Information 1.3 Important information The content of this Flight Manual covers all instructions for carrying out a safe flight with the Viper SD - 4 aircraft. Each pilot, student pilot, instructor and maintenance technician of the Viper SD - 4 aircraft is obliged to get acquainted with this Flight Manual. The Viper SD - 4 aircraft is operated upon its user s own responsibility. The Viper SD - 4 is designed for sporting purposes, recreational purposes and pilot training. This Flight Manual must be present on board of the aircraft, together with other prescribed documents, during all flights. The manufacturer of the Viper SD - 4 aircraft does not bear responsibility for damage to the aircraft caused by the use of the aircraft in breach of individual provisions of the operation, control or maintenance documentation of the aircraft. Documentation for the operation, control and maintenance of Viper SD - 4 : Flight Manual Technical Description and Operation and Maintenance Manual Engine Operation Manual MGL Voyager EFIS Operation Manual MGL XTreme EFIS Operation Manual Peszke AS Type Propeller s Manual Garrecht VT-01 Transponder Manual Funkwerk ATR 833 VHF Communication Transceiver Manual GRS6/473 SD DULV Ballistic Rescue System Manual 1-3

14 Chapter 1 Flight Manual General Information 1.4 Drawing of the aircraft 1-4

15 Flight Manual Chapter 1 General Information 1.5 Description of the aircraft Viper SD - 4 is an aerodynamically controlled, single-engine, single-pilot, two-seater, low-wing all-metal aircraft with the side-by-side configuration of the seats. Fuselage The aircraft s fuselage is made as an all-metal monocoque frame structure, comprising stringers and aluminium alloy skin; the vertical stabiliser is an integral part of the fuselage. The engine compartment is separated from the crew compartment by a steel firewall. Wing It is all-metal, of a rectangular planform and a single-spar design, with an auxiliary spar. The wing is equipped with ailerons, slot flaps, controlled electrically into four positions, and with integral fuel tanks. The wing tips are equipped with composite wingtip devices. Empennage It consists of a vertical tail surface and a horizontal tail surface at the back end of the fuselage. The vertical tail surface is made of a singlepiece stabiliser with a right and left elevators, which are interconnected by the control transmission. The elevator is equipped with a trimming tab, controlled electrically. The vertical tail surface of a trapeze shape consists of a vertical stabiliser and a rudder. Cockpit The seats are configured side-by-side. The cockpit is covered by a clear or tinned canopy, which ensures very good outlook. The canopy opens up and backwards. The closing of the canopy is a two point one, controlled by two independent levers on the inner sides of the canopy, which allow its locking. The cockpit is ventilated by the pressure of the flowing air above the instrument panel without a possibility to control the air through-flow. The canopy is equipped with two ventilation windows. The cockpit is equipped with three air vents. Two vents are located on 1-5

16 Chapter 1 Flight Manual General Information the left side of the fuselage in front of the cockpit and one on the right side of the fuselage in front of the cockpit. The air from the lower two vents is led to the air showers. The air showers are controllable and located in the corners of the instrument panel. The cockpit is equipped with an on-board electric socket, located on the right instrument panel. The socket is under voltage only when the master switch of the on-board electric network is switched on. CAUTION Connect only appliances with a power consumption of not more than 30 watts to the on-board network socket. Landing gear It is tricycle with a front wheel. The main landing gear comprises composite springs; the wheels of the main landing gear are braked by hydraulic disk brakes. The brakes are controlled centrally by a lever located on the central panel, between the pilots seats. The front landing gear is cushioned by a rubber band. The front landing gear wheel is steerable. The wheels of the landing gear are equipped with streamline covers. Control It is doubled. The elevator and the ailerons are controlled via control rods and the rudder is controlled via a pair of Bowden cables. Fuel system The fuel system comprises two lockable integrated tanks in the wings, equipped with fuel gauge floats and a drain valve, fuel piping, a main fuel valve and a fuel filter. Engine The aircraft is powered by a non-certified Rotax 912 ULS engine, whose cylinder heads are liquid-cooled and cylinders are air-cooled. The engine is equipped with a reduction gear and two carburettors, an electric starter, dual ignition and an exhaust silencer. 1-6

17 Flight Manual Chapter 1 General Information Propeller There is a Peszke AS 1730/1950 propeller with a constant-speed effect installed on the aircraft. The propeller used has very good flight and performance parameters, which ensure optimal transformation of the engine s power to a forward thrust during a take-off, climbing, as well as cruising modes. It also induces sufficient drag in descent modes or breaking by the engine. The description of the propeller is contained in the Peszke AS Type Propeller s Manual Orientation of the movements of control elements Rudder The pushing of the left control pedal turns aircraft leftwards during its movement on the ground and in the air; the pushing of the right control pedal turns the aircraft to the right. Control stick When the control stick is pulled, the nose of the aircraft goes up and the aircraft ascends, when the control stick is pushed, the aircraft descends. When the control stick is moved to a side, the aircraft rolls to the side of the movement of the control stick. Landing gear brakes Both wheels of the main landing gear are braked simultaneously, without the possibility of independent braking of individual wheels. The hydraulic brake control lever is located on the central control panel between the pilots seats, under the engine throttle lever. The braking effect on the wheels is actuated by the pushing of the lever downwards. The lever may be locked in the braking position by a push-button on the left side of the braking cylinder bracket. 1-7

18 Chapter 1 Flight Manual General Information Flaps The flaps are controlled in four positions electrically, by a lever control, located on the central control panel between the pilots seats. The signalling of individual positions of the flap lever control is done by a single LED in the OFF position (retracted) and three yellow LEDs in positions I, II and III (extended). By pushing the lever to the right and pulling it backwards, the pilot extends the flaps into individual positions: 0 - OFF I - 15 II - 30 III - 40 When the flap control lever is moved forwards, the flaps will retract. The flap servo is equipped with overload protection, which may be switched on or off according to the user s preferences. In the case of overloading, it is not possible to extend the flaps to a higher angle. Trimming The control of the elevator s trim tab and the right aileron tab are electric, by the joystick buttons located on the control stick of the commander s seat. The indicators of the positions of the trim tabs are located on the left instrument panel above the MGL Voyager EFIS. By pushing the joystick button at the top of the control stick forward, the aircraft is balanced into a nose-heavy position; by pushing it backward, the aircraft is balanced into a tail-heavy position. Two additional buttons on the control stick are reserved for the control of the autopilot and are not connected on this aircraft. 1-8

19 Flight Manual Chapter 1 General Information Basic technical specifications of the aircraft Wing span 8.34 m Length 6.40 m Height 2.20 m Wing area m 2 Wing chord 1.29 m Aspect ratio 6.6 Wing planform rectangular Sweep angle 0 Wing twist 0 Dihedral 3 Control surfaces Aileron length 0.96 m Aileron chord 0.27 m Aileron area 0.26 m 2 Type of flap slot Flap length m Flap depth m Flap area 0.57 m 2 Horizontal tail surface Planform rectangular Span m Chord m Area 2.20 m 2 Dihedral 0 Leading edge sweep angle 0 Twist 0 Elevator Chord 0.32 m Span 2.60 m Area 0.75 m 2 1-9

20 Chapter 1 Flight Manual General Information Vertical tail surface Planform trapeze Root chord m End chord m Area m 2 Height 1.3 m Rudder Area 0.61 m 2 Leading edge sweep angle 35 Trailing edge sweep angle 11 Landing gear Track width Wheel base Brakes mm mm hydraulic, disk on the wheels of the main landing gear the front wheel is not braked Cushioning of the main landing gear by tyres, flexibility of the legs Cushioning of the front wheel by the tyre and a rubber band Main landing gear wheel dimensions Front landing gear wheel dimensions Power plant Engine Maximum take-off power ROTAX 912 ULS 100 HP 73.4 kw at 5,800 RPM Propeller Peszke AS 1730/1950 Number of blades 3 Diameter 1730 mm Rescue system Type Weights Empty weight of the aircraft Maximum take-off mass MTOM Fuel tank capacity Galaxy High Technology GRS6/473 SD DULV 297 kg 472,5 kg 2 x 35 litres 1-10

21 Flight Manual Chapter 1 General Information Controls and instruments in the cockpit 1 Dual control stick 15 Canopy lock indicators 2 Dual rudder control pedals 16 Aileron trim indicator 3 Flaps 17 Elevator trim indicator 4 Elevator trim buttons 18 Funkwerk ATR833 transceiver 5 Aileron trim buttons 19 MGL Voyager EFIS/EMS 6 Main fuel valve 20 Magnetic compass 7 Engine throttle 21 Garrecht VT-01 transponder 8 Brake lever 22 Section switches/circuit breakers 9 Ignition switch ACS 23 MGL XTreme EFIS/EMS 10 Master switch 24 Onboard 12 V power supply socket 11 Air shower 25 Choke 12 Battery charging warning light 26 Ballistic rescue parachute control 13 EMS alarm light 27 Push-to-talk button 14 Electric fuel pump indicator 28 Headset sockets 1-11

22 Chapter 1 Flight Manual General Information Basic control of onboard instruments MGL Voyager EFIS/EMS To switch on: Switch on the EFIS section switch. To switch off: Switch off the EFIS section switch. MGL XTreme EMS To switch on: Switch on the EMS section switch. To switch off: Switch off the EMS section switch. Garrecht VT-01 transponder To switch on: Push the ON/OFF button. STBY: to choose the standby mode. ON: to choose the A/C and S mode, altitude info set to zero. ALT: to choose the A/C and S mode. To switch off: Push the ON/OFF button. Funkwerk ATR 833 transceiver: To switch on: Push the I/O button for about 0.5 sec. To adjust the volume: Push the SET button for 1.5 sec., set the VOL option, and adjust the volume by turning the VOL/SEL button. To choose a standby frequency: With the button, highlight the part of the standby frequency to be changed and change its value by turning the FREQ button. To switch between the standby and active frequencies: Push the button. To switch off: Push the I/O button for about 2 sec. 1-12

23 Flight Manual Chapter 2 Limitations 2. Limitations 2.1 Introduction 2.2 Types of operation 2.3 Weights and useful load Maximum useful load 2.4 Aircraft s CG positions 2.5 Power plant Operational limitations of the Rotax 912 ULS engine Colour markings of the power plant instruments 2.6 Propeller Operational limitations of the propeller 2.7 Fuel Fuel reserve Fuel consumption 2.8 Lubrication oil 2.9 Airspeed limitations 2.10 Manoeuvring limitations Allowed turns Flight g-forces 2.11 Service ceiling 2.12 Meteorological limitations 2.13 Crew Crew Minimum crew weight 2.14 Luggage distribution 2.15 On-board smoking 2.16 Labels 2-1

24 Chapter 2 Flight Manual Limitations 2.1 Introduction This section contains operational limitations specified by the aircraft s manufacturer for the safe operation of the aircraft, of the power plant and of the systems and equipment of the aircraft. The operational limitations specified in this section have been approved European Aviation Safety Agency. 2.2 Types of operation Viper SD - 4 may only be used for flights during the day, under the VMC conditions, according to the VFR rules. Other flights are forbidden. Aerobatic flights and intentional spins with the Viper SD - 4 are forbidden. 2.3 Weights and payload Aircraft empty weight kg Maximum take-off weight kg Maximum landing weight kg Maximum useful load Maximum crew weight kg Minimum crew weight kg Maximum fuel weight kg Maximum luggage weight... 2 x 7.5 kg Table: Payload versus fuel quantity Fuel tank filling Litres Crew + luggage weight 1/ kg 3/ kg 1/ kg 1/ kg 2-2

25 Flight Manual Chapter 2 Limitations WARNING Do not exceed the maximum take-off weight of kg. 2.4 Aircraft s CG positions Empty aircraft CG position % 297 kg Operational limit CG positions... front 25.0 % 402 kg rear 32.5 % kg Design CG range % MAC 2.5 Power plant Operational limitations of the Rotax 912 ULS engine Minimum air temperature for starting C Maximum air temperature for starting C Minimum oil temperature C Maximum oil temperature C Maximum cylinder head temperature C Maximum allowed engine RPM... 5,800 (5 min) Maximum permanent engine RPM... 5,500 Idle engine RPM... 1,400 Maximum oil pressure... 7 bar (102 psi) Minimum oil pressure bar (12 psi) Maximum fuel pressure bar (6 psi) Minimum fuel pressure bar (2 psi) CAUTION The aircraft is not equipped with a fuel pressure sensor. 2-3

26 Chapter 2 Flight Manual Limitations Colour marking of the engine instruments Instrument Red line Lower limit Yellow band Warning range Tachometer 1,400 RPM Cylinder head thermometer Oil temperature Green band Normal operation 1,400 5,500 RPM Yellow band Warning range 5,500 5,800 RPM Red line Upper limit 5,800 RPM max. 5 min 60 C C C C 135 C 50 C C C C 130 C Fuel pressure Oil pressure 0.8 bar (12 psi) below 3,500 RPM bar (12 29 psi) bar (29 73 psi) above 3,500 RPM bar ( psi) 7.0 bar (102 psi) Ammeter -14 A A A 16 A Voltmeter 11 V V V 15.6 V Fuel gauge 10 litres litres WARNING In the event of exceeding operational limits of the engine, it is necessary to make a record in the engine log book and carry out an inspection of the engine. 2-4

27 Flight Manual Chapter 2 Limitations 2.6 Propeller Operational limitations of the Peszke AS 1730/1950 propeller with constant-speed effect: Maximum RPM of the propeller:...3,000 RPM Operation temperature range: C C The propeller has very good flight and performance parameters, which ensure optimal transformation of the engine s power to a forward thrust during the take off and climbing as well as during cruising modes. It also produces a sufficient drag during descents and braking by the engine. In the case of any damage to the propeller that causes increased vibrations, it is necessary to interrupt the flight and repair the propeller according to the manufacturer s instructions. WARNING In the event of exceeding the operational limits of the propeller, it is necessary to make a record in the propeller s log book and check the propeller in line with its documentation. The manufacturer of the aircraft recommends to observe the following values: Power Setting Engine RPM Manifold Pressure mbar (inhg) Take off (27.0) Climb (26.5) Cruise (23-25) 2-5

28 Chapter 2 Flight Manual Limitations WARNING Do not start the engine without a mounted propeller. There is a risk of exceeding its maximum allowed RPM. 2.7 Fuel The following fuels may be used MOGAS 912 UL/A/F 912 ULS/S European standard EN 228 Normal 1) EN 228 Super 1) EN 228 Super 2) EN 228 Super plus 1) EN 228 Super plus 2) Canadian standard CAN/CGSB-3,5 Grade 1 3) CAN/CGSB-3,5 Grade 3 4) US standard ASTM D 4814 ASTM D 4814 AVGAS US standard 1) min. ROZ 90 2) min. ROZ 95 3) min. AKI 87 4) min. AKI 91 AVGAS 100LL (ASTM D910) AVGAS 100LL (ASTM D910) The AVGAS 100LL petrol, with its higher content of led, more stresses valve seats, forms more sediments in the lubrication system and carbonates more. Use this fuel only in the event of problems with the fuel evaporation or if no other type of fuel is available. You can find more information about the choosing of the right fuel in the valid issue of the Service Information SI

29 Flight Manual Chapter 2 Limitations Fuel reserve Total tank volume Left tank litres Right tank litres Unusable fuel reserve Left tank litre Right tank litre Minimum fuel quantity for take off Left tank litres Right tank litres CAUTION At outside air temperatures exceeding 25 C do not fill the fuel tanks at more than 90 % of their maximum volume Fuel consumption The fuel consumption is influenced significantly by the following factors: flying technique, total aircraft weight, flight altitude, chosen flight mode and meteorological conditions. For a stable flight at 190 km/h (102 kts) of indicated airspeed with the Rotax 912 ULS engine, the Peszke AS 1730/1950 propeller and the aircraft s weight kg, the average fuel consumption is 18.5 litres of fuel per hour. 2-7

30 Chapter 2 Flight Manual Limitations 2.8 Lubrication oil For the lubrication of the ROTAX 912 ULS engine only use oils marked according to API SG or higher. ROTAX 912 ULS is lubricated by the Shell Advance ULTRA4 10W-40 or AeroShell Oil Sport Plus 4 Aviation Oil 10W 40. Filled oil quantity... 3 litres Minimum oil quantity:... 2 litres Oil consumption: litre/h You can find details in the Operation Manual for the ROTAX 912 ULS engine, section You can find more information on the selection of suitable oil in the valid issue of the Service Information SI

31 Flight Manual Chapter 2 Limitations 2.9 Airspeed limitations The following airspeeds apply at the maximum take-off weight of kg: Airspeed Description IAS (km/h) (kts) V NE Never-exceed speed 240 (130) V NO V A Maximum structural cruising speed Design manoeuvring speed 200 (108) 154 (83) V ra Rough air speed 160 (86) V FE V S1 V SO Maximum flap extended speed Stalling speed in clean configuration Stalling speed in landing configuration 134 (72) 77 (42) 65 (35) Notes Do not exceed this speed in any flight mode! Do not exceed this speed except when flying in calm air. Above this speed do not use full movements of controls or make fast interventions into the aircraft s control the aircraft might get overloaded. Do not exceed this speed except in calm air. Flight in rotors of lee waves, in storm clouds or above mountain ridges is considered to be a flight in rough air. It must not be exceeded with extended flaps. The aircraft s weight, soiling of the wing, rain and frost on the wing increase the aircraft s stalling speed. 2-9

32 Chapter 2 Flight Manual Limitations Marking on the airspeed indicator Marking White band Green band Yellow band Red line Value or range (IAS) in km/h (kts) (35-72) (42-108) ( ) 240 (130) Meaning Operating range with extended flaps. The lower limit is V S1 at the maximum weight in the landing configuration. The upper limit is the maximum flap extended speed. Normal operating range. The lower limit is V SI at the maximum weight and the front-most CG position with retracted flaps. The upper limit is the maximum structural cruising speed. Turns must be made with care and in calm air. Never-exceed speed for any flight mode. 2-10

33 Flight Manual Chapter 2 Limitations 2.10 Manoeuvring limitations Allowed turns: Sharp turns with banks of up to 60 recommended entry speed 160 km/h (86 kts). WARNING The aircraft is designed only for non-aerobatic operation Flight g-forces A flight g-force expresses the loading of the aircraft s structure in operation by aerodynamic forces in relation to its total allowed maximum take-off weight and airspeed. At its maximum take-off weight of kg, Viper SD - 4 has the allowed operational g-forces as follows: positive + 4 negative - 2 Turning speed Speed in km/h (kts) g-force V A turn with the full movement of the elevator 154 (83) +4 V NE never-exceed airspeed 240 (130) +4 V A turn with the full movement of the elevator V NE never-exceed airspeed 154 (83) (130) -2 V FE with extended flaps 134 (72)

34 Chapter 2 Flight Manual Limitations 2.11 Service ceiling The aircraft s service ceiling depends on the actual weight of the aircraft, meteorological conditions, engine throttle setting, etc. Viper SD - 4 has the service ceiling of 5,000 m (16,400 ft) MSL Meteorological limitations Depending on meteorological conditions, the operation of the aircraft, is limited by the provisions of the applicable regulations for carrying out a flight and by technical and flight properties of the aircraft. Limitations for the aircraft s take off : Maximum outside air temperature C Minimum outside air temperature C Maximum head wind speed m/s (23 kts) Maximum cross-component of wind... 4 m/s (8 kts) Maximum back wind speed... 1 m/s (2 kts) WARNING It is forbidden to carry out flights with Viper SD - 4 in icing conditions and IFR flights! CAUTION The aircraft s engine is equipped with an air intake heating system (AIRBOX). Icing from the air humidity forms in the carburettor at the fuel nozzle and on the throttling flap. Icing leads to a loss in the engine s power and to a change in the richness of the mixture. 2-12

35 Flight Manual Chapter 2 Limitations 2.13 Crew Crew Viper SD - 4 is designed as a single-pilot aircraft. The left pilot s seat is specified as the commander s seat Minimum crew weight The crew s minimum weight is 55 kg. This minimum weight guarantees the observation of the CG position range of the aircraft and thus its good manoeuvrability and flight stability. If this condition is not met, it is necessary to meet it by attaching a weight to the right seat Luggage distribution The maximum weight of the luggage is 2 x 7.5 kg. The luggage must be placed behind the pilots seats in closable compartments designed for that On-board smoking It is FORBIDDEN to smoke on board the Viper SD - 4 aircraft. 2-13

36 Chapter 2 Flight Manual Limitations 2.16 Labels 2-14

37 Flight Manual Chapter 2 Limitations 2-15

38 Chapter 2 Flight Manual Limitations Location of label Left and right flaps Tank filling openings Text DON T STEP Max. 35 l ROZ 95 Oil tank SHELL ADVANCE ULTRA 10W-40 Cooling system expansion tank Main landing gear spring Main landing gear Canopy frame right lock control Canopy frame left lock control Ailerons, flaps, elevator Baggage area Marking of section switches Right instrument panel Aircraft s registration marks on the sides of the fuselage and on the bottom surface of the left wing SHERON ANTIFREEZE G12 TYRE kpa TYRE kpa CLOSE - OPEN OPEN - CLOSE NO PUSH Baggage max. 7.5 kg Right panel above section switches Labels with basic data 2-16

39 Flight Manual Chapter 3 Emergency Procedures 3. Emergency Procedures 3.1 Introduction 3.2 Engine failure Engine failure during take off Engine failure after take off 3.3 Engine in-flight restart 3.4 Fire and smoke Engine fire during take off (on the ground) Engine fire after take off 3.5 Fire in the cockpit 3.6 Vibrations 3.7 Electrical system failures 3.8 Drop in oil pressure under the minimum value in flight 3.9 Drop in fuel pressure under the minimum value in flight 3.10 Recovery from an unintended spin 3.11 Activation of the rescue system 3.11 Emergency landing 3-1

40 Chapter 3 Flight Manual Emergency Procedures 3.1 Introduction This section contains a control list of steps and procedures for the solution of emergency situations on the ground or in flight. 3.2 Engine failure Engine failure during take off Engine throttle... pull back to idle Ignition switch ACS... switch off Main fuel valve... close Brakes... brake until the aircraft stops Master switch... switch off Harness... release (after the aircraft stops) Canopy...open and get out Engine failure after take off Airspeed... adjust to 120 km/h (65 kts) Ignition switch ACS... switch off Main fuel valve... close Flaps... extend as necessary Carry out an emergency landing Instruments... switch off after landing Section switches... switch off after landing Master switch... switch off after landing Harness... release (after the aircraft stops) Canopy... open and get out CAUTION - If the engine fails under or at 50 m (160 ft), carry out landing in the direction of the flight (with diverting, if there are obstacles in the direction of the flight). - If the engine fails above 50 m (160 ft), choose landing in the direction of a free area without obstacles and land against the wind, if possible. 3-2

41 Flight Manual Chapter 3 Emergency Procedures 3.3 Engine in-flight restart If the engine fails in-flight at an altitude above 200 m (650 ft): Airspeed... adjust to 120 km/h (65 kts) Main fuel valve... switch to the tank with more fuel; Master switch... check it is switched ON Fuel Pump... switch on Ignition switch ACS... off and then on Start cutout section switch... check it is ON Start the engine After starting the engine, land at the nearest airport or airfield. CAUTION If you do fail to start the engine, proceed according to point Fire and smoke Engine fire during take off (on the ground) Main fuel valve... close (OFF) Engine throttle... idle Ignition switch ACS... switch off Brakes... stop the aircraft Master switch switch off Harness... release (after the aircraft stops) Canopy... open and get out 3-3

42 Chapter 3 Flight Manual Emergency Procedures Engine fire after take off Main fuel valve... close Engine throttle... idle Ignition switch ACS... switch off Equipment unnecessary for the continuation of the flight... switch off Carry out an emergency landing Brake... stop the plane Master switch... switch off after landing Harness... release (after the aircraft stops) Canopy... open and get out CAUTION Do not start the engine after you extinguish a fire! 3.5 Fire in the cockpit Localise the place of fire Extinguish the fire with all available means If you fail to extinguish the fire: Main fuel valve... close Engine throttle... idle Ignition switch ACS... switch off Equipment unnecessary for the continuation of the flight... switch off Carry out an emergency landing Brakes... stop the aircraft Master switch... switch off after landing Harness... release (after the aircraft stops) Canopy... open and get out 3-4

43 Flight Manual Chapter 3 Emergency Procedures 3.6 Vibrations Vibrations may occur as a consequence of: 1. An adverse flight mode (slipping/skidding, stalling speed) Change the flight mode. 2. A technical fault of the engine or propeller Choose an engine mode in which the vibrations are the lowest (by controlling the engine s RPM) Carry out an emergency landing If the vibrations increase, carry out an emergency landing with the engine switched off 3. Carburettor icing 4. Lack of fuel Switch to the other fuel tank. 3.7 Electrical system failures Generator failure When the red CHARGE indicator on the left instrument panel, located above the master switch, is ON, it informs the pilot about charging failure. Switch off electrical devices not necessary for the continuation of the flight. Carry out safety landing at the nearest suitable airport, airfield or land within 30 min. NOTE: If the battery is fully charged, it should be able to supply power for at least 30 minutes. The failure of the generator does not affect the operation of the engine. CAUTION After a flight with a failed generator, the battery has to be checked and recharged before the next flight. 3-5

44 Chapter 3 Flight Manual Emergency Procedures Overloading of the current circuit (shortcut) An overloading of a current circuit is signalled by the failure of the device concerned and the activation of the automatic circuit breaker in the respective section switch on the right instrument panel. Let the automatic circuit breaker to cool for about 60 seconds. Switch on the respective automatic circuit breaker. Check the functionality of the device concerned. WARNING After repeated overloading of a current circuit do not switch on the respective automatic circuit breaker; there is a risk of permanent damage to the current circuit and/or to the device concerned. 3.8 Drop in oil pressure under the minimum value in flight Decrease the power of the engine to essential minimum. Land at the nearest suitable airport or land. After landing check the lubrication system. 3.9 Drop in fuel pressure under the minimum value in flight Check the quantity of fuel. Switch the main fuel valve to the tank with a bigger quantity of fuel. Switch on the electric fuel pump Recovery from an unintended spin Engine throttle... idle Rudder pedals... fully push against the direction of rotation Elevator... full forward without the use of ailerons Rudder pedals... when the rotation stops, return the pedals into the neutral position Elevator... recover from the dive (do not exceed the never-exceed airspeed) 3-6

45 Flight Manual Chapter 3 Emergency Procedures 3.10 Activation of the rescue system Engine throttle... pull to idle Ignition switch ACS... switch off Activation handle... pull strongly Protect your face and body, if possible. After the activation of the ballistic rescue system, switch off all devices not necessary for further descent. WARNING The maximum allowed airspeed to activate of the rescue system is 310 km/h (167 kts). The guaranteed functioning of the system is in the temperature range between -30 and +50 C. The period until repackaging has been set by the manufacturer to 6 years. CAUTION The system is designed for the use in the following cases: Damage to the aircraft after its collision with other aircraft; Damage to the aircraft caused by the loss of the integrity of the aircraft s structure; Loss of the possibility to control the aircraft; Engine failure over a terrain in which it is not possible to land safely; Pilot s difficulties during the flight that may cause his inability to land normally. CAUTION The use of the rescue system will always cause damage to the plane. 3-7

46 Chapter 3 Flight Manual Emergency Procedures 3.11 Emergency landing It is carried out in the case of a fault on the aircraft, orientation loss, insufficient fuel reserves, dangerous worsening of meteorological conditions (visibility, storms), or a starting sunset. Select a suitable area for landing, against the wind direction, if possible. Carry out a fly-over 50 m (165 ft) above the ground against the wind with flaps at 15 at 120 km/h (65 kts) and examine thoroughly the condition of the surface (obstacles, quality of the surface). Do a traffic pattern at 150 m (650 ft) above the ground or at an altitude allowed by a decreased cloud base, carry out mandatory procedures downwind, connect the 3rd and 4th turns, extend the flaps into the take-off position before making the last turn. In the case of decreased visibility, do not lose the sight of the selected area. Make the final approach in the landing configuration, with increased power of the engine, adjust the approach to touch down right after the passing of the edge of the selected area. Brake after touch down; when the aircraft stops, stop the engine, switch off the master switch, close the fuel valve and secure the aircraft against movement. 3-8

47 Flight Manual Chapter 4 Normal Procedures 4. Normal Procedures 4.1 Pre-flight inspection 4.2 Engine start After getting into the cockpit Engine start 4.3 Engine test 4.4 Important steps after engine start 4.5 Taxiing 4.6 Before take off 4.7 After take off at 50 m (165 ft) 4.8 When the flight level is reached 4.9 Descent and landing 4.10 Slip 4.11 Landing 4.12 Aborted landing 4.13 After the landing 4.14 Engine stop 4.15 Flight in a cross-wind 4.16 Flight in rough air 4.17 Between-flight inspection 4.18 After-flight inspection 4-1

48 Chapter 4 Flight Manual Normal Procedures 4.1 Pre-flight inspection Pre-flight inspection is carried out by the plane s mechanic always before the first flight of the day according to the procedure specified below. Identified deficiencies have to be removed before the flight and the carried out inspection must be recorded in the maintenance log book. Cockpit Check the canopy for cleanliness, possible damage, functioning of the canopy locks. Check the seat harness. Attach free objects (put them into boxes) or remove them. Check whether the magneto switches and the master switch are off. Check the movements of the control stick. Set all on-board instruments to zero. Check the quantity of fuel (MGL XTreme EMS) Left side of the fuselage Check the fuselage skin, damage to the coating, riveted joints, check the attachment of covers. Empennage Check the attachment and skins of the surfaces, riveted joints, free movement of the rudder and of the elevator; the functioning of the trimming; play in the hinge pins of the rudder and elevator hinges. Check the static pressure sensor at the top of the vertical stabiliser for possible damage. Right side of the fuselage Check the fuselage skin for damage to the coating and riveted joints, check the attachment of the covers and antennas. 4-2

49 Flight Manual Chapter 4 Normal Procedures Right half of the wing Check the wing for the integrity of the skin, riveted joints, attachment of the wing-tip device; flap and aileron hinges and their free movement, securing of flap and aileron pins; identical extension of the flaps in all positions; check visually the quantity of fuel; check the closing of the fuel tank, check the functioning and the condition of the navigation lights. Engine compartment Demount the upper part of the engine cowl. Check the attachment of the engine mount and of the engine. Check the electric cable cabling, connector connections. Check hoses and their attachment. Check the attachment of the cables to the battery and the air filter. Check the attachment of the exhaust pipes. Check the tightness of the engine, lubrication system, cooling system, oil radiator and cooling radiator (traces of operation fluids), attachment of the high-voltage cables of the sparking plugs. Check the level of the oil, coolant, brake fluid and add more oil, coolant or brake fluid if necessary. Check the fuel filter for clogging. Check the free movement of the operation of the carburettor throttle plates and choke plates. Check the exhaust pipes and muffle for damage, leakage, and overall condition. Check the cleanness of the radiator inlets. Check the condition of the cushioning rubber band of the front landing gear. Mount the upper part of the engine cowl. Propeller Check propeller for plays in its attachment and for damage, check the attachment of the spinner. Turn the propeller several turns in the direction of its rotation. 4-3

50 Chapter 4 Flight Manual Normal Procedures WARNING Before manual turning of the propeller, switch off both ignition circuits (if the ignition is not off, there is a risk of injury). The propeller must not be turned in the direction opposite to that of its normal rotation. Front landing gear Check the wheel for symmetry, deformities and plays of the wheel fairing; integrity of the colour line indicating the turning of the tyre against the disk; the locking of the wheel pin nut; the inflation of the tyre (the pressure according to the value on label); the wear of the tyre; check condition of the rubber cushioning band of the front landing gear; check the condition of the grounding cable on the landing gear s leg. Left half of the wing Check the wing for the integrity of the skin, riveted joints, attachment of the wing-tip device, flap and aileron hinges and their free movement; securing of flap and aileron pins; identical extension of the flaps in all positions; check visually the quantity of fuel; check the closing of the fuel tank; check the functioning and the condition of the navigation lights; remove the Pitot tube cover. Main landing gear Check the wheels for symmetry, deformities and plays of the wheel fairing; integrity of the colour line indicating the turning of the tyre against the disk, the inflation of the tyres and their wear; check the surface of the main landing gear legs for cracks; the locking of the wheel pin nuts, the overall condition of the disk brakes and of the brake tubing. 4-4

51 Flight Manual Chapter 4 Normal Procedures Cockpit 2 - Left side of the fuselage 3 - Empennage 4 - Right side of the fuselage 5 - Right half of the wing 6 - Engine compartment 7 - Propeller 8 - Front landing gear 9 - Left half of the wing 10 - Main landing gear 4-5

52 Chapter 4 Flight Manual Normal Procedures 4.2 Engine start After getting into the cockpit Canopy... close, lock Remove the lock of the rescue system Harness... fasten, tighten Brakes... brake Control stick movements... free Engine start Main fuel valve... position to the tank with the higher quntity of fuel; if the fuel quantity in the tanks is the same, switch to the LEFT tank Master switch... switch on EMS... switch on Start Cutout section switch... switch on Choke... pull out (if the engine is cold) Ignition switch ACS... switch ON both Start the engine EFIS... switch on After starting... increase engine speed to 2,000 RPM Other section switches... switch on as necessary 4-6

53 Flight Manual Chapter 4 Normal Procedures CAUTION The oil pressure must rise within 10 seconds after starting. Only when the oil reaches a stable pressure, the engine s RPM may be increased. If the oil is cold, constantly monitor the oil pressure since, because of an increased flow resistance in the suction branch, the oil pressure may drop again. To avoid acceleration stresses, when starting the engine, set the throttle to idle or do not open it to more than 10 %. For the same reason, after reducing the throttle, wait for about 3 seconds before increasing the throttle to achieve constant RPM of the engine. NOTE When starting a cold engine, move the engine throttle to idle and switch on the choke. When starting a warm engine, move the engine throttle to a no more than 10 % position with the choke off. If the engine does not start, repeat the starting not earlier than in 2 minutes, during which the starter will cool off. 4.3 Engine test Before starting the engine test, put wedges in front on the wheels. Start the engine in line with point RPM... for 2 minutes 2500 RPM... warm up the oil to 50 C Maximum take off RPM... for a short time 4000 RPM... carry out ignition test (A drop in RPM for each ignition circuit must not exceed 300 RPM and the RPM difference between the two circuits must not exceed 115 RPM). Set the throttle to idle. 4-7

54 Chapter 4 Flight Manual Normal Procedures CAUTION When testing the ignition circuits, only one ignition circuit may be switched on/off at a time. After testing the full power, leave the engine to cool for a short time, so that the steam in the cylinder heads is released into the expansion tank. No run irregularity or RPM fluctuations may occur during the engine test. The maximum allowed temperatures and pressures must not be exceeded during the engine test. 4.4 Important steps after the engine start RADIO... switch on TRANSPONDER... set the respective code Flaps... extend and retract Flight instruments... set the QNH 4.5 Taxiing elevator... full back taxiing speed... max. 4 km/h (2 kts) brakes... test WARNING It is forbidden to taxi with a partially open canopy. The canopy might get damaged when taxiing through rough surface or due to the airflow from the rotating propeller. 4-8

55 Flight Manual Chapter 4 Normal Procedures 4.6 Before take off Main fuel valve... (position to the tank with the higher quntity of fuel; if the fuel quantity in the tanks is the same, switch to the LEFT tank) Flaps extended (position 1) Trim... central position Master switch... switched on Ignition switch ACS... switched to BOTH Section switches... switched on Choke... closed Flight instruments... adjust Navigation and communication instruments...adjust Check of the canopy locking... check the locking (two red LEDs on above flight instruments) Check of the engine values... check they are in the green bands Harness... check its locking and tightening Check the area ahead is free before the taxiing to the runway Brakes... release Engine throttle... smoothly full WARNING Take off is forbidden, if: - the engine runs irregularly; - any of the engine parameter is not in the green band; - the fuel quantity in the tanks is less than 2x10 litres. 4.7 After take off at 165 ft (50 m) Airspeed... adjust to 120 km/h (65 kts) Flaps... retract at a safe height Engine RPM... set 5,100 RPM Trim... trim both as necessary Engine parameters... in green bands 4-9

56 Chapter 4 Flight Manual Normal Procedures 4.8 When the flight level is reached Engine RPM... keep within the cruise range (4,400 5,100 RPM) Engine parameters... green field Trims... trim as necessary Fuel... keep even withdrawal from both tanks by switching the fuel valve 4.9 Descent and landing Airspeed... adjust to 120 km/h (65 kts) Flaps... extend as necessary Trim... trim as necessary Main fuel valve... (position - the tank with the higher quntity of fuel NOTE It is recommended to descend from higher flight levels with the engine at increased idle RPM to prevent its excessive cooling. 4-10

57 Flight Manual Chapter 4 Normal Procedures 4.10 Slip Carry out slips in the landing configuration of the aircraft at 120 km/h (65 kts). A slip must be ended not lower than 50 m (165 ft) above the ground. Putting the aircraft into a slip Airspeed... adjust to 120 km/h (65 kts) Engine throttle... idle Rudder... smoothly to full position Ailerons... maintain the flight direction in the slip Elevator... keep the aircraft s nose at the chosen descent angle CAUTION Due to a side airflow around the static pressure sensor and pitot tube, the aircraft s airspeed indicator may provide distorted airspeed indication in a slip. Recovery from a slip Airspeed... adjust to 120 km/h (65 kts) Rudder... smoothly back to straight Ailerons... return to the zero bank angle Elevator... adjust the descent angle Trim... trim the aircraft 4.11 Landing Airspeed... adjust to 120 km/h (65 kts) Engine RPM... as necessary Flaps... extended as necessary Trim... trim as necessary 4-11

58 Chapter 4 Flight Manual Normal Procedures NOTE When landing in a strong wind, we recommend to increase the airspeed to 130 km/h (72 kts) and extend the flaps to position II or position I. NOTE When landing in a strong cross-wind (more than 4 m/s (8 kts)) maintain the flight speed at 130 km/h (72 kts). and extend the flaps to position II or position I Aborted landing Airspeed... adjust to 120 km/h (65 kts) Engine throttle... full Flaps... move to position 1 (retract at 50 m /160 ft) 4.13 After the landing Flaps... retract 4.14 Engine stop Engine throttle... idle Brakes... in the parking position EFIS... switch off Individual devices... switch off Ignition switch ACS... switch OFF both EMS... switch off Section switches... switch off Master switch... switch off Main fuel valve... close 4-12

59 Flight Manual Chapter 4 Normal Procedures NOTE Under normal conditions, during the descent and taxiing, the engine is cooled sufficiently, so it can be switched off without the necessity of further cooling. At higher operational temperatures, the engine is cooled at idle RPM until the temperatures drop to normal operational values, as it is specified in the Operation Manual for the Rotax 912ULS engine, section Flight in a cross wind A safe take off or landing in a crosswind can be made only up to the wind speeds of 4 m/s (8 kts). When landing in a strong crosswind, it is recommended to extend the flaps to position II or position I Flight in rough air Flight in rough air is demanding for both the pilot and the aircraft. If it is possible, avoid flying in rough air by changing the flight direction or the flight level. The maximum allowed airspeed in rough air is 160 km/h (86 kts) Between-flight inspection Check the aircraft s skin. Check the condition of the propeller s blades. Check the tightness of the fuel, oil and cooling systems. Check the condition of the tyres. Check the quantity of fuel, oil and coolant. Check the covers After-flight inspection Carry out the inspection to the extent of the pre-flight inspection. Clean the aircraft s surfaces, if necessary. 4-13