Atec 321 FAETA Flight And Operation Manual
Flight and Operations Manual of ATEC 321 Faeta UL aircraft
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 1 of 53
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
Flight and Operations Manual
Libice nad Cidlinou, March 2011
Flight and Operations Manual of ATEC 321 Faeta UL aircraft
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 2 of 53
Type of aircraft:
ATEC 321 FAETA
Serial number :
Registration/call sign:
LAA CR 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 UL aircraft
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 3 of 53
Contents Chapter
General
1
Operational 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 UL aircraft
ATEC v.o.s. Libice nad Cidlinou, Czech Republic 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
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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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ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 6 of 53
1.3. Aircraft Description
ATEC 321 FAETA 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 front wheel. The power unit
is of pulling configuration and consists of ROTAX 912 iS engine and of two-blade or three-blade fix or
ground adjustable FITI propeller.
1.4. Modifications and Changes
If any structural or operational changes are made by the Manufacturer and need to be advised to the
owner, the related documentation will be delivered to you and you are obliged to record them into
your Manual. These documents will be published in ascending numerical series.
If the aircraft is sold to another person, the Manufacturer shell be announced about 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 m2
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 base 1,4 m
Tire dimensions 350 x 120
Tire pressure 0,16 MPa / 1,6 atp
Suspension
Main gear composite springs
Front wheel rubber suspension
Flight and Operations Manual of ATEC 321 Faeta UL aircraft
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 7 of 53
Brakes hydraulic disc brakes 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 Republic
Type of propeller FITI ECO COMPETITION 2 blade / 3 blade
Engine producer BOMBARDIER – ROTAX GmbH, 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 bar
Minimum 0,8 bar (engine speed below 3500 RPM)
Operational 2,0 – 2,5 bar (over 3500 RPM)
Fuel Type Recommended motor unleaded petrol of minimum octane number RON 95, 97
Flight and Operations Manual of ATEC 321 Faeta UL aircraft
ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 8 of 53
Oil Type Any brand-name oil intended for 4 stroke motorcycle engines,
containing gearbox 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 responsible 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 responsibility of the pilot.
The pilot of a sport flying device is obliged to consider the flight altitude and flight track so that he
could be able to make safety landing in case of engine failure.
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1.6. Three-View Sketch
Flight and Operations Manual of ATEC 321 Faeta UL aircraft
ATEC v.o.s. Libice nad Cidlinou, Czech Republic 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. Labels 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 vNE 270 km/h 146 kt
Do not exceed this speed in any case!
Design manoeuvre speed vA 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 vC 230 km/h 123 kt
Do not exceed this speed except the flight in smooth air, but with caution!
Max. cruising speed at severe turbulence vRA 224 km/h 122 kt
Do not exceed this speed at severe turbulence!
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. VFE 90 km/h 49 kt
Never exceed these speed limits when flaps deflected!
Stall speed, flaps retracted vS1 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 vSO 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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ATEC v.o.s. Libice nad Cidlinou, Czech Republic Page 14 of 53
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
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 by visual reference to the ground during the daytime)
IFR flights ( instrument 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
2.10. Fuel tank
Fuel capacity 2 x 50 L
Not usable rest of fuel 1,2 L
Recommended motor unleaded petrol of minimum octane number RON 95, 97
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 against wind up to 12 m/s
b) 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 mobile phone, explosives and combustible materials and movable objects
transportation 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 pilot and must contain following information:
- Identification of the aircraft
• Identification label
• Serial number
• 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 aerobatics prohibition
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