Flight and Operations Manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS

Maximum (short-term operated when cold start-up) 7,0 bar Operating 2,0 – 5,0 bar (over 3500 RPM) Fuel Pressure Minimum 2,8 bar Maximum 3,2 bar Fuel Type Recommended motor unleaded petrol of minimum octane number RON 95, 97 MOGAS EN228 Super or Super Plus, with max. 10% content of ethanol Oil Type Use only oil with RON 424 classification or AeroShell Sport Plus 4 10W-40 as an option. Coolant Type Conventional coolant for aluminium engines, mixed with water (mix ratio 1:1) – see Rotax manual. In case of mix ratio is 1:1, the freezing point is -38°C. Water-less coolant (e.g. Evans or Aero Cool 180) can be applied as an option. These coolants are not to be mixed with water! The engine characteristics, operation and maintenance are preferentially directed by appropriate Operating Manual of the engine manufacturer. Informations listed in appropriate engine manual are preferential to this manual. ROTAX 912 iS Sport is not certified aviation engine. Any engine failure may occur at any time. The pilot is fully responsible for the operation of the engine and accepts all risks and consequences of an engine failure. The correct operation of this aircraft is the sole responsibility of the pilot. The pilot of sport flying device is obliged to plan the flight track and altitude so that to be able to make safety landing at anytime in case of engine failure. Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 9 of 57 1.6. Three-View Sketch (mm) Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 10 of 57 Chapter 2 2. Operating Limits 2.1. Introduction 2.2. Air Speed 2.3. Speed indicator markings 2.4. Weight 2.5. Centre of Gravity 2.6. Manoeuvre and Gust Envelope 2.7. Permitted Manoeuvres 2.8. Load Factors 2.9. Type of Operation 2.10. Crew 2.11. Fuel tank 2.12. Wind 2.13. Other Restrictions 2.14. Labels and Markings Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 11 of 57 2.1. Introduction The Chapter 2 contains operating limits necessary for safe operation of the aircraft. 2.2. Air Speed (IAS) Never exceed speed VNE 272 km/h 147 kt Do not exceed this speed in any case! Design manoeuvre speed VA 190 km/h 102 kt After exceeding this speed, do not use full deflection of any control surfaces and do not make any sudden control operations. An overload of the aircraft may occur! Max. continuous cruising speed VC 242 km/h 131 kt Do not exceed this speed except the flight in smooth air, but with caution! Max. cruising speed at severe turbulence VRA 215 km/h 116 kt Do not exceed this speed at severe turbulence! Max. speed, flaps extended to III. VFE 117 km/h 63 kt Recommended speed, flaps extended to III. VFE 90 km/h 49 kt Do not exceed these speed limits when flaps extended! Stall speed, flaps retracted VS1 75 km/h 40 kt Flying this speed when flaps retracted results in loss of lift force and stall! Stall speed in landing configuration VS0 56 km/h 30 kt Flying this speed with flaps extended in the position III. results in stall due to loss of lift force! Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 12 of 57 2.3. Speed Indicator Markings Speed (km/h) IAS Speed (kt) IAS Colour marking Note 56 - 117 30 - 63 White section The speed from VS0 up to the speed defined for flaps extended in max. position VFE 75 - 215 40 - 116 Green section From the speed VS1 up to the max. cruising speed 215 - 272 116 - 147 Yellow section From the max. cruising speed up to the never exceed speed VNE 272 147 Red section Never exceed speed VNE 2.4. Weight Empty weight kg Maximum take-off weight 600 kg Useful load kg Max. load in the luggage compartment 20 kg (for specific permissible max. load see Chapt. 8) Do not ever exceed maximum take-off weight of the aircraft! Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 13 of 57 2.5. Centre of Gravity ( CG ) CG of the empty aircraft % MAC CG range in flight 25-36 % MAC 2.6. Manoeuvre and Gust Envelope (CAS) Envelope point Speed Manoeuvre and Gust Envelope / m = 600,0 kg Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 14 of 57 2.7. Permitted Manoeuvres Category of the aircraft: Normal Operations are limited to non-aerobatic manoeuvres that include: - Any manoeuvres necessary for normal flight - Training of stalls - Steep turns with the bank angle not more than 60° Aerobatic manoeuvres are prohibited! 2.8. Load Factors (600 MTOW) Maximum positive load factor in CG + 4,0 g Maximum negative load factor in CG - 2,0 g 2.9. Type of Operation Only VFR day flights are permitted (flight by visual reference to the ground during the daytime) IFR flights ( instrumental flights ) and flights by ice formation are prohibited! 2.10. Crew Number of seats 2 Minimum weight of the crew 70 kg Maximum weight of the crew 220 kg Maximum load of the seat 110 kg 2.11. Fuel tank Fuel capacity 2 x 50 L Non-usable rest of fuel 0,82 L for each tank 2.12. Wind A safe take-off and landing is only possible if the following wind speed limits are not exceeded: a) take-off or landing headwind up to 12 m/s = 23,3 kt b) take-off or landing tailwind up to 3 m/s = 5,8 kt c) take-off or landing crosswind up to 6 m/s = 11,6 kt Never operate the aircraft when above listed wind limits are exceeded! Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 15 of 57 2.13. Other Restrictions Smoking, using of mobile phones, explosives and combustible materials and transport of movable objects are prohibited on board of the aircraft. 2.14. Labels and Markings The aircraft shall be equipped with mandatory labels and markings. These must be placed on the instrumental board in a visual field of the pilot and must contain at least following actual information: - Identification of the aircraft • Identification label • Serial number • Designation • Empty weight • Maximum take-off weight - Operating limits • Load and weight limits depending on weight of the crew, fuel and luggage • Speed limits in standard flight configuration - Passenger Warnings • Definition of aircraft category, its airworthiness conditions and restrictions • Prohibition alert of intentional spins, stalls and aerobatics Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 16 of 57 Chapter 3 3. Emergency Procedures 3.1. Engine Failure on Take-off 3.2. Engine Failure in Flight 3.3. Rescue System Activation 3.4. Fire on Board 3.5. Engine Loss 3.6. Emergency Landing 3.7. Safety Landing 3.8. Aborted Landing 3.9. Vibrations Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 17 of 57 3.1. Engine Failure on Take-off 1. Get the aircraft to gliding flight by pushing the stick forward maintaining the airspeed of 100 km/h (54 kt). 2. Determine the wind direction, adjust flaps to appropriate position, close the fuel valve, switch-off the ignition, adjust safety belts and switch off the master switch just before landing. Note: Electric flaps actuation is only possible when the master switch is switched-on. A) If altitude is below 50m (160ft), get the aircraft to landing configuration and make a landing in take-off direction with respect to eventual obstacles. B) If altitude is higher than 50m (160ft), choose a suitable area for emergency landing. 3.2. Engine Failure in Flight 1. Get the aircraft to gliding flight maintaining the airspeed of 100 km/h (54 kt). 2. Check the fuel level and make sure ignition is switched on. 3. Make sure that both LANE A and LANE B are switched on. Check the voltage on both LANE A and LANE B. Check the fuel pressure. Must be within limits. 4. A) If no significant failure on engine or its installation found, try to start up the engine again. Proceed as follows:  Fuel valve  open for appropriate fuel tank in use  Master switch  switched-on  START POWER  switch on (to “START” position)  Throttle lever  50% open position (approx. 8mm from idle position)  Fuel pump  switch-on, wait until the fuel pressure reaches approx. 3 bar  LANE A  switch on  LANE B  switch on  Check EMS indicators  lights off (see the engine Operations Manual)  Starter button  press and hold (without interruption) for max. 10 seconds until the engine runs the speed 1500 RPM. The engine can be started by electric starter even though the propeller continues to rotate during flight by windmilling and its speed is not sufficient. It is not necessary to wait for standstill of the propeller.  START POWER  switch off (to “FLIGHT” position)  Throttle  adjust to required RPM B) If there is no voltage on LANE A and LANE B, proceed as follows:  Fuel valve  open for appropriate fuel tank in use  Master switch  switched-on  BACK-UP BATTERY  switch on  Throttle lever  50% open position (approx. 8mm from idle position)  Fuel pump  switch-on, wait until the fuel pressure reaches approx. 3 bar.  LANE A  switch on  LANE B  switch on  Check EMS indicators  lights off (see the engine Operations Manual)  Starter button  press and hold (without interruption) for max. 10 seconds until the engine runs the speed 1500 RPM. The engine can be started by electric starter even though the propeller continues to rotate during flight by windmilling and its speed is not sufficient. It is not necessary to wait for standstill of the propeller.  Throttle  adjust to required RPM Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 18 of 57  Carry out landing on the nearest suitable place. The engine run via back-up battery is time- limited. Once the back-up battery is wasted, the engine stops and it will not be possible to start it up again! 5. If the engine start-up is not successful, carry out emergency landing as described in the Art. 3.1. 3.3. Rescue System Activation In case of distress, when definitively losing control of flight, activate the rescue system. 1. Switch off the ignition 2. Fasten the safety belts 3. Activate the rescue system In case of landing on limited space, and when collision with an obstacle is inevitable, use the balistic rescue system as a braking device of the aircraft. The aircraft may be damaged or the crew may be injured when using the rescue system! 3.4. Fire on Board 1. Close the fuel valve 2. Open the throttle 3. Switch off the master switch and ignition 4. Carry out emergency landing 5. Get off the aircraft 3.5. Engine Loss 1. Speed 100 km/h (54 kt) 2. Flaps retracted 3. Instruments within tolerated values 3.6. Emergency Landing Carried out in case of engine failure: 1. Speed 100 km/h (54 kt) 2. Fasten safety belts 3. Flaps position according to situation 4. Report the situation by radio 5. Close the fuel valve 6. Switch off the ignition 7. Switch off the master switch In case of emergency landing on terrain, on a surface which is not approved for take-off/landing of sport flying device, the aircraft may be damaged or the crew may be injured! Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 19 of 57 3.7. Safety Landing Carried out in case of orientation loss, fuel exhaustion or any other reason, while the aircraft is fully controllable. 1. Determine the wind direction 2. Choose any suitable landing surface 3. Carry out low pass headwind along the right-hand side of the landing surface and inspect the terrain thoroughly 4. Carry out pattern flight 5. Calculate the landing manoeuvre 6. Land in the first third of the landing area with the flaps in the position for landing 3.8. Aborted Landing Carried out in case of wrong landing manoeuvre or bounce during the landing and when the pilot considers aborted landing manoeuvre as safer and decides to proceed the flight. 1. Set the engine run up to full power 2. Fluently set up flaps to take-off position – I 3. Reach the horizontal speed of 110 km/h (59 kt) 4. Pull the control stick slowly to make the aircraft climbing by speed 120 – 140 km/h (65 – 75 kt) 5. Retract flaps Keep the aircraft within runway centerline by using rudder control throughout the flight. 3.9. Vibrations In case of unusual vibrations occure, it is necessary to: 1. Set up the engine run to appropriate RPM on which the vibrations are the lowest 2. Carry out safety landing, eventually find the nearest airfield to land Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 20 of 57 Chapter 4 4. Standard Procedures 4.1. Pre-Flight Inspection 4.1.1. Procedures Before Entering the Cockpit 4.1.2. Procedures After Entering the Cockpit 4.1.3. Procedures Before Engine Start-up; Engine Start-up 4.2. Engine Warming up 4.3. Taxiing 4.4. Engine Check 4.5. Procedures Before Take-off 4.6. Take-off and Climbing 4.7. Cruising Flight 4.8. Flight on Traffic Pattern 4.9. Approach and Landing 4.10. Flight in Rainy Conditions 4.11. Engine Shut-off Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 21 of 57 4.1. Pre-Flight Inspection It is important to carry out appropriate pre-flight inspection. To perform a negligent or incomplete inspection could be a cause of an accident. The Manufacturer recommends to make the following procedure before each flight: 1/ Cockpit – switches, safety belts, instruments, seats, controls, canopy locks, canopy condition 2/ Left wing – coating, condition, plays, Pitot tube, fuel tank cap, drain valve, fuel tank ventilation 3/ Left aileron – coating, free movement, attachments, controls 4/ Left flap – coating, attachments, controls, play Left gear leg – condition, brake fluid leak, wheel, tyre condition and inflation, wheel spat attachment 5/ Left horizontal tail and elevator – surface condition, attachment, elevator free movement, plays, trimming tab 6/ Vertical tail and rudder – surface condition, rudder attachment, plays, ropes tension 7/ Right horizontal tail and elevator – surface condition, attachment, elevator free movement, plays, check the securing of the pin of the HT control 8/ Tailplane – surface condition, radio antenna check 9/ Right flap - coating, attachments, controls, play Right gear leg - condition, brake fluid leak, wheel, tyre condition and inflation, wheel spat attachment 10/ Right aileron - coating, free movement, attachments, controls 11/ Right wing – coating, condition, plays, fuel tank cap, drain valve, fuel tank ventilation 12/ Nose wheel – condition, play, wheel, tyre condition and inflation Engine - condition and fastening of engine cowling, engine bed, hoses intactness (fuel, oil, cooling system), clamps tightness, screws/nuts securing, exhaust pipes attachment, drain plug, oil/coolant level: Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 22 of 57 a) Oil level – Never open the oil tank when the oil is hot! Open the cover of the inspection hole on the engine cowling and unscrew the cap of the oil tank. Manually turn the propeller few times in its rotating direction to press the oil from the engine into the oil tank. Stop turning the propeller when you hear the „bubbling sound“ signalizing that only air starts flowing from the engine into the oil tank. Check the oil level with the dipstick in the oil tank and refill up to the maximum level if needed. Pay attention not to stain surrounding engine parts or its compartment by oil, otherwise remove oil spots properly. Cover the oil tank with the cap. Install the cover of inspection hole and secure by screws. Keep the oil level within the range marked on the dipstick. Always use the same type of the oil which is already used in the engine. Cover the oil tank with the cap. b) Coolant level – Remove the upper cowling of the engine. The engine must always be cold when checking the coolant level. Open the expansion tank and check the coolant level. Do not open the expansion tank if the coolant is hot! The max. coolant level must be flush with the bottom of the filler neck. If the level is low, refill. Cover the engine by the upper cowling. Verify the coolant level in the overflow bottle. Keep the level between „MAX.- MIN.“ mark. 13/ Propeller – surface condition, blades and spinner tightness 4.1.1. Procedures Before Entering the Cockpit 1. Canopy  open 2. Ignition  switched off 3. Master switch  switched off 4. Rescue system  secured 5. Pedals position  adjust to appropriate position (if equipped with adjustable pedals) 6. Seats position  adjust to appropriate position (if equipped with adjustable seats) 4.1.2. Procedures After Entering the Cockpit 1. Cockpit  check canopy fastening and locking, proper function and condition of electric installation, instruments and flight instruments, fuel level, proper function of controls, rescue system locked against unintended activation 2. Foot-operated steering  check function, proper adjustment of pedals 3. Brakes  check function, brakes on 4. Hand–operated steering  check function, free movement, stops 5. Flaps  check function, retract 6. Fuel valve  open for appropriate tank in use 7. Throttle  idle 8. Fuel level indicator  check fuel amount 9. Master switch  switched off 10. LANE A  switched off 11. LANE B  switched off 12. Instruments  check condition, zero values, altimeter setting Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 23 of 57 4.1.3. Procedures Before Engine Start-up; Engine Start-up Do not start-up the engine if there is a person in vicinity of the aircraft! 1. Safety belts  fasten 2. Canopy  close and lock 3. Parking brake  on 4. Fuel valve  open/select for appropriate fuel tank to use 5. Master switch  switch on 6. START POWER  switch on (to “START“ position) 7. Throttle  50% open position (approx. 8mm from idle position) 8. Fuel pump  switch on (use only one fuel pump when starting-up engine) 9. EMS  switch on (wait for the engine readings, fuel pressure 3 bar) 10. LANE A  switch on 11. LANE B  switch on 12. EMS indicators check  lights off (see the engine Operations Manual) 13. Starter button  press and hold (without interruption) for max. 10 seconds until the engine runs the speed over 1500 RPM. Do not press the starter button as long as the engine is running. Wait until complete stop of the engine and keep the engine cooling down for a period of 2 min. before next start-up) 14. START POWER  switch off (to “FLIGHT“ position) 15. Adjust throttle to reach smooth run with approx. 2000 RPM 16. Oil pressure  check if oil pressure has risen within 10 seconds and monitor. Increase engine speed when oil pressure remains steady above 3 bar 17. Throttle  Increase RPM to get over 2500 RPM for a period of 5 sec. (the generator B will switch-over to generator A). The battery is being charged only from generator A. Check the charging of the battery based on the value indicated by ampermeter. 18. EMS  check the engine warning lights. If lights-on or blinking, there is a failure which must be removed. Follow the Operators Manual of the engine. 19. Continue warming-up the engine according to Art. 4.2. Never unlock neither open the canopy when engine is running! 4.2. Engine Warming up Start warming up the engine when 2000 RPM for approx. 2 min. and then continue warming up with 2500 RPM until reaching oil temperature of 50oC. After the engine is warmed up to the operating temperature, start taxiing and prepare to take-off without undue delay to avoid overheating of the engine. 4.3. Taxiing Maximum recommended speed of taxiing is 15km/h (8kt). The direction is controlled by the nose wheel. Braking is carried out with the brake lever on the left control stick. Control stick is in neutral position. - in case of strong headwind, push the control stick forward - in case of side wind, hold the control stick in the position opposite to wind direction. Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 24 of 57 4.4. Engine Check 1. Brakes  on 2. Throttle  engine speed 4000 RPM 3. LANE A  switch off (max. RPM drop after stabilization must not exceed 250 RPM) 4. LANE A  switch on 5. LANE B  switch off (max. RPM drop after stabilization must not exceed 250 RPM) 6. LANE B  switch on 7. Throttle  reduce to idle run 8. Left and right fuel tank check  during engine run, the fuel pressure must not drop below tolerated values in either of fuel tanks in use. To change-over the fuel tanks, move the fuel valve selector quickly without stop. During the change-over of fuel tanks, a short-term pressure drop may occur. After the appropriate fuel tank is selected, the fuel pressure must return to appropriate values. 9. Fuel pumps check  set up the engine speed to 2000 RPM  switch on both fuel pumps  switch off the auxiliary fuel pump for a period of 5 seconds and check the fuel pressure  switch on the auxiliary fuel pump  switch off the main fuel pump for a period of 5 seconds and check the fuel pressure  switch on the main fuel pump 10. Acceleration and power check  set the brakes on to max. braking power  set the full throttle for 10 seconds  engine speed shall reach 5200 RPM  set idle run After a full-load ground test allow a short cooling run at idle speed to prevent vapour formation in the cylinder head! After the engine check is finished and operating temperature is reached, carry on take-off within max. 5 min. In case the aircraft is standing on spot for a long time when engine is running, the engine and its compartment are not sufficiently cooled by the airflow. This may be a cause of overheating and damage of the engine and composite structure in its compartment. Notes: The sensors of LANE A and LANE B have different inputs. During the check of LANES and ignition, some values on EMS screen are not displayed depending on activation of the LANES. If the EMS power supply fails (alternator A), the ECU (engine control unit) automatically switches one-time over to the second power supply (alternator B). While alternator B runs, there is no drop of voltage. The engine is running, but the battery is not being charged! 4.5. Procedures Before Take-off 1. Brakes  on 2. Rescue system  unlock (if equipped with) 3. Foot-operated steering  free travel 4. Hand-operated steering  free travel 5. Flaps  position I. Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 25 of 57 6. Fuel valve  open/select (left/right) for appropriate fuel tank to use 7. Fuel pumps  both ON (main and auxiliary) 8. MASTER SWITCH  switched on 9. START POWER  switched off (on “FLIGHT” position) 10. BACK-UP BATTERY  switched off 11. LANE A and LANE B  both switched on 12. Propeller  in “TAKE-OFF” position (if equipped with propeller adjustable in flight) 13. Throttle  idle 14. Fuel indicator  fuel amount check 15. Instruments  values within operating limits 16. Safety belts  adjusted, fastened, secured 17. Canopy  closed and locked 4.6. Take-off and Climbing Release the brakes. Make the aircraft move by opening the throttle up to its maximal position. The control stick is in neutral position. Control the nose wheel and the rudder to keep the aircraft within the runway centerline. When reaching the speed of 80 km/h (43 kt), gently pull the control stick to lift up the aircraft and continue take-off until reaching the speed of 110 km/h (59 kt). Then, gently pull the control stick to make the aircraft climb. After reaching stable climb speed of 130 (70 kt) and altitude over 50m (160 ft), fluently retract the flaps. Optimal climb speed is 140 km/h (75 kt). During take-off, the engine operating limits must not be exceeded. Climbing at full (take-off) power is only allowed for a max. period of 5 minutes. When approx. 1000 ft GND is reached, switch off auxiliary fuel pump. After reaching required altitude, adjust the propeller to “CRUISE” position (if equipped with in- flight adjustable propeller). 4.7. Cruising Flight ATEC 321 FAETA NG has good flight characteristics within the whole range of permitted speeds and position of the centre of gravity. The cruising speed is within a range of 140 – 242 km/h (75 – 131 kt). In case of severe turbulence, do not exceed the speed VRA 215 km/h. Pay attention to values displayed on flight and engine instruments. The values must not be exceeded throughout the flight. Optimal operating oil temperature shall be within a range of 90 - 110°C. When changing-over the fuel tanks, always move the fuel valve selector quickly, without stop on the middle position. 4.8. Flight on Traffic Pattern Join the traffic pattern in the 2nd turn / follow downwind leg. In the downwind position:  decrease the engine power - throttle on idle  adjust the propeller to „take-off“ position (if equipped with in-flight adjustable propeller)  decrease the speed to 130 km/h (70 kt)  open the flaps to position I. and continue descending in downwind direction Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 26 of 57 Before the 3rd turn and base leg:  decrease the speed to 110 km/h (59 kt)  open the flaps to position II. and join the base leg Descend and continue base leg with the speed of 110 km/h (59 kt). Before the runway centerline, make the 4th turn keeping the speed of 110 km/h (59 kt) and then:  put the aircraft to appropriate position to approach runway centerline  decrease the speed to 90 km/h (49 kt)  open the flaps to position III., continue descending and approach to the runway threshold Landing manoeuvre can be corrected by increasing the engine power or by making a side slip. In case of doing side slip when side wind, a windward wing shall be banked downwards. E.g. if on final, the wind blows from the left side, push the right pedal and ailerons are directed to the left facing opposite the wind direction. 4.9. Approach and Landing Approach Make an approach with the throttle on idle and the speed of 90km/h (49 kt) with flaps position III. Approach manoeuvre can be corrected by increasing the engine power. Flaps positions within limits according to Art. 2.2. Propeller in “take off” position (if equipped with in-flight adjustable propeller). Procedures on final: 1. Propeller in “take-off” position (if equipped with propeller adjustable in flight) 2. Speed of 90km/h (49 kt). Minimum speed VX for descending is 85 km/h (46 kt). Do not ever approach with the speed lower than minimum speed! 3. Flaps position III (position II in case of severe turbulence or strong headwind), speed 100 km/h (54 kt) 4. Switch on auxiliary fuel pump 5. Throttle on idle or corrected if necessary 6. Instruments within tolerated values Landing The speed of the aircraft in hold-up position decreases by soft pulling of the control stick until the touch- down by the speed of 56 km/h (30 kt). After touch-down of the nose wheel, the landing distance can be shortened by using brakes. Approach: Speed: 90 km/h (49 kt) Flaps position: III. Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 27 of 57 Do not apply maximum brake power except an extreme situation occures. A frequent use of brakes results in undue wear of tyres, brake pads and discs. A frequent intensive braking may cause a mechanical over-stress of the undercarriage and other load bearing parts. This may shorten life-time of the airframe. 4.10. Flight in Rainy Conditions Intentional flights in rainy conditions are not recommended. The flights must be always realized under VFR conditions only. In case of flight in the rain is inevitable, it is necessary to pay higher attention to aircraft control because of poor visibility and limited transparency of the canopy. In addition, a shorter hold-up position during landing, higher stall speed and extended take-off distance shall be taken into account. Keep the following speeds in case of flight in the rain: 1. Climbing 140 km/h (75 kt) 2. Cruising flight 140 – 180 km/h (75 – 97kt) 3. Descending to land 110 km/h (59kt), flaps positions I. and II. as by Art. 2.2. Note, that the rain can be accompanied also by other meteorological phenomena such as reduced visibility, strong wing, icing and hails. Under these conditions the flight is no longer possible! 4.11. Engine Shut-off After landing and reaching the parking place, keep the engine running for a cooling period of at least 2 min. with approx. 2000 RPM. If the engine was cooled down enough during descending and taxiing, it can be shut-off as soon as the aircraft stops. 1. Switch off all individual switches except fuel pumps 2. Switch off LANE A, LANE B, fuel pumps and the master switch Keep the fuel valve open for any of the fuel tanks (L/R)! Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 28 of 57 Chapter 5 5. Performance 5.1. Introduction 5.2. Air Speed Indicator Corrections 5.3. Stall Speed 5.4. Altitude Loss by Stalling 5.5. Take-off Distance to reach 15m (50ft) altitude 5.6. Rate of Climb 5.7. Cruising Speeds 5.8. Flight Range Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 29 of 57 5.1. Introduction The Chapter contents information on speed indicator calibration, stall speed and other performances of the aircraft equipped with the engine ROTAX 912 iS Sport and the propeller FITI ECO COMPETITION 2L/160 with the pitch adjusted to 23°/ 85 % (climbing configuration). 5.2. Air Speed Indicator Corrections Cruise config. Take-off config. Landing config. Flaps retracted Flaps position for take- off Flaps position for landing Speed IAS Speed CAS km/h kt km/h kt km/h kt km/h kt 50 27,0 60,8 32,9 60 32,4 68,8 37,2 70 37,8 78,1 42,2 80 43,2 91,1 49,2 85,7 46,3 90 48,6 100,5 54,3 99,5 53,8 94,3 51,0 100 54,1 106,9 57,8 106,6 57,6 103,4 55,9 110 59,5 115 62,2 111,3 60,2 112,8 61,0 120 64,9 123,1 66,5 121,6 65,7 130 70,3 131 70,8 128,5 69,5 140 75,7 137,9 74,5 150 81,1 147 79,5 160 86,5 155,1 83,8 170 91,9 163 88,1 180 97,3 170,9 92,4 190 102,7 180 97,3 200 108,1 187,6 101,4 210 113,5 195 105,4 220 118,9 203,2 109,8 230 124,3 212 114,6 240 129,7 220,1 119,0 250 135,1 228 123,2 260 140,5 237,4 128,3 270 145,9 245 132,4 280 151,4 253,1 136,8 Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 30 of 57 5.3. Stall Speed (IAS) Engine idle Flaps retracted Flaps I (12°) Flaps II (22°) Flaps III (32°) solo flight 70 km/h 37,8 kt 63 km/h 34 kt 51km/h 27,5 kt 42 km/h 22,7 kt 600 kg 75 km/h 40,5 kt 68 km/h 36,7 kt 56 km/h 30,3 kt 47 km/h 25,4 kt Engine off Flaps retracted Flaps I (12°) Flaps II (22°) Flaps III (32°) solo flight 70 km/h 37,8 kt 63 km/h 34 kt 51 km/h 27,5 kt 42 km/h 22,7 kt 600 kg 75 km/h 40,5 kt 68 km/h 36,7 kt 56 km/h 30,3 kt 47 km/h 25,4 kt 5.4. Altitude Loss by Stalling Flap position (level flight) Flap deflection Altitude loss I 12° 30 m 100 ft II 22° 30 m 100 ft III 32° 30 m 100 ft 0 0 30 m 100 ft 5.5. Take-off Distance to reach 15 m (50 ft) altitude, TOW 600 kg Engine 100 HP Runway surface Take-off distance Paved surface 345 m 1132 ft Grass 350 m 1148 ft 5.6. Rate of Climb - when speed of 140 km/h (75 kt) Engine 100 HP Solo flight 7,5 m/s 1475 ft/min 600 kg 5,84 m/s 1150 ft/min 5.7. Cruising Speeds ROTAX 912 iS Air speed km/h kt RPM Fuel consumption l/h 120 65 3500 7,5 140 76 3700 8 160 86 4100 10,1 180 97 4500 13,2 200 108 4800 14,7 220 119 5200 17,5 242 131 5500 20 Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 31 of 57 5.8. Flight Range When maximum fuel amount of 100 L ROTAX 912 iS Sport Speed km/h kt Flight range km n.m. Flight endurance h Fuel reserve (10 L) h 140 76 1575 850 11:15 1:15 160 86 1425 769 8:54 1:00 180 97 1227 662 6:48 0:45 200 108 1224 661 6:06 0:40 220 119 1131 610 5:06 0:34 239 129 1080 583 4:30 0:30 Information on engine RPM, consumption, flight endurance and flight range has informative character only. Listed values depend on propeller type and pitch, flight altitude, air temperature, air pressure and loading of the aircraft. The flight range is considered as theoretic when windless conditions. When planning the flight track, do consider all above factors and safe amount of fuel! Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 32 of 57 Chapter 6 6. Aircraft Assembly/Disassembly 6.1. Introduction 6.2. Tailplanes Assembly/Disassembly 6.3. Wings Assembly/Disassembly Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 33 of 57 6.1. Introduction This chapter contains description of assembly and disassembly of individual parts of the aircraft. At least two persons are needed for assembly/disassembly. All parts necessary for assembly are being delivered with the aircraft. Before assembly, clean, grease and then secure all pins. Pay attention to correct adjustment of ailerons and flaps, which is carried out by shortening and prolonging of connecting pushrods. With each next assembly, it is necessary to replace locking nuts and split pins with new pieces. After the aircraft is assembled, make deflections adjustment according to levelling record and carry out engine check with a focus on both fuel tanks function. Check the correct values on fuel indicators. 6.2. Tailplanes Assembly / Disassembly At least two people are needed for assembly/disassembly. Pay attention to avoid a fall of small parts into the inner space of the tail during manipulation!! Horizontal (HT) tail assembly • Vertical tail rudder disassembly To reach better access to attachment points of the HT, it is recommended to remove the VT rudder. Unscrew two M5 screws fixing the VT rudder in the lower carrier. Then, deflect the rudder fully to the left or right. Pull the bottom part of the rudder out of the lower carrier and then, lift the rudder upwards to remove it out of the upper hinge. • Horizontal tail mounting to the fuselage Remove the cover of the mounting hole situated under the HT on the left side of the fuselage. Connect the right half of the HT with the elevator first. Insert its crossbeam into the hole in the fuselage and insert the elevator into the pin in the steering lever at the same time. Connect the left half of the HT same way. At the same time, it is necessary to get the trim servo wire through the hole into the fuselage. Install two M8 screws, which connect both halves of the HT, into appropriate holes and screw them into the bulkhead inside the tail. The screws must be fitted with a locking washer to avoid their self-loosening and must be properly tightened. Install M4 screws in the holes situated in the front root area of each half of the HT stabilizer. These fix both HT halves via connecting tube. Secure the screws by the Loctite glue. Install two washers and nuts on M6 screws, each mounted on each steering lever. These secure the elevators on the steering levers. Install the cover of the mounting hole situated under the HT stabilizer on the left side of the fuselage. Finally, cover the gap between the fuselage and HT stabilizer by any suitable white plastic tape (eg. 3M) which avoids water intrusion into the fuselage. Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 34 of 57 • Vertical tail rudder installation Adjust the foot-operated steering to the left or right deflection. In that position, insert the VT rudder (its upper pin) into its upper hinge on the tail and push its lower carrier inside the tail at the same time. Adjust the steering back to neutral position and install two M5 screws securing the VT rudder in the lower carrier. HT disassembly Disassembly of the HT is being performed in reverse order. Pull the VT rudder out of the tail first, then unscrew the front M4 screws from the upper side of the HT. Finally, unscrew both M8 screws connecting both HT halves with the fuselage. Pull both HT halves out of the fuselage. 6.3. Wings Assembly/Disassembly At least two people are needed for wings assembly/disassembly. One for assembly and one (or better two) assistant(s) to hold and support the wing to avoid its fall and damage. Do not press the wing surface to avoid cracks in the gel-coat especially in the areas of material connections, dividing lines, edges and not-stiffened areas. The assistant holds the wing by the wingtip and you hold it by the root (the third person can support it also by the trailing edge near to its root). Lift the wing up and lay it down on any smooth soft pad (e.g. mattress) to prevent it from damage. Wings assembly (same for both left and right wing) • Flap pushrod preparation - connection to the wing Place the wing by its leading edge on the soft pad. Hold the wing together with your assistant (who holds the wing by its wingtip). Connect the pushrod to the flap steering lever situated inside the wing. The assistant deflects the flap to enable better accessibility to the flap steering lever. Pay attention to install correct pushrod (LEFT („L“) or RIGHT („R“)) to appropriate wing. Pay attention to correct pushrod position (its non-adjustable end leads into the wing, the adjustable end leads into the fuselage (see the sticker with letters L/R on the upper side of the pushrod). Secure the connection by the pin of Ø5mm with the spacer + split pin (all such parts delivered together with pushrods). • Aileron pushrod preparation - connection to the wing Screw the aileron pushrod to the adjustable end protruding from the wing. Pay attention to install the correct pushrod (LEFT or RIGHT) to appropriate aileron. Exact adjustment will be done later. • Wing attachment to the fuselage Prepare two of main wing pins. Grease them by appropriate quantinty of vaseline. Pay attention to their correct position – UPPER pin is WITHOUT thread, LOWER pin is WITH thread. The assistant holds the wing by the wingtip and you hold it by the root (the third person can hold the wing by its trailing edge near to its root). Attach the wing close to the fuselage, so that both pushrods (aileron and flap) enter the fuselage through the corresponding holes. But, leave some sufficient space between the wing and fuselage to have enough Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 35 of 57 access to interconnect the rest of the equipment between the wing root and fuselage. All persons must still hold and support the wing to avoid its fall. Support the wing at the area of its root rib with a help of the assistant (or you can support it by your knees) to be able to interconnect the rest of the equipment. Then connect the equipment: - static and dynamic pressure hoses of Pitot tube (on the left wing only) Note: Pay attention not to interchange the hoses of Pitot tube during assembly. - quick couplings of fuel hoses - cable connector of the fuel gauge - cable connector of the strobes/position lights (if equipped with) Push the wing towards the fuselage to attach it completely without any gap in between. Insert main wing pins into the holes with fittings. Insert the upper pin (without thread) first and then insert the lower pin (with thread). This operation requires careful use of the hammer and any auxiliary metallic rod (Ø 18mm) to beat the pins into the holes. During this operation, the assistant (holding the wing by the wingtip) pays attention to keep the correct dihedral angle. If needed, he can slightly lift the wing to match the holes with the fittings and so to get appropriate position needed for smooth passing of the pins through the fittings. Both pins must be inserted to their fully beaten position. Then the assistant can leave the wing then. From the upper side, secure the pins by the bolt and tighten it by the torque 25 Nm. Install the M10 self- locking nut on its lower end to secure the wing connection properly. Finally, cover the holes with composite covers (delivered with the plane). Upper one with the hole heading backwards, lower one is half ball- shaped. Or when any next re-assembly, you can use any removable white plastic sticker (to avoid water intrusion). • Flaps pushrods connection inside the cockpit Remove the seats to have better access to the flap steering lever situated in the central tunnel. Connect the pushrod with the lever and secure it by the pin Ø 5mm and spacer + split pin (all parts delivered with the pushrod). Eventually, it is possible to insert the pin Ø 5mm via from the bottom side (better accessibility to insert the spacer and split pin). Install seats back. • Ailerons pushrods connection inside the cockpit Screw the connecting pushrods of the ailerons to the control stick to be in fully tightened position. Then loosen it again by a number of turns indicated on the pushrod. This assures correct neutral position of ailerons. Secure the connection with the pin Ø 5mm and spacer + split pin (all parts delivered with the pushrod). Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 36 of 57 Wings disassembly First of all, drain off the fuel from both wing tanks. Inside the cockpit, disconnect ailerons pushrods from the control stick and flaps pushrods (in the central tunnel). Release and remove the locking nut of the wing pins bolt. Screw the bolt out by approx. 2cm. If needed, the assistant (holding the wing by the wing tip) can slightly lift the wing to allow the pins to be pulled out more smoothly. Beat out the lower pin by the hammer by light tapping on the head of the bolt. Unscrew the bolt and remove the lower pin. Push out the upper pin with a help of any metal rod of Ø 18mm and the hammer. The assistant still holds the wing by the wingtip and you hold it by the root (the third person can hold the wing by the trailing edge near its root) to avoid its fall and damage. After the pins are removed, partially pull the wing out of the fuselage to have the space between the wing and fuselage and to have enough access to disconnect the equipment. Support the wing at the area of its root rib with a help of the assistant (or you can support it by your knees) to be able to disconnect the rest of the equipment. Then disconnect: - static and dynamic pressure hoses of the Pitot tube (only on the left wing) Note: Pay attention not to interchange the hoses of the Pitot tube during their next re-assembly. - quick couplings of fuel hoses - cable connector of the fuel gauge - cable connector of the strobes/position lights (if equipped with) Store the wings on any safe and dry place with stable temperature. Wings need to be properly secured and prevented from structural and surface damage. Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 37 of 57 Chapter 7 7. Aircraft and Systems Description 7.1. Wing 7.2. Fuselage 7.3. Tailplanes 7.4. Landing Gear 7.5. Steering 7.6. Propulsion unit 7.7. Fuel System 7.8. Instruments 7.9. Controlling Elements 7.10. Canopy 7.11. Cockpit Equipment Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 38 of 57 7.1. Wing The cantilever tapered backswept wings with combined structure, slotted lift flaps and composite coating have SM 701 airfoil along the whole span and winglets on wingtips. The main spar is made of laminated hard beech wood saturated with synthetic resin and is situated in 30% of the wing depth. Ailerons are hinged on the rear spar. Flaps are hinged on composite hinges with turning point under the outline profile. Root ribs are made of carbon sandwich, other ribs are made of plastic foam. The wing coating is made of carbon sandwich. Ailerons and flaps have all-composite structure. The centrewing is welded of CrMo steel tubes of high quality. Inside of each wing, the fiberglass composite fuel tank of 50L capacity is inbuilt. Fuel tank is situated in the area of leading edge of the wing. 7.2. Fuselage The fuselage is a carbon composite shell braced with carbon sandwich bulkheads, NOMEX honeycomb and hardened foam. The fuselage cross-section is elliptic with aerodynamic wing base and spacious cockpit covered by perspex canopy. The luggage compartment with two small side-windows behind the seats is a part of the cockpit. The engine compartment in the front part of the fuselage is separated from the cockpit by the firewall to which the engine bed and the steerable nose wheel are mounted. 7.3. Tailplanes The tailplanes have carbon composite structure designed in classical cross tail arrangement. The horizontal tail has trapezoidal shape and consists of fix stabilizer and elevator. The vertical tail has trapezoidal shape. The tail fin is an integral part of the fuselage. The VT rudder has carbon composite structure. The elevator trim is electrical. 7.4. Landing Gear The landing gear is a fixed tricycle undercarriage with a steerable nose wheel. The main gear is designed as a pair of composite leaf springs with the wheels size of 350x120 mm. Main wheels are fitted with hydraulic disc brakes and aerodynamic wheel spats. Integral nose leg with aerodynamic fairing consists of composite construction and the metal tube with shock absorbing rubber springs. Nose wheel size is 300x100 mm. 7.5. Steering All controls have dual steering. Ailerons and elevator are controlled by pushrods and levers. The rudder is controlled by steel wire ropes. Flaps are driven electrically. All controls attachments are designed as to not to disturb outline profile of the airframe. Important check points in the wings are fitted with inspection holes covered by perspex covers. The pitch angle can be trimmed. The cockpit can be optionally equipped with co-pilot control stick. 7.6. Propulsion unit The propulsion unit consists of ROTAX 912 iS Sport engine and three or two blade FITI ECO COMPETITION propeller, which can be either ground or in-flight adjustable. Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 39 of 57 7.7. Fuel System The fuel system consists of two fuel tanks inbuilt in wings. Its total fuel capacity is 100 liters (2 x max. 50L). The piping connection is equipped with a sediment bowl and a drain plug. The fuel supply is provided by two independent circuits with two electrical fuel pumps (main and auxiliary). Unconsumed fuel returns back to the fuel tank. The fuel pressure is measured by the pressure gauge. When the fuel amount indicating light turns on, the fuel reserve is 5 liters. 7.8. Instruments The instrumental equipment consists of basic flight and engine instruments and navigation system. Static and dynamic pressure is taken from the Pitot tube installed on the underside of the left wing. Instrumental layout on the dashboard is displayed on the picture in the Art. 7.11. If the aircraft is equipped with SSR transponder, this must be switched-on during the flight. The installation of SSR transponder must be provided by appropriate authorized person. Basic transponder squawks: 2000 - controlled flight 7000 - uncontrolled flight 7500 - unlawful interference 7600 - communication failure / radio contact loss 7700 - emergency When setting up the new squawk, the transponder must be in “STAND-BY” mode. When handling the device, follow operating instructions of its manufacturer and instructions of air traffic controller! 7.9. Controlling Elements Foot-operated control By pushing the left pedal when sufficient speed is reached, the aircraft turns to the left when moving either on the ground or in flight, and vice versa. Pedals can be fix or optionally adjustable in three positions. Hand-operated control By pulling the control stick towards the pilot, the nose lifts up (pitch angle increases) and the aircraft is climbing. By pushing the control stick forward, the aircraft is descending. By moving the control stick to the left, the aircraft banks to the left, and vice versa. Electrical flaps The electrical flaps are controlled by electronic flaps controller. By moving the control lever of the actuator backwards, the flaps move from 0 position to the positions I, II or III, and vice versa. Each flap position is indicated by indicator light. In case the limit of airspeed appropriate to certain flaps position is exceeded, the controller does not allow further opening of flaps to the next position. For detailed instructions to use, see the User Manual to the e-flaps controller issued by its manufacturer and delivered with the aircraft. Engine throttle By pushing the throttle lever forward, the engine power increases and vice versa. Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 40 of 57 7.10. Canopy The cockpit is covered by hinged perspex canopy with two small sliding windows. The canopy opens up- and backwards. Electrical blocking system installed on the canopy locks disables to start up the engine in case the canopy is not properly closed. Mechanical blocking system (i.e. the lever to OPEN/CLOSE the canopy) prevents the canopy from its self-opening during the flight. Small demisting fan installed on the top of the dashboard avoids canopy fogging. 7.11. Cockpit Equipment The aircraft shall be equipped with at least minimum equipment, which is: 1. Speed indicator with colour markings of speed limits 2. Altimeter 3. Skid ball 4. Compass 5. EMS device (engine monitoring system) with colour indicators suitable for Rotax 912 iS example