ICP Savannah Airplane Flight Manual

l I.C.P. Sri j

Savannah

FLIGHT

MANUAL

Pag.

11

AIRPLANE

Savannah

FLIGHT

MANUAL

/

Issue l /Revision l

Apr.

Ol

ICP

Sri-

Phone

l

l

Via Torino 12, 14020 PIOVA' MASSAIA

[phone] • Fax [phone]

(AT)-

Italy

l I.C.P.

Sri

Pag.

J

Savannah

FLIGHT

MANUAL

21

Page

l

2
3
4
5
6
7
8
9

lO

11

12
13
14
15
16
17
18

19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
35

36
37

LIST

OF

THE

Conten

Original l l
Original l 5 July
Original
Original l l
Original
Original
Original
Original l
Original
Original l
Original
Original l l
Original l l Apr.
Original
Original l l Apr.
Original l l Apr.
Original l l Apr.
Original l 2
Original

Original l l
Original l 2 Ott.02
Original
Original l l
Original l 2 Ott.02
Original l l Apr.
Original l l Apr.
Original l l Apr.
Original
Original l l Apr.
Original
Original
Original l 2
Original
Original l 2
Original
Original

Original

EFFECTIVE

t

PAGES

Is

s u e Rev.

l

l
l
l 2

l

l 2

l 4 July

l l

l l

l 2

l l Apr.
l l Apr.

l l Apr.

l l
l l Apr.
l l

5

2 July
6 July '04

3
3
3 Julv

Date

Apr.

Ju~v

Apr.

Ott.
July
July

Ott.

Apr.

Ott.

Apr.
Apr.

Apr.
Apr.

Ott.

Ott.

Ott.

Apr.

Apr.

Ol

'03
'03

Ol

'03

02
'03
'03
'03
02

Ol
Ol

'03

Ol
Ol
Ol

02

Ol
Ol

Ol
Ol

Ol
Ol
Ol

02

Ol
Ol
Ol

02

Ol

02

Ol
Ol
Ol

Issue l /Revision 6

July'04

ICP

Sri-

Phone

Via

Torino 12, 14020

[phone] • Fax [phone]

PlOV

A'

MASSAIA

(AT)-

Italy

l I.C.P. Sri l

Savannah

FLIGHT

MANUAL

LOG OF REVISIONS

Revision Revised Description o f Revision Date
Number Pages

00

Ol

02

03
04
05

06

All
All

6 to11,18,

21,24,28,

32,34

2,3,14,

2,3,14

2,3,5,8,9,

10

2,3,6

New emission

Cerreetions 04/01
Cerreetions 10/02

Cerreetion 10/02

N o te o n Instruments

N o te o n Engine

03/01

Ju1y
Ju1y

Pag.31

'03
'03

Issue l /Revision 6

July '04

ICP

Sri-

Via Torino 12, 14020 PIOVA' MASSAIA

Phone [phone]

• Fax [phone]

(AT)-

Italy

l I.C.P.

Sri

Pag.

j

Savannah

FLIGHT

MANUAL

41

SECTION l

SECTION2

SECTION 3

SECTION 4

SECTIONS

SECTION 6

TABLE

OF

CONTENTS

AIRPLANE TECHNICAL DESCRIPTION

LIMITATIONS

EMERGENCYPROCEDURES

NORMALPROCEDURES

PERFORMANCE

WEIGHT

AND BALANCE

Issue l /Revision l

Ol

Apr.

ICP

Sri-

Via Torino 12, 14020 PlOV

Phone [phone] • Fax [phone]

A'

MASSAIA

(AT)-

Ita1y

l I.C.P. Sri l

Savannah

FLIGHT

TABLE OF CONTENTS

MANUAL

Pag.

si

Paragraph

1.1

1.2

1.3

1.4

1.5

1.6

1.7

1.8

1.9

1.10

1.11

1.12

1.13

1.14

1.15

1.16

1.17

SECTION

AIRPLANE TECHNICAL DESCRIPTION

Airplane three view and general specifications
General specifications
Structure
Landing gear
Engine
Engine controls

Propeller
Fuel system
Electrical system

C ab in

Cabin features and upholstery
Ventilation

Cabin heating
Instrument panel
Flight controls
Flaps control system
Pitot-static system
Baggage compartment

l

Page

6

7
8

8

8

8
9
9

lO

lO

11
11
11

14
15
15
15
15

Issue l/Revision 2

July'03

ICP

Sri-

Via

Torino 12, 14020

Phone [phone] • Fax [phone]

PlOV

A'

MASSAIA

(AT)-

Italy

l I.C.P.

Sri

l

Savannah

FLIGHT

MANUAL

Pag.

61

AIRPLANE

THREE

- 2580

VIEW

--

Issue l /Revision 6

july.

04

ICP

Sri-

Via Torino 12, 14020 PlOV

Phone [phone] • Fax [phone]

A'

MASSAIA

(AT)-

Ita1y

l I.C.P. Sri (

I.I

GENERAL SPECIFICATIONS

Dimensions

Wing span 30.0/9.0
Wing area
Length 2I.3/6.5
Height
Propeller diameter

w,

. h

· ·

ezgJ

ts

Maximum take-off weight
Em_Qty
Usefulload
NOTE: empty weight may increase and is depended on the optional equipment instalied as per the
customer requirements

p l

Engine
Take
Dispiacement
Compression ratio
Fuei consumption (75% power)

weight 600/272 Ibs/kg

owerp, ant

off

performance

Savannah

FLIGHT

DIMENSION

cu.in/cm

gphllt/h 4.3/16.2 4.9/18.5

MANUAL

3

ft/m

I41/I2.7 sq. ft/m

ft/m

8.0/2.45 ft/m

68/I.73 in/m

I000/454 Ibs/kg

400/I82 l b s/kg

ROTAX9I2

59.6

kW

73.9/12II 82.5/1352

9.0:I I0.5:I

(5800

UL

rpm)

ROTAX9I2 ULS

75.3 kW

2

Pag.

(5800

71

rpm)

Fuel

and

oil

Fuel capacity
Fuel grade
Oil capacity

L

d.

an

mg gear

Wheel track
Tire size
Tire pressure

72 l t
Mogas/ A vgas
3/3.I6

5.6/1.7
6

I4.5/I p silbar

IOO/IOO

lt/US qts

ft/m
m

LL

Issue l /Revision 2

Ott.

02

ICP

Sri-

Via Torino I2, I4020 PIOVA' MASSAIA

Phone +39-0I4I-996503 • Fax +39-0I41-996506

(AT)-

Italy

l I.C.P.

1.2 STRUCTURE

supported by struts. The wing presents a
along the full
metal one with load-resisting panels. The horizontal tailplane features a simmetric bi-convex airfoil.
The rudder is attached
stability.

1.3

single-piece aluminium alloy single-leafleg. The noselanding gear is fitted with a telescopic, elastic

chord shock absorber, and is steerable in order to ease the taxying.

1.4 ENGINE

Sri

l

The aircraft is a monoplane type, with two side-by-side seats, fitted with a high wing

wingspanand

LANDING GEAR

The aircraft is fitted with a tri-cycle type landing gear. The main landing gear is made by a

Savannah

Junkers type flaperon (aileron +flap). The airframe structure is a full-

to

the fixed vertical

FLIGHT

MANUAL

"high lift" NACA 650-18 modified airfoil with fixed slats

fin.

The dorsal fin is fitted

to

improve the directional

Pag. s j

The engines instalied onboard the aircraft are the

Piease refer to Engine manual for any data and specifications.

W ARNING:
can

result

le

ad

to serious bodil y
locations, airspeeds, altitudes,
landing
must
aircraft
aircraft
which
acknowledges

1.5

The mixture control is located near to pilot's side throttle control. The air-box control (Rotax 912
ULS)
carburators (for values oftemperature

electrical system is protected bythermal type re-settable breakers.

ignition system is independent and can be cut-offby switching OFF the two magneto switches only.
With the master switch OFF any electrical instrument and all other electrical devices, electric engine
starter included, won't be operating.

only fly

an

ENGINE CONTROLS

There are two vemier type (push-pull) throttle controls fitted with a frietion adjusting knob.

is

The key-operated master switch connects the electrical system to the 12V battery. The whole

The engine can be operating with the master switch

the

instalied engine,

in

crash

eannot

engine.

standards.

engine failure will

located near the throttle control: pull for hot air

landings, forced landings

in

jury

be made,

in

DAYLIGHT

It

has

This is for use

by

his use

after

not

that

by

its design is

o r de a th. N ever fly

or

other

sudden

VFR

received

in

not

he knows this engine is

to

circumstances

engine stoppage.

conditions.

any

safety

experimental, uncertificated

compromise safety. User assumes all

maintain see chapter 2.3).

subject

or

no

ROTAX 912 ULS or ROTAX 912 UL.

to

sudden

power

the

The

or

subject

landings.

aircraft

from

Aircraft

instalied engine is

durability

to

to

OFF and the breakers OFF since the

stoppage. Engine stoppage

Such

crash

equipped

which a successful

equipped

testing,

aircraft

sudden

carburators, push for cold air to

with

and

and

stoppage.

landings

the

with

not

a certificated

conforms to

vehicles only

risk

can

en

gine

at

no

power

this engine

no

in

of

use

and

W ARNING: The engine may be started-up with the master switch OFF
only is
recommended

ON, when the propeller is hand rotating or due to windmilling. For safety,

to

pull-out the master switch key when the engine is shut-off.

Issue l/Revision 3

July '03 Phone [phone] • Fax [phone]

ICP

Sri-

Via Torino 12, 14020 PlOV

if

even one magneto switch

it's

strongly

A'

MASSAIA

(AT)-

Italy

l I.C.P. Sri j

Savannah

FLIGHT

MANUAL

Pag.

91

The master switch key is located near

controls commute to ON
activated pulling it BACKWARD.

PROPELLER

1.6

The aircraft features the foliowing propeller:

"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.

1.7

FUEL SYSTEM

With reference

are

instalied into the wings and have a
reservoirs features an overcapacity fuel pipe ending below the wing. The left fuel tank is with a
visual fuel level indicator located on left wing first rib. The drain valve (5.) is located in the fuel
bowl (3.) instalied in the fuselage, o n the right side; a fuel reserve warning is instalied o n the bowl
to indicate low remaining fuel. A fuel valve is fitted (7.): this fuel valve is held in the OPEN
position by a safety wire. That safety wire can be broken in an emergency. This safety wire must be
used to prevent an accidental in-flight fuel valve elosure leading to an engine shut-down or, even

to

worse,
pressure gauge is installed.

a elosed fuel valve take-off. The fuel pump (8.) is mechanically cams operated. A fuel

if

moved UPWARD or FOREWARD. The mixture control only, is

to

fig. l on page

to

the pilot's throttle. All the switches and the engine

11,

the fuel system is equipped with two tanks (1, 2). They

72

lt.

capacity. The filler caps inelude a vent hole. The

Issue l/Revision 3

July'03

ICP

Sri-

Via Torino 12, 14020 PlOV

Phone [phone] • Fax [phone]

A'

MASSAIA

(AT)-

Italy

l I.C.P. Sri l

1.8

ELECTRICAL SYSTEM

Savannah

FLIGHT MANUAL l Pag.

10

l

With reference
generator, wiring and switches
anti-collision and navigation lights, and the avionics. A voltmeter
equipment.

The key-operatedmaster switch connects the electrical system
electrical system

With the master switch OFF any electrical instrument and all other electrical devices,
electric
With reference

A.

B.

C.
D.
E.
F. elevator trim motor
G.

4.

5.

6.

7.

8.

9.
l

O.

15.

18.

21-25 switches
26-27 breakers

engirre starter included, won't be operating.

to
starter relais
regulator
electric fuel pump
master switch

power supply

battery
revolution counter supply
hourmeter
voltmeter

left head temperature

right head temperature
o il temperature
oil pressure
low voltage waming lamp
elevator trim switch

to

fig.2 on page

to

is

protected by thermal type re-settable breakers.

fig.

2:

12,

the airplane's electrical system ineludes a 12V battery, a

supply and connect the engirre starter, an auxiliary fuel pump,

is

provided

to

the 12V battery. The whole

as

a standard

1.9 CABIN

to

Two large lateral doors allow an easy indipendent access
two hinges on the upper edge o f the doors , and may b e closed by a key handle located in the lo w er
edge and a latch in the front edge. The doors may be removed unscrewing the hinges bolt

required for flying in hot regions or

flight.

W ARNING: close latch in the front edge before flight.

Issue l/Revision 3

July'03

to

take pictures. Those windows MUST NOT be opened in

ICP

Sri-

Via Torino 12, 14020 PlOV

Phone [phone]

the cabin. They are hinged by means

A'

MASSAIA

• Fax [phone]

(AT)-

of

as

Italy

l I.C.P. Sri l

1.10 CABIN FEATURES AND UPHOLSTERY

The cabin arrangement features two canvas covered side-by-side seats.

1.11

VENTILATION

Savannah

FLIGHT MANUAL

l Pag.

ni

The cabin's ventilation is provided by an opening between the doors and the upper part
the cabin door frame. A dynamic air scoop intended to extract the cabin air is fitted at the hottom
the baggage compartment
scoops in the doors windows.
windshield frosting in high humidity, low temperature and rainy weather.

1.12 CABIN BEATING

On the right-upper side
havingahot
skin. The air is heated by the heat exehanged integrated the silencer.

ventilation in the cockpit.The outlet may be opened by a rotating panel on the cockpit

lt's

possible to improve the cabin ventilation by using two rotating air

lt's

important to get an efficient cabin ventilation to avoid the

ofthe

instruments panel there is a push-pull control.

Pullit

for

of
of

Issue l !Revision 2

Ott. 02

ICP

Sri-

Via Torino 12, 14020 PIOVA' MASSAIA

Phone [phone] e Fax [phone]

(AT)-

Italy

l I.C.P.

FUELSYSTEM

Sri

l

Savannah

FLIGHT

MANUAL

l Pag. 12j

..:

Pigure nr.l

(

l

l

l

l

--,

/

--

/

/

/

l
l
l

\

'

'

.....

____

'

l
l

l

l

l

l

~l

Hl

l
l

IIII

l

l

l

.J

Issue l /Revision l

Apr.

Ol

ICP

Sri-

Via Torino

Phone [phone] • Fax [phone]

12,

14020 PlOV

A'

MASSAIA (AT)

-ltaly