Atec 321 FAETA NG User manual

Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 UL/ULS
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 NG
with ROTAX 912 UL/ULS
Flight and Operations Manual
Libice nad Cidlinou, Czech Republic, November 2016

Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 UL/ULS
ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 2 of 56
Type of aircraft: ATEC 321 FAETA NG
Serial number:
Registration/call sign:
Type Certificate: ULL-04 / 2005 Date of issue: 19. 10. 2005
The UL 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 NG aircraft with Rotax 912 UL/ULS
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
Maintenance 8
Weight, Centre of Gravity 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 UL/ULS
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 NG aircraft with Rotax 912 UL/ULS
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 NG 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 NG aircraft with Rotax 912 UL/ULS
ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 6 of 56
1.3. Aircraft Description
ATEC 321 FAETA NG is an ultralight, two-seater, cantilever, low-wing aircraft of all carbon composite
construction. The landing gear has a fixed tricycle gear with a steerable nose wheel. The propulsion unit
is in pulling configuration and consists of ROTAX 912 UL or ROTAX 912 ULS engine and 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. These documents will be 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 2,6 m
Flap position I 10 ° 45 mm
II 20 ° 90 mm
III 35 ° 150 mm
Aileron deflection up 20 ° 80 mm
down 12 ° 58 mm
Elevator deflection up 22 ° 80 mm
down 18 ° 60 mm
Rudder deflection L/R +-20° 140 mm
Wing profile
Root area SM 701
End area SM 701
Landing Gear (tricycle with nose wheel)
Wheel spacing 1,9 m
Wheel base 1,4 m
Tyre dimensions (main gear) 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 wheel rubber suspension

Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 UL/ULS
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 UL / ROTAX 912 ULS
Noise level 65 dB(A) in the altitude of 160 m (2 blades propeller, full power)
Engine Performance
Take-off power 59,6 kW/80 HP/5800 RPM 73,5 kW/100 HP/5800 RPM
Maximum continuous power 58,0 kW/78 HP/5500 RPM 69,0 kW/94 HP/5500 RPM
Cruising power 37,7 kW/51 HP/4800 RPM 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.
Cylinder Head Temperature
Minimum 60°C 60°C
Maximum 150°C 135°C
Oil Temperature
Minimum 50°C 50°C
Maximum 140°C 130°C
Operating 90°C-110°C 90°C - 110°C
Oil Pressure
Maximum (short-term operated when cold start-up) 7,0 bar
Minimum 0,8 bar (below 3500 RPM)
Operating 2,0 –5,0 bar (over 3500 RPM)
Fuel Type 912 UL/80HP MOGAS EN228 Normal, Super or Super Plus / min. RON 90
912 ULS/100HP MOGAS EN228 Super or Super Plus/ min. RON 95

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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 conventional (mix ratio 1:1) or Evans (see the Rotax Manual)
The engine characteristics, operation and maintenance are preferentially directed by appropriate Rotax
Manual).
ROTAX 912 UL or ULS 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 NG aircraft with Rotax 912 UL/ULS
ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 9 of 56
1.6. Three-View Sketch
(mm)

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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
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

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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 290 km/h 157 kt
Do not exceed this speed in any case!
Design manoeuvre speed vA167 km/h 90 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 occure!
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 240 km/h 130kt
Do not exceed this speed at severe turbulence!
Max. speed, flaps extended I. (10 °) VFE,I 130 km/h 70 kt
Max. speed, flaps extended II. (20 °) VFE,II 120 km/h 65 kt
Max. speed, flaps extended III. (35 °) VFE,III 110 km/h 59 kt
Recommended speed, flaps extended III. VFE 90 km/h 49 kt
Do not exceed these speed limits when flaps extended!
Stall speed, flaps retracted vS1 73 km/h 39 kt
Flying this speed with flaps retracted results in loss of lift force and stall!
Stall speed in landing configuration vS0 54 km/h 29 kt
Flying this speed with flaps extended in position III. results in loss of lift force
and stall!

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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 maximum take-off weight of the aircraft!
2.4. Centre of Gravity ( CG )
CG of the empty aircraft % MAC
CG range allowance 25-35 % MAC

Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 UL/ULS
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
60
32,4
54
29,2
Vs1
78,4
42,3
73
39,4
VAF
86,2
46,5
83
44,8
VS1N
111,9
60,4
111
60,0
VF
110
59,4
110
59,4
VA
159
85,9
167
90,2
VG
158
85,3
166
89,6
VC
230
124,2
248
133,9
VH
249
134,5
269
145,3
VNE
268
144,7
290
156,6
VD
298,8
161,3
324
175,0

Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 UL/ULS
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 (when 472,5 kg MTOW)
Maximum positive load factor in CG + 5,05G
Maximum negative load factor in CG - 3,05G
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 180kg
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 NG aircraft with Rotax 912 UL/ULS
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
instrumental board in a visual field of 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 the weight of 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 NG aircraft with Rotax 912 UL/ULS
ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 16 of 56
INTENTIONALLY LEFT BLANK

Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 UL/ULS
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 NG aircraft with Rotax 912 UL/ULS
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 main switch just before landing.
Note: Electric flaps actuation is only possible when the main 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 obstacles.
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. If no significant failure on engine or its installation found, try again to start up the engine using
the back-up fuel circuit. The engine can be started by electric starter even though the propeller
turns in flight because of windmilling and its speed is not sufficient. It is not necessary to wait for
the standstill of the propeller.
4. 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 main switch and ignition
4. Make emergency landing
5. Get off the aircraft

Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 UL/ULS
ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 19 of 56
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 main 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!
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 level 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.

Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 UL/ULS
ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 20 of 56
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