Flight and operations manual of ATEC 321 Faeta NG aircraft with Rotax 912 iS
ATEC v.o.s., Libice nad Cidlinou, Czech Republic Page 6 of 59
1.3. Aircraft Description
ATEC 321 FAETA NG is an ultralight, two-seater, cantilever, low-wing aircraft of carbon composite
construction. The landing gear is a fixed tricycle undercarriage with steerable nose wheel. The propulsion
unit is in pulling configuration and consists of ROTAX 912 iS Sport engine and two or three-blade fix or
adjustable FITI propeller.
1.4. Modifications and Changes
If the Manufacturer makes any structural or operating changes necessary to be advised to the owner, a
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.
In his own interest, the owner of the aircraft should regularly check manufacturer´s or its authorized
representative´s websites, where actual informations and bulletins are published. In case the owner sells
the aircraft to another person, the owner shall announce this fact to the competent authority who has this
aircraft in its registry. The manufacturer should be also announced about the contact details 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
Defined deflections of controls
Flap position I 12 ° 55 mm +-5 mm
II 22 ° 105 mm +-5 mm
III 32 °145 mm +-5 mm
Ailerons deflection up 18 °80 mm +-3 mm
(measured towards end bow) down 14 °60 mm +-3 mm
Max. hinge moment 250 g (0,6 Nm)
(measured on the trailing edge in the distance of 250 mm from the turning point)
Elevator deflection up 24 °80 mm +-2 mm
(measured towards end bow) down 18 °60 mm +-2 mm
Max. hinge moment 130 g (0,3 Nm)
(measured on the trailing edge in the distance of 250 mm from the turning point)
VT Rudder deflection L/R +/-32°120 mm +-5 mm
(measured at the bottom of the trailing edge)
Max. hinge moment 600 g (2 Nm)
(measured on the trailing edge in the distance of 350 mm from the axis of turning)
Airfoil Section
Root section SM 701
End section SM 701
