Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS

The engine characteristics, operation and maintenance are preferentially directed by appropriate engine Manual. ROTAX 912 UL or ULS is not certified aviation engine. Any engine failure may occur at any time. The pilot is fully responsible for operation of this 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 consider the flight altitude and flight track so that to be able to make safety landing in case of engine failure. Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS 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 ultralight aircraft with Rotax 912 UL/ULS 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. Weight 2.4. Centre of Gravity 2.5. Manoeuvre and Gust Envelope 2.6. Permitted Manoeuvres 2.7. Load Factors 2.8. Type of Operation 2.9. Crew 2.10. Fuel tank 2.11. Wind 2.12. Other Restrictions 2.13. Labels and Markings Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS 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 295 km/h 159 kt Do not exceed this speed in any case! Design manoeuvre speed VA 165 km/h 89 kt After exceeding this speed, do not use full deflection of any control surface and do not make any sudden control operations. An overload of the aircraft may occure! Maximum design cruising speed VC 248 km/h 134 kt Do not exceed this speed except the flight in smooth air, but with caution! Max. cruising speed at severe turbulence VRA 179 km/h 96 kt Do not exceed this speed at severe turbulence! Max. speed, flaps extended to I. (10 °) VFE,I 130 km/h 70 kt Max. speed, flaps extended to II. (20 °) VFE,II 120 km/h 65 kt Max. speed, flaps extended to III. (35 °) VFE,III 110 km/h 59 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 64 km/h 35 kt Flying this speed with flaps retracted results in loss of lift force and stall! Stall speed in landing configuration VS0 51 km/h 28 kt Flying this speed with flaps extended on the position III. results in loss of lift force and stall! Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 12 of 57 2.3. Weight Empty weight kg Maximum take-off weight 472,5 kg Useful load kg Never exceed maximum take-off weight of the aircraft! 2.4. Centre of Gravity (CG ) CG of the empty aircraft % MAC CG range in flight 27 - 36 % MAC Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 13 of 57 2.5. Manoeuvre and Gust Envelope (CAS) CAS (km/h) CAS (kt) IAS (km/h) IAS (kt) Vs0 57 31 51 28 Vs1 69 37 64 35 VAF 86 47 81 44 VS1N 112 61 111 60 VF 110 59 109 59 VA 158 85 165 89 VG 224 121 240 130 VC 230 124 248 134 VH 249 134 270 146 VNE 270 146 295 159 VD 299 161 329 178 Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 14 of 57 2.6. Permitted Manoeuvres Category of the aircraft: Normal Operations are limited to non-aerobatic manoeuvres that include: - Any manoeuvres necessary to normal flying - Training of stalls - Steep turns, in which the angle of bank is not more than 60° Aerobatic manoeuvres are prohibited! 2.7. Load Factors MTOW 450 kg 472,5 kg Maximum positive load factor in CG + 4,0 G + 5,06 G Maximum negative load factor in CG - 2,0 G - 3,06 G 2.8. 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! 2.9. Crew Number of seats 2 Minimum weight of crew 60 kg Maximum weight of crew 180 kg Maximum load of the seat 90 kg 2.10. Fuel tank Fuel capacity 2 x 50 L Non-usable rest of fuel 1,2 L 2.11. Wind The 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 b) take-off or landing tailwind up to 3 m/s c) take-off or landing crosswind up to 6 m/s Never operate the aircraft when above listed wind range limits are exceeded! Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 15 of 57 2.12. Other Restrictions Smoking, using of mobile phones, explosives and combustible materials and transport of movable objects are prohibited on board of the aircraft. 2.13. Labels and Markings The aircraft shall be equipped with mandatory labels and markings. These must be placed on instrumental board in a visual field of pilot and must contain following information: - Identification of the aircraft • Identification label • Serial number • Designation • Empty weight • Maximum take-off weight - Operating limits • Load and weight limits depending on the weight of crew, fuel and luggage • Speed limits for standard flight configurations - Passenger Warnings • Definition of aircraft category, its airworthiness conditions and restrictions • Prohibition of intentional spins, stalls and aerobatics Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 16 of 57 INTENTIONALLY LEFT BLANK Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 17 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 ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 18 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 main switch just before landing. Note: Electric flaps actuation is only possible when the main 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. If no significant failure on engine or its installation found, try again to start up the engine using the back-up fuel circuit. The engine can be started by electric starter even though the propeller turns in flight because of windmilling and its speed is not sufficient. It is not necessary to wait for the standstill of the propeller. 4. If the engine start-up is not successful, carry out emergency landing similar way 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 seatbelts 3. Remove the securing pin from activation handle 4. Fire the rescue system In case of landing on limited space, when collision with an obstacle is inevitable, use the balistic rescue system as a braking device of the aircraft. Note: the activation of the rescue system is only available from pilot´s seat The aircraft may be damaged or the crew may be injured when using the rescue system! 3.4. Fire on Board 1. Turn off the fuel valve 2. Open the throttle 3. Switch off the main switch and ignition 4. Make emergency landing 5. Get off the aircraft Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 19 of 57 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 seatbelts 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 main switch In case of emergency landing on terrain or surface not approved for take-off/landing of sport flying device, the aircraft may be damaged or the crew may be injured! 3.7. Safety Landing Carried out in case of orientation loss, fuel exhaustion or any other reason when the aircraft is fully controllable. 1. Determine the wind direction 2. Choose any suitable landing surface 3. Make a low pass headwind along the right-hand side of the landing surface and inspect the terrain thoroughly 4. Make a pattern flight 5. Calculate the landing plan 6. Land in the first third of the landing area using the flaps in landing position 3.8. Aborted Landing Carried out in case of wrong calculation of landing manoeuvre or bounce during landing and when the pilot considers aborted landing manoeuvre as more safe and decides to proceed the flight. 1. Set up the engine run to maximum power 2. Fluently set up flaps to take-off position – I 3. Reach the level speed of 110 km/h (59 kt) 4. Pull the control stick slowly to make the aircraft climbing by speed 110 – 120 km/h (59 – 65 kt) 5. Retract flaps Maintain the aircraft in take-off axis by using the rudder control throughout the flight. Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 20 of 57 3.9. Vibrations In case of unusual vibrations occurance, 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 ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 21 of 57 INTENTIONALLY LEFT BLANK Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 22 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. Descending and Landing 4.9. Flight in Rainy Conditions 4.10. Engine Shut-off Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 23 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: 1/ Cockpit – switches, seat 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 and spat attachment 5/ Horizontal tail and elevator – surface condition, attachment, elevator free movement, plays, trimming tab, fitting covers attachment Vertical tail and rudder – surface condition, rudder attachment, plays, ropes tension Tailplane – surface condition, radio antenna check 6/ Right flap - coating, attachments, controls, play Right gear leg - condition, brake fluid leak, wheel, tyre condition and inflation, wheel and spat attachment 7/ Right aileron - coating, free movement, attachments, controls 8/ Right wing – coating, condition, plays, fuel tank cap, drain valve, fuel tank ventilation 9/ Nose wheel – condition, play, wheel, tyre condition and inflation Propeller – surface condition, blades and spinner tightness Engine - condition and fastening of engine cowling, engine bed, hoses intactness (fuel, oil, cooling system), screws and nuts security, exhaust pipe and carburettors attachment, drain plug, oil and coolant level: Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 24 of 57 a) Oil level – 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 push 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. Never open the oil tank when the oil is hot! b) Coolant level – Remove the upper cowling of the engine. The engine must always be cool when checking the coolant amount. Do not open the expansion tank when the coolant is hot! Loosen the cap of the expansion tank and check the coolant level. The maximum level allowance is about 2 cm below the rim of the expansion tank. If the level is low, refill appropriate amount of the coolant. Cover the engine by upper cowling and fix it by screws. Keep the coolant level in the overflow bottle within the marked range „MIN- MAX“. 4.1.1. Procedures Before Entering the Cockpit 1. Canopy  open 2. Ignition  switched off 3. Main 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 of instruments, condition of flight instruments, fuel amount, proper function of controls, securing of the rescue system to avoid its 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 fuel tank in use 7. Throttle  idle 8. Fuel level indicator  check fuel amount 9. Main switch  switched off 10. Ignition  switched off 11. Instruments  check condition, zero values, altimeter setting Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 25 of 57 4.1.3. Procedures Before Engine Start-up, Engine Start-up Do not start-up the engine if there is any person in the vicinity of the aircraft! 1. Rescue system  unlock (if equipped with) 2. Safety belts  fasten 3. Canopy  close and lock 4. Parking brake  on 5. Fuel valve  turn on (open/select for appropriate tank intended to use) 6. Choke  turn on - in case of cold engine 7. Throttle  idle 8. Main switch  switch on 9. Ignition  both circuits switched on 10. Brakes  on Do not push the starter as long as the engine is running. Wait until complete stop of the engine. 11. Starter button  press and hold (without interruption) for max. 10 sec.; adjust throttle to reach a smooth run at approx. 2500 RPM 12. Oil pressure  minimum 0,8 bar within 10 seconds; Monitor oil pressure. Increase engine speed when oil pressure remains steady above 2 bar. 13. Choke  turn off 14. Warm the engine up to the operating temperature Never unlock neither open the canopy when engine is running! 4.2. Engine Warming up Start warming up the engine when 2000 RPM, after approx. 2 min. continue warming up to 2500 RPM until reaching the 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 crosswind, hold the control stick position opposite to wind direction 4.4. Engine Check 1. Brakes  on 2. Throttle  4000 RPM 3. Switch off 1st ignition circuit  max. RPM drop after stabilization must not exceed 300 RPM 4. Switch on both ignition circuits  4000 RPM 5. Switch off 2nd ignition circuit  max. RPM drop after stabilization must not exceed 300 RPM Note: The RPM speed difference between ignition circuits running separately must not be more than 115 RPM. 6. Throttle  reduce to idle run Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 26 of 57 7. Left and right fuel tank check  during engine run, the fuel pressure must not drop below tolerated value in either of fuel tanks in use. During the change-over of fuel tanks in use, a short- term pressure drop may occur. After the appropriate fuel tank is selected, the fuel pressure must return to appropriate values. After the engine check is finished and operating temperature is reached, carry on take-off within max. 5 min. If the aircraft is grounded when engine is running for a long period, the engine and its compartment are not sufficiently cooled by the airflow. This may cause overheating and damage of the engine and composite structure of its compartment. 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. 6. Fuel valve  open (left/right) for appropriate fuel tank intended to use 7. Choke  turned off 8. Throttle  idle 9. Fuel indicator  fuel amount check 10. Instruments  switched on, values within operating limits 11. Safety belts  adjusted, fastened, secured 12. Canopy  closed and locked 4.6. Take-off and Climbing Release the brakes. Make the aircraft move by accelerating until the maximum throttle position is reached. Control stick in neutral position. Control the nose wheel and the rudder to keep the aircraft within the runway axis. When reaching the speed of 75km/h (45kt), gently pull the control stick to lift up the aircraft and continue take-off up to the speed of 110km/h (59kt). Then, gently pull the control stick to start climbing by optimal speed of 110km/h (59kt). After reaching the stable climbing speed of 110-120km/h (59-65kt) and altitude over 50m (160ft), fluently retract the flaps. Limit values of the engine must not be exceeded during the take-off. Climbing at full take-off power is only allowed for a period of max. 5 minutes. When required flight level is reached, adjust the propeller to “cruise” position (if equipped with in-flight adjustable propeller). 4.7. Cruising Flight ATEC 321 FAETA has good flight characteristics within the whole range of permitted speeds and position of the centre of gravity. The cruising speed range is 120 – 248km/h (65 – 134kt). 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 the range of 90-110°C. Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 27 of 57 4.8. Descending and Landing Descending Descend with throttle on idle when speed of 100km/h (55 kt). Flaps position 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 in-flight adjustable propeller) 2. Speed of 90km/h (49kt) 3. Flaps position III (position II. in case of strong turbulence or strong headwind) 4. Throttle idle or corrected if necessary 5. Instruments within permitted limits Landing The speed of the aircraft in hold-up position decreases by soft pulling of the control stick until touch down at the speed of 70km/h (38kt). After the nose wheel touch-down, the landing distance can be shortened by braking. Do not apply maximum braking 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 undercarriage and other load bearing structure. This may shorten life-time of the airframe. 4.9. Flight in Rainy Conditions During the flight in the rain, it is necessary to pay close attention to the aircraft control because of poor visibility and limited transparency of the canopy. Furthermore, shorter hold-up position when landing and extended take-off distance must be taken into account. Maintain the following speeds during the flight in the rain: 1. Climbing 120 km/h (65kt) 2. Cruising flight 120 – 180 km/h (65 – 97kt) 3. Descending to land 110 km/h (59kt), flaps positions I and II as by Art. 2.2. 4.10. Engine Shut-off After landing and taxiing to the parking place, keep the engine running by approx. 2000 RPM for a period at least 2 min. to cool it down. If the engine was cooled down enough by descending flight and taxiing, it can be shut-off as soon as the aircraft is stopped. Always keep the fuel valve open for appropriate fuel tank in use. Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 28 of 57 Chapter 5 5. Performances 5.1. Introduction 5.2. Air Speed Indicator Corrections 5.3. Stall Speed 5.4. Altitude Loss by Stalling 5.5. Take-off Distance up to 15m / 50ft 5.6. Rate of Climb 5.7. Cruising Speed 5.8. Flight Range Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 29 of 57 5.1. Introduction The Chapter contents the information on speed indicator calibration, stalling speed and other performances of the ATEC 321 FAETA equipped with ROTAX 912 UL and ROTAX 912 ULS engine and propeller FITI ECO COMPETITION 3L/160 with the pitch adjusted to 18°/80 HP and 21°/100 HP. 5.2. Air Speed Indicator Corrections IAS (km/h) CAS (km/h) IAS (kt) CAS (kt) Deviation (km/h / kt) Note 51,2 57 27,6 30,8 -5,8/-3,1 Vso 64,0 69 34,6 37,3 -5,0/-2,7 Vs1 75,8 80 40,9 43,2 -4,2/-2,3 97,2 100 52,5 54 -2,8/-1,5 108,8 110 58,7 59,4 -1,2/-0,7 VFIII 120,4 120 65,0 64,8 0,4/0,2 VFII 132,0 130 71,3 70,2 2,0/1,1 VFI 143,7 140 77,6 75,6 3,7/2,0 164,6 158 88,9 85,3 6,6/3,6 VA 178,5 170 96,4 91,8 8,5/4,6 VRA 190,1 180 102,7 97,2 10,1/5,5 213,4 200 115,2 108,0 13,4/7,2 227,3 212 122,8 114,5 15,3/8,3 236,6 220 127,8 118,8 16,6/9,0 259,9 240 140,3 129,6 19,9/10,7 248,0 230 133,9 124,2 18,0/9,7 VC 270,3 249 146,0 134,4 21,3/11,5 VH 283,1 260 152,9 140,4 23,1/12,5 294,7 270 159,2 145,8 24,7/13,4 VNE 306,4 280 165,4 151,2 26,4/14,2 329,6 300 178,0 162,0 29/6/16,0 VD 5.3. Stall Speed (CAS) Engine idle Flaps retracted Flaps I (10°) Flaps II (20°) Flaps III (35°) Solo flight 64,0 km/h 34,6 kt 61,9 km/h 33,4 kt 58,7 km/h 31,7 kt 47,1 km/h 25,4 kt 472,5 kg 70,5 km/h 38,1 kt 62,0 km/h 33,5 kt 60,8 km/h 32,8 kt 51,2 km/h 27,6 kt Engine off Flaps retracted Flaps I (10°) Flaps II (20°) Flaps III (35°) Solo flight 64,0 km/h 34,6 kt 61,9 km/h 33,4 kt 58,7 km/h 31,7 kt 47,1 km/h 25,4 kt 472,5 kg 70,5 km/h 38,1 kt 62,0 km/h 33,5 kt 60,8 km/h 32,8 kt 51,2 km/h 27,6 kt Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 30 of 57 5.4. Altitude Loss by Stalling Level flight flap position Flap deflection Altitude loss I 10° 30 m 100 ft II 20° 30 m 100 ft III 35° 30 m 100 ft 0 0 30 m 100 ft 5.5. Take-off Distance up to 15m / 50ft Engine 80 HP 100 HP Runway surface Take-off distance Take-off distance Asphalt 270 m 880 ft 245 m 800 ft Grass 290 m 950 ft 265 m 870 ft 5.6. Rate of Climb (when speed of 110 km/h (59 kt)) Engine 80 HP 100 HP Solo flight 6,0 m/s 1182 ft/min 7,5 m/s 1476 ft/min 472,5 kg 4,5 m/s 886 ft/min 6,0 m/s 1182 ft/min 5.7. Cruising Speed ROTAX 912 UL 80 HP Air speed km/h kt RPM Consumption l/h 120 65 4000 5,8 140 76 4250 7,2 160 86 4400 9,5 180 97 4700 10,8 200 108 5000 13,1 220 119 5300 17,0 ROTAX 912 ULS 100 HP Air speed km/h kt RPM 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 17,5 240 130 5500 20 Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 31 of 57 5.8. Flight Range When maximum fuel capacity of 100 L ROTAX 912 UL 80 HP Air speed km/h kt Flight range km n.m. Flight endurance h Flight reserve (10 L) h 140 76 1750 945 12:30 1:23 160 86 1515 818 9:28 1:23 180 97 1500 810 8:20 0:55 200 108 1374 742 6:52 0:45 220 119 1164 628 5:17 0:35 ROTAX 912 ULS 100 HP Air speed km/h kt Flight range km n.m. Flight endurance h Flight 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 0:34 240 130 1080 583 4:30 0:30 Information on engine RPM, consumption, flight endurance and flight range are of informative character only. Listed values are dependent on propeller type and pitch, flight altitude, temperature, air pressure and aircraft load. The flight range is considered as theoretic, when windless conditions. When planning the flight track, do consider these factors and safe amount of fuel reserve! Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 32 of 57 Chapter 6 6. Aircraft Assembly/Disassembly 6.1. Introduction 6.2. Horizontal Tail Assembly/Disassembly 6.3. Wings Assembly/Disassembly Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 33 of 57 6.1. Introduction The assembly of individual parts of the aircraft is described in this chapter. At least two persons are needed for assembly/disassembly. All parts necessary for assembly are delivered with the aircraft. Do not push hardly on any surface during manipulation with parts to avoid cracks in the gel-coat (especially in the area of dividing lines, edges, not-stiffened areas). Clean, grease and secure all pins before assembly. Pay attention to correct adjustment of ailerons and flaps, which is carried out by shortening and prolonging of connecting pushrods (screw/unscrew adjustable ends). With each next assembly, it is necessary to replace locking nuts and split pins with new ones. After the aircraft assembly, carry out deflections adjustment according to levelling record and carry out engine run test with a focus on correct function of the fuel tanks and correct values on the fuel indicator. 6.2. Horizontal Tail (HT) Assembly / Disassembly At least two persons are needed for HT assembly/disassembly. Third person is recommended to push the fuselage tail down to the ground to enable better access to the HT and its fitting. Pay attention to avoid a fall of small parts into the inner space of the tail fin during manipulation!! Horizontal tail assembly • Elevator pushrod connection Deflect the control stick to fully „pushed“ position and secure (block) it softly to avoid its movement during assembly. This position enables better access to the elevator pushrod, which is then protruding from the tail fin. The assistant can carefully push the fuselage tail down to the ground and hold it in a position which enables to reach better access to the HT and its fitting during all the process of assembly. Take the HT and place it over the siderudder in such a position to keep an access to the end of the pushrod protruding from the tail fin. The assistant holds the HT keeping the elevator maximally deflected upward, so that the elevator control lever is protruding from the HT surface. Connect the pushrod with the elevator control lever by the pin of Ø 5mm and spacer + split pin. Connect the cable connector of the servo (in case of electrical trim option). •Fixing the HT to the fuselage Settle the HT on the fuselage tail and screw two M8 screws of the main fitting, but do not tighten them fully yet. Insert the vertical screw M6 (with nylon) into the hole on the upper side of the HT and tighten it fully with adequate power. Come back to both M8 screws on the main fitting and tighten them fully. • Screws Securing Secure both M8 screws with a binding wire. Appropriate holes for binding wires are situated in the main fitting and four holes are in the head of the screw. Secure the vertical nylon-screw with a binding wire Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 34 of 57 too. One hole is drilled in the horizontal tail body and two holes are in the head of the screw. Finally, cover the hole on upper side of the HT with a white plastic sticker (to avoid water intrusion). •HT fittings covers assembly Covers of the HT fittings help to avoid vibration occurence in flight. Install the composite covers (with double-side tape) according to following picture: Horizontal tail disassembly Remove the composite covers of the HT fittings. Pay attention not to damage them. These will be needed for any next installation. Release and unscrew M6 screw (by which the position of HT is adjusted) on the upper side of the HT. Release and remove M8 screws of the main HT fitting. Tilt the HT so that it is possible to disconnect the pin of the HT pushrod. Remove the HT and secure the ball bearing by a binding wire. Store the HT on a safe and dry place with stable temperature. The HT needs to be enough secured and prevented from structural and surface damages. 6.3. Wings Assembly/Disassembly At least two persons 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. The assistant holds the wing by the wingtip and you hold it by the root (the third person can hold the wing by the flap). Pick the wing up and then lay it down on any smooth, soft pad (e.g. mattress). Wings assembly (same for both left and right wing) •Flap pushrod preparation - connection to the wing Put the wing to the position by its leading edge down (on the soft pad). Hold the wing together with your assistant, who deflects the flap so that the rod lever is protruding outside the wing. This enables better access to connect the flap pushrod with the flap lever. Pay attention to install the correct pushrod (LEFT („L“) or RIGHT („R“)) to appropriate wing. Pay attention to correct pushrod position. Its non-adjustable end leads into the wing and the adjustable one towards the fuselage. The sticker with letters L/R shall be situated on the upper side of the pushrod. Fix the connection by the pin of Ø5mm and spacer + split pin (all such parts delivered with the pushrod). •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 carried out later. Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 35 of 57 •Wing Connection to the fuselage Prepare two of main wing pins. Lubricate them with an appropriate quantinty of vaseline. Pay attention to their correct position - UPPER wing pin is WITHOUT thread, LOWER wing pin is WITH thread. The assistant holds the wing on the wingtip and you hold it by the root (the third person can hold the wing by the flap). Pick the wing up and attach it close to the fuselage so that pushrods (aileron and flap) enter the fuselage through the corresponding holes. But, keep the space between the wing and fuselage to reach enough access to be able to connect the rest of the equipment protruding from the wing. All persons keep holding and supporting the wing to avoid its fall. You can support the wing by your knees at the area of wing root (or the third person can assist with) to connect the rest of the equipment: - static and dynamic pressure hoses of Pitot tube (just on the left wing) 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) Attach (push) the wing towards the fuselage completely without any gap in between. Insert the main wing pins into the hole with fittings (wing attachment) inside. Insert the upper pin (without thread) first and then insert the bottom pin (with thread). This operation requires careful use of the hammer and auxiliary metal rod (Ø 18mm) to beat the pin into the hole. During this operation, the assistant (holding the wing by the wing tip) pays attention to keep the correct dihedral angle. If needed, he can slightly lift the wing to fit the fittings exactly with the hole in correct position and so to enable pins to easily pass through the fittings. Both pins must be inserted to their fully beaten position. Then the assistant can leave the wing. Secure the pin from upper side by the bolt and tighten by torque approx. 25 Nm. Install the M10 locking nut from the bottom side, so that the wing connection is properly secured. Cover the holes with any plastic white sticker (to avoid water intrusion). •Flap pushrod connection inside the cockpit Take the seats out of the cockpit to reach an access to the flap control lever situated in the central tunnel. Connect the pushrod with the flap lever by the pin Ø 5mm and spacer + split pin (all parts delivered with the pushrod). You can insert the pin Ø 5mm via from the bottom side (better accessibility for the spacer and split pin installation). Install seats back. • Aileron pushrod connection inside the cockpit Screw the pushrod to the control stick until the connection is fully tightened. Then loosen it again by the number of turns indicated on the pushrod. This ensures correct neutral position of the aileron. Secure the connection by the pin Ø 5mm and spacer + split pin (all parts delivered with the pushrod). Wings disassembly First of all, drain off the fuel from both wing tanks. Disconnect ailerons pushrods from the control stick and flaps pushrods (in the central tunnel) inside the cockpit. Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 36 of 57 Release and remove the locking nuts of the wing pins bolts. Screw the bolts out by approx. 2cm. Beat out the bottom pin by slight tapping on the head of the bolt by the hammer. Unscrew the bolt and remove the bottom pin. If necessary, the assistant (holding the wing by the wing tip) can slightly lift the wing up to enable pins to be pulled-off more easily. Beat out the upper pin by the hammer with a help of any metallic rod of Ø 18mm. After the pins are removed, the assistant holds the wing by the wingtip and you hold it by the root. (the third person can hold the wing by the flap). Partially pull the wing out of the fuselage to reach the space between the wing and fuselage and so to reach enough access to disconnect the equipment. All persons keep holding and supporting the wing to avoid its fall. You can support the wing by your knees at the area of wing root (or the third person can assist with) to disconnect the rest of the equipment: - static and dynamic pressure hoses of Pitot tube (just on the left wing) Note: Pay attention not to interchange the hoses of Pitot tube during their next re-assembly. - quick couplings of the 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 damages. Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 37 of 57 Chapter 7 7. Aircraft and System Description 7.1. Wing 7.2. Fuselage 7.3. Tailplane 7.4. Landing Gear 7.5. Steering 7.6. Propulsion 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 ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 38 of 57 7.1 Wing The cantilever tapered backswept wing of an angle of 5,5° with SM 701 airfoil along the whole span is a reinforced shell of carbon composite sandwich with carbon composite coating. The wing spar is made of laminated hard beech wood saturated with synthetic resin and is situated in 30% of the wing depth. The ailerons are hinged on the rear spar and slotted flaps are hinged on composite hinges with turning point under the outline profile. Ailerons and flaps are of all-composite structure. Wing root ribs are made of carbon sandwich, other ribs are made of plastic foam. The main spar is welded of high quality CrMo steel tubes. 7.2 Fuselage The fuselage is all carbon composite shell braced with carbon sandwich bulkheads, NOMEX honeycomb and hardened foam. The fuselage cross section has elliptic shape with aerodynamic wing base and spacious cockpit covered by the perspex canopy. The luggage compartment with two small side-windows behind the seats are the part of the cockpit. The engine is in the front part of the fuselage. It is separated from the cockpit by the firewall to which the engine mount and the steerable nose wheel are attached. 7.3 Tailplane The T-shaped all-composite tailplane construction consists of tapered vertical and horizontal tailplanes. The horizontal tailplane consists of fix stabilizer and elevator. The elevator trim can be mechanical or electrical (optional). The tail fin is integral part of the fuselage. The vertical tailplane is of trapezoidal shape. The vertical rudder is suspended to the last fuselage bulkhead. 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. The integral nose leg with aerodynamic fairing is made of composites and the metal tube. The leg is fitted with shock absorbing rubber springs. Main wheels size is 350x120 mm, nose wheel size is 300x100 mm. The main wheels are fitted with hydraulic disc brakes. All wheels are covered by wheel spats. 7.5 Steering Each control surface has dual steering. The ailerons, flaps and elevator are controlled by control rods and levers, the rudder is controlled by stainless steel wire ropes. Lift flaps are optionally equipped with electrical control. All controls attachments are designed the way not to disturb the pure airframe contour. Important checking points in wings are equipped with inspection holes with perspex covers. The control can be trimmed longitudinally in flight. The cockpit can be optionally equipped with the second control stick (for the crew). 7.6 Propulsion The propulsion unit is ROTAX 912 UL 80HP or ROTAX 912 ULS 100HP engine and three- or two-blade FITI ECO COMPETITION propeller, which can be fix, ground or in-flight adjustable. Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS 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 with a total fuel capacity of up to 100 litres (2 x max. 50L). The piping connection is equipped with a sediment bowl and a drain plug. The fuel supply is assured by two independent circuits with back-up electrical fuel pump. Unused fuel returns back to the fuel tank. The fuel pressure is measured by the pressure gauge. When the fuel indicator light turns on, the fuel reserve is 5L. 7.8 Instruments The instrumental equipment consists of basic flight and engine instruments and navigation system. The static and dynamic pressure value is taken from the Pitot tube installed on the underside of the left wing. Instruments layout on the dashboard (individual) is shown 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 (hijack) 7600 - communication failure / radio contact loss 7700 - emergency When setting up the new squawk, the transponder must be in “STAND-BY” mode. 7.9 Controlling Elements Foot-operated control By pushing the left pedal when appropriate speed is reached, the aircraft turns left when moving on the ground or in the air, and vice versa. Pedals can be adjustable in three positions (optional equipment). Hand-operated control By pulling the control stick towards the pilot, the nose lifts up (the pitch increases) and the aircraft climbs. By pushing the control stick forward, the aircraft descends. By deflecting the control stick to the left, the aircraft banks to the left, and vice versa. Wing flaps – mechanical option The flaps are released to move when the release button on the control lever is pushed. By pulling the lever upward, flaps are extending step by step to positions I, II, III, and vice versa. After the button is released, the flaps stay in appropriate stabilized position. Wing flaps – electric option The flaps are actuated by linear potentiometer (flaps actuator) which adjusts them to positions I, II, III or OFF with a help of its servo engine. Each flap position is indicated by indicator light. Engine throttle By pushing the throttle lever forward, the engine power increases and vice versa. Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 UL/ULS ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 40 of 57 Choke By pushing the choke lever forward, the choke opens and vice versa. 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 on canopy locks disables to start-up the engine in case the canopy is not properly closed. Mechanical blocking system (the lever to open/close canopy) prevents the canopy from self-opening during the flight. Small dismisting fan installed on the top of the dashboard avoids canopy fogging (optional equipment). 7.11 Cockpit Equipment (picture and description as by individual configuration)