Flight and Operations Manual of ATEC 321 FAETA (Rotax 912 iS)
Contents
1. 9 1 Introduction 9 2 Empty Weight 9 3 Maximum Take off Weight 9 4 CG Range 9 5 CG Determination 9 6 Useful Load Weight Table Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 43 of 53 9 1 Introduction Weight useful load and centre of gravity data are described in this chapter 9 2 Empty Weight The empty weight is the weight of fully equipped ready to operate aircraft excluding fuel and crew Empty weight is a total sum of all weight values measured under all undercarriage wheels simultaneously The empty weight of the aircraft is 9 3 Maximum Take off Weight The maximum take off weight defined by the Manufacturer and Czech UL 2 regulation is Never exceed the maximum take off weight 9 4 Centre of Gravity Range Centre of gravity of empty aircraft is of MAC Flight range of centre of gravity 27 36 of MAC Operation over this range is prohibited Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 44 of 53 9 5 Centre of gravity determination The aircraft has to be weighed in flight position including crew and fuel Weight on mainwheels ss a Gi Weight onfrontwheel G2 Total weight Git Go G Git G2 Distance from main wheel axis to front wheel axis__ Xmw Fw 1 44 Distance from main wheel axis to wing leading edge in wing root area Xmw Le 0 76 CG distance f2. 7 3 7 4 7 5 7 6 7 1 7 8 7 9 Aircraft and System Description Wing Fuselage Tail Surface Landing Gear Steering Drive Unit Fuel System Instruments Controlling Elements 7 10 Canopy 7 11 Cockpit Equipment Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 35 of 53 7 1 Wing The cantilever tapered backswept wing of an angle of 5 5 with SM 701 airfoil along the all span is a reinforced shell of a carbon fibre sandwich with a carbon fibre coating The wing spar is made of laminated hard beech wood saturated with synthetic resin and is situated in 30 of wing depth The ailerons are hinged on the rear spar and slotted flaps are hinged on fiberglass hinges Ailerons and flaps are made of all composite structure Wing root ribs are made of carbon sandwich other ribs are of plastic foam The main spar is welded of high quality CrMo steel tubes 7 2 Fuselage The fuselage is all composite carbon fibre shell braced with carbon sandwich bulkheads NOMEX honeycomb and hardened foam The fuselage cross section is of elliptic shape with a spacious cockpit and aerodynamic wing bases In the front part of the fuselage is the engine separated from the cockpit by fireproof wall to which the engine mount and the steerable nosewheel are fixed The cockpit is covered with the canopy The luggage compartment with two small side windows behind seats are the part of the cock
3. Dimensions Wingspan 9 6m Length of fuselage 6 2 m Totalheight 2 0 m Wing area 10 1 m Depth of mean aerodynamic chord s___ _ 1 11 m Span of horizontal tail surface 2 4m Flap position e l 10 45mm II 20 90mm III 35 150mm Aileron deflection ss up 20 90mm down 12 55mm Elevator deflection s_s s up 22 80mm down 18 65mm Rudder deflection ss L R 20 180mm Wing profile Rooi aaa y C O Oaa SM 701 fnd aaa y C Oaa SM 701 Landing Gear tricycle with frong wheel Wheel spacing kkk 1 9 m Wheelbase 1 4m Tire dimensions 350 x 120 0 16 MPa 1 6 atp Suspension Main gear C O composite springs Front wheel ss rubber suspension Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 6 of 53 Brakes Weight Empty weight Maximum take off weight Power Unit and Engine Parameters Propeller producer Type of propeller Engine producer Engine type Engine Power Take off power Maximum continuous power Cruising power Engine Speed Maximum take off engine speed Max continuous engine speed Cruising engine speed Engine idle speed Water Temperature Minimum k Maximum Oil Temperature Minimum k Maximum aa Operational optimum Oil Pressure Maximum short term operated when cold start up Minimum Maximum take off weight including rescue system installed Maximum luggage weight in th
4. ATEC v o s Libice nad Cidlinou Czech Republic Page 36 of 53 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 50I 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 pump The fuel pressure is monitored by fuel pressure gauge When the fuel indicator light is turned on the fuel reserve is 7L 7 8 Instruments The instrumental equipment consists of basic instruments for flight and engine control and navigation The static and dynamic pressure is taken from the Pitot tube installed at the bottom of the left wing Instruments layout on the dashboard is described on the picture in Art 7 11 If the aircraft is equipped with SSR transponder this must be active during the flight The installation of SSR transponder must be provided by competent 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 Pushing the left pedal when adequate speed 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
5. Hand operated control By pulling the control stick towards the pilot the nose lifts up the angle of attack increases and the aircraft climbs By pushing the control stick the aircraft descends By deflecting the control stick to left the aircraft banks to left and vice versa Wing flaps mechanical option By pressing the securing pin on the flaps control lever wing flaps are released and ready to actuate Pulling the lever upward flaps are extending step by step to positions Il Ill and vice versa Wing flaps electric option The flaps are actuated by linear potentiometer adjusting positions OFF Il Ill All flap positions are indicated by indicator light Engine throttle By moving the throttle forward the engine power increases and vice versa Choke Choke pushrod pulled choke is turned on Choke pushrod pushed choke is turned off Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 37 of 53 7 10 Canopy The cockpit is covered with hinged perspex canopy with two small sliding windows The canopy is opening up and backward Electrical blocking system on canopy lock disables to start up the engine if the canopy is not closed well Mechanical blocking system the lever to open close canopy prevents from canopy self opening during the flight Small fan installed upside the dashboard avoids canopy fogging optional equipment 7 11 Cockpit Equipmen
6. Never exceed the maximum take off weight of the aircraft 2 4 Centre of Gravity CG CG of the empty aircraft 28 7 MAC Flight range of CG 27 36 MAC Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 12 of 53 2 5 Manoeuvre and Gust Envelope CAS Obalka obratu a poryvu FAETA 321 m 472 5 kg n g 40 60 80 100 120 140 160 180 200 220 240 260 280 300 320 V km h vSO 61km h 16 9m s 32 9kt vS1 79 3km h 22 0m s 42 8kt VAF 86 2km h 24m s 46 6kt vSIN 111 9km h 31 1m s 60 5kt vF 130km h 36 1m s 70 2kt vA 156km h 43 5m s 84 6kt vG 156km h 43 5m s 845kt vC 230km h 63 8m s 124kt vH 249km h 692m s 134kt vNE 270km h 75 4m s 146kt vD 298 8km h 83 m s 161 5 kt Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 13 of 53 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 Maximum positive load factor in CG 5 1G Maximum negative load factor in CG ___ 2 8 Type of Operation Only VFR day flights are permitted flight by visual reference to the ground during the d
7. Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 4 of 53 1 1 Introduction Information provided within this manual is a necessary requirement for an effective and save operation of the ATEC 321 FAETA aircraft The manual contents information which Manufacturer considers as important 1 2 Personal Data of the Owner Owner of aircraft Owner of aircraft Address eee Owner of aircraft Address 223th aa aa E ae A E eth deta Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 5 of 53 1 3 Aircraft Description ATEC 321 FAETA is an ultralight two seater cantilever low wing aircraft of all carbon composite construction The landing gear has a fixed tricycle gear with a steerable front wheel The power unit is of pulling configuration and consists of ROTAX 912 iS engine and of two blade or three blade fix or ground adjustable FITI propeller 1 4 Modifications and Changes If any structural or operational changes are made by the Manufacturer and need to be advised to the owner the related documentation will be delivered to you and you are obliged to record them into your Manual These documents will be published in ascending numerical series If the aircraft is sold to another person the Manufacturer shell be announced about the name and the address of the new owner 1 5 Aircraft Technical Data
8. are kept the centre of gravity is situated in permitted position range Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 46 of 53 Enclosure 1 Log Book Each aircraft must be equipped with the log book where flight informations are noted just after each flight track performed OK ABC 12 Take off euel Pilot name Track filled up L number Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 47 of 53 Enclosure 2 Records of Revisions Any revisions of the present manual except actual weight data must be recorded into following table according to information from the Manufacturer New or amended text on the revised pages shall be indicated by black vertical line on the left margin along the section affected The revision number and date shall be shown on the bottom left side of the page Revision Affected Affected Insertion Number Section Pages Approval Date Approved by Date Signature Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 48 of 53 Enclosure 3 page 1 4 Service and Maintenace Book Any mandatory inspection w
9. condition 6 Landing gear check laminate spring surface condition secure fixation of main and front wheels and their covers screws and nuts security correct tire pressure brake function 7 Engine check condition and fastening of engine cowlings the condition of engine bed intact fuel oil and cooling system hoses screws and nuts security exhaust pipe and carburettor attachment cooling liquid and oil level fuel system drain 8 Propeller check surface condition intact condition and fastening of the propeller cone 4 1 2 Procedures After Entering the Cockpit 1 Cockpit check fastening and locking of the canopy correct function and condition of electrical installation of instruments condition of flight instruments fuel level check proper function of controls 2 Foot operated steering check function 3 Brakes check function brakes on 4 Hand operated steering check function 5 Flaps check function retract 6 Fuel valve turned off 7 Engine controls switched off throttle idle 8 Fuel level indicator check fuel volume 9 Main switch switched off 10 Ignition switched off 11 Instruments check condition zero values altimeter adjustment 4 1 3 Procedures Before Engine Start up Engine Start up 1 Rescue system gt unlock 2 Safety belts gt fasten 3 Canopy gt close and lock 4 Parking brake gt on 5 Fuel valve gt turn on open select the left or right position depend
10. the spacer and split pin Install seats back eAileron pushrods connection in the cockpit Screw the pushrod to the control stick into the fully tightened position and then loosen it up ina number of turns marked on the pushrod This ensures correct neutral position of ailerons Realize the connection with the pin 5 and spacer split pin all parts attached to the pushrod Wings disconnection First of all drain off the fuel from both wing tanks Disconnect the rods of ailerons on the control stick and flaps rods in the central tunnel in the cockpit Release and remove the locking nut of the bolts of the wing pins Screw the bolt off by approx 2cm The assistant holding it at the wing tip can lift the wing a little Using hammer knock out the bottom pin by light taps on the head of the bolt Unscrew the bolt and remove the bottom pin Then the upper pin is driven out using the hammer through the metal rod of 18mm After pins removal support the wing by your knees and disconnect 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 re assembly quick coupling of fuel hoses from fuel tanks fuel gauges cable and strobes position lights cable if equipped with Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 34 of 53 Chapter 7 7 7 1 7 2
11. 3 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 of Altitude 5 6 Rate of Climb 5 7 Cruising Speeds 5 8 Flight Range Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 27 of 53 5 1 Introduction The Chapter contents the information on speed indicator corrections stalling speed and other performances of the ATEC 321 FAETA with ROTAX 912 iS engine and propeller FITI ECO COMPETITION 3L 158 adjusted to the angle of attack 5 2 Air Speed Indicator Corrections CAS km h CASkt IASkm h IAS kt Deviation km h Deviation kt_ Note_ 570 308 512 276 58 31 vso 690 373 640 346 50 27 Wa 80 0 432 758 409 42 23 100 0 540 972 525 28 45 1100 594 1088 587 12 07 Vm 1200 648 1204 650 oa 02 vm 2 0 1580 85 3 1646 889 1700 918 1785 96 4 2120 1145 2273 1228 153 83 2490 1344 270 3 146 0 260 0 140 4 2831 1529 231 125 270 0 1458 294 7 1592 5 3 Stall Speed CAS Engine idle Flaps retracted Flaps 10 Flaps lI 20 Flaps III 35 l 70 5 km h 61 9 km h 58 7 km h 47 1 km h aolo flight 38 1 kt 33 4 kt 31 7 kt 25 4 kt ie 64 0 km h 62 0 km h 60 8 km h
12. 51 2 km h 9 KB 34 6 kt 33 5 kt 32 8 kt 27 6 kt Engine off Flaps retracted Flaps 10 Flaps lI 20 Flaps III 35 70 5 km h 61 9 km h 58 7 km h 47 1 km h solo flight 38 1 kt 33 4 kt 31 7 kt 25 4 kt ee 64 0 km h 62 0 km h 60 8 km h 51 2 km h 2 KE 34 6 kt 33 5 kt 32 8 kt 27 6 kt Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 28 of 53 5 4 Altitude Loss by Stalling Level flight flap position Flap deflection Altitude loss l 10 30m 100 ft II 20 30m 100 ft III 35 30m 100 ft 0 0 30m 100 ft 5 5 Take off Distance up to 15m 50ft of Altitude engine Rotax 912 iS Runway surface Take off distance Asphalt 245m 800 ft Grass 265m 870 ft 5 6 Rate of Climb when speed of 110 km h 59 kt engine Rotax 912 iS Solo flight 7 5 m s 24 60 ft s 472 5 kg 6 0 m s 19 70 ft s 5 7 Cruising Speeds ROTAX 912 iS Speedu RPM Fuel consumption km h kt 1 min TP l h 120 65 3350 52 5 4 140 76 3700 62 7 0 160 86 4050 69 8 0 180 97 4330 73 9 4 200 108 4700 86 12 1 220 119 5100 92 14 7 240 130 5500 98 18 4 Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 29 of 53 5 8 Flight Range When maximum fuel capacity of 100 ROTAX 912 iS Speed Range of
13. EC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 19 of 53 INTENTIONALLY LEFT Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 20 of 53 Chapter 4 4 4 1 4 1 1 4 1 2 4 1 3 4 2 4 3 4 4 4 5 4 6 4 7 4 7 1 4 8 4 9 Standard Procedures Pre Flight Inspection Procedures Before Entering the Cockpit Procedures After Entering the Cockpit Procedures Before Engine Start up Engine Start up Engine Warm up Taxiing Engine Check Procedures Before Take off Take off and Climbing Cruising Flight Autopilot Descending and Landing Flight in Rainy Conditions Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 21 of 53 4 1 Pre Flight Inspection It is important to carry out the appropriate pre flight inspection To perform a negligent or incomplete inspection could be the cause of an accident The Manufacturer recommends to do the following procedure 4 1 1 Procedures Before Entering the Cockpit 1 Ignition switched off 2 Mainswitch switched off 3 Wings check surfaces condition ailerons and flaps free movement clearances hinges and connections of the controls security of wing pins Pitot tube 4 Tailsurfaces check surface condition elevator and rudder secure connections clearances and free movement 5 Fuselage check surface
14. III position II in case of strong turbulence or strong headwind Throttle idle or corrected if necessary Instruments within the permitted limits oD Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 25 of 53 Landing The speed of the aircraft in the hold up position decreases by soft pulling the control stick until touching down at the speed of 70km h 38kt After the touch down of the front wheel the landing distance can be shortened by braking Do not apply a maximum braking effect except an extreme situation A frequent brake use 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 the 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 canopy limited transparency 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 and II as by Art 2 2 Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 26 of 5
15. The Sole Manufacturer and Distributor in Czech Republic ATEC v o s Factory address ATEC v o s Opolansk 350 289 07 Libice nad Cidlinou Czech Republic ATEC 321 FAETA Flight and Operations Manual Libice nad Cidlinou March 2011 Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 1 of 53 Type of aircraft ATEC 321 FAETA Serialnumber i esse Registration callsign LAA CR Type Certificate ULL 04 2005 Date of issue 19 10 2005 The aircraft Sport Flying Device is not a subject of CAA authorisation and is to be operated at own risk of the user The aircraft must be operated according to informations and limits listed in this manual Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 2 of 53 Contents General Operational Limits Emergency Procedures Standard Procedures Performances Assembly Disassembly Aircraft Description and Systems Maintenance Enclosures 1 Log Book example 2 Records of Revisions 3 Service and Maintenance Book Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Chapter Page 3 of 53 Chapter 1 1 General 1 1 Introduction 1 2 Personal Data of the Owner 1 3 Aircraft Description 1 4 Modifications and Changes 1 5 Aircraft Technical Data 1 6 Three View Sketch Flight and
16. aft ATEC v o s Libice nad Cidlinou Czech Republic Page 8 of 53 1 6 Three View Sketch XVW OOLLS 0002 00472 Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 9 of 53 Chapter 2 2 Operational 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 Limitations 2 13 Labels and Markings Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 10 of 53 2 1 Introduction The Chapter 2 contains operational limits necessary for safe operation of the aircraft 2 2 Air Speed CAS Never exceed speed Max speed flaps deflected to 10 Max speed flaps deflected to Il 20 Max speed flaps deflected to III 35 Recommended speed flaps deflected to Ill Vee Stall speed in landing configuration 130km h 70 kt 120km h st 65 kt 110km h 59 kt 90 km h ist 49 kt Flying this speed with flaps deflected at the position III results in loss of lifting force and fall of the aircraft Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 11 of 53 2 3 Weight Empty weight ss kg Maximum take off weight f 450 _ kg Usefulload ss kg
17. aytime IFR flights instrument flights and flights by ice formation are prohibited 2 9 Crew Numberofseats O 2 Minimum weight of crew 60 kg Maximum weight of crew 180 kg 2 10 Fuel tank Fuelcapacity 2x50L Not usable rest of fuel _ _ 1 2 L Recommended motor unleaded petrol of minimum octane number RON 95 97 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 against wind up to 12 m s b take off or landing tail wind upto 3 m s c take off or landing cross wind ss upto 6m s Never operate the aircraft exceeding wind range limits determined Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 14 of 53 2 12 Other Limitations Smoking using of mobile phone explosives and combustible materials and movable objects transportation 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 the instrumental board in a visual field of pilot and must contain following information Identification of the aircraft e Identification label e Serial number e Designation e Empty weight e Maximum take off weight Operating limits e Weight limits depending on the weight of crew fuel and luggage e Speed limits for standard flight configurations Passenger Warnings e Definition
18. destination point the aircraft begins circling around such area After the required flight mode is adjusted the AP is activated and the AP ON sign on Integra screen is switched on The aircraft continues the flight according to selected flight mode Keep the engine RPM speed according to appropriate flight mode The AP is adjusted for minimum and maximum speed limits If the aircraft speed is getting close to limit values you will be announced by warning message requesting you to adjust the engine performance If you do not follow the warning request the AP will stop keeping adjusted altitude and start to keep the aircraft within the speed limits by descending or climbing AP deactivation Hold the control stick before the AP deactivation Deactivate the AP either by pressing the AP FN button then AP OFF button on Integra or by pressing deactivating button installed on the control stick The AP ON sign on Integra screen will switch off Note The general user set up of the AP functions is available in AUTOPILOT SETUP menu For more information check the Integra s appropriate manual 4 8 Descending and Landing Descending Carry out the descending with the throttle on idle run at the speed of 100km h 54kt Flaps position limits according to Art 2 2 Propeller into take off position Procedures on final Propeller into take off position in case of flight adjustable propeller Speed of 90km h 49kt Flaps position
19. e luggage compartment hydraulic disc brakes on the main gear USH 52 S SOFT PACK VMAX 293 km h e ee en nee ae kg 450 kg 472 5 kg 5 kg FITI desing s r o Revnice Czech Republic FITI ECO COMPETITION 2 blade 3 blade BOMBARDIER ROTAX GmbH Austria ROTAX 912 iS SPORT 73 5 kW 100 HP 5800 RPM 72 0 kW 98 HP 5500 RPM 44 6 kW 60 HP 4800 RPM 5800 RPM 5 minutes maximum 5500 RPM 4800 RPM 1400 RPM approximately 50 C 120 C 50 C 130 C 90 C 110 C 7 0 bar 0 8 bar engine speed below 3500 RPM 2 0 2 5 bar over 3500 RPM Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 7 of 53 Oil Type _ sy Any brand name oil intended for 4 stroke motorcycle engines containing gearbox additives API SF SG GL4 or GL5 AeroShell Sport Plus 4 10W 40 preferentially recommended Cooling Liquid conventional mix ratio 1 2 ROTAX 912 iS is not a certified aviation engine Any engine failure may occur at any time The pilot is fully responsible for the operation of this engine and accepts all risk and consequences of an engine failure The correct operation of this aircraft is the sole responsibility of the pilot The pilot of a sport flying device is obliged to consider the flight altitude and flight track so that he could be able to make safety landing in case of engine failure Flight and Operations Manual of ATEC 321 Faeta UL aircr
20. ease secure Flap Control Check free movement of flaps and control lever stable bearing in each flap position interlock pin wear Replace worn out parts grease secure Canopy Open Close Check condition and function of locks and hinges canopy bearing Adjust replace worn out parts grease secure Flight and Engine Instruments Check legibility markings mounting in the panel board air operated and electric installation wiring Electric Installations Check condition integrity and purity of cables insulations contacts and welds Battery attachment operating condition Safety Belts Check fixing points rigidity belt surface condition adjustment Fuel System Check leak proofness fuel supply pumps gauge and valve function tank ventilation and deterioration Replace fuel filters Parachute Rescue System Maintenance as by instructions of rescue system producer Visual check of general condition rocket lines attachment to bulkhead Landing Gear Main Gear Check attachment rigidity surface condition clearance degree of permanent deformation Wheels Check attachment brakes condition brake pads and disc condition braking system leak proofness Attachment and purity of wheel spats Front Gear Check general condition surface integrity rubber spring condition and deflection when loaded steering condition Grease sliding bearings replace rubber springs if worn ou
21. flight Flight endurance Fuel reserve 30 min km h kt km nm h l 140 76 1930 1043 13h 47 min 3 5 160 86 1920 1038 12h 0 min 4 180 97 1824 986 10h 8min 4 7 200 108 1553 840 7h 46 min 6 220 119 1385 749 6h 18min 7 4 240 130 1184 640 4h 55 min 9 2 Information on engine RPM consumption flight endurance and flight range are of informative character only These values depend on propeller type and adjustment flight altitude temperature air pressure and loading The flight range is considered as theoretic when windless conditions Consider these factors when planning your flight and figure on the safety flight reserve Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 30 of 53 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 UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 31 of 53 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 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 During each next assembl
22. he fuel flows back only into this tank If the left tank is filled up select first the left tank and then the right one The fuel can only return to the left tank 6 Throttle idle 7 Fuel gauge indicator fuel volume check 8 Propeller in take off position in case of flight adjustable propeller 9 Instruments on and within operating limits 10 Safety belts adjusted secured 11 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 is in neutral position Control the front wheel and the rudder as to keep the aircraft in the runway trajectory When reaching the speed of 75km h 45kt lift up the aircraft of the ground and continue the take off up to the speed of 110 km h 59kt Then gently pull the control stick to start climbing when optimum speed of 110km h 59kt After reaching the stable climbing speed of 110 120km h 59 65kt and over 50m 160ft of altitude retract the flaps fluently During the take off the engine operating limits must not be exceeded After reaching the flight level adjust the propeller into cruise position in case of flight adjustable propeller 4 7 Cruising Flight ATEC 321 FAETA has good flight characteristics in the whole range of permitted speeds and centre of gravity positions The cruising speed range is of 120 227km h 65 122kt 4 7 1 Integra Au
23. ill according to instructions of engine producer i Coolers Check integrity sealing purity 7 Controls Check control forces free play hinges end stops adjustment self x locking Adjust secure Exhaust piping Check integrity sealing surface condition corrosion degree springs condition and springs prestress Grease ball connections with a special s lubricant Carburettors Check surface condition controls adjustment condition of elastic i connection flange integrity sealing Replace flange if material degradations or surface cracks appear Electric Installations Check condition integrity and purity of cables insulation contacts 5 welds bunched cables attachments to airframe and bushings Check gauges and senders connections Propeller Attachment Check condition of bolts tightening moments securing E Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 40 of 53 10 25 50 100 200 Cockpit Control Sticks Check free movement in longitudinal and cross direction clearance fits end stops adjustment securing Replace pins or bolts if worn out grease secure Rudder Control Check integrity of pedals with a special focus on surface cracks near welds Full and free movement right and left raise nose wheel off ground end stops adjustment rudder cables tension clearance fits securing Adjust replace worn out parts gr
24. ing your needs for the appropriate tank use 6 Electric fuel pump gt on 7 Throttle gt idle Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 22 of 53 8 Main switch gt switch on 9 Propeller gt in take off position in case of flight adjustable propeller 10 EMS gt switch on wait for the display activation 11 LANE switch circuitA gt turn on 12 LANE switch circuit B turn on 13 EMS lights gt see engine user manual 14 Backup battery switch gt turn off 15 Start power switch turn on 16 Starter button gt push untill the engine runs 17 Start power switch turn off 18 Backup battery switch gt turn on 19 Increase RPM to cca 2000 min 20 Oil pressure check must be in operation range in 10 seconds continue in RPM increase by 3 bar 21 Continue in warm up engine according to article 4 2 Never unlock neither open the canopy after the engine start up 4 2 Engine Warm up Start to warm up the engine when 2000 RPM hold approx 2 minutes and then continue up to 2500 RPM until the oil temperature reaches 50 C Start taxiing right after engine s warm up to the operation temperature to prevent unsufficient cooling of the engine by staying at the place 4 3 Taxiing Recommended maximum speed of taxiing is 15km h 8kt The direction is controlled by the front wheel Braking is carried out with the brake lever on the left stic
25. k Control stick is on the neutral position in case of strong headwind push the control stick forward in case of crosswind keep the control stick position opposite to wind direction 4 4 Engine Check 1 Brakes on 2 Engine throttle engine speed of 4000 RPM 3 Switch off 1 ignition circuit engine speed after stabilizing must not drop bellow 300 RPM 4 Switch on both ignition circuits engine speed of 4000 RPM 5 Switch off 2 ignition circuit engine speed after stabilizing must not drop bellow 300 RPM Note The RPM speed difference between ignition circuits running separately must not be more than 120 RPM 6 Left and Right fuel tank check during engine run the fuel pressure must not drop bellow the allowed value in either of fuel tanks in use During the change over of fuel tank a short term pressure drop may occur but after the tank is selected the pressure must increase back to appropriate values Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 23 of 53 4 5 Procedures Before Take off 1 Brakes brake on 2 Foot operated steering free travel 3 Hand operated steering free travel 4 Flaps position 5 Fuel valve open select the appropriate left right position on the selector depending on fuel tank intended to use Note The left fuel tank is considered as the main one where the return circuit is installed so t
26. o both M8 main fitting screws and tighten them fully eSecuring the screws Secure these both screws M8 with a wire Appropriate holes are situated in the main fittings and four holes are in the screw head Secure the vertical nylon screw also with wire One hole is drilled in the horizontal tail body and two holes in the screw head Finally cover this hole with white sticker to avoid water inlet Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 32 of 53 eHT fittings covers assembly HT fittings covers help to avoid vibration occurence in flight Apply the HT fittings fiber glass covers obtained with double side tape according to following picture Horizontal tail disassembly Put away the fiber glass covers of HT fittings pay attention to not to dammage it needed for next assembly Release and unscrew M6 screw which adjusting the position of HT and is situated on the upper side of stabilizer Release and remove M8 screws of the main HT fittings Tilt the HT so that it is possible to disconnect the pin of HT control Remove the HT and put it into a safe place to prevent its damage Secure the ball bearing with a binding wire 6 3 Wings Assembly Disassembly At least two persons are needed for wings assembly disassembly Do not push on the wing surface during manipulation to avoid cracks on the gel coat especially in the area of material connections Lay wings
27. of aircraft category its airworthiness conditions and limitations e Intentional spins stalls and aerobatics prohibition Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 15 of 53 INTENTIONALLY LEFT Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 16 of 53 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 UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 17 of 53 3 1 Engine Failure on Take off 1 Push the stick forward to get the aircraft _to gliding flight 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 up to 50m 160ft of altitude get the aircraft into the landing configuration and make a landing in take off direction with respect to eventual obstructions B If higher than 50m 160ft of altitude choose a suitable area for emergency landing 3 2 Engine Failu
28. on a smooth soft pad e g mattress Wings assembly valid for the left as for the right wing eFlap pushrod preparation connection in wings Put the wing by its leading edge down on the soft pad Hold the wing with your assistant who deflect the flap to enable a better access to you Connect the flap pushrod with the flap lever installed inside the wing Pay attention to install the correct pushrod LEFT or RIGHT to appropriate wing Pay attention to correct pushrod position non adjustable end leads into the wing and the adjustable one into the fuselage see the sticker with letters L R on its upper side Fix the connection with the pin 5mm and spacer split pin all parts attached to the pushrod eAileron pushrod preparation connection in wings Screw the aileron pushrod to the adjustable end which extrudes from the wing Pay attention to install the correct pushrod LEFT or RIGHT to appropriate aileron Exact tuning will be adjusted later eWing Connection to the fuselage Prepare two of main wing pins lubricating them with an adequate quantity of vaseline Pay attention UPPER wing pin is WITHOUT scroll LOWER wing pin is WITH scroll Your assistant holds the wing at the wingtip and you at the root the third assistant which can hold the wing at the root s trailing edge is useful but not necessary Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 33 of 53 In
29. orks works as by Manufacturer bulletins reparations changes modifications replacements inspection reports or important notes must be recorded into following table Works performed reason Date mandatory inspection works bulletins reparations modifications Signature replacements inspection reports notes Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 49 of 53 Enclosure 3 page 2 4 Service and Maintenace Book Any mandatory inspection works works as by Manufacturer bulletins reparations changes modifications replacements inspection reports or important notes must be recorded into following table Works performed reason Date mandatory inspection works bulletins reparations modifications Signature replacements inspection reports notes Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 50 of 53 Enclosure 3 page 3 4 Service and Maintenace Book Any mandatory inspection works works as by Manufacturer bulletins reparations changes modifications replacements inspection reports or important notes must be recorded into following table Works performed reason Date mandatory inspection works bulletins reparations modifications Signat
30. pairs or changes a white tone colour must be kept on upper side surfaces 8 3 Engine Major Overhaul The major overhaul is carried out after 2000 flight hours but not later than 10 years after putting the aircraft into operation unless decided otherwise during regular technical inspections or by the Manufacturer bulletin The overhaul is performed by authorized or special workshop The overhaul and maintenance are carried out according to instructions of the engine producer 8 4 Anchorage of the Aircraft Anchorage of the aircraft is necessary in order to avoid eventual damage caused by wind or wind blasts during parking outside the hangar For this purpose the aircraft is equipped with screw mounting points for eyelets on the underside of the wingtips 8 5 Cleaning and Care The aircraft surface should always be treated with suitable cleaning agents Oil and grease remnants can be removed from the aircraft surface by suitable surface active substances or alcohol The canopy should be only cleaned with a sufficient lukewarm water flow with addition of suitable surface active substances Never use petrol or chemical solvents Do not use water jet stream for airframe cleaning and avoid water inlet into Pitot static system engine compartment ventilation and other airframe open spaces Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 42 of 53 Chapter 9 9 Weight and Balance
31. pit 7 3 Tail Surface The T shaped tail surface construction consists of tapered vertical and horizontal tail with fix stabilizer and elevator The elevator trim can be mechanical or electrical The tail fin is an integral part of fuselage The rudder suspended to the last fuselage bulkhead is made of fiber glass 7 4 The Landing Gear The landing gear is a fixed tricycle undercarriage with a steerable front wheel main gear is constructed as a pair of leaf springs of composites The front leg is made of composites and metal tube suspended with rubber spring The main gear is a pair of composite springs Electronic main wheels size is 350x120 mm front wheel size is 300x100 mm The main wheels are equipped with hydraulic disc brakes Fairings are installed on all wheels 7 5 Steering The steering of all control surfaces is duplicated The ailerons flaps and elevator are controlled by control rods and levers the rudder is controlled by steel wire ropes Lift flaps are optionally equipped with electrical control All control attachments are situated as to not interfere with the airframe contour The important checking points in wings are equipped with inspection holes with perspex covers 7 6 Drive Unit The standard option of the drive unit is ROTAX 912 iS engine and three or two blade FITI ECO COMPETITION propeller which can be fix ground adjustable or adjustable in flight Flight and Operations Manual of ATEC 321 Faeta UL aircraft
32. re 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 engine or installation failure found try to start up the engine again using back up fuel circuit 4 If engine start up is not possible follow the instructions as described in Art 3 1 3 3 Rescue System Activation In case of distress when definitely losing control of flight activate the rescue system 1 Switch off the ignition 2 Adjust safety belts 3 Activate the rescue system In case of landing on a limited area when collision with an obstacle is inevitable use the rescue system as a braking device of the aircraft The aircraft can be damaged or the crew may be injured when using a rescue system 3 4 Fire on Board 1 Close the fuel valve 2 Open the throttle 3 Switch off the main switch and ignition 4 Make emergency landing 5 Get off the aircraft 3 5 Engine Loss 1 Speed hee 100 km h 54 kt 2 Flaps retracted 3 Instruments within tolerated values Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 18 of 53 3 6 Emergency Landing Carried out in case of engine failure 1 2 3 4 5 6 7 In case of emergency landing on terrain on areas which are not authorized to take off landing of raana 100 km h 54 kt Adjust safety belts Flaps according to
33. rom main wheel axis ss Xmw ce G2 xmw rw G Lengthof MAC bmac 1 112 Length of wing chord in the root area b 1 300 Back swept MAC displacement sss sy 0 19 Distance from CG to leading edge ss XcG XMW LE XMW CG Distance from CG to leading edge of MAC XCG MAC XMW LE XMW CG Sy 0 57 1 44 G G Xce mac Xce mac 100 1 112 ATEC 321 FAETA W B CHART AA 0 524 bwc 1 112 Sy 0 188 DATUM PLANE L 27 0 300 Fec 0 488 B 36 0 400 ACG 0 588 0 76 FUSELAGE Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic 51 26 129 5 G2 G Page 45 of 53 kg kg kg m m m m m m m m 9 6 Useful load weight sheet Useful load is the weight difference between the maximum take off weight and the empty weight determined by weighing When the aircraft empty weightisof ss kg the useful load iS kg Aircraft weight and centre of gravity sheet fuel tanks of 2 x 50 L take off weight of sss kg Fuel amount L Crew weight Load in luggage Centre of gravity Total aircraft 1L 0 775 kg kg compartment kg MAC weight kg 0 MAX 5 450 0 0 MAX 0 450 0 wm 25 MAX 5 450 0 Vea 50 MAX 5 450 0 75 MAX 5 450 0 1 100 MAX 5 450 0 If above listed limits
34. sert the wing into the fuselage partially that those two pushrods aileron and flap enter the fuselage through corresponding holes Support the wing by your knees and connect the rest of 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 coupling of fuel hoses from fuel tanks connector of fuel gauges cable connector of strobes position lights cable if equipped with Finish inserting of the wing into the fuselage and apply the main pins Start with upper pin without scroll and then the bottom pin with scroll This operation requires careful using of the hammer through the metal rod 18mm The assistant at the wing tip pays attention to the correct dihedral angle Both pins must be inserted to their fully beaten position Secure the pins with the bolt from upper side tightening moment is approx 25 Nm Apply the locking nut M10 from the bottom side then the wing connection is secured completely Finally cover the holes with white sticker to avoid water inlet eFlaps pushrods connection in the cockpit Take the seats out of the cockpit as to be the flap lever in the central tunnel accessible Realize the connection with the pin 5 and spacer split pin all parts attached to the pushrod There is a permitted exception to insert the pin 5 from the bottom side for better accessibility by assembling
35. situation Report the situation by the radio Close the fuel valve Turn off the ignition Turn off the main switch sport flying devices the aircraft can be damaged or the crew may be injured 3 7 Safety Landing Carried out in case of orientation loss fuel exhaustion or another reason when the aircraft is fully controllable 1 Determine the wind direction 2 Choose a suitable landing area 3 Make a low pass into the wind along the right hand side of landing area and inspect the terrain thoroughly 4 Make a pattern flight Calculate the landing plan 6 Land in the first third of the landing area using flaps landing position or 3 8 Aborted Landing Carried out in case of wrong calculation of landing manoeuvre or bounce when landing and the pilot considers aborted landing manoeuvre as more safety and decides to continue the flight Set up engine speed on maximum power Set up take off flaps position Get to level speed of 110 km h 59 kt Draw up control stick slowly to get aircraft into climbing by speed 110 120 km h 59 65 kt Retract flaps 2 E Throughout the flight maintain the aircraft in take off trajectory using rudder control 3 9 Vibrations In case of unusual vibrations occur it is necessary to 1 Set the engine speed to appropriate run on which the vibrations are the lowest 2 Carry out the safety landing eventually find the nearest aerodrome to land Flight and Operations Manual of AT
36. t Fuselage Check general condition integrity purity Antennas lights covers and cowlings attachment Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 41 of 53 10 25 50 100 200 Wings Check general condition surface condition integrity attachment fittings bolts clearance Ailerons and flaps condition surface condition x hinges clearance securing Controls condition free movement end positions clearance Pitot tube condition and attachment Tail Surfaces Rudder Elevator Check general condition hinges movement clearance securing HT Stabilizer Check general condition attachment fittings securing 8 2 Aircraft Repairs Each damage which may have an influence on airframe strength or flight characteristics must be reported to the Manufacturer The Manufacturer determines a way of repair Minor repairs mean the repairs of those parts which substantially do not take a part in the aircraft function and stiffness Among permitted repairs are paint repairs e worn out parts replacement repairs of wheel tyres Above mentioned minor repairs can be carried out by the owner himself Repairs of torsion box spars wings and tail surfaces landing gear and fuselage load bearing structure must be carried out by authorized or any special workshop If any surface re
37. t picture and description of concrete cockpit Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 38 of 53 Chapter 8 8 Care and Maintenance 8 1 Maintenance Schedule 8 2 Aircraft Repairs 8 3 Engine Major Overhaul 8 4 Anchorage of the Aircraft 8 5 Cleaning and Care Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 39 of 53 8 1 Maintenance Schedule Inspection Mandatory Work Inspection Period hours 10 25 50 100 200 Engine As per ROTAX Manual attached Engine Compartment Engine Bed Check integrity of construction with a special focus on welds fixing x points silent blocks bushings Check surface condition Bolted Connections Check surface condition of bolted connections bearing surfaces Check securing and tightening Tighten and re secure if necessary Replace locking nuts split pins and securing wires Silentblocks Check elasticity of engine bearing integrity of rubber blocks degree of permanent deformation Replace silent blocks if necessary tighten i secure Oil Water and Fuel Hoses Check surface integrity liquid leak proofness condition of connections protection avoiding touch with oscillating parts and exhaust system Replace if necessary Working Liquids Check level ref
38. topilot optional The Autopilot AP is two axis device controlled by EFIS TL 6524 Integra If the AP is not active the electromagnetic connector of servo units is disconnected and the AP installation does not influence the steering system of the aircraft The AP system is intended to keep requested track and altitude Activate the AP after the take off when reaching minimum 1000 ft altitude For landing deactivate the AP before entering aerodrome traffic circuit Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 24 of 53 AP activation instructions 1 Balance the aircraft into horizontal direct flight by trimming 2 Push the AP button on Integra 3 To select the type of controlled axis push the appropriate button BOTH ROLL PITCH 4 Select requested flight mode STABILIZATION the aircraft will continue the same tracking and altitude since the moment of the AP activation BUGS the aircraft will continue the tracking and altitude adjusted with BUGS The tracking and altitude bugs are adjusted by the left button on Integra NAV the aircraft will follow the track adjusted on GPS and will keep the same altitude since the moment of AP activation The altitude is possible to change by adjusting the bug by the left button on Integra For the flight in NAV mode it is needed that GPS communicate with Integra and the tracking is active When reaching the
39. ure replacements inspection reports notes Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 51 of 53 Enclosure 3 page 4 4 Service and Maintenace Book Any mandatory inspection works works as by Manufacturer bulletins reparations changes modifications replacements inspection reports or important notes must be recorded into following table Works performed reason Date mandatory inspection works bulletins reparations modifications Signature replacements inspection reports notes Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 52 of 53 Issued by the Manufacturer Atec V O S Opolanska 301 289 07 Libice nad Cidlinou Czech Republic www atecaircraft eu Flight and Operations Manual of ATEC 321 Faeta UL aircraft ATEC v o s Libice nad Cidlinou Czech Republic Page 53 of 53
40. y it is necessary to replace locking nuts and split pins with new pieces After aircraft assembly carry out deflections adjustment by levelling record and engine run test with a focus on both fuel tanks function and check fuel indicators correct function 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 for better access to HT Pay attention during the manipulation avoid a fall of small parts into the tail fin inner space during manipulation Horizontal tail assembly eElevator pushrod connection Deflect the control stick into the pushed position and secure softly for better accessibility of elevator pushrod Put the elevator on the appropriate place on the fuselage tail over the rudder Your assistant holds the horizontal tail in upward position for better access to pushrod over the rudder keeping stabilizer deflected maximally in up position Connect the pushrod with the elevator by the pin of 5mm and spacer split pin Connect the cable connector of servo if electrical trim option eFixing the horizontal tail to the fuselage Put the horizontal tail on the fuselage and fix it with two M8 main fitting screws Do not fully tighten it yet Insert the vertical screw M6 with nylon into the hole on the upper side of horizontal tail and tighten it fully with adequate power Come back t
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