Atec Wheelchair ATEC 212 SOLO ROTAX 912 ULの取扱説明書

デバイスAtec Wheelchair ATEC 212 SOLO ROTAX 912 ULの取扱説明書

デバイス: Atec Wheelchair ATEC 212 SOLO ROTAX 912 UL
サイズ: 0,32 MB
追加した日付: 2013-06-13 16:26:23
ページ数: 35
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Atec Wheelchair ATEC 212 SOLO ROTAX 912 ULの取扱説明書
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要旨

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内容要旨
ページ1に含まれる内容の要旨





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

ページ2に含まれる内容の要旨

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

ページ3に含まれる内容の要旨

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

ページ4に含まれる内容の要旨

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

ページ5に含まれる内容の要旨

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:

ページ6に含まれる内容の要旨

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

ページ7に含まれる内容の要旨

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

ページ8に含まれる内容の要旨

1.6. Three-View Sketch 8

ページ9に含まれる内容の要旨

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

ページ10に含まれる内容の要旨

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

ページ11に含まれる内容の要旨

2.4. Centre of Gravity ( CG ) CG of the empty aeroplane ………………… % MAC Flight range of CG ………………………… 28 – 36% MAC 11

ページ12に含まれる内容の要旨

2.5. Manoeuvre and Gust Envelope 12

ページ13に含まれる内容の要旨

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

ページ14に含まれる内容の要旨

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.

ページ15に含まれる内容の要旨

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

ページ16に含まれる内容の要旨

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

ページ17に含まれる内容の要旨

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

ページ18に含まれる内容の要旨

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

ページ19に含まれる内容の要旨

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

ページ20に含まれる内容の要旨

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


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