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Atec 212 SOLO Flight Manual

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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 582 UL DCDI 2V
Flight and Operations Manual
Libice nad Cidlinou January 2007
1

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Summary of Contents for Atec 212 SOLO

  • Page 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 582 UL DCDI 2V Flight and Operations Manual Libice nad Cidlinou January 2007...
  • Page 2 ATEC 212 SOLO Type of aeroplane 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.

  • Page 3: Table Of Contents

    Contents Chapter General ……………………………………. Operational Limits …………………………… Emergency Instructions ……………………… Standard Procedures ……………………… Specifications …………………………… Assembly, Disassembly ……………………… Description of Aircraft and its Systems …… Maintenance …………………………… Weight, Centre of Gravity …………………..

  • Page 4: General

    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 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:...
  • Page 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 582 UL DCDI 2V 65 HP engine and a two-blade or three-blade ground adjustable propeller FITI.
  • Page 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 582 UL DCDI 2V 65 HP Power Take-off power …………………… 48 kW / 65 HP / 6500 RPM Maximum continuous power ……………...
  • Page 8 1.6. Three-View Sketch...

  • Page 9: Operational Limits

    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 2.13.
  • Page 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 … 286 km/h 154 kt Do not exceed this speed in any case Design manoeuvre speed … 187 km/h 101 kt Do not use full deflection of the rudders and sudden control operations.
  • Page 11 2.3. Weights Empty weight …………………………………. Maximum take-off weight …………………. Useful load …………………………………. 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 …………………………...
  • Page 12 2.5. Manoeuvre and Gust Envelope...
  • Page 13 2.6. Permitted Manoeuvres Category of the aeroplane: Normal 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 ………...
  • Page 14 2.11. Wind The safe taking off and landing is possible if the following wind speed limits are not exceeded: taking off or landing against wind ………. up to 12 m/s taking off or landing tail wind ………. up to 3 m/s taking off or landing cross wind ……….

  • Page 15: Emergency Instructions

    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...
  • Page 16 3.1. Engine Failure on Take-Off Push stick forward aircraft into gliding attitude and maintain airspeed of 100 km/h (54 kt). 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.
  • Page 17 3.6. Emergency landing Carried out in case of engine failure Speed ……………………. 100 km/h ….. 54 kt Adjust safety belts Flaps according to situation Announce the situation by the aeroplane radio station Close the fuel valve Turn off ignition 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.

  • Page 18: Standard Procedures

    Chapter 4 4. Standard Procedures Pre-Flight Inspection 4.1.1 Procedures Before Entering the Cockpit 4.1.2 Procedures After Entering the Cockpit Procedures Before Starting the Engine and Starting the Engine Warming up the Engine, Engine Check Taxiing Pre Take-Off Take-Off and Climb Away Cruising Flight Descend and Landing Flight in the Rain...
  • Page 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 Check ignition - turned off.
  • Page 20 4.2. Procedures Before Starting the Engine and Starting the Engine Rescue system - unlock Safety belts - fasten Close the canopy and secure Turn on the fuel valve Throttle to idle run Open the choke if the engine is cold Pull up the control stick Main switch on Ignition on...
  • Page 21 4.8. Cruising flight ATEC 212 SOLO has good flight features in the whole range of permitted speeds and centre of gravity positions. The cruising speed is in the range 120 – 243 km/h …… 65 – 131 kt. 4.9.
  • Page 22 4.10. Flight in the rain During the flight in the rain, the pilotage should be carried out with increased caution because of the decreased visibility 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: Climb away 140 km/h...
  • Page 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 5.1. Introduction The information in stalling speed and other performances of the ATEC 212 SOLO with ROTAX 582 UL DCDI 2V 65 HP and propeller FITI ECO COMPETITION 2b/160. 5.2. Stalling Speeds Engine idling Flaps retracted Flaps I (10°) Flaps II (20°) Flaps III (35°)
  • Page 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 6.1. Introduction The assembly of individual parts of the aeroplane is described in this chapter. At least two persons are necessary for the assembly and dismantling. 6.2. Dismantling the Horizontal and Vertical Rudder The HT and VT stabilizers are an integral part of the fuselage Dismantling VT rudder.
  • Page 27 Chapter 7 7. Description 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 7.1. Wing The cantilever tapered wing with conventional ailerons, slotted flaps and wing-tips. The main spar of laminated beech wood is in the 30% depth of wing. The wing skin is made of carbon sandwich. The wing is reinforced by ribs of plastic and composites, the root ribs are of carbon –...
  • Page 29 7.7. Fuel System The fuel system is formed by an integral fuselage tank with a fuel drain. Double fuel supply circuit with a spare electric pump. The pressure of supplied fuel is measured with a fuel- pressure gauge. The fuel reserve 10 l at flight position is indicated by control light. 7.8.

  • Page 30: Maintenance

    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 8.1. Maintenance Schedule Inspection, Mandatory Work Inspection Period 10 25 50 100 200 Engine As per Manual attached. Engine Compartment Engine Attachment Check integrity of construction with special care for welds, fixing points, silent blocks, bushings. Surface finish quality. Bolted Connections Check surface quality of bolted connections and bearing surfaces.
  • Page 32 stops adjustment, rudder cable tensioning, clearance fits, securing. Adjust, replace worn-out parts, grease, secure. Flap Control Check free movement of flap control lever, stable bearing in every flap position, interlock pin wear. Replace worn-out parts, grease, secure. Canopy – Open / Close Check quality and function of locks and hinges, canopy bearing.
  • Page 33 8.2. Aeroplane Repairs The owner of aeroplane is obliged to report to the manufacturer each damage which may has an influence on an airframe strength or flight qualities. The manufacturer determines a way of repair. Minor repairs are the repairs of those parts, which do not participate substantially in the aeroplane function and stiffness.

  • Page 34: Weight, Centre Of Gravity

    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 The weight of aircraft full equipped, without fuel and pilot. It is weighed as a total weight of all wheels weights. The empty weight of the ATEC 212 SOLO including ROTAX 582 DCDI 2V and standard equipment with / without rescue system is ………………………………...
  • Page 36 9.5. Centre of gravity determination The aircraft has to be weighed at flight position including pilot and fuel. Weight on main wheels (kg) Weight on tail wheel (kg) Total weight G = G (kg) Wheel base = 3,7 MW-TW Distance from main wheel centre to leading edge of wing in root point = 0,19 MW-LE...