ICP Savannah VG Technical specifications

I.C.P. Srl Savannah™VG FLIGHT MANUAL Pag. 1
Issue 1/Revision 03 ICP Srl – S.P.16 km 15,150 14022 Castelnuovo Don Bosco (AT)
Jan.2012 Tel. [phone] Fax [phone]
AIRPLANE FLIGHT MANUAL
Savannah™VG
Copyright I.C.P. 2002
Savannah™ is registered trademark solely owned by ICP Srl and their use in any form is strictly
forbidden.
The content of this manual is the sole property of I.C.P. srl and cannot be reproduced by third
parties in any form whatsoever without ICP’s previous written authorization.

I.C.P. Srl Savannah™VG FLIGHT MANUAL Pag. 2
Issue 1/Revision 03 ICP Srl – S.P.16 km 15,150 14022 Castelnuovo Don Bosco (AT)
Jan.2012 Tel. [phone] Fax [phone]
LOG OF REVISIONS
Revision
Number
Revised
Pages
Description of Revision Date
00 All New emission 07/06
01 36, 37 Updated data on W&B 01/07
02 19, 37 Updated front limit CG and minimum WTO 03/07
03 all General revision 01/2012

I.C.P. Srl Savannah™VG FLIGHT MANUAL Pag. 3
Issue 1/Revision 03 ICP Srl – S.P.16 km 15,150 14022 Castelnuovo Don Bosco (AT)
Jan.2012 Tel. [phone] Fax [phone]
TABLE OF CONTENTS
SECTION 1 TECHNICAL DESCRIPTION
SECTION 2 LIMITATIONS
SECTION 3 EMERGENCY PROCEDURES
SECTION 4 NORMAL PROCEDURES
SECTION 5 PERFORMANCE
SECTION 6 WEIGHT AND BALANCE

I.C.P. Srl Savannah™VG FLIGHT MANUAL Pag. 4
Issue 1/Revision 03 ICP Srl – S.P.16 km 15,150 14022 Castelnuovo Don Bosco (AT)
Jan.2012 Tel. [phone] Fax [phone]
TABLE OF CONTENTS
SECTION 1
TECHNICAL DESCRIPTION
Paragraph Page
Airplane views and dimensions 5
1.1 General specifications 7
1.2 Structure 8
1.3 Landing gear 8
1.4 Engine 8
1.5 Engine controls 8
1.6 Propeller 9
1.7 Fuel system 9
1.8 Electrical system 9
1.9 Cabin 10
1.10 Cabin features and upholstery 10
1.11 Ventilation 10
1.12 Cabin heating 10
1.13 Instrument panel 14
1.14 Flight controls 15
1.15 Flaps control system 15
1.16 Pitot-static system 15
1.17 Baggage compartment 15

I.C.P. Srl Savannah™VG FLIGHT MANUAL Pag. 5
Issue 1/Revision 03 ICP Srl – S.P.16 km 15,150 14022 Castelnuovo Don Bosco (AT)
Jan.2012 Tel. [phone] Fax [phone]
AIRPLANE VIEWS (Rotax 912/912 S)
Wing span: 30ft/8.98 m
Lenght: 21.3ft/6.25m
Height: 8ft/2.58m
Track: 5.57ft/1.7m

I.C.P. Srl Savannah™VG FLIGHT MANUAL Pag. 6
Issue 1/Revision 03 ICP Srl – S.P.16 km 15,150 14022 Castelnuovo Don Bosco (AT)
Jan.2012 Tel. [phone] Fax [phone]
AIRPLANE VIEWS (Jabiru 2200)
Wing span: 30ft/8.98 m
Lenght: 21.3ft/6.25m
Height: 8ft/2.58m
Track: 5.57ft/1.7m

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. [phone] Fax [phone]
1.1 GENERAL SPECIFICATIONS
Dimensions
Wing span 30.0/8.98 ft/m
Wing area 128/11.9 sq. ft/m2
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/cm373.9/1211 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.

I.C.P. Srl Savannah™VG FLIGHT MANUAL Pag. 8
Issue 1/Revision 03 ICP Srl – S.P.16 km 15,150 14022 Castelnuovo Don Bosco (AT)
Jan.2012 Tel. [phone] Fax [phone]
1.3 LANDING GEAR
The aircraft has a tri-cycle type landing gear. The main landing gear is made by a single-piece
aluminium alloy single-leaf leg. The nose landing gear has a telescopic, elastic chord shock absorber
and is steerable in order to ease the taxiing.
1.4 ENGINE
This aircrft has two engine installation options: the ROTAX 912 ULS/ROTAX 912 UL or
Jabiru2200. Please refer to Engine manual for any data and specifications.
WARNING: Rotax and Jabiru manufacturers issue several service and information bulletins.
It is the owner’s responsibility to acquire these documents available at www.rotax-aircraft-
engines.com or www.jabiru.net.au.
WARNING: All engines are subject to sudden stoppage. Engine stoppage can result in crash
landings, forced landings or no power landings. Such crash landings can lead to serious bodily
injury or death. Never fly the aircrafts at locations, airspeeds, altitudes, or other circumstances
from which a successful no power landing cannot be made.
These engines are not certificated aircraft engines. They have not received any safety or
durability testing and may not conform to aircraft standards.
User assumes all risks of use and fully acknowledges by his use that he knows this engine is
subject to sudden stoppage.
Note: check your country’s regulations to establish the approved condition in which the
airplane can be flown (VFR/IFR, Night/Day) and the type of airworthiness certificate that can
be issued.
1.5 ENGINE CONTROLS
There are two push-pull throttle controls with a friction adjusting knob. In the Jabiru
installation the mixture control is located near the pilot’s side throttle control. In the Rotax
installation the choke is in that position. The air-box control (Rotax 912 ULS) is located near the
throttle control: pull for hot air to carburetors, push for cold air to carburetors (for values of
temperature to maintain see chapter 2.3).
The key-operated master switch connects the electrical system to the 12V battery. The whole
electrical system is protected by thermal type re-settable breakers.
The engine can be operating with the master switch OFF and the breakers OFF since the
ignition system is independent. It can only be turned off by switching OFF the two magnetos
switches. All of the electrical instruments and devices, including the engine starter will not operate
when the master switch is OFF.
WARNING: The engine may start with the master switch OFF, if the magnetos switch (even
only one) is ON and the propeller is hand rotating or windmilling. For safety, it is strongly
recommended to pull-out the master switch key when exiting the cabin.

I.C.P. Srl Savannah™VG FLIGHT MANUAL Pag. 9
Issue 1/Revision 03 ICP Srl – S.P.16 km 15,150 14022 Castelnuovo Don Bosco (AT)
Jan.2012 Tel. [phone] Fax [phone]
The master switch key is located near the pilot’s throttle. All the switches and the engine
controls are turned ON if moved UPWARD or FORWARD. Only the mixture control is operated
by pulling it BACKWARD or the choke in the Rotax installation.

I.C.P. Srl Savannah™VG FLIGHT MANUAL Pag. 10
Issue 1/Revision 03 ICP Srl – S.P.16 km 15,150 14022 Castelnuovo Don Bosco (AT)
Jan.2012 Tel. [phone] Fax [phone]
1.6 PROPELLER
One of the following propellers may be installed on this airplane:
-“DUC Helice”, 3 blades in carbon fiber (Rotax 912 ULS), adjustable on ground.
-“DUC Helice”, 2 blades in carbon fiber (Rotax 912 UL), adjustable on ground.
-2 BLADES IN CARBON FIBER (Jabiru2200)
1.7 FUEL SYSTEM
With reference to fig. 1 on page 11, the fuel system is equipped with two tanks (1, 2). They
are installed in the wings and have a 72 lt (19 gal) capacity. The filler caps have a vent hole. The
reservoirs have an overcapacity fuel pipe ending below the wings. The left fuel tank has a visual fuel
level indicator located on left wing first rib. The drain valve (5) is located in the fuel tank behind the
right seat (3). A fuel reserve warning light is installed to indicate low remaining fuel in the collector
tank behind the seat. The installed fuel valve (7) is held in the OPEN position by a safety wire. That
safety wire can be broken in an emergency. This safety wire is used to prevent an accidental in-flight
fuel valve closure leading to an engine shut-down or, even worse, to a closed fuel valve take-off. The
fuel pump (8) is mechanically operated by the engine, a fuel pressure gauge is installed to check the
system operation.
1.8 ELECTRICAL SYSTEM
With reference to fig.2 on page 12, the airplane’s electrical system includes a 12V battery, a
generator, wiring and switches to supply and connect the engine starter, an auxiliary fuel pump, anti-
collision, navigation lights and the avionics. A voltmeter is provided as a standard equipment.
The key-operated master switch connects the electrical system to the 12V battery. The whole
electrical system is protected by thermal type re-settable breakers.
With the master switch OFF any electrical instrument and all other electrical devices, electric
engine starter included, will not operate.
With reference to fig. 2:
A. starter relay
B. voltage regulator
C. electric fuel pump
D. master switch
E. power supply (aux)
F. elevator trim motor
G. battery
4. RPM gauge
5. hourmeter
6. voltmeter
7. left head temperature
8. right head temperature
9. oil temperature
10. oil pressure
15. low voltage warning lamp
18. elevator trim switch
21-25 switches

I.C.P. Srl Savannah™VG FLIGHT MANUAL Pag. 11
Issue 1/Revision 03 ICP Srl – S.P.16 km 15,150 14022 Castelnuovo Don Bosco (AT)
Jan.2012 Tel. [phone] Fax [phone]
26-27 breakers
FUEL SYSTEM
Figure nr.1

I.C.P. Srl Savannah™VG FLIGHT MANUAL Pag. 12
Issue 1/Revision 03 ICP Srl – S.P.16 km 15,150 14022 Castelnuovo Don Bosco (AT)
Jan.2012 Tel. [phone] Fax [phone]
ELECTRIC SYSTEM (engines ROTAX 912 and 912S)
Figure nr.2

I.C.P. Srl Savannah™VG FLIGHT MANUAL Pag. 13
Issue 1/Revision 03 ICP Srl – S.P.16 km 15,150 14022 Castelnuovo Don Bosco (AT)
Jan.2012 Tel. [phone] Fax [phone]
ELECTRIC SYSTEM (engine JABIRU 2200)
Figure nr.2bis

I.C.P. Srl Savannah™VG FLIGHT MANUAL Pag. 14
Issue 1/Revision 03 ICP Srl – S.P.16 km 15,150 14022 Castelnuovo Don Bosco (AT)
Jan.2012 Tel. [phone] Fax [phone]
1.9 CABIN
Two large lateral doors allow an easy indipendent access to the cabin. They are hinged with two
hinges on the upper edge of the doors. They may be locked by a key handle located in the lower
edge and by a latch in the front edge. The doors may be removed unscrewing the hinges, if so
desired (flying in hot regions or to take pictures). The doors MUST NOT be opened in flight.
WARNING: Is very important to verify that the latch in the front edge of the door is locked before
taking off.
1.10 CABIN FEATURES AND UPHOLSTERY
The cabin arrangement features two canvas covered side-by-side seats.
1.11 VENTILATION
The cabin’s ventilation is provided by an opening between the doors and the upper part of
the cabin door frame. A dynamic air scoop intended to extract the cabin air is installed at the top of
the baggage compartment. Cabin ventilation may be improved by using two rotating air scoops in
the doors windows. It is important to achieve an efficient cabin ventilation to prevent windshield
condensation in high humidity, low temperature weather conditions.
1.12 CABIN HEATING
On the upper right side of the instrument panel there is a push-pull control. Pull it for hot
ventilation in the cockpit. The outlet may be opened by a rotating panel on the cockpit glare shield.
The air is heated by a heat exchanger located around the muffler.
.
1.13 INSTRUMENT PANEL
ATTENTION:
The installed instruments are not certified according to any aeronautical regulations.
Dangerous flight conditions should be avoided at all times.
Do not consider the values given by the instruments as an absolute value.
As standard equipment the following instruments are fitted:
Each aircraft may have different instrument configuration according to customers request.

I.C.P. Srl Savannah™VG FLIGHT MANUAL Pag. 15
Issue 1/Revision 03 ICP Srl – S.P.16 km 15,150 14022 Castelnuovo Don Bosco (AT)
Jan.2012 Tel. [phone] Fax [phone]

I.C.P. Srl Savannah™VG FLIGHT MANUAL Pag. 16
Issue 1/Revision 03 ICP Srl – S.P.16 km 15,150 14022 Castelnuovo Don Bosco (AT)
Jan.2012 Tel. [phone] Fax [phone]
1.14 FLIGHT CONTROLS
The aircraft is controlled by a single “Y” shaped stick and dual conventional rudder pedals.
Two operated brakes controls are installed on the pilot’s side only. The aircraft is equipped with one
longitudinal electrical trim.
Flaperons range: ±15° (±2°)
Elevator: UP 29°±3°, DOWN 25°±3°
Rudder range: ±25° (±2°)
1.15 FLAPS CONTROL
In the Savannah, the system controling the “flaperons” (a full-spaning trailing edge movable
surfaces), is located on the cabin floor.
With the stick in the center and the flaps control lever full forward the flaps are fully retracted.
With the flaps control lever in the intermediate position the flaps are 20° (±3°) down.
With the flaps control lever full back the flaps are fully extended 40° (±3°) down.
In the Savannah VG is it possible to install an electric motor (installed under the pilot seat) to
operate the “flaperons” with a switch on the instrument panel.
The maximum speed for flaps extension is 60mph (96Km/h).
1.16 PITOT-STATIC SYSTEM
The ram air to the pitot-static instruments is supplied by the Pitot tube located on the left
hand forward wing strut.
No static pressure source is provided on the earlier model.
On later model the static pressure port is located on the left fusolage.
WARNING: blowing into the Pitot tube may damage the airspeed indicator.
1.17 BAGGAGE COMPARTMENT
An open space behind the seats is provided to carry some baggage up to 45 lbs.
The luggage MUST be evenly arranged on the baggage compartment floor and firmly fastened.
NOTE: the pilot MUST check, before every flight, that the weight and balance of the aircraft are
within the allowed limits.

I.C.P. Srl Savannah™VG FLIGHT MANUAL Pag. 17
Issue 1/Revision 03 ICP Srl – S.P.16 km 15,150 14022 Castelnuovo Don Bosco (AT)
Jan.2012 Tel. [phone] Fax [phone]
FLIGHT CONTROLS
Figure nr.3

I.C.P. Srl Savannah™VG FLIGHT MANUAL Pag. 18
Issue 1/Revision 03 ICP Srl – S.P.16 km 15,150 14022 Castelnuovo Don Bosco (AT)
Jan.2012 Tel. [phone] Fax [phone]
TABLE OF CONTENTS
SECTION 2
LIMITATIONS
Paragraph Page
2.1 Speed limits 18
2.2 Load factors 18
2.3 Engine operations limits 18
2.4 Weight limitations 19
2.5 C of G limitations 19
2.6 Weather flying conditions 19
2.7 Type of maneuverings 19
2.8 Max demonstrated crosswind for T/O and landing 19

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Issue 1/Revision 03 ICP Srl – S.P.16 km 15,150 14022 Castelnuovo Don Bosco (AT)
Jan.2012 Tel. [phone] Fax [phone]
2.1 SPEED LIMITS
NOTE: the following speed limits (IAS) are set at a maximum take off weight of 1000 lbs/454 kg
Stall speed, full flaps, Vso 30 mph / 48 km/h
Flaps range (white arc) 30-60 mph / 48-96 km/h
Stall speed, no flaps, Vs 35 mph / 56 km/h
Normal operating range (green arc) 35- 93mph / 56-150 km/h
Max. maneuvering speed (1) 85 mph / 137 km/h
Caution zone (yellow arc) (2) 93-125 mph / 150-201 km/h
Vmo 100 mph / 160 km/h
Never exceeding speed, Vne (red line) 125 mph / 201 km/h
Flaps speed limit 60 mph / 96 km/h
NOTES:
(1): the maximum maneuvering speed is the maximum speed at which the flight controls can be
abruptly move to full deflection with out over stressing the airplane (maximum movable surfaces
deflection angles);
(2): when flying in turbulence conditions this speed range has to be avoided.
2.2 LOAD FACTORS
Flaps retracted + 4 g - 2 g
Flaps full extended + 2 g ----
NOTE: the maximum load factors (limit load factors) are obtained multiplying the above indicated
values by the coefficient 1.5.
2.3 ENGINE OPERATIONS LIMITATIONS
·Maximum RPM for T/O and climb 5800 RPM (5 min.) (red line)
·Caution range 5500-5800 RPM (yellow arc)
·Normal range 1400-5500 RPM (green arc)
·Maximum continuous power 5500 RPM
·Idle speed around 1400 RPM
·Oil pressure normal range 2-5 bar (29-73 psi) (green arc)
caution range 5-7 bar (73-102 psi) (yellow arc)
min. 0.8 bar (12 psi) (red line), max 7 bar (102 psi) (red
line)
·Oil temperature normal range 90-110 °C (green arc)
caution range 50-90 / 110-140 °C (yellow arc)
max 140 °C (red line)
·Fuel pressure max 0.4 bar (5.8 PSI)
Min 0.15 bar (2.2 PSI)
·Air-box temperatures (Only 912 ULS)Caution range 18 °C – 20 °C (yellow arc)
Caution range 24 °C – 35 °C (yellow arc)
Normal range 20 °C – 24 °C (green arc)
Minimum air box temp. 18 °C
Maximum air-box temp. 35 °C (red line)

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ENGINE OPERATION LIMITATIONS (engine JABIRU 2200)
·Maximum RPM for T/O and climb 3300 RPM (red line)
·Continuous RPM 3300 RPM
·Idle speed around 900 RPM
·Oil pressure normal range 220-525 kPa (green arc)
min. 80 kPa (red line), max 525 kPa (red line)
·Oil temperature normal range 80-100 °C (green arc)
Min. temp for operation 15°C (red line)
max 118 °C (red line)
·Fuel pressure max 20 kPa (2.9 PSI)
min 5 kPa (0.7 PSI)
CHT temperature Normal range 180 °C (356 °F) – 200 °C (392 °F) (green arc)
2.4 WEIGHT LIMITATIONS
Maximum take off weight: 454 kg*
Minimum take off weight (minimum pilot weight 55 kg and ½ h flight fuel **): 336 kg
*Note: If the increase maximun take-off weight kit is installed, the Max take-off weight is
increased to 1234 lbs or 560Kg. Please make correction in your manual.
(**) According to CS-VLA-25
2.5 CG LIMITATIONS
Forward CG limit: 25% MAC +/- 0.9 % (*)
Rear CG limit: 38.5% MAC +/- 0.9% (*)
(*) According to CS-VLA-21
See also section 6.
2.6 WHEATHER FLYING CONDITIONS
Check your country regulation to determine the allowable flying condition (VFR/IFR and
DAY/NIGHT)
2.7 TYPE OF MANEUVERINGS
The airplane is intended for non-aerobatic operations only. Intentional Spins are proibited.
2.8 MAX CROSSWIND FOR T/O AND LANDING
The maximum demonstrated cross-wind component allowed during take-off and landing is 30/48
mph/km/h.