AtecメーカーATEC 212 SOLO ROTAX 912 ULの使用説明書/サービス説明書
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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.
2 Type of aeroplane ATEC 212 SOLO Serial number …………………………………………………… Identification label …………………………………………………… LAA CR ty.
3 C o n t e n t s C h a p t e r General ……………………………………. 1 Operational Limits …………………………… 2 Emergency Instructions ……………………… 3 Standa.
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.
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.
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.
7 Driving Unit Propeller manufacturer ………………... Josef Faturik Type of propeller ……………… FI TI ECO COMPETITION 2 blade, 3-blade Engine manufacturer …………………… Bo mb.
8 1.6. Three-View Sketch.
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.
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 ….
11 2.4. Centre of Gravity ( CG ) CG of the empty aeroplane ………………… % MAC Flight range of CG ………………………… 28 – 36% MAC.
12 2.5. Manoeuvre and Gust Envelope.
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.
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 ……….
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.
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.
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.
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.
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.
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.
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 ….
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.
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 .
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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 + .
デバイスAtec ATEC 212 SOLO ROTAX 912 ULの購入後に（又は購入する前であっても）重要なポイントは、説明書をよく読むことです。その単純な理由はいくつかあります：
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Atec ATEC 212 SOLO ROTAX 912 ULを既にお持ちだが、まだ読んでいない場合は、上記の理由によりそれを行うべきです。そうすることにより機能を適切に使用しているか、又はAtec ATEC 212 SOLO ROTAX 912 ULの不適切な取り扱いによりその寿命を短くする危険を犯していないかどうかを知ることができます。
ですが、ユーザガイドが果たす重要な役割の一つは、Atec ATEC 212 SOLO ROTAX 912 ULに関する問題の解決を支援することです。そこにはほとんどの場合、トラブルシューティング、すなわちAtec ATEC 212 SOLO ROTAX 912 ULデバイスで最もよく起こりうる故障・不良とそれらの対処法についてのアドバイスを見つけることができるはずです。たとえ問題を解決できなかった場合でも、説明書にはカスタマー・サービスセンター又は最寄りのサービスセンターへの問い合わせ先等、次の対処法についての指示があるはずです。
