Atec 321 FAETA NG User manual

Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS
ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 1 of 59
The Sole Manufacturer and Distributor in Czech Republic:
ATEC v.o.s.
Factory address: ATEC v.o.s., Opolanská 350, 289 07 Libice nad Cidlinou
Czech Republic
ATEC 321 FAETA NG
with ROTAX 912 iS
(MTOW 600 kg)
Flight and Operations Manual
Libice nad Cidlinou, May 2019

Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS
ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 2 of 59
Type of aircraft: ATEC 321 FAETA NG
Serial number :
Registration/call sign:
Type Certificate of LAA Czech republic: ULL 06/2020 Issued: 16.11. 2020
The ultralight aircraft (Sport Flying Device) is not a subject of CAA authorization and is to be operated at
own risk of the user.
The aircraft must be operated according to information and limits described in this manual.

Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS
ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 3 of 59
Contents Chapter
General 1
Operating Limits 2
Emergency Procedures 3
Standard Procedures 4
Performances 5
Assembly, Disassembly 6
Aircraft Description and Systems 7
Weight and Balance 8
Care and Maintenance 9
Enclosures:
1. Log Book (example)
2. Records of Revisions
3. Service and Maintenance Book

Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS
ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 4 of 59
Chapter 1
1. General
1.1. Introduction
1.2. Personal Data of the Owner
1.3. Aircraft Description
1.4. Modifications and Changes
1.5. Aircraft Technical Data
1.6. Three-View Sketch

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ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 5 of 59
1.1. Introduction
Informations provided within this manual are necessary for an effective and save operation of the ATEC
321 FAETA NG aircraft. The manual contents information considered by the Manufacturer as important.
1.2. Personal Data of the Owner
Owner of aircraft:
Address:
Telephone No:
E-mail:
Date of ownership from: to:
Owner of aircraft:
Address:
Telephone No:
E-mail:
Date of ownership from: to:
Owner of aircraft:
Address:
Telephone No:
E-mail:
Date of ownership from: to:

Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS
ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 6 of 59
1.3. Aircraft Description
ATEC 321 FAETA NG is an ultralight, two-seater, cantilever, low-wing aircraft of carbon composite
construction. The landing gear is a fixed tricycle undercarriage with steerable nose wheel. The propulsion
unit is in pulling configuration and consists of ROTAX 912 iS Sport engine and two or three-blade fix or
adjustable FITI propeller.
1.4. Modifications and Changes
If the Manufacturer makes any structural or operating changes necessary to be advised to the owner, a
related documentation will be delivered to the owner, who is obliged to record them into this Manual. Such
documents are published in ascending numerical series.
In his own interest, the owner of the aircraft should regularly check manufacturer´s or its authorized
representative´s websites, where actual informations and bulletins are published. In case the owner sells
the aircraft to another person, the owner shall announce this fact to the competent authority who has this
aircraft in its registry. The manufacturer should be also announced about the contact details of the new
owner.
1.5. Aircraft Technical Data
Dimensions
Wing span 9,6 m
Length of fuselage 6,2 m
Total height 2,0 m
Wing area 10,1 m2
Depth of mean aerodynamic chord 1,11 m
Span of horizontal tailplane 2,6 m
Defined deflections of controls
Flap position I 12 ° 55 mm +-5 mm
II 22 ° 105 mm +-5 mm
III 32 °145 mm +-5 mm
Ailerons deflection up 18 °80 mm +-3 mm
(measured towards end bow) down 14 °60 mm +-3 mm
Max. hinge moment 250 g (0,6 Nm)
(measured on the trailing edge in the distance of 250 mm from the turning point)
Elevator deflection up 24 °80 mm +-2 mm
(measured towards end bow) down 18 °60 mm +-2 mm
Max. hinge moment 130 g (0,3 Nm)
(measured on the trailing edge in the distance of 250 mm from the turning point)
VT Rudder deflection L/R +/-32°120 mm +-5 mm
(measured at the bottom of the trailing edge)
Max. hinge moment 600 g (2 Nm)
(measured on the trailing edge in the distance of 350 mm from the axis of turning)
Airfoil Section
Root section SM 701
End section SM 701

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ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 7 of 59
Landing Gear (tricycle with nose gear)
Wheel spacing 1,9 m
Wheel base 1,4 m
Tyre dimension (main wheels) 350 x 120 mm
Tyre dimension (nose wheel) 300 x 100 mm
Tyre pressure 0,16 MPa / 1,6 atp
Suspension
Main gear composite springs
Nose gear rubber springs
Brakes hydraulic disc brakes on the main gear
(synthetic brake fluid DOT 3 or DOT 4)
Ballistic Rescue System USH 600
VMAX = 300 km/h
Weight
Empty weight kg
Maximum take-off weight 600 kg
Maximum luggage weight in the luggage compartment 10 kg
Propulsion Unit and Engine Parameters
Propeller manufacturer FITI design s.r.o., Řevnice, Czech Republic
Type of propeller FITI ECO COMPETITION -2 blades or 3 blades
Engine manufacturer BRP - ROTAX GmbH, Austria
Engine type ROTAX 912 iS Sport
Engine Performance
Take-off power 73,5 kW / 100 HP / 5800 RPM
Maximum continuous power 72,0 kW / 96,5 HP / 5500 RPM
Cruising power 54,0 kW / 72 HP / 5000 RPM
Engine Speed
Maximum take-off engine speed 5800 RPM / for max. 5 minutes
Max. continuous engine speed 5500 RPM
Cruising engine speed 5000 RPM
Min. engine idle speed 1400 RPM approx.
Coolant Temperature
Minimum 50 °C
Maximum 120 °C
Oil Temperature
Minimum 50 °C
Maximum 130 °C
Operating 90 °C - 110 °C

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ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 8 of 59
Oil Pressure
Minimum 0,8 bar (below 3500 RPM)
Maximum (short-term operated when cold start-up) 7,0 bar
Operating 2,0 –5,0 bar (over 3500 RPM)
Fuel Pressure
Minimum 2,8 bar
Maximum 3,2 bar
Fuel Type Recommended motor unleaded petrol of minimum octane number RON 95, 97
MOGAS EN228 Super or Super Plus, with max. 10% content of ethanol
Oil Type Use only oil with RON 424 classification or AeroShell Sport Plus 4 10W-40 as
an option.
Coolant Type Conventional coolant for aluminium engines, mixed with water (mix ratio 1:1) –see
Rotax manual. In case of mix ratio is 1:1, the freezing point is -38°C.
Water-less coolant (e.g. Evans or Aero Cool 180) can be applied as an option. These
coolants are not to be mixed with water!
The engine characteristics, operation and maintenance are preferentially directed by appropriate
Operating Manual of the engine manufacturer. Informations listed in appropriate engine manual are
preferential to this manual.
ROTAX 912 iS Sport is not certified aviation engine. Any engine failure may occur at any time.
The pilot is fully responsible for the operation of the engine and accepts all risks and consequences of
an engine failure. The correct operation of this aircraft is the sole responsibility of the pilot.
The pilot of sport flying device is obliged to plan the flight track and altitude so that to be able to make
safety landing at anytime in case of engine failure.

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ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 9 of 59
1.6. Three-View Sketch
(mm)

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ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 10 of 59
Chapter 2
2. Operating Limits
2.1. Introduction
2.2. Air Speed
2.3. Speed indicator markings
2.4. Weight
2.5. Centre of Gravity
2.6. Manoeuvre and Gust Envelope
2.7. Permitted Manoeuvres
2.8. Load Factors
2.9. Type of Operation
2.10. Crew
2.11. Fuel tank
2.12. Wind
2.13. Other Restrictions
2.14. Labels and Markings

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ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 11 of 59
2.1. Introduction
The Chapter 2 contains operating limits necessary for safe operation of the aircraft.
2.2. Air Speed (IAS)
Never exceed speed VNE 272 km/h 147 kt
Do not exceed this speed in any case!
Design manoeuvre speed VA190 km/h 102 kt
After exceeding this speed, do not use full deflection of any control surfaces and do not make any
sudden control operations. An overload of the aircraft may occur!
Max. continuous cruising speed VC242 km/h 131 kt
Do not exceed this speed except the flight in smooth air, but with caution!
Max. cruising speed at severe turbulence VRA 215 km/h 116 kt
Do not exceed this speed at severe turbulence!
Max. speed, flaps extended to III. VFE 117 km/h 63 kt
Recommended speed, flaps extended to III. VFE 90 km/h 49 kt
Do not exceed these speed limits when flaps extended!
Stall speed, flaps retracted VS1 75 km/h 40 kt
Flying this speed when flaps retracted results in loss of lift force and stall!
Stall speed in landing configuration VS0 56 km/h 30 kt
Flying this speed with flaps extended in the position III. results in stall due to loss of lift force!

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ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 12 of 59
2.3. Speed Indicator Markings
Speed (km/h)
IAS
Speed (kt)
IAS
Colour marking
Note
56 - 117
30 - 63
White section
The speed from vS0 up to the speed defined
for flaps extended in max. position vFE
75 - 215
40 - 116
Green section
From the speed vS1 up to the max. cruising
speed
215 - 272
116 - 147
Yellow section
From the max. cruising speed up to the never
exceed speed vNE
272
147
Red section
Never exceed speed vNE
2.4. Weight
Empty weight kg
Maximum take-off weight 600 kg
Useful load kg
Max. load in the luggage compartment kg
(for specific permissible max. load see Chapt. 8)
Do not ever exceed maximum take-off weight of the aircraft!

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ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 13 of 59
2.5. Centre of Gravity ( CG )
CG of the empty aircraft % MAC
CG range in flight 25-36 % MAC

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2.6. Manoeuvre and Gust Envelope (CAS)
Envelope point Speed
Manoeuvre and Gust Envelope / m = 600,0 kg

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ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 15 of 59
2.7. Permitted Manoeuvres
Category of the aircraft: Normal
Operations are limited to non-aerobatic manoeuvres that include:
-Any manoeuvres necessary for normal flight
-Training of stalls
-Steep turns with the bank angle not more than 60°
Aerobatic manoeuvres are prohibited!
2.8. Load Factors (600 MTOW)
Maximum positive load factor in CG + 4,0 g
Maximum negative load factor in CG - 2,0 g
2.9. Type of Operation
Only VFR day flights are permitted (flight by visual reference to the ground during the daytime)
IFR flights ( instrumental flights ) and flights by ice formation are prohibited!
2.10. Crew
Number of seats 2
Minimum weight of the crew 70 kg
Maximum weight of the crew 220 kg
Maximum load of the seat 110 kg
2.11. Fuel tank
Fuel capacity 2 x 50 L
Non-usable rest of fuel 0,82 L for each tank
2.12. Wind
A safe take-off and landing is only possible if the following wind speed limits are not exceeded:
a) take-off or landing headwind up to 12 m/s = 23,3 kt
b) take-off or landing tailwind up to 3 m/s = 5,8 kt
c) take-off or landing crosswind up to 6 m/s = 11,6 kt
Never operate the aircraft when above listed wind limits are exceeded!

Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS
ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 16 of 59
2.13. Other Restrictions
Smoking, using of mobile phones, explosives and combustible materials and transport of movable objects
are prohibited on board of the aircraft.
2.14. Labels and Markings
The aircraft shall be equipped with mandatory labels and markings. These must be placed on the
instrumental board in a visual field of the pilot and must contain at least following actual information:
- Identification of the aircraft
•Identification label
•Serial number
•Designation
•Empty weight
•Maximum take-off weight
- Operating limits
•Load and weight limits depending on weight of the crew, fuel and luggage
•Speed limits in standard flight configuration
- Passenger Warnings
•Definition of aircraft category, its airworthiness conditions and restrictions
•Prohibition alert of intentional spins, stalls and aerobatics

Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS
ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 17 of 59
Chapter 3
3. Emergency Procedures
3.1. Engine Failure on Take-off
3.2. Engine Failure in Flight
3.3. Rescue System Activation
3.4. Fire on Board
3.5. Engine Loss
3.6. Emergency Landing
3.7. Safety Landing
3.8. Aborted Landing
3.9. Vibrations

Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS
ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 18 of 59
3.1. Engine Failure on Take-off
1. Get the aircraft to gliding flight by pushing the stick forward maintaining the airspeed
of 100 km/h (54 kt).
2. Determine the wind direction, adjust flaps to appropriate position, close the fuel valve, switch-off
the ignition, adjust seat belts and switch off the master switch just before landing.
Note: Electric flaps actuation is only possible when the master switch is switched-on.
A) If altitude is below 50m (160ft), get the aircraft to landing configuration and make a landing in
take-off direction with respect to eventual obstructions.
B) If altitude is higher than 50m (160ft), choose a suitable area for emergency landing.
3.2. Engine Failure in Flight
1. Get the aircraft to gliding flight maintaining the airspeed of 100 km/h (54 kt).
2. Check the fuel level and make sure ignition is switched on.
3. Make sure that both LANE A and LANE B are switched on. Check the voltage on both LANE A and
LANE B. Check the fuel pressure. Must be within limits.
4. A) If no significant failure on engine or its installation found, try to start up the engine again.
Proceed as follows:
•Fuel valve open for appropriate fuel tank in use
•Master switch switched-on
•START POWER switch on (to “START” position)
•Throttle lever 50% open position (approx. 8mm from idle position)
•Fuel pump switch-on, wait until the fuel pressure reaches approx. 3 bar
•LANE A switch on
•LANE B switch on
•Check EMS indicators lights off (see the engine Operations Manual)
•Start button press and hold until the engine reaches 1500 RPM or more; hold
(without interruption) for max. 10 sec. The engine can be started even though the propeller
continues to rotate during flight because of windmilling. It is not needed to wait until the
propeller stands still.
•START POWER switch off (to “FLIGHT” position)
•Set up RPM to requested power
B) If there is no voltage on LANE A and LANE B, proceed as follows:
•Fuel valve open for appropriate fuel tank in use
•Master switch switched-on
•BACK-UP BATTERY switch on
•Throttle lever 50% open position (approx. 8mm from idle position)
•Fuel pump switch-on, wait until the fuel pressure reaches approx. 3 bar.
•LANE A switch on
•LANE B switch on
•Check EMS indicators lights off (see the engine Operations Manual)
•Start button press and hold until the engine reaches 1500 RPM or more; hold
(without interruption) for max. 10 sec. The engine can be started even though the propeller
continues to rotate during flight because of windmilling. It is not needed to wait until the
propeller stands still.
•Set up RPM to requested power

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•Carry out landing on the nearest suitable place. The engine run via back-up battery is time-
limited. Once the back-up battery is wasted, the engine stops and it will not be possible to
start it up again!
5. If the engine start-up is not successful, carry out emergency landing as described in the Art. 3.1.
3.3. Rescue System Activation
In case of distress, when definitively losing control of flight, activate the rescue system.
1. Switch off the ignition
2. Fasten the seatbelts
3. Activate the rescue system
In case of landing on limited space, and when collision with an obstacle is inevitable, use the balistic rescue
system as a braking device of the aircraft.
The aircraft may be damaged or the crew may be injured when using the rescue system!
3.4. Fire on Board
1. Turn off the fuel valve
2. Open the throttle
3. Switch off the master switch and ignition
4. Carry out emergency landing
5. Get off the aircraft
3.5. Engine Loss
1. Speed 100 km/h (54 kt)
2. Flaps retracted
3. Instruments within tolerated values
3.6. Emergency Landing
Carried out in case of engine failure:
1. Speed 100 km/h (54 kt)
2. Fasten seatbelts
3. Flaps position according to situation
4. Report the situation by radio
5. Close the fuel valve
6. Switch off the ignition
7. Switch off the master switch
In case of emergency landing on terrain, on a surface which is not approved for take-off/landing of
sport flying device, the aircraft may be damaged or the crew may be injured!

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3.7. Safety Landing
Carried out in case of orientation loss, fuel exhaustion or any other reason, while the aircraft is fully
controllable.
1. Determine the wind direction
2. Choose any suitable landing surface
3. Carry out low pass headwind along the right-hand side of the landing surface and inspect the terrain
thoroughly
4. Carry out pattern flight
5. Calculate the landing manoeuvre
6. Land in the first third of the landing area with the flaps in the position for landing
3.8. Aborted Landing
Carried out in case of wrong landing manoeuvre or bounce during the landing and when the pilot considers
aborted landing manoeuvre as safer and decides to proceed the flight.
1. Set the engine run up to full power
2. Fluently set up flaps to take-off position –I
3. Reach the horizontal speed of 110 km/h (59 kt)
4. Pull the control stick slowly to make the aircraft climbing by speed 110 –120 km/h (59 –65 kt)
5. Retract flaps
Keep the aircraft within runway centerline by using rudder control throughout the flight.
3.9. Vibrations
In case of unusual vibrations occure, it is necessary to:
1. Set up the engine run to appropriate RPM on which the vibrations are the lowest
2. Carry out safety landing, eventually find the nearest airfield to land