Atec 212 SOLO User Manual
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
Flight and Operations Manual
ROTAX 912 UL
Libice nad Cidlinou January 2007
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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 manual must be at all times be carried on board of the aircraft
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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
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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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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:
5
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
Total height ……………………………………. 1,4 m
Wing area ……………………………………. 7,27 m
2
Depth of mean aerodynamic chord …………….. 1,032 m
Span of horizontal tail surface …………….. 2,18 m
Flap position ……………………………………. I 10°
II 20°
III 35°
Airfoil Section
Root section …………………………………….. SM 701
End section …………………………………….. SM 701
Tail Wheel Landing Gear
Wheel spacing…………………………………….. 1,56 m
Wheel base …………………………………….. 3,66 m
Tyre dimensions …………………………….. 350 * 120
Tyre pressure …………………………………….. 0,16 MPa / 1,6 atp
Springing system
Main wheels …………………………….. composite spring
Tail wheel …………………………….. composite spring
Brakes ……………………………………. Main wheels hydraulic disc brakes
Rescue System installed / not installed………. GRS 6/360
Weights
Empty weight …………………………………………………. kg
Maximum take-off weight …………………………………. 300 kg
Maximum take-off weight including rescue system installed … 315 kg
Maximum weight of luggage in luggage space … 5 kg
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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
Max. continuous engine speed ……. 5500 RPM
Cruising engine speed ……. 4800 RPM
Idling ……. 1400 RPM approximately
Oil Temperature
Minimum ……………………………. 60°C
Operational optimum ……………………. 90 - 110°C
Maximum ……………………………. 140°C
Temperature of Engine Cylinders
Minimum ……………………………. 60°C
Maximum ……………………………. 150°C
Oil Pressure
Minimum ……………………………. 0,8 bar
Operational ……………………………. 2,0 – 2,5 bar (over 3500 RPM)
Maximum short time operated by cold start 7,0 bar
Fuel Pressure
Maximum ……………………………. 0,4 bar
Minimum ……………………………. 0,2 bar
Operational Temperature
Maximum ……………………………. 50°C
Minimum ……………………………. -25°C
Fuel Type ……………………………. See Art. 2.9.
Oil Type
Any branded oil for 4 stroke motorcycle engines with gearbox additives. Power class SF, SG
+ GL4 or GL5.
ROTAX 912 UL is not certificate as an aircraft engine and a failure may occur
whenever. The pilot is fully responsible for consequence of engine failure
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1.6. Three-View Sketch
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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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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 vNE ….. 286 km/h ….. 154 kt
Do not exceed this speed in any case
Design manoeuvre speed vA …… 187 km/h ….. 101 kt
Do not use full deflection of the rudders and sudden control operations. Overload of the
aircraft may occur
Maximum design cruising speed vC …… 238 km/h ….. 128 kt
Operation over this speed must be conducted with caution in smooth air only
Maximum speed at flaps deflection 10° vFI …… 140 km/h ….. 75 kt
Maximum speed at flaps deflection 20° v
....... 130 km/h ...... 70 kt
FII
Maximum speed at full deflection 35° vFE …… 120 km/h ….. 65 kt
Maximum recommended speed at def. 35° v
…… 100 km/h ….. 55 kt
FIII
Do not exceed this speed by flaps deflected
Stalling speed flaps retracted vS1 …… 76,4 km/h ….. 41 kt
The loss of uplift and fall of aircraft with flaps retracted happens by this speed
Stalling speed in landing configuration v
…... 64,2 km/h ….. 35 kt
SO
The loss of uplift and fall of aircraft with flaps position III deflected happens by this
speed
2.3. Weights
Empty weight …………………………………. kg
Maximum take-off weight …………………. 300 315 kg
Useful load …………………………………. kg
Never exceed the maximum take-off weight of the aeroplane
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2.4. Centre of Gravity ( CG )
CG of the empty aeroplane ………………… % MAC
Flight range of CG ………………………… 28 – 36% MAC
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