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Table of contents for the manual
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Page 1
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[...]
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Page 2
2 Type of aeroplane ATEC 212 SOLO Serial number …………………………………………………… Identification label …………………………………………………… LAA CR type licence …………………… issued …………………… This aircraft is not registered at the state offi ce and is to be operated at oper[...]
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Page 3
3 C o n t e n t s C h a p t e r General ……………………………………. 1 Operational Limits …………………………… 2 Emergency Instructions ……………………… 3 Standard Procedures ……………………… 4 Specifications …………………………… 5 Assembly, Disassembly ……………………… 6 Des[...]
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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[...]
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Page 5
5 1.1. Introduction The information provided by this manual is nece ssary for an effective and save operation of the ATEC 212 SOLO aircraft. Also included are info rmation and docum ents 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 [...]
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Page 6
6 1.3. Description of the Aeroplane ATEC 212 SOLO is an ultralight single-seater cantile ver low-wing airc raft of an all carbon composite construction. It is e quipped with a tail landing gear with the steerable tail wheel. The power plant is a pull arrangement and cons ists of a ROTAX 912 UL 80 HP engine and a two-blade or three-blade fix or gr o[...]
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Page 7
7 Driving Unit Propeller manufacturer ………………... Josef Faturik Type of propeller ……………… FI TI ECO COMPETITION 2 blade, 3-blade Engine manufacturer …………………… Bo mbardier – ROTAX GmbH Type of engine …………………… ROTAX 912 UL 80 HP Power Take-off power …………………… 59,6 kW / 80 HP / 5800 [...]
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Page 8
8 1.6. Three-View Sketch[...]
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Page 9
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[...]
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Page 10
10 2.1. Introduction The chapter 2 contents are opera tional lim its necessary for a sa ve operation of the aircraft 2.2. Air Speeds Never exceed speed v NE ….. 286 km/h ….. 154 kt Do not exceed this speed in any case Design manoeuvre speed v A …… 187 km/h ….. 101 kt Do not use full deflection of the rudders a nd sudden control operations[...]
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Page 11
11 2.4. Centre of Gravity ( CG ) CG of the empty aeroplane ………………… % MAC Flight range of CG ………………………… 28 – 36% MAC[...]
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Page 12
12 2.5. Manoeuvre and Gust Envelope[...]
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Page 13
13 2.6. Permitted Manoeuvres Category of the aeroplane: Normal Except of the normal flight manoeuvres, the sharp turns up to bank of 60 o , level and clim bing turns are perm itted. 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 C[...]
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Page 14
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 telephone s[...]
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Page 15
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[...]
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Page 16
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, adju st flaps for suitable pos ition, 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 th[...]
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Page 17
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 terrai[...]
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Page 18
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 [...]
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Page 19
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 m anufacturer recommends using the following procedure: 4.1.1. Procedures Before Entering the Cockpit 1. Check ignition - turned off. 2. Check main switch – turned of[...]
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Page 20
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 , hol d approx. 2 minutes, continue until[...]
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Page 21
21 4.8. Cruising flight ATEC 212 SOLO has good flight features in the whole range of permitted speeds and centre of gravity positions. Th e cruising speed is in the range 120 – 243 km/h …… 65 – 131 kt. 4.9. Descent and landing Carry out the descent with th e throttle in idle run at speed of 100 km/h ….. 54 kt Flaps position limitations ac[...]
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Page 22
22 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[...]
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Page 23
23 5.1. Introduction The information in stalling sp eed and other performances of the ATEC 212 SOLO with ROTAX 912 UL 80 HP and propell er FITI ECO COMPETITION 2b/168. 5.2. Stalling Speeds (CAS) Engine idling Flaps retracted Flaps I (10°) Flaps II (20°) Flaps III (35°) 72 km/h …39 kt 65 km/h ... 35 kt 63 km/h ... 34 kt 62 km /h ... 33 kt Engin[...]
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Page 24
24 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[...]
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Page 25
25 6.1. Introduction The assembly of individual parts of the aeroplane is described in this chapter. At leas t two persons are necessary for th e 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. Disconnect control. Release and unbolt t[...]
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Page 26
26 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[...]
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Page 27
27 7.1. Wing The cantilever tapered wing with con ventional a ilerons, slotted flaps and wing-tips. The m ain spar of laminated beech wood satu rated with synthetic resin at a high temperature is placed 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 [...]
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Page 28
28 7.7. Fuel System The fuel system is formed by an integral fuse lage tank with a fuel drain. Double fuel supply circuit with a spare electric pump. The pressure of supplied fuel is m easured with a fuel- pressure gauge. The fuel reserve 10 l at f light position is indi cated by control light. 7.8. Instrument Equipment The instrument equipment con[...]
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Page 29
29 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[...]
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Page 30
30 8.1. Maintenance Schedule Inspection, Mandatory Work Inspection Period 10 25 50 100 200 Engine As per ROTAX Manual attached. Engine Compartment Engine Attachment Check integrity of construction with special care for welds, fixing points, silent blocks, bushings. S urface finish quality. x Bolted Connections Check surface quality of bolted c onne[...]
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Page 31
31 stops adjustment, rudder cable tens ioning, clearance fits, securing. Adjust, replace worn-out parts, grease, secure. Flap Control Check free movement of flap control le ver, stable bearing in every flap position, interlock pin wear. Replace worn-out parts, grease, secure. x Canopy – Open / Close Check quality and function of lock s and hinges[...]
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Page 32
32 8.2. Aeroplane Repairs The owner of aeroplane is obliged to report to the m anufacturer 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 par ticipate substantially in th e aeroplane function and stiffness. Am[...]
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Page 33
33 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[...]
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Page 34
34 9.1. Introduction The weight, useful weight and centre of gravity inform ation is described in this chapter. 9.2. Empty Weight The weight of aircraft full equippe d, without fuel and p ilot. It is weighed as a total weight of all wheels weights. The empty weight of the ATEC 212 SOLO including ROTAX 912 UL 80 HP and standard equipment with / with[...]
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Page 35
35 9.5. Centre of gravity determination The aircraft has to be weighed at flight position including pilot and fuel. Weight on main wheels G 1 (kg) Weight on tail wheel G 2 (kg) Total weight G = G 1 + G 2 (kg) W h e e l b a s e x MW-TW = 3,7 (m) Distance from main wheel cen tre to leading edge of wing in root point x MW-LE = 0,19 (m) CG distance fro[...]