Atec 321 FAETA NG User manual

Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 iS Sport
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 1 of 56
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
with ROTAX 912 iS Sport
Flight and Operations Manual
Libice nad Cidlinou, March 2011

Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 iS Sport
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 2 of 56
Type of aircraft: ATEC 321 FAETA
Serial number:
Registration/call sign:
Type Certificate: ULL-04 / 2005 Date of issue: 19. 10. 2005
The aircraft (Sport Flying Device) is not a subject of CAA authorisation and is to be operated at own
risk of the user.
The aircraft must be operated according to informations and limits listed in this manual.

Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 iS Sport
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 3 of 56
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 ultralight aircraft with Rotax 912 iS Sport
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 4 of 56
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

Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 iS Sport
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 5 of 56
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:

Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 iS Sport
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 6 of 56
1.3. Aircraft Description
ATEC 321 FAETA is an ultralight, two-seater, cantilever, low-wing aircraft of all carbon composite
construction. The landing gear is a fixed tricycle undercarriage with a steerable nose wheel. The
propulsion unit is in pulling configuration and consists of ROTAX 912 iS Sport engine and of two- or
three- blade fix or ground adjustable FITI propeller.
1.4. Modifications and Changes
If the Manufacturer makes any structural or operation changes necessary to be advised to the owner,
the 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.
If the aircraft is sold to another person, the Manufacturer shall be announced about the name and
contact information 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 2,4 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
Airfoil Section
Root section SM 701
End section SM 701
Landing Gear (tricycle with nose gear)
Wheel spacing 1,9 m
Wheel base 1,4 m
Tyre dimensions (main wheels) 350 x 120 mm
Tyre dimensions (nose wheel) 300 x 100 mm
Tyre pressure 0,16 MPa / 1,6 atp
Suspension
Main gear composite springs
Nose gear rubber springs

Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 iS Sport
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 7 of 56
Brakes hydraulic disc brakes on the main gear
(brake fluid DOT 4 or DOT 5)
Rescue System USH 52 S SOFT PACK / vMAX = 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
Propulsion Unit and Engine Parameters
Propeller producer FITI design s.r.o., Řevnice, Czech Republic
Type of propeller FITI ECO COMPETITION 2 blades or 3 blades
Engine producer 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/ 97 HP/5500 RPM
Cruising power 44,6 kW/ 60 HP/4800 RPM
Engine Speed
Maximum take-off engine speed 5800 RPM / 5 minutes max.
Max. continuous engine speed 5500 RPM
Cruising engine speed 4800 RPM
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
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

Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 iS Sport
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 8 of 56
Oil Type Use only oil with RON 424 classification or AeroShell Sport Plus 4 10W-40
as an option.
Coolant Type conventional (mix ratio 1:1) or Evans (see Rotax Manual)
The engine characteristics, operation and maintenance are preferentially directed by appropriate Rotax
Manual.
ROTAX 912 iS Sport is not certified aviation engine. Any engine failure may occur at any time.
The pilot is fully responsible for operation of this 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 consider the flight altitude and flight track so that to be
able to make safety landing in case of engine failure.

Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 iS Sport
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 9 of 56
1.6. Three-View Sketch
(mm)

Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 iS Sport
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 10 of 56
Chapter 2
2. Operating Limits
2.1. Introduction
2.2. Air Speed
2.3. Weight
2.4. Centre of Gravity (CG)
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 Restrictions
2.13.Labels and Markings

Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 iS Sport
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 11 of 56
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 295 km/h 159 kt
Do not exceed this speed in any case!
Design manoeuvre speed VA165 km/h 89 kt
After exceeding this speed, do not use full deflection of any control surface and do not make any
sudden control operations. An overload of the aircraft may occur!
Maximum design cruising speed VC248 km/h 134 kt
Do not exceed this speed except the flight in smooth air, but with caution!
Max. cruising speed at severe turbulence VRA 179 km/h 96 kt
Do not exceed this speed at severe turbulence!
Max. speed, flaps extended to I. (10 °) VFE,I 130 km/h 70 kt
Max. speed, flaps extended to II. (20 °) VFE,II 120 km/h 65 kt
Max. speed, flaps extended to III. (35 °) VFE,III 110 km/h 59 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 64 km/h 35 kt
Flying this speed with flaps retracted results in loss of lift force and stall!
Stall speed in landing configuration VS0 51 km/h 28 kt
Flying this speed with flaps extended on the position III. results in loss of lift force
and stall!

Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 iS Sport
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 12 of 56
2.3. Weight
Empty weight kg
Maximum take-off weight 472,5 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: % MAC
CG range in flight: 27 - 36 % MAC

Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 iS Sport
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 13 of 56
2.5. Manoeuvre and Gust Envelope (CAS)
CAS
(km/h)
CAS
(kt)
IAS
(km/h)
IAS
(kt)
Vs0
57
31
51
28
Vs1
69
37
64
35
VAF
86
47
81
44
VS1N
112
61
111
60
VF
110
59
109
59
VA
158
85
165
89
VG
224
121
240
130
VC
230
124
248
134
VH
249
134
270
146
VNE
270
146
295
159
VD
299
161
329
178

Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 iS Sport
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 14 of 56
2.6. Permitted Manoeuvres
Category of the aircraft: Normal
Operations are limited to non-aerobatic manoeuvres that include:
-Any manoeuvres necessary to normal flying
-Training of stalls
-Steep turns, in which the angle of bank is not more than 60°
Aerobatic manoeuvres are prohibited!
2.7. Load Factors (472,5 kg MTOW)
Maximum positive load factor in CG + 5,06 G
Maximum negative load factor in CG - 3,06 G
2.8. 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!
2.9. Crew
Number of seats 2
Minimum weight of crew 60 kg
Maximum weight of crew 180 kg
Maximum load of the seat 90 kg
2.10. Fuel tank
Fuel capacity 2 x 50 L
Non-usable rest of fuel 1,2 L
2.11. Wind
The 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
b) take-off or landing tailwind up to 3 m/s
c) take-off or landing crosswind up to 6 m/s
Never operate the aircraft when above listed wind range limits are exceeded!

Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 iS Sport
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 15 of 56
2.12. Other Restrictions
Smoking, using of mobile phones, explosives and combustible materials and transport of movable
objects are prohibited on board of the aircraft.
2.13. 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 following 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 for standard flight configurations
- Passenger Warnings
•Definition of aircraft category, its airworthiness conditions and restrictions
•Prohibition of intentional spins, stalls and aerobatics

Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 iS Sport
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 16 of 56
INTENTIONALLY LEFT BLANK

Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 iS Sport
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 17 of 56
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 ultralight aircraft with Rotax 912 iS Sport
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 18 of 56
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 safety 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 LANES.
4. Check the fuel pressure. Must be within tolerated limits.
5. A) If no significant failure on engine or its installation found, try again to start up the engine,
proceed as follows:
•Fuel valve open for appropriate fuel tank in use
•Master switch switched-on
•START POWER switch on (in “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 release after the engine reaches 1500 RPM or more; hold
(without interruption) for max. 10 sec.. The engine can be started even though the propeller
turns in flight because of windmilling. It is not necessary to wait for the standstill of the
propeller.
•START POWER switch off (in “FLIGHT POSITION”)
•Set the RPM up 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 of 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 release after the engine reaches 1500 RPM or more; hold
(without interruption) for max. 10 sec.. The engine can be started even though the propeller
turns in flight because of windmilling. It is not necessary to wait for the standstill of the
propeller.
•Set the RPM up to requested power

Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 iS Sport
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 19 of 56
•Make a landing on the nearest suitable place. The engine run via back-up battery is time-
limited. After the back-up battery is wasted, the engine stops and it will not be possible to
start it up again!
6. If the engine start-up is not successful, carry out emergency landing similar way 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. Remove the securing pin from activation handle
4. Fire the rescue system
In case of landing on limited space, when collision with an obstacle is inevitable, use the balistic rescue
system as a braking device of the aircraft.
Note: the activation of the rescue system is only available from pilot´s seat
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. 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
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, a surface not approved for take-off/landing of sport flying
device, the aircraft may be damaged or the crew may be injured!

Flight and Operations Manual of ATEC 321 Faeta ultralight aircraft with Rotax 912 iS Sport
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 20 of 56
3.7. Safety Landing
Carried out in case of orientation loss, fuel exhaustion or any other reason when the aircraft is fully
controllable.
1. Determine the wind direction
2. Choose any suitable landing surface
3. Make a low pass headwind along the right-hand side of the landing surface 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 by using flaps in landing position
3.8. Aborted Landing
Carried out in case of wrong calculation of landing manoeuvre or bounce during landing and when the
pilot considers aborted landing manoeuvre as more safe and decides to proceed the flight.
1. Set the engine run up to maximum 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
Maintain the aircraft in take-off axis by using rudder control throughout the flight.
3.9. Vibrations
In case of unusual vibrations occurance, it is necessary to:
1. Set the engine run up to appropriate RPM on which the vibrations are the lowest
2. Carry out safety landing, eventually find the nearest airfield to land