Atec 212 SOLO Technical specifications

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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

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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 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:

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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.
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 …………………………………….. 0,12 MPa / 1,2 atp
Springing system
Main wheels …………………………….. composite spring
Tail wheel …………………………….. composite spring
Brakes ……………………………………. Main wheels hydraulic disc brakes
Rescue System installed / not installed……….
Weights
Empty weight …………………………………….. kg
Maximum take-off weight …………………….. 300 315 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 582 UL DCDI 2V 65 HP
Power
Take-off power …………………… 48 kW / 65 HP / 6500 RPM
Maximum continuous power …………… RPM
Cruising power …………………… RPM
Engine Speed
Maximum take-off engine speed ….… 6800 RPM / 5 minutes maximum
Max. continuous engine speed ……. 6500 RPM
Cruising engine speed ……. 5000 RPM
Idling ……. 2000 RPM approximately
Engine Cylinders Temperature
Maximum ……………………………. 150°C
Operational ……………………………. 110 - 130°C
Cooling Liquid Temperature
Maximum ……………………………. 80°C
Minimum ……………………………. 65°C
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
1. Engine lubrication, rotary slide valve lubrication – motor oil for high loaded two stroke
engines of API-TC class (CASTROL TTS equivalent). Oil / Fuel mixture 1: 50 (2%).
2. Gearbox lubrication – gearboxes oil of API-GL5 or API-GL6, SAE 140 EP or 85W – 140
EP.
ROTAX 582 UL DCDI 2V 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
2.13. Placards and Markings

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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 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 and sudden control operations. Overload of the
aircraft may occur
Maximum design cruising speed v
C
… 222 km/h 120 kt
Operation over this speed must be conducted with caution in smooth air only
Maximum cruising speed at severe turbulence v
RA
… 200 km/h 108 kt
Never exceed this speed at severe turbulence
Maximum speed at flaps deflection 10° v
FI
…… 140 km/h ….. 75 kt
Maximum speed at flaps deflection 20° v
FII
....... 130 km/h ...... 70 kt
Maximum speed at full deflection 35° v
FE
…… 120 km/h ….. 65 kt
Maximum recommended speed at def. 35° v
FIII
…… 100 km/h ….. 55 kt
Do not exceed this speed by flaps deflected
Stalling speed flaps retracted v
S1
…… 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
SO
…... 64,2 km/h ….. 35 kt
The loss of uplift and fall of aircraft with flaps position III deflected happens by this
speed