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
ATEC v.o.s. Li ice nad Cidlinou, Czech Repu lic Page 2 of 53
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.

Flight and Operations Manual of ATEC 321 Faeta UL aircraft
ATEC v.o.s. Li ice nad Cidlinou, Czech Repu lic Page 3 of 53
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

Flight and Operations Manual of ATEC 321 Faeta UL aircraft
ATEC v.o.s. Li ice nad Cidlinou, Czech Repu lic Page 4 of 53
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 UL aircraft
ATEC v.o.s. Li ice nad Cidlinou, Czech Repu lic Page 5 of 53
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 UL aircraft
ATEC v.o.s. Li ice nad Cidlinou, Czech Repu lic Page 6 of 53
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

Flight and Operations Manual of ATEC 321 Faeta UL aircraft
ATEC v.o.s. Li ice nad Cidlinou, Czech Repu lic Page 7 of 53
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

Flight and Operations Manual of ATEC 321 Faeta UL aircraft
ATEC v.o.s. Li ice nad Cidlinou, Czech Repu lic Page 8 of 53
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.

Flight and Operations Manual of ATEC 321 Faeta UL aircraft
ATEC v.o.s. Li ice nad Cidlinou, Czech Repu lic Page 9 of 53
1.6. Three-View Sketch

Flight and Operations Manual of ATEC 321 Faeta UL aircraft
ATEC v.o.s. Li ice nad Cidlinou, Czech Repu lic Page 10 of 53
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