Atec 321 FAETA NG User manual

Flight and Operations Manual of ATEC 321 Faeta UL aircraft
ATEC v.o.s. Li ice nad Cidlinou, Czech Repu lic Page 1 of 53
The Sole Manufacturer and Distri utor in Czech Repu lic:
ATEC v.o.s.
Factory address: ATEC v.o.s., Opolanská 350, 289 07 Li ice nad Cidlinou
Czech Repu lic
ATEC 321 FAETA
Flight and Operations Manual
Li ice nad Cidlinou, March 2011

Flight and Operations Manual of ATEC 321 Faeta UL aircraft
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Type of aircraft: ATEC 321 FAETA
Serial num er :
Registration/call sign:
LAA CR Type Certificate: ULL-04 / 2005 Date of issue: 19. 10. 2005
The aircraft (Sport Flying Device) is not a su ject of CAA authorisation and is to e operated at own
risk of the user.
The aircraft must e operated according to informations and limits listed in this manual.

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Contents Chapter
General 1
Operational Limits 2
Emergency Procedures 3
Standard Procedures 4
Performances 5
Assem ly, Disassem ly 6
Aircraft Description and Systems 7
Maintenance 8
Weight, Centre of Gravity 9
Enclosures:
1. Log Book (example)
2. Records of Revisions
3. Service and Maintenance Book

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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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1.1. Introduction
Information provided within this manual is a necessary requirement for an effective and save
operation of the ATEC 321 FAETA aircraft. The manual contents information which Manufacturer
considers 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:

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1.3. Aircraft Description
ATEC 321 FAETA is an ultralight, two-seater, cantilever, low-wing aircraft of all car on composite
construction. The landing gear has a fixed tricycle gear with a steera le front wheel. The power unit
is of pulling configuration and consists of ROTAX 912 iS engine and of two- lade or three- lade fix or
ground adjusta le FITI propeller.
1.4. Modifications and Changes
If any structural or operational changes are made y the Manufacturer and need to e advised to the
owner, the related documentation will e delivered to you and you are o liged to record them into
your Manual. These documents will e pu lished in ascending numerical series.
If the aircraft is sold to another person, the Manufacturer shell e announced a out the name and
the address 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 m
2
Depth of mean aerodynamic chord 1,11 m
Span of horizontal tail surface 2,4 m
Flap position I 10 ° 45 mm
II 20 ° 90 mm
III 35 ° 150 mm
Aileron deflection up 20 ° 90 mm
down 12 ° 55 mm
Elevator deflection up 22 ° 80 mm
down 18 ° 65 mm
Rudder deflection L/R +-20° 180 mm
Wing profile
Root area SM 701
End area SM 701
Landing Gear (tricycle with frong wheel)
Wheel spacing 1,9 m
Wheel ase 1,4 m
Tire dimensions 350 x 120
Tire pressure 0,16 MPa / 1,6 atp
Suspension
Main gear composite springs
Front wheel ru er suspension

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Brakes hydraulic disc rakes on the main gear
Rescue System USH 52 S SOFT PACK,
v
MAX
= 293 km/h
Weight
Empty weight kg
Maximum take-off weight 450 kg
Maximum take-off weight including rescue system installed 472,5 kg
Maximum luggage weight in the luggage compartment 5 kg
Power Unit and Engine Parameters
Propeller producer FITI desing s.r.o., Řevnice, Czech Repu lic
Type of propeller FITI ECO COMPETITION 2 lade / 3 lade
Engine producer BOMBARDIER – ROTAX Gm H, Austria
Engine type ROTAX 912 iS SPORT
Engine Power
Take-off power 73,5 kW/100 HP/5800 RPM
Maximum continuous power 72,0 kW/ 98 HP/5500 RPM
Cruising power 44,6 kW/ 60 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
Engine idle speed 1400 RPM approximately
Water Temperature
Minimum 50 °C
Maximum 120 °C
Oil Temperature
Minimum 50 °C
Maximum 130 °C
Operational optimum 90 °C-110 °C
Oil Pressure
Maximum (short-term operated when cold start-up) 7,0 ar
Minimum 0,8 ar (engine speed elow 3500 RPM)
Operational 2,0 – 2,5 ar (over 3500 RPM)
Fuel Type Recommended motor unleaded petrol of minimum octane num er RON 95, 97

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Oil Type Any rand-name oil intended for 4 stroke motorcycle engines,
containing gear ox additives - API SF, SG + GL4 or GL5.
AeroShell Sport Plus 4 10W-40 preferentially recommended.
Cooling Liquid conventional (mix ratio 1:2)
ROTAX 912 iS is not a certified aviation engine. Any engine failure may occur at any time.
The pilot is fully responsi le for the operation of this engine and accepts all risk and consequences
of an engine failure.
The correct operation of this aircraft is the sole responsi ility of the pilot.
The pilot of a sport flying device is o liged to consider the flight altitude and flight track so that he
could e a le to make safety landing in case 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 Speed
2.3. Weight
2.4. Centre of Gravity
2.5. Manoeuvre and Gust Envelope
2.6. Permitted Manoeuvres
2.7. Load Factors
2.8. Type of Operation
2.9. Crew
2.10.Fuel tank
2.11.Wind
2.12.Other Limitations
2.13.La els and Markings

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2.1. Introduction
The Chapter 2 contains operational limits necessary for safe operation of the aircraft.
2.2. Air Speed (CAS)
Never exceed speed v
NE
270 km/h 146 kt
Do not exceed this speed in any case!
Design manoeuvre speed v
A
156 km/h 85 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!
Maximum design cruising speed v
C
230 km/h 123 kt
Do not exceed this speed except the flight in smooth air, ut with caution!
Max. cruising speed at severe tur ulence v
RA
224 km/h 122 kt
Do not exceed this speed at severe tur ulence!
Max. speed, flaps deflected to I. (10 °)
FE,I
130 km/h 70 kt
Max. speed, flaps deflected to II. (20 °)
FE,II
120 km/h 65 kt
Max. speed, flaps deflected to III. (35 °)
FE,III
110 km/h 59 kt
Recommended speed, flaps deflected to III. V
FE
90 km/h 49 kt
Never exceed these speed limits when flaps deflected!
Stall speed, flaps retracted v
S1
64 km/h 35 kt
Flying this speed and with flaps retracted results in loss of lifting force and fall of the aircraft!
Stall speed in landing configuration v
SO
51 km/h 28 kt
Flying this speed with flaps deflected at the position III. results in loss of lifting force
and fall of the aircraft!

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2.3. Weight
Empty weight kg
Maximum take-off weight 450 kg
Useful load kg
Never exceed the maximum take-off weight of the aircraft!
2.4. Centre of Gravity ( CG )
CG of the empty aircraft 28,7 % MAC
Flight range of CG 27-36 % MAC

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2.5. Manoeuvre and Gust Envelope (CAS)
vSO = 61 km/h = 16,9 m/s = 32,9 kt
vS1 = 79,3 km/h = 22,0 m/s = 42,8 kt
vAF = 86,2 km/h = 24 m/s = 46,6 kt
vS1N = 111,9 km/h = 31,1 m/s = 60,5 kt
vF = 130 km/h = 36,1 m/s = 70,2 kt
vA = 156 km/h = 43,5 m/s = 84,6 kt
vG = 156 km/h = 43,5 m/s = 84,5 kt
vC = 230 km/h = 63,8 m/s = 124 kt
vH = 249 km/h = 69,2 m/s = 134 kt
vNE = 270 km/h = 75,4 m/s = 146 kt
vD = 298,8 km/h = 83 m/s = 161,5 kt

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2.6. Permitted Manoeuvres
Category of the aircraft: Normal
Operations are limited to non-aero atic manoeuvres that include:
-Any manoeuvres necessary to normal flying
-Training of stalls
-Steep turns, in which the angle of ank is not more than 60°
Aero atic manoeuvres are prohi ited!
2.7. Load Factors
Maximum positive load factor in CG + 5,1 G
Maximum negative load factor in CG - 3,1 G
2.8. Type of Operation
Only VFR day flights are permitted (flight y visual reference to the ground during the daytime)
IFR flights ( instrument flights ) and flights y ice formation are prohi ited!
2.9. Crew
Num er of seats 2
Minimum weight of crew 60 kg
Maximum weight of crew 180 kg
2.10. Fuel tank
Fuel capacity 2 x 50 L
Not usa le rest of fuel 1,2 L
Recommended motor unleaded petrol of minimum octane num er RON 95, 97
2.11. Wind
The safe take-off and landing is only possi le if the following wind speed limits are not exceeded:
a) take-off or landing against wind up to 12 m/s
) take-off or landing tail wind up to 3 m/s
c) take-off or landing cross wind up to 6 m/s
Never operate the aircraft exceeding wind range limits determined!

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2.12. Other Limitations
Smoking, using of mo ile phone, explosives and com usti le materials and mova le o jects
transportation are prohi ited on oard of the aircraft.
2.13. La els and Markings
The aircraft shall e equipped with mandatory la els and markings. These must e placed on the
instrumental oard in a visual field of pilot and must contain following information:
- Identification of the aircraft
• Identification la el
• Serial num er
• Designation
• Empty weight
• Maximum take-off weight
- Operating limits
• Weight limits depending on the weight of crew, fuel and luggage
• Speed limits for standard flight configurations
- Passenger Warnings
• Definition of aircraft category, its airworthiness conditions and limitations
• Intentional spins, stalls and aero atics prohi ition

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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. A orted Landing
3.9. Vi rations

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3.1. Engine Failure on Take-off
1. Push the stick forward to get the aircraft to gliding flight 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 safety elts and switch off the main switch just efore landing.
Note: Electric flaps actuation is only possible when the main switch is switched-on.
A) If up to 50m (160ft) of altitude, get the aircraft into the landing configuration and make a
landing in take-off direction with respect to eventual o structions.
B) If higher than 50m (160ft) of altitude, choose a suita le 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. If no significant engine or installation failure found, try to start up the engine again using
ack-up fuel circuit.
4. If engine start-up is not possi le, follow the instructions as descri ed in Art. 3.1.
3.3. Rescue System Activation
In case of distress, when definitely losing control of flight, activate the rescue system.
1. Switch off the ignition
2. Adjust safety elts
3. Activate the rescue system
In case of landing on a limited area, when collision with an o stacle is inevita le, use the rescue
system as a raking device of the aircraft.
The aircraft can e damaged or the crew may e injured when using a rescue system!
3.4. Fire on Board
1. Close the fuel valve
2. Open the throttle
3. Switch-off the main switch and ignition
4. Make 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

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3.6. Emergency Landing
Carried out in case of engine failure:
1. Speed 100 km/h (54 kt)
2. Adjust safety elts
3. Flaps according to situation
4. Report the situation y the radio
5. Close the fuel valve
6. Turn off the ignition
7. Turn off the main switch
In case of emergency landing on terrain, on areas which are not authorized to take-off/landing of
sport flying devices, the aircraft can e damaged or the crew may e injured!
3.7. Safety Landing
Carried out in case of orientation loss, fuel exhaustion or another reason when the aircraft is fully
controlla le.
1. Determine the wind direction
2. Choose a suita le landing area
3. Make a low pass into the wind along the right-hand side of landing area and inspect the
terrain thoroughly.
4. Make a pattern flight
5. Calculate the landing plan
6. Land in the first third of the landing area using flaps landing position
3.8. A orted Landing
Carried out in case of wrong calculation of landing manoeuvre or ounce when landing and the pilot
considers a orted landing manoeuvre as more safety and decides to continue the flight.
1. Set up engine speed on maximum power
2. Set up take-off flaps position – I
3. Get to level speed of 110 km/h (59 kt)
4. Draw up control stick slowly to get aircraft into clim ing y speed 110 – 120 km/h (59 – 65 kt)
5. Retract flaps
Throughout the flight, maintain the aircraft in take-off trajectory using rudder control.
3.9. Vi rations
In case of unusual vi rations occur, it is necessary to:
1. Set the engine speed to appropriate run on which the vi rations are the lowest
2. Carry out the safety landing, eventually find the nearest aerodrome to land

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