ICP SAVANNAH S Installation and operating instructions

SavannahTM-S Tail Dragger
Ultralight Aircraft
POH Addendum
English version
Page:1/11
Serial number
- -54-
Rev.02
ORIGINAL ISSUE DATE: 20.03.2013
REVISION DATE: 16.10.2017
Serial number - -54-Year 20 .
Manufacturer:
ICP S.r.l.
Address: Contacts:
S.p. 16 km 15,150 Phone: [phone]
Castelnuovo Don Bosco (AT) ITALY Fax: [phone]
14022 Web: www.icp.it
Email: [email protected]
The technical data and the information embodied therein are property of I.C.P. srl and shall not be disclosed
in whole or in part to third parties, without prior written permission of I.C.P. srl. The manual must remain with
the aircraft in case of sale.

SavannahTM-S Tail Dragger
Ultralight Aircraft
POH Addendum
English version
Page:2/11
Serial number
- -54-
Rev.02
ORIGINAL ISSUE DATE: 20.03.2013
REVISION DATE: 16.10.2017
1 Introduction.......................................................................................................................2
2.5 Landing Gear .............................................................................................................3
2.9 Aircraft Technical Specifications................................................................................4
4 WEIGHT AND BALANCE.................................................................................................5
4.1STANDARD INSTALLED EQUIPMENT LIST.............................................................5
4.2 BASIC EMPTY WEIGHT AND BALANCE DETERMINATION...............................6
4.3 BASIC EMPTY WEIGHT TABLE...............................................................................7
4.4 WEIGHT AND BALANCE COMPUTING TABLE AND GRAPH.................................8
7.5 NORMAL TAKE-OFF CHECKLIST..........................................................................11
11 LIST OF REVISIONS...............................................................................................11
1 Introduction
The Savannah S tail dragger version has the same weight of the standard version. The
increase in weight due to the additional structural parts is balanced by the nose landing
gear removal.
The aerodynamic configuration and the weight distribution of the tail dragger version has
not been modified except for the small increase of the rudder surface.
Operational speeds and operational limits remain unchanged, for this reason limits section
of the Pilot Operating Handbook remain unchanged.
In order to describe differencies of the tail dragger version and to describe weight and
balance measure and calculation an Addendum to the Pilot Operating Handbook has
been emitted.
The Addendum at the P.O.H. contains only the paragraph that varies form the standard
configuration.

SavannahTM-S Tail Dragger
Ultralight Aircraft
POH Addendum
English version
Page:3/11
Serial number
- -54-
Rev.02
ORIGINAL ISSUE DATE: 20.03.2013
REVISION DATE: 16.10.2017
2.5 Landing Gear
The main landing gear is composed of a single-piece aluminium 7075 alloy spring; the
spring is fixed to welded steel plates bolted to the fuselage. The tail wheel is a pivot small
wheel connected to the rudder command. When the tail wheel exceed 41° steering angle
the wheel is automatically disconnected from the command, allowing very close turn
(using differential braking). In order to reconnect the tail wheel to the control line it is
necessary to proceed in straight line, when the tail wheel steering angle decrease it
automatically reconnect to the controls.
Disc brakes are installed on main landing gear wheels and have hydraulic calliper. Two
hydraulic fluid cylinders are installed on the rudder pedals allowing pilot to perform
differential breaking. Brake system for both pilot and Co-pilot side as well as a park break
are options.
The parking brake (option) MUST be used only with engine-off and for short period of
time. Parking brake is composed of a shut off valve that isolates the brake cylinders from
the wheel callipers.
In order to set parking brake, pilot has to apply pressure on brake pedals, then with
pressure applied shut the parking brake valve (move PB lever).
CAUTION
If parking brake valve is moved on “BRAKE ON” position without having applied pressure
to the system, foot braking will no longer be available until parking brake is released and
no braking action will be provided.
In case of long term parking use chocks to prevent aircraft movements.
Brake fluid: mineral based oil (Renofluid 3.000 IT, Fiat TUTELA GI/A);
(DO NOT USE synthetic oil type DOT4)
Wheels size:6.00”x6.00” (4.00”x6.00” and Tundra tyres as options, as well as fairings)

SavannahTM-S Tail Dragger
Ultralight Aircraft
POH Addendum
English version
Page:4/11
Serial number
- -54-
Rev.02
ORIGINAL ISSUE DATE: 20.03.2013
REVISION DATE: 16.10.2017
2.9 Aircraft Technical Specifications

SavannahTM-S Tail Dragger
Ultralight Aircraft
POH Addendum
English version
Page:5/11
Serial number
- -54-
Rev.02
ORIGINAL ISSUE DATE: 20.03.2013
REVISION DATE: 16.10.2017
4 WEIGHT AND BALANCE
The following paragraphs explain the procedure to calculate and verify the weight and
balance of the aircraft.
WARNING
It is pilots responsibility to verify that take off and flight weight and balance conditions are
within limits. Failure to respect appropriate limits could lead to dangerous situations
4.1STANDARD INSTALLED EQUIPMENT LIST
SAVANNAHTM-S
Engine Rotax 912 ULS 100HP
Airbox with airfilter and airbox
temperature sensor
propeller “DUC Helice Swirl fixed
pitch adjustable on ground.
70lt wing tanks + 6lt collector in the
fuselage
Visual fuel level indicators
Anti vapour lock fuel return line
Central control stick with
mechanical flaps
4” tyres with disc brake system
fabric seats
12V/DC plug
cabin light
landing light
cabin heating
electric elevator
auxiliary electric fuel pump
doors snap vents
tie down kit
flight and maintenance manual
Basic flight instruments
NOTE
Installed options may vary total weight and weight distribution. If a configuration change
occurs, weighing should be performed to update weight and balance data.

SavannahTM-S Tail Dragger
Ultralight Aircraft
POH Addendum
English version
Page:6/11
Serial number
- -54-
Rev.02
ORIGINAL ISSUE DATE: 20.03.2013
REVISION DATE: 16.10.2017
4.2BASIC EMPTY WEIGHT AND BALANCE DETERMINATION
Forward C of G limit: 25% +/- 0.9 % (330 mm from L. E.) MAC
Rear C of G limit: 38.5%+/- 0.9 % (508 mm from L.E.) MAC
The aircraft is allowed to fly within a quite large weight and balance range thus easing the
aircraft’s load and balance.
Pilot should file the weight and balance table with crew’s weight, on board fuel weight and
luggage weight then check if condition remanis within limits, if not aircraft loading should
be revised.
WARNING
Failure to respect appropriate limits could lead to dangerous situations
In order to calculate weight and balance the basic empty weight and centre of gravity
position should be determined. Every time a configuration change occurs as addition or
removal of options, it is the pilot/owner’s responsibility to update the basic empty weight.
The aircraft MUST be weighed fitted with all equipment, accessories, engine oil,
coolant and WITHOUT FUEL. (NOTE: all the fuel MUST be drained accurately)
Place the aircraft in level flight attitude, rear fuselage upper skin should be
horizontal (Lift the tail).
Place the aircraft on three weight measuring equipment (one under each wheel of
the landing gear).
Record the three weight measuring equipment readings: the rear wheel weight will
be called P1, the left wheel weight P2, the right wheel weight P3.
By using a plumbing wire fixed to the leading edge, measure the distance DT
between the projection on the floor of the leading edge and the rear wheel axle,
and the distance DM between the same projected point and the main landing gear
axle.
Fill in the basic empty weight table reported below and calculate the momentum

SavannahTM-S Tail Dragger
Ultralight Aircraft
POH Addendum
English version
Page:7/11
Serial number
- -54-
Rev.02
ORIGINAL ISSUE DATE: 20.03.2013
REVISION DATE: 16.10.2017
4.3 BASIC EMPTY WEIGHT TABLE
Aircraft serial number
Weight measuring equipment
Location and date
Certifying staff
Weight [lbs] /[Kg]
Arm [ft] /[m]
Mom.[lbs x ft] / [kg x m]
Rear
landing
gear
PT= P1
DT
Main
gear
PM =P2+P3
DM
TOTAL
The centre of gravity position of the aircraft measured from the wing leading edge can be
found with the following formula:











MT
MMTT
CG PP DPDP
X
Signature

SavannahTM-S Tail Dragger
Ultralight Aircraft
POH Addendum
English version
Page:8/11
Serial number
- -54-
Rev.02
ORIGINAL ISSUE DATE: 20.03.2013
REVISION DATE: 16.10.2017
4.4 WEIGHT AND BALANCE COMPUTING TABLE AND GRAPH
Before any flight, the pilot must check the weight and balance compiling the following
table:
Compile the weight column with data from the empty weight table, crew weight, fuel
weight, and baggage weight (if present).
Compile the arm of the empty aircraft with the XCG position previously obtained.
Multiply weight and arm and compile the “Momentum” column.
Sum the columns and compile the “Totals” line.
Weight W [lbs]/[Kg]
Arm X [ft]/[m]
Momentum [W x X]
Empty aircraft
Pilot
1.80
0.55
Passenger
1.80
0.55
Fuel
1.62
0.495
Baggage
4.33
1.32
TOTALS
===============
===============
Actual centre of gravity position can be obtained with the following formula or from the
following charts.
 
100
...
100
...
%








 CAM tTotalweigh
tumTotalMomen
CAM
X
XCG
CG
Where:
Total weight is the total of the weight before considered in the table
Total moment is the total of the moment before obtained in the table
MAC is the Mean Aerodynamic Chord that is equal to 1320mm/4.33ft.
WARNING
Use homogenous unit of measure!

SavannahTM-S Tail Dragger
Ultralight Aircraft
POH Addendum
English version
Page:9/11
Serial number
- -54-
Rev.02
ORIGINAL ISSUE DATE: 20.03.2013
REVISION DATE: 16.10.2017

SavannahTM-S Tail Dragger
Ultralight Aircraft
POH Addendum
English version
Page:10/11
Serial number
- -54-
Rev.02
ORIGINAL ISSUE DATE: 20.03.2013
REVISION DATE: 16.10.2017
7.5 Normal takeoff
1. Wing flaps in the takeoff position (Flaps at 15°);
2. Air Box control set for cold air intake (if installed).
3. Engine at 5800 RPM (if installed a variable pitch propeller);
4. Propeller at takeoff pitch (if adjustable in flight);
5. Push the stick to lift the tail;
6. At 60 Km/h (38 mph / 33 KIAS) lift the front wheel by pulling the bar;
7. At 100 Km/h (62 mph / 54 KIAS) set the climb;
8. Throttle open and propeller pitch (if adjustable in flight) so as to achieve 5800 RPM;
8.9 Normal landing
1. Touch down if possible with all wheels;
2. Taxi on the ground up to halting with the control bar pulled (elevator turned
upwards);
After landing
1. Wing flaps in;
2. Carry on keeping the control rod pulled;
Engine shutdown
1. Keep the throttle pulled (engine to the minimum level ) for two minutes
approximately:
2. Radio off;
3. Both ignition switches disengaged;
4. Main switch off.
DANGER
SAFETY WARNING DURING AN ABORTED LANDING: Pay attention not to pull the bar too
much. In this phase it is necessary to gain speed first and then to gain height. The aircraft
would otherwise slow down up to stalling and falling wing down due to the strong
overturning torque generated by the fully powered propeller.
8.10 Short field takeoff and landing procedures
Short takeoff
1. Apply pressure on the brakes;
2. Air Box control for cold air intake.
3. Wing flaps fully out (Flaps at 30°);
4. Throttle fully forward so as to obtain 5800 RPM (if installed a variable pitch
propeller);
5. Propeller at takeoff pitch (if adjustable in flight);
6. Release the brakes;
7. At 50 Km/h (31 mph / 27KIAS) lift the front wheel by pulling the bar;
8. At 70 km/h (44 mph / 38 KIAS) set the climb;

SavannahTM-S Tail Dragger
Ultralight Aircraft
POH Addendum
English version
Page:11/11
Serial number
- -54-
Rev.02
ORIGINAL ISSUE DATE: 20.03.2013
REVISION DATE: 16.10.2017
7.5 NORMAL TAKE-OFF CHECKLIST
1. Set Flap 1/2;
2. Set Trim neutral;
3. Switch ON Electric Fuel Pump and EXT. LIGHTS;
4. Verify CARB HEAT not used;
5. Throttle advance to max power;
6. Verify T/O RPM;
7. Push the stick to lift the tail;
8. Rotate at 65 kph / 41 mph / 35 kts @ 500 kg;
9. Accelerate to best climb speed 105kph /65 mph / 57 kts @ 500 kg;
10.Retract Flaps;
11.At safe altitude, reduce throttle;
12.If ice condition exists, apply Carb heat;
CAUTION
Hot air from Airbox (Carb heat) will decrease the probability of carburettor ice, but does
not completely prevent it, Carburator ice conditions should be avoided and carburettor
heat should be used each time suspect of icing conditions exist.
11LIST OF REVISIONS
A list of all revisions made to the Pilot Operating Handbook since its original issue are
resumed in the table below.
Revision No.
Date
Chapters
Pages
Original Issue
20.03.2013
N/A
N/A
01
10/7/2015
General revision
all
02
16/10/2017
Added CG limits in mm
6/11
CAUTION
During take-off run remember to keep the heels on the floor to avoid braking.