I.C.P. Srl Savannah™VG FLIGHT MANUAL
Pag. 7
Issue 1/Revision 03
ICP Srl – S.P.16 km 15,150 14022 Castelnuovo Don Bosco (AT)
Jan.2012 Tel. 011.9927503 Fax 011.9927266
1.1 GENERAL SPECIFICATIONS
Dimensions
Wing span 30.0/8.98 ft/m
Wing area 128/11.9 sq. ft/m
2
Length 21.3/6.25 ft/m
Height 8.0/2.58 ft/m
Propeller diameter 68/1.73 in/m
Weights
Maximum take-off weight * 1000/454 lbs/kg
Empty weight** 600/272 lbs/kg
Useful load 400/182 lbs/kg
*Note: If the increase maximum take-off weight kit is installed, the Max take-off weight is increased
to 1234 lbs or 560Kg. Please make correction in your manual.
**NOTE: empty weight varies depending on the aiplane configuration requested by the owner.
Please refer to the weight and balance document to establish your precise aircraft empty weight.
Powerplant
Engine DIMENSION ROTAX 912 UL ROTAX912 ULS JABIRU2200
Take off performance 59.6 kW (5800 rpm) 75.3 kW (5800 rpm) (63.4 kW) 3300rpm
Displacement cu.in/cm
3
73.9/1211 82.5/1352 134/2200
Compression ratio 9.0:1 10.5:1 8:1
Fuel consumption (75% power) gph/lt/h 4.3/16.2 4.9/18.5 3.5/13
Fuel and oil
Fuel capacity 19/72 usgal/lt
Fuel grade Mogas/Avgas 91/100 LL
Oil capacity 3/3.16 lt/US qts
Landing gear
Wheel track 5.6/1.7 ft/m
Tire size 6 in
Tire pressure 14.5/1 psi/bar
1.2 STRUCTURE
The aircraft is a high wing single engine, with two side-by-side seats. The wings are supported by
struts and are a “high lift” NACA 650-18 modified airfoil with Junkers type flaperon (aileron + flap).
The airframe structure is full-metal with load-resisting panels. The horizontal stabilizer is a
simmetric bi-convex airfoil.
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