Atec 212 SOLO Flight Manual Download

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Driving Unit

Propeller manufacturer ………………... Josef Faturik
Type of propeller ………………

FITI ECO COMPETITION 2 blade, 3-blade

Engine manufacturer …………………… Bombardier – ROTAX GmbH
Type of engine

…………………… ROTAX 582 UL DCDI 2V 65 HP

Power
Take-off power

…………………… 48 kW / 65 HP / 6500 RPM

Maximum continuous power …………… RPM
Cruising power

…………………… RPM

Engine Speed
Maximum take-off engine speed

….… 6800 RPM / 5 minutes maximum

Max. continuous engine speed

……. 6500 RPM

Cruising engine speed

……. 5000 RPM

Idling

……. 2000 RPM approximately

Engine Cylinders Temperature
Maximum

……………………………. 150°C

Operational

……………………………. 110 - 130°C

Cooling Liquid Temperature
Maximum

……………………………. 80°C

Minimum

……………………………. 65°C

Fuel Pressure
Maximum

……………………………. 0,4 bar

Minimum

……………………………. 0,2 bar

Operational Temperature
Maximum

……………………………. 50°C

Minimum

……………………………. -25°C

Fuel Type

……………………………. See Art. 2.9.

Oil Type
1.

Engine lubrication, rotary slide valve lubrication – motor oil for high loaded two stroke
engines of API-TC class (CASTROL TTS equivalent). Oil / Fuel mixture 1: 50 (2%).

Gearbox lubrication – gearboxes oil of API-GL5 or API-GL6, SAE 140 EP or 85W – 140
EP.

ROTAX 582 UL DCDI 2V is not certificate as an aircraft engine and a failure may

occur whenever. The pilot is fully responsible for consequence of engine failure

Summary of Contents for 212 SOLO

Page 1: ...istributor in the Czech Republic ATEC v o s Location of factory ATEC v o s Opolanská 350 289 07 Libice nad Cidlinou Czech Republic ATEC 212 SOLO ROTAX 582 UL DCDI 2V Flight and Operations Manual Libice nad Cidlinou January 2007 ...

Page 2: ...raft is not registered at the state office and is to be operated at operator s own responsibility The aeroplane must be operated according to the information and limits of this flight manual This manual must ever be on the board of aeroplane This manual must at all times be carried on board of the aircraft ...

Page 3: ...s Chapter General 1 Operational Limits 2 Emergency Instructions 3 Standard Procedures 4 Specifications 5 Assembly Disassembly 6 Description of Aircraft and its Systems 7 Maintenance 8 Weight Centre of Gravity 9 ...

Page 4: ...4 Chapter 1 1 General 1 1 Introduction 1 2 Personal Data of the Owner 1 3 Description of the Aeroplane 1 4 Completing of the Manual Changes 1 5 Specification 1 6 Three View Sketch ...

Page 5: ...ration of the ATEC 212 SOLO aircraft Also included are information and documents of importance from the manufacturer 1 2 Personal data of the owner Owner of aircraft Address Telephone No Date from to Owner of aircraft Address Telephone No Date from to Owner of aircraft Address Telephone No Date from to ...

Page 6: ...ion Dimensions Wing span 7 48 m Length of fuselage 5 2 m Total height 1 4 m Wing area 7 27 m2 Depth of mean aerodynamic chord 1 032 m Span of horizontal tail surface 2 18 m Flap position I 10 II 20 III 35 Airfoil Section Root section SM 701 End section SM 701 Tail Wheel Landing Gear Wheel spacing 1 56 m Wheel base 3 66 m Tyre dimensions 350 120 Tyre pressure 0 12 MPa 1 2 atp Springing system Main ...

Page 7: ...y Engine Cylinders Temperature Maximum 150 C Operational 110 130 C Cooling Liquid Temperature Maximum 80 C Minimum 65 C Fuel Pressure Maximum 0 4 bar Minimum 0 2 bar Operational Temperature Maximum 50 C Minimum 25 C Fuel Type See Art 2 9 Oil Type 1 Engine lubrication rotary slide valve lubrication motor oil for high loaded two stroke engines of API TC class CASTROL TTS equivalent Oil Fuel mixture ...

Page 8: ...8 1 6 Three View Sketch ...

Page 9: ...troduction 2 2 Air Speeds 2 3 Weights 2 4 Centre of Gravity 2 5 Manoeuvre and Gust Envelope 2 6 Permitted Manoeuvres 2 7 Operational Load Factors 2 8 Type of Operation 2 9 Crew 2 10 Fuel 2 11 Wind 2 12 Other Limits 2 13 Placards and Markings ...

Page 10: ... only Maximum cruising speed at severe turbulence vRA 200 km h 108 kt Never exceed this speed at severe turbulence Maximum speed at flaps deflection 10 vFI 140 km h 75 kt Maximum speed at flaps deflection 20 vFII 130 km h 70 kt Maximum speed at full deflection 35 vFE 120 km h 65 kt Maximum recommended speed at def 35 vFIII 100 km h 55 kt Do not exceed this speed by flaps deflected Stalling speed f...

Page 11: ...ghts Empty weight kg Maximum take off weight 300 315 kg Useful load kg Never exceed the maximum take off weight of the aeroplane 2 4 Centre of Gravity CG CG of the empty aeroplane MAC Flight range of CG 28 36 MAC ...

Page 12: ...12 2 5 Manoeuvre and Gust Envelope ...

Page 13: ...in CG 6 0 g Maximum negative load factor in CG 4 0 g 2 8 Type of operation Permitted day flights VFR only flights by unobstructed field of vision IFR flights instrument flights and flights by ice formation are prohibited 2 9 Crew Number of seats 1 Minimum weight of crew 65 kg see Art 9 4 Maximum weight of crew 90 kg see Art 9 4 2 10 Fuel Recommended motor unleaded petrol of minimum octane number R...

Page 14: ... and free loaded objects is prohibited 2 13 Placards and Markings The aircraft shall be equipped with mandatory placards placed on instrument panel containing following information Identification of aircraft Identification label Serial number Designation Empty weight Maximum take off weight Operating limitations Weight limits depending on weight of crew fuel and luggage Speed limits for standard f...

Page 15: ...ency Instructions 3 1 Engine Failure Taking Off 3 2 Engine Failure in Flight 3 3 Rescue System Application 3 4 Fire in Flight 3 5 Power Off Flight 3 6 Emergency Landing 3 7 Safety Landing 3 8 Aborted landing 3 9 Vibration ...

Page 16: ...h 54 kt 2 Check a fuel level switch on and make sure ignition is switched on 3 If no problem found try restarting the engine once more using additional fuel system 4 If restarting impossible use the instructions 3 1 3 3 Rescue system deployment In distress by final loss of flight control do activate the rescue system 1 Switch off ignition 2 Adjust safety belts 3 Activate the rescue system In case ...

Page 17: ...and side of landing area and inspect the area thoroughly 4 Carry out a circuit flight 5 Calculate the landing plan 6 Land in the first third of the landing area using landing flaps 3 8 Aborted landing Carry out in case of wrong calculation of landing manoeuvre or after jump out by landing in case of pilot s consideration to abort landing manoeuvre and continue to fly 1 Set up engine speed on maxim...

Page 18: ...ering the Cockpit 4 1 2 Procedures After Entering the Cockpit 4 2 Procedures Before Starting the Engine and Starting the Engine 4 3 Warming up the Engine Engine Check 4 4 Taxiing 4 5 Pre Take Off 4 6 Take Off and Climb Away 4 7 Cruising Flight 4 8 Descend and Landing 4 9 Flight in the Rain ...

Page 19: ...ine the state of fastening of the engine covers the state of the engine bed intact fuel oil and cooling system hoses the fuel system drain 8 Propeller the surface state if it is intact the state and fastening of the propeller cone 9 Canopy control of fastening and proper locking of the canopy correct functioning and condition of the electrical installation of instruments the state of the flight in...

Page 20: ...ntinue until 3000 rpm till the oil temperature reaches 65o C Check both ignition circuits according to the engine operational manual 4 4 Taxiing Recommended speed of taxiing is 15 km h 8 kt max direction is controlled by the tail wheel using pedals Hand brake control is on the control stick Control stick pulled up 4 5 Pre Take Off Compulsory procedures prior take off 1 Brakes checked 2 Foot operat...

Page 21: ...of permitted speeds and centre of gravity positions The cruising speed is in the range 120 243 km h 65 131 kt 4 9 Descent and landing Carry out the descent with the throttle in idle run at speed of 100 km h 54 kt Flaps position limitations according to Art 2 2 Procedures in the final 1 Speed 90 km h 49 kt 2 Wing flaps in position III at strong turbulence or headwind position II 3 Throttle idle or ...

Page 22: ...sibility and cockpit transparency Furthermore one should take into account a shortened hold up position during the landing and extended take off distance Maintain the following speeds during the flight in the rain 1 Climb away 140 km h 75 kt 2 Cruising flight 120 200 km h 65 108 kt 3 Descent at landing 100 km h 54 kt flaps I or II see Art 2 2 ...

Page 23: ...23 Chapter 5 5 Performances 5 1 Introduction 5 2 Stalling Speeds 5 3 Take off Distance at 15 m 50 ft Height 5 4 Rate of Climb 5 5 Cruising Speeds 5 6 Range of Flight ...

Page 24: ...b Air speed Rate of climb 120 km h 65 kt 5 5 m s 1080 FPM 140 km h 75 kt 5 m s 980 FPM 5 5 Cruising Speeds ROTAX 582 UL DCDI 2V Air speed RPM Fuel consumption 120 km h 64 8 kt 4300 6 5 l h 1 72 USGPH 140 km h 75 6 kt 4750 8 l h 2 11 USGPH 160 km h 86 4 kt 5150 10 l h 2 64 USGPH 180 km h 97 2 kt 5700 12 5 l h 3 30 USGPH 200 km h 108 kt 6000 15 7 l h 4 15 USGPH 220 km h 119 kt 6400 20 l h 5 28 USGPH...

Page 25: ...25 Chapter 6 6 Assembly and Dismantling 6 1 Introduction 6 2 Dismantling the Horizontal Tail Surface and the Rudder 6 3 Dismantling the Wings 6 4 Assembly ...

Page 26: ...and remove the lock nut of the M10 bolt of the wing pins Screw the bolt off by about 20 mm The helper lifts the wing a bit by holding it at the end By light taps on the head of the bolt the bottom pin is knocked out Unscrew the bolt and remove the pin Then the upper pin is driven out with the help of a rod with 18 mm diameter After removed pins lift up the wing and disconnect the hoses of the stat...

Page 27: ...iption of the Aeroplane and Its Systems 7 1 Wing 7 2 Fuselage 7 3 Tail Surfaces 7 4 The Landing Gear 7 5 Control 7 6 The Driving Unit 7 7 Fuel System 7 8 Instrument Equipment 7 9 The Sense of Motion of the Control Elements ...

Page 28: ...l Surfaces The conventional tail surfaces are of all carbon composite construction The horizontal tail surface has a trapezoidal shape formed by a rigid stabiliser and elevator The vertical tail surface and the rudder have a trapezoidal shape The tail unit is an integral part of the fuselage 7 4 The Landing Gear The landing gear is a fixed two wheel undercarriage with a controllable tail wheel The...

Page 29: ...ft pedal the aeroplane turns left when mowing at sufficient speed on the ground or in the air and vice versa Hand operated control By pulling the control stick towards the pilot the nose lifts up the angle of incidence increases and the aeroplane climbs By pushing the control stick the aeroplane descends By deflecting the control stick to left the aeroplane banks to left and vice versa Wing flaps ...

Page 30: ...30 Chapter 8 8 Care and Maintenance 8 1 Maintenance Schedule 8 2 Aeroplane Repairs 8 3 Major Overhaul 8 4 Anchorage of the Aeroplane 8 5 Cleaning and Care ...

Page 31: ...keeping instruction of engine manufacturer x Coolers Check integrity sealing purity x Controls Check control forces free play hinges end stops adjustment self locking Adjust secure x Exhausts Check integrity sealing corrosion degree springs quality and prestress Grease ball connections x Carburetors Check surface quality controls adjustment quality of elastic connection flange integrity sealing Re...

Page 32: ... x Parachute Rescue System Check general condition attachment Do mandatory work as per instructions of rescue system manufacturer x Landing Gears Main Gear Check attachment rigidity surface quality degree of permanent deformation x Wheels Check attachment brakes condition brake pads disc quality leak proof condition Attachment and purity of wheel spats x Front Gear Check general condition integrit...

Page 33: ...years after putting the aeroplane into operation unless decided otherwise during regular technical inspections or by the company bulletin The overhaul will be carried out in a special workshop The overhaul and maintenance are carried out according to the instructions of the engine producer 8 4 Anchorage of the Aeroplane The anchorage of the aeroplane is necessary in order to protect the aeroplane ...

Page 34: ...34 Chapter 9 9 Weight Centre of Gravity 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 ...

Page 35: ...f all wheels weights The empty weight of the ATEC 212 SOLO including ROTAX 582 DCDI 2V and standard equipment with without rescue system is kg 9 3 Maximum take off weight 300 315 kg Never exceed the maximum take off weight 9 4 Centre of gravity range The aircraft CG including the pilot of kg without fuel is of MAC The flight range of CG specified by manufacturer is 28 36 of MAC Operation over this...

Page 36: ...wing chord in the root area b 1 19 m Back swept MAC displacement sy 0 158 m CG distance from leading edge of wing in root point xLE CG xMW LE xMW CG 0 19 G2 3 7 G m Distance from CG to leading edge of MAC xCG MAC xLE CG sy 0 032 3 7 G2 G m xCG MAC xCG MAC 100 1 032 3 1 358 5 G2 G 9 6 Useful weight weight table Useful weight is a difference between maximum take off weight and the weight of empty ai...

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