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 (a flap).
The airframe structure is full-metal with load-resisting panels. The horizontal stabilizer is a
simmetric bi-convex airfoil.
