ICP Savannah Airplane Flight Manual

l I.C.P. Sri j

Savannah

FLIGHT

MANUAL

Pag.

11

AIRPLANE

Savannah

FLIGHT

MANUAL

/

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Apr.

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FLIGHT

MANUAL

21

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6 July '04

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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

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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

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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

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FLIGHT

MANUAL

Pag.

61

AIRPLANE

THREE

- 2580

VIEW

--

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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

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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.

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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

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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

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to

take pictures. Those windows MUST NOT be opened in

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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

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FUELSYSTEM

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Savannah

FLIGHT

MANUAL

l Pag. 12j

..:

Pigure nr.l

(

l

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l

l

--,

/

--

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.....

____

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ELECTRIC SYSTEM

Savannah

FLIGHT

MANUAL

......

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l Pag.

13j

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Issue l /Revision l

Apr.

Ol

_j

Figure nr.2

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FLIGHT

MANUAL

1.13 INSTRUMENT PANEL
ATTENTION:
is advisable
instruments

the instalied instrumentsarenot certified according

to

avoid dangerous flight conditions and do not consider the values given by the

as

an absolute value.

As standard equipment the foliowing instruments are fitted:

l Pag.

to

any aeronautical regulation: it

141

Fuel pump

l

Choke

o.ctuoto

r"'

l

(O

switc

h

swltch

es

occe

te r

ch

<optionan

or

triM

switc

us

ed

er

eter

ercoM <optlonol)

on

co~,.~nter

preSSl,.lr"E' i

ess

r e

co

tor"

cylind

er he

er

ter~pero.tur"

externol

ur e

o.

ture

e r

ery

e

f'uet tonk

serve

ndicoto

head

indico tor

va

ttog

wo.rning

nt y

Rotox

atol"'

h

ad

t

eMperature

teMpera

e

t

eMperuture

indic

o

tor

e

wor

(Nut"is

912 UL

r

t u

re

<9

12

UU

+ A1r!oox

-

oir

nin

g l oMp

e) test butt

lo

Mp

/Cobin light

S>

bo x

teMperatur-e

teMpera

on

t u

re

<912 ULS)

(

only 912 UL S)

Position

Ib Ai

rbox contr"o

2

Moster

3

,4

Magneta

5 P

ilot side

6 PTT swit

7 Elev

o t

8 n

ot

9 Aner'lOr'let

lO

Al

t1

Meter

11

Voriol"''

12

Rodio-int

13

Revoluti

14 Fuel
15

Slip incl i

16o Left

l6b

Right cylind

17 Ex

ternol

17b

Swit

ch

18 Oil p r

19 Dit

ter~per

20

Houn"'et

2 1

Volt

Meter

22 L

ow bott

23 Possenger side occeterotot"

24

R

eserv

25 F

uel

lights

(optional)

0 0

l

/

S

trobe

l

La

nding

light

_,

le

reaker

1 O A

Instruments for each aircraft may vary according to the requirernents o f the customers.

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1.14 FLIGHT CONTROLS

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Savannah

FLIGHT

MANUAL

IPag.15j

The aircraft
fitted with toe operated brake controls on the pilot's side only. The aircraft is provirled with one
longitudinal trim electrically operated. Longitudinal trim: by pushing upwards the toggie switch the

pilot achieves a nose-down attitude.

Flaperons range:

Elevators range: -35° (±2°) l +28° (±2°)

Rudder range: ±25° (±2°)

1.15 FLAPS CONTROL

This system controls the "flaperons", full-span trailing edge movable surfaces, and is located

on the cabin floor. With the stick in the center and the control lever full forward the flaps are fully

In

retracted.
lever full backward the flap results
completely pushed
results extended

1.16 PITOT-STATIC SYSTEM

forward wing strut. No static pressure source is provirled since it is assumed the static pressure is

to

equal

the intermediate position the flap results

The total pressure to the instruments is supplied by the

the pressure inside the cabin.

is

equipped with a single "Y" shaped stick and dual conventional rudder pedals

±15° (±2°)

18°

(±3

°)

extended, w hil e with the contro l

36° (±3°) lowered; with flaps fully extended and stick

to

the right position, the left flap results extended

of32°

(±3°).

of

40° (±3°) the right flaperon

Pitot tube located on the left hand

WARNING: biowing into the

1.17 BAGGAGE

An

open space behind the seats is provirled

MUST be evenly arranged on the baggage compartment floor and firmly fastened.

NOTE: the pilot MUST check, for every configuration, that the weight and balance

are within the allowed limits.

COMPARTMENT

Pitot tube may results in an airspeed indicator damage.

to

carry some baggage up

to

45

lbs. The luggage

ofthe

aircraft

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FLIGHT CONTROLS

Savannah

l \

l l

} \

l

l

FLIGHT

1 J

1

l

<1:

l

~

f

l \

CL

MANUAL

Figure nr.3

l Pag.

16j

Issue l /Revision l

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FLIGHT MANUAL

l Pag.

171

Paragraph

2.1

2.2

2.3

2.4

2.5

2.6

2.7

2.8

Speed limits
Load factors
Engine operating limits
Weight !imitations
C o f G !imitations
Kind o f operations
Kind o f maneuverings
Max crosswind for

T/0

TABLE

and landing

OF CONTENTS

SECTION2

LIMIT A TIONS

Page

18
18
18
19
19
19
19
19

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2.1 SPEED LIMITS

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FLIGHT

MANUAL

l

Pag.181

NOTE

Stall

Flaps range (white arc)

Stall speed, n o flaps, V s
Normal operating range (green arc)
Max. maneuvering speed
Attention zone (yellow arc) (2)

Vmo
Never exceeding speed, Vne (red line)

Flaps speed limit

NOTES:
(1): the maximum maneuvering speed is the maximum speed at which the flight controls
fully operated (maximum movable surfaces detleetion angles);
(2): when flying

2.2
Fia
Fia s full extended + 2

h

ti

U : t e o owmg spee

SQ_eed,

LOAD FACTORS

s retracted + 4

full flaps, Vso

in

turbulence conditions this speed range has to

d r · (IAS)

1m1ts

(l)

are set a a max1mum a e o w e
30
30-60
35
40-85
70
85-125

100

125
60

mph

mph

mph

mph

mph

mph
mph

mph

t

l 48 km/h

l 48-96 km/h

l 56 km/h

l 64-13 7

l 112

km/h

mph

l 137-201

l 160

km/h

l 201

km/h

l 96

km/h

t k

'Y,

j

~.J

l)

km/h

km/h

/-1.

. j

be

avoided.

ff

2

·~

6

l>

~

~

-'/

.":}

ight

of

,_

70

l

'"6c-11.2

9

2

1000 lbs/454

kg

may

be

NOTE: the maximum load factors (limit load factors) are obtained multiplying

by

values

2.3 ENGINE

•

• Caution range

• Normal range

• Maximum continuous power

• Idle speed

• Oil pressure

• Oil temperature

• Fuel pressure

• Air-box temperatures (Only 912 ULS)

the coefficient 1,5.

OPERA TING LIMITS

Maximum

RPM for

T/0

and climb

5800

RPM

(5

min.) (red line)
5500-5800
1400-5500
5500
around 1400
normal range 2-5
caution
min.

0.8
line)
normal range
caution range
max

140 °C (red line)

max

0.4

Min

0.15
Caution range
Caution range 24

Normal range

Minimum air
Maximum

RPM
RPM

RPM

RPM

range5-7

bar

(12 psi) (red line), max 7

90-11 O o c (green arc)

50-90 l 110-140

bar

(5.8 PSI)

bar

(2.2 PSI)

18

20 oc-24 °C (green arc)

box

air-box temp. 35 °C (red line)

(yellow arc)
(green arc)

bar

(29-73 psi) (green arc)

bar

(73-102 psi) (yellow arc)

oc

(yellow arc)

o c - 20 °C (yellow arc)

oc- 35 °C (yellow arc)

temp. 18 °C

theabove

bar

(102 psi) (red

indicated

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2.4 WEIGHT LIMITATIONS

Maximum tak e
Minimum take

2.5 C

ofG

off

offweight

LIMITATIONS

Savannah

weight:

(minimum pilot weight 86

FLIGHT

MANUAL

kg

and~

h flight fuel):

'1s-o

-454
367

Is

kg
kg

Forward C
Rear C

See also section

2.6 KIND OF OPERATIONS

The airplane can b e operated only in da y-VFR conditions.

2.

7 KIND OF MANEUVERINGS

The airplane is intended for non-aerobatic operations only.

2.8

MAX

The maximum cross-wind component allowed during take-off and landing is 30/48 mph/km/h.

of

G limit:

ofG

limit:

6.

CROSSWIND

FOR

30%MAC

38.5%MAC

T/0

AND LANDING

---

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Savannah

FLIGHT

MANUA~

l Pag.

20

1

Paragraph

3.1

3.2

3.3

3.4

3.5

3.6

3.7

3.8

TABLE

EMERGENCYPROCEDURES

Emergency landing

on

Fire
Fire
In flight fire
Cabin fire
Unintentional spins
Engine failure during
(lo w altitude)

Engine start during flight

the ground

on

the ground, engine operating

T/0

OF CONTENTS

SECTION 3

(on the ground)

or

immediately after

T/0

Page

21
21
21

21

21
21

22

22

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3.1 EMERGENCY LANDING

Savannah

FLIGHT MANUAL

l Pag.

211

Best descent ratio speed
Flaps
Fuel valve
Engine

Seat helts

Steep tums
Flaps in final
Landing

3.2 FIRE

Starter
Fuel valve
Throttle

3.3 FIRE

Fuel valve
Throttle

ON THE GROUND

ON THE GROUND, ENGINE OPERATING

60 mph/96 km/h
Retracted
Shut-off
Shut-off
Fastened and tightened
Avoid
Fully extended,

N ormallanding

Keep engaged
Shut-off
Fully open, to

Shut-off
Fully open, to

40°

bum

the fuel and stop the fire

bum

the fuel and stop the fire

3.4 IN FLIGHT FIRE

Fuel valve
Engine

Electrical system
Landing

3.5 CABIN FIRE

Electrical system
Fire extinguisher

3.6 UNINTENTIONAL SPINS

Rotation

Control stick

Upon taking aircraft's control

Shut-off
Stop

Don't

All switches

Go on to an emergency landing

All switches
Operate

To stop the rotation push the pedal opposite the
rotation direction
Center, slightly forward
Level flight attitude

trv to restart the engine

OFF

OFF

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Savannah

FLIGHT

MANUAL

l Pag.

221

3.7 ENGINE F AlLURE DURING

Magneto switches OFF
Master switch OFF
Throttle
Fuel valve Shut-off
Brak e Fully operated

Immediately after take

Airspeed
Evenmallanding

Throttle
lf

previous point fails

Flaps
On

the ground

off

T/0

Idle

Keep

60 m

ph
Check for adequate spaces within
30° right
50%, fuel pump ON and _!!y to restart the engine
Before touching the ground, magnetces

master switch OFF, throttle i dl e, fuel val ve shut

off
Fully deflected
Touch and brake

lAS and firs t notch o f flap

30° left and

OFF,

3.8 ENGINE START

Throttle
Magneto switches
Master switch
Fuelpump
Restart the engine
RPM

DURING FLIGHT

l dl e
ON
ON
ON

-

-----

·-·

--

As requested for the type o f flight

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Savannah FLIGHT MANUAL

TABLE OF CONTENTS

l Pag.

231

SECTION

NORMALPROCEDURES

Paragraph Page

4.1 Before flight checks 24

4.2 Exterior checks 24

4.3 Engine start-up 24

4.4

4.5

4.6 Take-off and climb 27

4.7 Cruise 28

4.8 Descent 28

4.9 Approach and landing

4.10 Cross-wind landing

4.11 Aborted landing (Go-around) 29

4.12

4.13

Taxying
Before to take-off

Engine shut-down 29
Parking and mooring

4

26
26

28
29

29

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Savannah

FLIGHT MANUAL

l Pag.

24j

NOTE: The flight characteristics

exceptional piloting skilis to manage the aircraft within its flight envelope.

4.1

BEFORE FLIGHT CHECKS

Master switch
Magnetos
Fuel selector OPEN
Flight controls UNLOCKED
Fuel gascolator DRAIN
Powerplant fairings
Pre-flight/Daily inspection

4.2 EXTERIOR CHECKS

Propeller andengine Visual check to bolts and nuts,
Forward landing gear Visual check o f connection pionts
Main landing gear and strut attachments Visual check to bolts and nuts

Slat
Ailerons
Horizontal and vertical tail
Coolant radiator

of

the

Savannah

are conventional. There is no needing

OFF
OFF

FASTENED
PERFORM

oilleaks

Visual check to damages and dirt
Visual check ofhinges
Visual check to attachment bolts and nuts
Visual check to absence o f dirt, insects

boltsand

of

nuts

4.3 ENGINE

Master switch
Magnetos
Brak es
Throttle
Chok e
Starter
NOTE

START-UP

COLDENGINE

ON
ON
OPERA
FULL Y CLOSED
ON
ENGAGE

Upon enginestart-up let the

seconds then gradually release the mixture
contro l while slightly pushing the throttle contro l

TE

enginerun

for some

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HOTENGINE

NOTE

NOTE

NOTE It's strongly recommended the pilot, immediately

Engine warm-up W AlT FOR PROPER CHT READ ING
Instruments operation
Windshield cleanliness
Brake effectiveness
Safety belts and shoulder hamesses FASTENED AND CHECKED
Fuel quantitv
Electrical devices operation

Savannah

FLIGHT MANUAL

Perform the same
except pulling the choke control

The engine starts easily with the throttle full
closed. In case o f fuel flooding only i
open the throttle
to

recreate the normal carburation condition.

before to engage the engine starter, call with loud
vmce
upon making sure himself none is close
propeller, he can start the engine.
standing close to the aircraft, it would be his
responsibility
the pilot

CHECK
CHECK
CHECK

CHECK
CHECK

as

for COLD ENGINE items

to

supply a large amount

"BEWARE

"PROPELLER CLEARED".

OF

PROPELLER".

to

stay away enough and answer

j Pag.

t'

s useful to

If

someone is

of

Then,

to

the

251

air

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4.4TAXYING

Sri

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Savannah

FLIGHT

MANUAL

J Pag.

26j

POWER

S TE ERIN G

CROSSWIND In the event

NOTE U se rudder holding the heels o n the floor: in that

4.5

BEFORE TAKE-OFF

Altimeter AD
Trim ADJUST to neutral position
Flaps retracted CHECK
Flight controls freedom o f movement and correct CHECK
movement o f surfaces
Doors closed and locked CHECK

Safety helts fastened CHECK
Fuellevel
Engine instruments, green arc CHECK
NOTE The engine has been running at 2.500/3.000

Magnetos; check the RPM drop: one magneto at
a time at
drop with only one ignition circuit is
(the max difference o f speed by use
circuit is

Magnetos
Full power check ASREQUIRED
Runway and circuit traftic
Runway threshold

3.000 RPM (the max. allowed speed
300 RPM)

of

either

115

RPM max)

Apply reduced enginepower and use the brakes
at the minimum
The steering should be obtained by using the
rudder pedals and not the brakes

of

a stronger than
crosswind, taxy at a very low speed and move
the control stick laterally towards the up-wind
wing; this will raise the up-wind wing flaperon
thus avoiding the wing accidental raising.

no

way there will be

JUST

CHECK

RPM while warming-up; the CHT reading has
risen

to

60 °C.

CHECK

BOTHON

CLEARANCE CHECK
LINE-UP

accidental brake operation.

19

mph/30 km/h

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4.6 TAKE-OFF AND CLIMB

Savannah

FLIGHT MANUAL

j Pag.

271

Flaps,
Brak es

Throttle (operate progressively)

Engine RPM CHECKE D
Air-box control
Control stick
NOTE

NOTE While take-off running, be sure to hold your

Flaps, at a safety altitude
Climb airspeed at
Upon
Cruise speed
Trim (to get no reaction on the control stick)

Flaps, 40°
Brak es FULL Y APPLIED
Throttle FULL Y OPENED

Air-box control
Brak es RE
Pilot's heels
Nose-up attitude, control stick pulled-on until
taking
Climb airspeed at
clearing
Flaps, upon reaching a safe altitude and airspeed
NOTES:

time;

distance;

a
flaps decrease the rate

extended flaps induced drag increase affects the aircraft's performance as far
off
advantageous the flaps extension in the take-off.

20°

60-65 mph

reaching the required altitude

as

required, RPM as required SET

SHORT TAKE OFF

off

45

mph until the 50

- the hest rate

- the hest angle

- in normal flight conditions, set the flaps to

50

ft.

high obstacle. That's possible since the aircraft flies at a lower airspeed but the extended

- in case

run. So

it's

of

climb makes the aircraft climb to the required altitude in the shortest flight

of

climb makes the aircraft climb

of

climb.

of

operation from high elevation airfields andfor at high ambient temperature the

recommended to check the take-off performance chart

ft

obstacle

SET
RELEASED
FULL Y OPENED

COMPLETEL Y PUSHED FOR COLD AIR
SLIGHTL Y
The aircraft will take-off at a 30-35 mph speed
and will keep climbing at a

heels in contact with the cabin floor to avoid to
inadvertently operate the brakes
FULL Y RETRACTED

SET
LEVEL

SET

SET

COMPLETBLY PUSHED FOR COLD AIR

LEAS ED
ONTHEFLOOR
SET

ANDHOLD

SET

FULL Y RETRACTED

20° to shorten the take-off roll in ord er to clear

PULLED

40-45 mph speed

to

the required altitude in the shortest

as

to

increase the take-

to

determine

if

it is

The above indicated data are medium ones since they may be varied with relation

aircraft's weight, balance and configuration.

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4.7 CRUISE

Savannah

FLIGHT MANUAL

l Pag.

28j

The cruising speed is achieved
propeller. Normally the propeller required power (fixed pitch propeller only) decrease
foliowing a 20% RPM decrease only. So, at a constant aircraft's configuration, the propeller will use
the full
full

(5000rpml26 in.HG) with Rotax 912 ULS; remember that the fastestwill run the engirre the highest
will be its fuel consumption and the lowest its operating life, while a slow running engine, for the
same power output, will have its mechanical components loaded

increasing the risk to break rods, crankshaft and the other moving (rotating) parts. Low RPM

settings

propeller's thrust: to compensate it,
running speed is 4,000 to 5,400 RPM.

settin

4.8 DESCENT

engirre power (full RPM) while, at 4.600 RPM, the propeller will

engirre power.

The cruise speed is

DON'T
Low RPM settings produce low power output thus a lower airspeed would be achieved.
By increasing the flight attitude the

The

g.

Air-box control: keep 20-24

increase safety!

engirre has been designed to be safely and continuously operated at the maximum RPM

90 mph (5000rpml27.2in.HG) with Rotax 912 UL and 95mph

by

applying the 75%

engirre power output will decrease as well as the

it's

required to increase the engine's RPM. The normal engirre

oc

oftemperature. (Only Rotax 912 ULS)

of

the engirre power available at the

be

supplied with

by

greater forces and torques, thus

by

half

50%

the

During the

cooling which could lead to cylinder heads cracks.

Keep air-box control pulled for hot air.

4.9 APPROACH AND LANDING

Throttle
Airspeed
Flaps
Airspeed
Flaps 40°
Airspeed 40 mph l 64 km/h (lAS)
Brakes, upon touching down APPLY

If

a higher rate

may

be

slightly varied

flown in a nose-up attitude. Upon touching down,

willlower.

If

downwind attitude, keep air-box controlpushed for cold air. (Only Rotax 912 ULS)

descentit's

of

descent is required, fully extend the flaps. The angle

by

throttle operation as required to modify the gliding path. The flare will be

recommended not to operate the engirre at idle to avoid a hard engirre

IDLE

60

mph

l 97 km/h (lAS)

20 o
45

mph

(lAS)

by

releasing the control stick, the aircraft's nose

of

the descent path

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4.1

O CROSS-WIND LANDING

Savannah

FLIGHT

MANUAL

l Pag.

291

In the event
applying the yaw control to achieve a nose-into-the-wind aircraft's attitude or using both the two
control techniques at the same time

The aircraft mustbelined-up along the runway shortly before the ground contact.

The maximum cross-wind component allowed during take-off and landing

m ph/km/h.

4.11

ABORTED LANDING (GO-AROUND)

Throttle, full power
Flaps, when reaching a 54 mph (lAS)

The throttle control must be pushed smoothly and gradually

worse, anengine shut-down.

4.12 ENGINE SHUT-DOWN

Engine operating, low RPM
Throttle
Magnetos
Master switch

of

a crosswind the approach has to be flown lowering the up-wind wing or

as

required.

airsp_eed

l

SET
RETRACT

2MINUTES
IDLE
OFF
OFF

IS 30/48

to

avoid an engine flooding or,

It's recommended
order to avoid a thermal shock and
components. Moreover it will be achieved a good pistons and piston rings lubrication

will be let in the hest condition to the next start-up.

PARKING AND MOORING

4.13

To moore the aircraft tie two ropes

the wing spar) and a third one to the rear mooring ring.

Tie the control stick together with the rudder pedals by using an elastic chord to lock all the

movable surfaces.

Make sure the doors are closed and locked.

Put in place the optional windshield and windows proteetion canvas to prevent dust

accumulation and scratches.

to

keep the engine running at low RPM for

to

achieve a thermal balance between the different engine's

to

the mooring rings fitted under the wings (bolted to the

as

long

as

two minutes in

so

the engine

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Savannah

FLIGHT

MANUAL

j Pag. 30 l

Paragraph

5.1

5.2

5.3

5.4

Stall speed
Take-off run
Landing distances from

Rate

of

climb

TABLE

15

OF CONTENTS

SECTION 5

PERFORMANCE

m and landing run

Page

31
31
31
32

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5.1

NOTE: the speed values are expressed as anemometric (indicated) airspeed (lAS). It's assumed the

aircraft and the powerplant are factory new and the airplane is flying in standard air condition.

Sri

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STALL SPEED

Savannah

FLIGHT

MANUAL

l Pag.

3Ij

Stall speed

Flaps retracted 35 mph/56 km/h

Flaps extended (

The above indicated airspeeds are achieved with engirre set to IDLE:

aircraft simply sink without modifying the flight attitude while the control stick is pulled-up.

By applying power, the aircraft's

stall occurs, followed by a quick nose lowering.

NOTE: the maximum flaps extended airspeed is 60/96 mph/km/h.

TAKE-OFF RUN

5.2

Take-off

l

(hard

Sea level (MSL)
3,000 ft/900 m pressure altitude 160ft/50 m
6,000 ft/1,800 m press. altitude

run

surface, flaps 20°) Ibs/kg)

40°) 30 mph/48 km/h

nosego

Maximum weight
l b s/kg)

up

to

a great angle, the airspeed decrease until the

Maximum weight

115ft/35m

210 ft/63 m

(l

000/454

(l

000/454

in

those situations the

NOTE:

NOTE: to clear a 50/15 ft/m high obstacle, a practical rule suggests to double the take-off ground

ro l l.

5.3 LANDING DISTANCES

The airplaneneeds
condition at full weight, with airspeed

ifthe

airplane is operatedfrom a grass runway the take-off ground roll will increase.

150m

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for landing upon a

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AND LANDING RUN

of

60-65 km/h lAS.

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5.4 RATE OF CLIMB (Rotax 912 UL)

Savannah

FLIGHT

MANUAL

l Pag.

32j

Rate

of

climb

Full power setting

Sea level (MSL)

3,000 ft/900 m pressure altitude

6,000

ft/1

,800 m press. al titude

9,000 ft/2,700 m press. attitude 300 fpm/1.5 m/s

The maximum ceiling is

The hest rate o f climb speed is

of

The hest angle

The hest gliding angle with flaps retracted is achieved at a

Lift to Drag ratio is 12.

The fuel consumption at 75% power setting amounts to 4.9/18.5

and 4.3/16.2 gphllt/h for Rotax 912 UL

climb speed is

14,000 ft/4200 m pressure attitude at the maximum weight.

48177

45172

Maximum weight
Ibs/kg)

1,100 fpm/5.5 m/s

790 fpm/4.0 m/s

520 fpm/2.6 m/s

mph/kmlh.

mphlkm/h.

(l

000/454

48 mph/77 km/h

45 mph/72 km/h

40 mph/64 km/h

3 7

mph/60 km/h

60/96 mph/km/h airspeed. The

gphllt/h for Rotax 912 ULS

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Savannah

FLIGHT

TABLE OF CONTENTS

WEIGHT AND BALANCE

MANUAL

SECTION 6

l Pag. 331

Paragraph

6.1

6.2

6.3

6.4

General
W eight and balance report
W eight and balance drawings
Weight and balance pilot' s computing table and graph

Page

34
35
36
37

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6.1

GENERAL

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FLIGHT

MANUAL

j Pag.

341

The aircraft is allowed
easing the aircraft's loading and balancing. By knowing the weights
to be carried on board and using the attached W
proper aircraft's weight and balance configuration. To find out the CG position piease refer to the
attached table. Compute the total weight and the total moment, given by adding all the single
moments. To be acceptable, the found point MUST be located into the WHITE area, between the
two limit lines.

W ARNING: a CG beyond the most foreward limit,

may result in a VERY DANGERODS flight condition.

NOTE:

modifications may affect the balance limits set by the manufacturer.

it's

strictly forbidden

to

have its CG (Centre

&B

to

make any change or modification to the aircraft since those

of

Gravity) within a quite large range thus

ofthe

report, the pilot would be

as

well

as

a CG beyond the most rearward limit

people, fuel and baggage

ab

le to check for the

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6.2 WEIGHT AND BALANCEREPORT

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Savannah

FLIGHT

MANUAL

l Pag.

351

Procedure

- The aircraft
and

WITHOUT FUEL;

NOTE:

Put the aircraft on three weight measuring equipments ( each under each wheel o f the landing

-

gear);

- Put the aircraft in the flight level position by using a level fitted o n the aircraft' s fuselage, o n the

horizontal plane where doors will be closed;

-Record
the left wheel weight P2, the right wheel weight P3;

- By using a plumbing wire fix ed to the leading edge, measure the distance D l between the
projection on the floor o f the leading edge and the nose wheel axle, and the distance D2 between the
same projected point and the main landing gear axle;

- By filling out the table below, make the calculations and find out the CG position. The airplane is
in the correct balance
inside the white area.

to be used to determine the Centre o f Gravity position:

MUST be weighed fitted with all equipments, accessories, engine oil, coolant

all the fuel MUST be drained accurately.

the three weight measuring equipments readings: the nose wheel weight will be called

if

the line o f the actual weight and the line o f the actual total moment cross

Pl,

TABLE

Aircraft serial number
Weight measuring equipment
Location and date
Certifying staff

N ose landing gear

LH

main landing gear

RH

main landing gear

TOTALS

TO

DETERMINE

l Signature

PI

=

P2=

p3 =

THE

AIRCRAFT'S

Weight (kg)

BASIC

Arm

n,{),

D2=€J

D2=fJ

EMPTY

(m)

t

~

WEIGHT

Moment

(kg x m)

L/5~s

71..

,u

<,./'

7o,)-

"

/CJIX

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6.3 WEIGHT AND BALANCE DRA WINGS

Sri

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Savannah

FLIGHT

MANUAL

i i

- o

' ' -

N

Q_

l Pag.

361

where:
D1=700mm;
D2=700mm;
P l =weight on forward gear;
P2=total weight on principal gear;

X=(P2*D)/(Pl +P2)-Dl X =-ff.-/

Z

'?f~

l

J.:Ttt

1

L-f

f.-

/foD'

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!J-

A'

MASSAIA

(AT)-

Italy

l I.C.P.

6.4 WEIGHT AND BALANCE PILOT'S COMPUTINO TABLE AND GRAPH

Sri

l

Savannah

FLIGHT

MANUAL

l Pag.

37j

COMPUTING

Item

Basic
Pilot

Passeng~r

Fuel (max
Baggage (

!TOTALS

Total

1100~-T~--~--~~~~~~~~--~~

900

em_Q_ty

weight [Ib]

weight

11

O l b max)

45

l b max)

l

Weight W

Ino

'-1,

IC.?

/LO!

//0

/075'}. \

;

7-'

c-

l

o,

i

f<'orward limit

[Ibs]

(;.,ot.t

/(.

t

L_,

/i})

c~)

cf

cl'?

r

..

:-;

t_,,

~.._

G

RAP

30%

TABLE

ArmX[m]

O,'tt'J

0.65

0.65

0.595

1.42

l

H

MAC

X=0.429 m

--

~~~~~---.

--

l

Moment

2

')

l

l

a.:::·

/

f)Lj

"J-:-iJ

&3(

~

/(_l

[W x X/

~·

(

c;;)

~

c.y

-3({.

--

i-

j)

7

!P,

l

800

500

100

Forward C
Rear C o f G limit:

of

G limit:

Issue l/Revision l

Apr.

Ol

200

300

30%MAC

38.5%MAC

ICP

Sri-

Via Torino 12, 14020 PlOV

Phone [phone] • Fax [phone]

.1100

Total

A'

MASSAIA

moment

W*X

(AT)-

[lb*m]

Italy