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

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 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)

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 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