2.III.8 Maximum operating altitude 15 544 m (51,000 ft)
200 kts 0,70 245 kts 0,75 80 kts (CAS) 81,3 kts (CAS) Datum is 25 per cent of mean aerodynamic chord (MAC): 12 183 mm from the forward end of the aircraft nose cone
2.III.9 All-weather capability
Category I Auto Pilot
2.III.10 Maximum Mass
Mean aerodynamic chord (MAC): 3 347.54 mm
Mass Forward limit % MAC Aft limit % MAC
kg lbs
Minimum flight - Aft Minimum flight - Forward Maximum zero fuel Maximum landing Maximum for aft CG at 38,5 % Maximum takeoff Maximum ramp 14 696 15 694 18 597 28 304 25 890 31 298 31 389 32 400 34 600 41 000 62 400 57 078 69 000 69 200 N/A 26.0 19.5 19.5 19.5 19.5 19.5 38.5 N/A 38.5 38.5 38.5 33.65 31.5
For mass and balance calculation refer to the Loading Manual (manufacturer document reference) -See Note 1.
2.III.11 Leveling means
Aircraft is leveled in the longitudinal and lateral axis by means of a plumb bob and target in the left main landing gear bay
2.III.12 Minimum flight crew:
2 — pilot and copilot
2.III.13 Maximum Seating Capacity:
2 + 1 crew — third crew member seat authorized for take-off and landing in the cockpit. 19 passengers in cabin. See note 2.
2.III.14 Exits
Type Size
1 Passenger door I 0.800 x 1.72 m (31.50 x 67.72 in)
1 Emergency exit III 0.534 x 0.916 m (21.02 x 36.06 in)
2.III.15 Baggage/cargo compartments
Baggage compartment: 909 Kg, not to exceed 400 kg per square meter. See note 2.
2.III.16 Wheels and tyres
This aircraft is equipped with wheels, brakes and H type radial tubeless tires.
Main wheel tyres are H32×10.5R16.5 Nose wheel tyres are 16×6.0R6
No mixabiality (tyre manufacturer + others) is not approved.
2.IV Aircraft name Operating and Service Instructions
The aircraft must be operated according to the EASA approved Airplane Flight Manual manufacturer document reference
The Instructions for Continued Airworthiness consist of:
Maintenance Review Board Report Manufacturer document reference Airplane Maintenance Manual Manufacturer document reference Structural Repair Manual Manufacturer document reference CMR and ALI
2.V Notes Note 1:
a) A current mass and balance report must be carried in the aircraft at all times from the moment the aircraft is originally certified.
b) Loading of the aircraft must be accomplished in a manner that always maintains the center of gravity within the specified limits considering crew and passenger movements as well as fuel consumption and transfer.
Note 2:
Cabin interior and seating configuration must be approved.
— — — — — — — —
APPENDIX C.— EXAMPLE OF SMALL AEROPLANE ICA CHECKLIST
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS (ICA) REQUIREMENTS Regulation Appendix (sample reference) Location In ICA
( ) ICA for each engine. G23.1(b)
( ) ICA for each propeller. G23.1(b)
( ) ICA for each appliance required by this chapter. G23.1(b)
( ) Required information on the interface of ( ) appliances, ( ) engines, and ( ) propellers with the aircraft. G23.1(b)
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