Inhaltszusammenfassung zur Seite Nr. 1
Sole Manufacturer and Distributor 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 912 UL
Flight and Operations Manual
Libice nad Cidlinou January 2007
1
Inhaltszusammenfassung zur Seite Nr. 2
Type of aeroplane ATEC 212 SOLO Serial number …………………………………………………… Identification label …………………………………………………… LAA CR type licence …………………… issued …………………… This aircraft 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 manua
Inhaltszusammenfassung zur Seite Nr. 3
Contents 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 3
Inhaltszusammenfassung zur Seite Nr. 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 4
Inhaltszusammenfassung zur Seite Nr. 5
1.1. Introduction The information provided by this manual is necessary for an effective and save operation 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:
Inhaltszusammenfassung zur Seite Nr. 6
1.3. Description of the Aeroplane ATEC 212 SOLO is an ultralight single-seater cantilever low-wing aircraft of an all carbon composite construction. It is equipped with a tail landing gear with the steerable tail wheel. The power plant is a pull arrangement and consists of a ROTAX 912 UL 80 HP engine and a two-blade or three-blade fix or ground adjustable propeller FITI. 1.4. Specification Dimensions Wing span ……………………………………. 7,48 m Length of fuselage ……………………………. 5,2 m Tot
Inhaltszusammenfassung zur Seite Nr. 7
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 912 UL 80 HP Power Take-off power …………………… 59,6 kW / 80 HP / 5800 RPM Maximum continuous power …………… 58 kW / 78 HP / 5500 RPM Cruising power …………………… 37,7 kW / 51 HP / 4800 RPM Engine Speed Maximum take-off engine speed ….… 5800 RPM / 5 minutes maximum M
Inhaltszusammenfassung zur Seite Nr. 8
1.6. Three-View Sketch 8
Inhaltszusammenfassung zur Seite Nr. 9
Chapter 2 2. Operational Limits 2.1. Introduction 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 9
Inhaltszusammenfassung zur Seite Nr. 10
2.1. Introduction The chapter 2 contents are operational limits necessary for a save operation of the aircraft 2.2. Air Speeds Never exceed speed v ….. 286 km/h ….. 154 kt NE Do not exceed this speed in any case Design manoeuvre speed v …… 187 km/h ….. 101 kt A Do not use full deflection of the rudders and sudden control operations. Overload of the aircraft may occur Maximum design cruising speed v …… 238 km/h ….. 128 kt C Operation over this speed must be conducted wi
Inhaltszusammenfassung zur Seite Nr. 11
2.4. Centre of Gravity ( CG ) CG of the empty aeroplane ………………… % MAC Flight range of CG ………………………… 28 – 36% MAC 11
Inhaltszusammenfassung zur Seite Nr. 12
2.5. Manoeuvre and Gust Envelope 12
Inhaltszusammenfassung zur Seite Nr. 13
2.6. Permitted Manoeuvres Category of the aeroplane: Normal o Except of the normal flight manoeuvres, the sharp turns up to bank of 60 , level and climbing turns are permitted. Acrobatics, intended spins and stalls are prohibited 2.7. Operational Load Factors Maximum positive load factor 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 ( ins
Inhaltszusammenfassung zur Seite Nr. 14
2.11. Wind The safe taking off and landing is possible if the following wind speed limits are not exceeded: a) taking off or landing against wind ………. up to 12 m/s b) taking off or landing tail wind ………. up to 3 m/s c) taking off or landing cross wind ………. up to 3 m/s 2.12. Other limits Smoking and using of mobile telephones is prohibited in the aircraft. Transportation of explosives and free loaded objects is prohibited.
Inhaltszusammenfassung zur Seite Nr. 15
Chapter 3 3. Emergency 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 15
Inhaltszusammenfassung zur Seite Nr. 16
3.1. Engine Failure on Take-Off 1. Push stick forward aircraft into gliding attitude and maintain airspeed of 100 km/h (54 kt). 2. Determine the wind direction, adjust flaps for suitable position, turn off fuel valve, switch-off ignition, adjust safety belts and switch-off the master switch just before landing. A. At a height up to 50 m get the aircraft into landing configuration and carry out a landing with respect for obstructions in take-off direction. B. At a height above 50
Inhaltszusammenfassung zur Seite Nr. 17
3.6. Emergency landing 1. Carried out in case of engine failure 2. Speed ……………………. 100 km/h ….. 54 kt 3. Adjust safety belts 4. Flaps according to situation 5. Announce the situation by the aeroplane radio station 6. Close the fuel valve 7. Turn off ignition 8. Turn off the main switch In case of emergency landing onto a terrain and surfaces non-approved for light aircraft landings an aircraft damage and crew injury may occur 3.7. Precautionary landing Carry out in
Inhaltszusammenfassung zur Seite Nr. 18
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 4.2 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 18
Inhaltszusammenfassung zur Seite Nr. 19
4.1. Pre-Flight Inspection It is important to carry out a proper pre-flight inspection failure to do so or perform an incomplete inspection could be the cause of an accident. The manufacturer recommends using the following procedure: 4.1.1. Procedures Before Entering the Cockpit 1. Check ignition - turned off. 2. Check main switch – turned off 3. Check the wings, wing surfaces ailerons and flaps, clearances, hinges and connections of the controls, security of the wing pins, Pit
Inhaltszusammenfassung zur Seite Nr. 20
5. Throttle to idle run 6. Open the choke if the engine is cold 7. Pull up the control stick 8. Main switch on 9. Ignition on 10. Brakes on 11. Start the engine 12. Turn off the choke 13. Warm up the engine until the operating temperature 4.3. Warming up the Engine Start to warm up the engine at 2000 rpm, hold approx. 2 minutes, continue until 2500 rpm till o the oil temperature reaches 50 C. Check both ignition circuits according to Art. 4.5. 4.4. Taxiing Recommended
