ICP Savannah Technical specifications

lI.C.P. Sri j Savannah
FLIGHT MANUAL Pag.
11
AIRPLANE FLIGHT MANUAL
/
Issue l/Revision l
Apr. Ol
Savannah
ll
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lI.C.P. Sri J Savannah
FLIGHT MANUAL
Pag. 21
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Savannah FLIGHT MANUAL Pag.31
LOG OF REVISIONS
Revision Revised Description of Revision Date
Number Pages
00
All
Ol
All
02
6 to11,18,
21,24,28,
32,34
03
2,3,14,
04
2,3,14
05
2,3,5,8,9,
10
06
2,3,6
Issue l/Revision 6
July '04
New emission 03/01
Cerreetions 04/01
Cerreetions 10/02
Cerreetion 10/02
Note on Instruments Ju1y '03
Note on Engine Ju1y '03
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Savannah FLIGHT MANUAL Pag.
41
SECTION l
SECTION2
SECTION 3
SECTION 4
SECTIONS
SECTION 6
Issue l/Revision l
Apr.
Ol
TABLE OF CONTENTS
AIRPLANE TECHNICAL DESCRIPTION
LIMITATIONS
EMERGENCYPROCEDURES
NORMALPROCEDURES
PERFORMANCE
WEIGHT AND BALANCE
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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
Savannah FLIGHT MANUAL
TABLE OF CONTENTS
SECTION l
AIRPLANE TECHNICAL DESCRIPTION
Airplane three view and general specifications
General specifications
Structure
Landing gear
Engine
Engine controls
Propeller
Fuel system
Electrical system
Cabin
Cabin features and upholstery
Ventilation
Cabin heating
Instrument panel
Flight controls
Flaps control system
Pitot-static system
Baggage compartment
Page
6
7
8
8
8
8
9
9
lO
lO
11
11
11
14
15
15
15
15
Pag. si
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lI.C.P. Sri l Savannah
FLIGHT MANUAL Pag.
61
AIRPLANE THREE VIEW
-2580 --
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Savannah FLIGHT MANUAL Pag.
71
I.I GENERAL SPECIFICATIONS
Dimensions
Wing span 30.0/9.0 ft/m
Wing area I41/I2.7 sq. ft/m2
Length 2I.3/6.5 ft/m
Height 8.0/2.45 ft/m
Propeller diameter 68/I.73 in/m
w, . h
·· ezgJ ts
Maximum take-offweight I000/454 Ibs/kg
Em_Qty weight 600/272 Ibs/kg
Usefulload 400/I82 lbs/kg
NOTE: empty weight may increase and is depended on the optional equipment instalied as per the
customer requirements
p l
owerp, ant
Engine
Take
off performance
Dispiacement
Compression ratio
Fuei consumption (75% power)
Fuel and oil
Fuel capacity
Fuel grade
Oil capacity
L
d.
an mggear
Wheel track
Tire size
Tire pressure
Issue l /Revision 2
Ott. 02
DIMENSION
ROTAX9I2 UL ROTAX9I2 ULS
59.6 kW (5800 rpm) 75.3 kW
(5800 rpm)
cu.in/cm3 73.9/12II 82.5/1352
9.0:I I0.5:I
gphllt/h 4.3/16.2 4.9/18.5
72 lt
Mogas/Avgas
IOO/IOO LL
3/3.I6 lt/US qts
5.6/1.7 ft/m
6 m
I4.5/I psilbar
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lI.C.P. Sri l Savannah
FLIGHT MANUAL
Pag. sj
1.2 STRUCTURE
The aircraft is a monoplane type, with two side-by-side seats, fitted with a high wing
supported by struts. The wing presents a "high lift" NACA 650-18 modified airfoil with fixed slats
along the full
wingspanand Junkers type flaperon (aileron +flap). The airframe structure is a full-
metal one with load-resisting panels. The horizontal tailplane features a simmetric bi-convex airfoil.
The rudder is attached
to the fixed vertical fin. The dorsal fin is fitted to improve the directional
stability.
1.3 LANDING GEAR
The aircraft is fitted with a tri-cycle type landing gear. The main landing gear is made by a
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
The engines instalied onboard the aircraft are the ROTAX 912 ULS or ROTAX 912 UL.
Piease refer to Engine manual for any data and specifications.
WARNING: the instalied engine, by its design is subject to sudden stoppage. Engine stoppage
can result in crash landings, forced landings or no power landings. Such crash landings can
le ad to serious bodily in jury or death. Never fly the aircraft equipped with the en gine at
locations, airspeeds, altitudes, or other circumstances from which a successful no power
landing eannot be made, after sudden engine stoppage. Aircraft equipped with this engine
must only fly in DAYLIGHT VFR conditions. The instalied engine is not a certificated
aircraft engine. It has not received any safety or durability testing, and conforms to no
aircraft standards. This is for use in experimental, uncertificated aircraft and vehicles only in
which an engine failure will not compromise safety. User assumes all risk of use and
acknowledges by his use that he knows this engine is subject to sudden stoppage.
1.5 ENGINE CONTROLS
There are two vemier type (push-pull) throttle controls fitted with a frietion adjusting knob.
The mixture control is located near to pilot's side throttle control. The air-box control (Rotax 912
ULS) is located near the throttle control: pull for hot air to carburators, push for cold air to
carburators (for values oftemperature
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 bythermal type re-settable breakers.
The engine can be operating with the master switch OFF and the breakers OFF since the
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.
WARNING: The engine may be started-up with the master switch OFF if even one magneto switch
only is ON, when the propeller is hand rotating or due to windmilling. For safety,
it's strongly
recommended to pull-out the master switch key when the engine is shut-off.
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lI.C.P. Sri j
Savannah FLIGHT MANUAL
Pag. 91
The master switch key is located near to the pilot's throttle. All the switches and the engine
controls commute to ON if moved UPWARD or FOREWARD. The mixture control only, is
activated pulling it BACKWARD.
1.6 PROPELLER
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 to fig. l on page 11, the fuel system is equipped with two tanks (1, 2). They
are instalied into the wings and have a
72 lt. capacity. The filler caps inelude a vent hole. The
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, on the right side; a fuel reserve warning is instalied on 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
worse,
to a elosed fuel valve take-off. The fuel pump (8.) is mechanically cams operated. A fuel
pressure gauge is installed.
Issue l/Revision 3
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lI.C.P. Sri l
Savannah FLIGHTMANUAL lPag. 10 l
1.8 ELECTRICAL SYSTEM
With reference
to fig.2 on page 12, the airplane's electrical system ineludes a 12V battery, a
generator, wiring and switches
to supply and connect the engirre starter, an auxiliary fuel pump,
anti-collision and navigation lights, and the avionics. A voltmeter
is provided as a standard
equipment.
The key-operatedmaster 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 engirre starter included, won't be operating.
With reference
to fig. 2:
A. starter relais
B. regulator
C. electric fuel pump
D. master switch
E. power supply
F. elevator trim motor
G. battery
4. revolution counter supply
5. hourmeter
6. voltmeter
7. left head temperature
8. right head temperature
9. oil temperature
l O. oil pressure
15. low voltage waming lamp
18. elevator trim switch
21-25 switches
26-27 breakers
1.9 CABIN
Two large lateral doors allow an easy indipendent access
to the cabin. They are hinged by means of
two hinges on the upper edge of the doors , and may be closed by a key handle located in the lower
edge and a latch in the front edge. The doors may be removed unscrewing the hinges bolt
as
required for flying in hot regions or to take pictures. Those windows MUST NOT be opened in
flight.
WARNING: close latch in the front edge before flight.
Issue l/Revision 3
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Savannah FLIGHTMANUAL lPag.
ni
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 fitted at the hottom of
the baggage compartment lt's possible to improve the cabin ventilation by using two rotating air
scoops in the doors windows. lt's important to get an efficient cabin ventilation to avoid the
windshield frosting in high humidity, low temperature and rainy weather.
1.12 CABIN BEATING
On the right-upper side ofthe instruments panel there is a push-pull control. Pullit for
havingahot ventilation in the cockpit.The outlet may be opened by a rotating panel on the cockpit
skin. The air is heated by the heat exehanged integrated the silencer.
Issue l!Revision 2
Ott. 02 ICP
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FUELSYSTEM
Issue l/Revision l
Apr. Ol
Savannah FLIGHT MANUAL
lPag. 12j
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ICP Sri- Via Torino 12, 14020 PlOV A' MASSAIA (AT) -ltaly
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jI.C.P. Sri l
Savannah FLIGHT MANUAL
ELECTRIC SYSTEM
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lPag. 13j
Issue l/Revision l
Apr. Ol
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lI.C.P. Sri l Savannah
FLIGHT MANUAL
lPag. 141
1.13 INSTRUMENT PANEL
ATTENTION: the instalied instrumentsarenot certified according
to any aeronautical regulation: it
is advisable
to avoid dangerous flight conditions and do not consider the values given by the
instruments
as an absolute value.
As standard equipment the foliowing instruments are fitted:
Fuel pu mp _,
l Choke o.ctuoto r"'
Ib Ai rbo x contr"o l (O nty Rotox 912 UL S>
2 Moster switc h
3 ,4 Magneta swltch es
5 P ilot s ide occe ter atol"'
6 PT T swit ch <opti o nan
7 El ev ot or triM s wi tc h
8 n ot us ed
9 An er'lOr'let er
lO Al t1 Meter
11 Vori o l"'' eter
12 Rodi o- int erco M <optlo no l)
13 Revoluti on co~,.~nter
14 F uel preSSl,.lr"E' i ndicoto r
15 Slip incli co tor"
16o L eft cylind er he ad t eMpera t ure
l6b Right c ylind er head teMpera t u re
17 Ex ternol ter~p e ro. t ur" e <9 12 UU + A1r!oox teMpera t ur-e <912 UL S)
17b Swit ch ext e rnol t eMperuture - oir bo x teMpera t u re ( only 91 2 ULS)
18 Oi l pr ess ur e indico t or
19 Dit t e r~p e r o. ture indic o tor
20 Houn "' et e r
2 1 V
ol t Meter
22 L ow bo tt ery va ttog e wor nin g loMp
23 P ossenger s id e occ et erotot"
24 R eserv e f'ue t tonk (Nu t" is e) t est bu tt on
25 F uel r e serve wo.rning lo Mp
Position lights (optional)
/ Co bin light
/
S trobe
0 0
l
l
le reaker 1O A
La
nding light
Instruments for each aircraft may vary according to the requirernents of the customers.
Issue l/Revision 4
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July
'03 Phone [phone] • Fax [phone]

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FLIGHT MANUAL
IPag.15j
1.14 FLIGHT CONTROLS
The aircraft is equipped with a single "Y" shaped stick and dual conventional rudder pedals
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: ±15° (±2°)
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
retracted.
In the intermediate position the flap results 18° (±3 °) extended, while with the control
lever full backward the flap results 36° (±3°) lowered; with flaps fully extended and stick
completely pushed
to the right position, the left flap results extended of 40° (±3°) the right flaperon
results extended
of32° (±3°).
1.16 PITOT-STATIC SYSTEM
The total pressure to the instruments is supplied by the Pitot tube located on the left hand
forward wing strut. No static pressure source is provirled since it is assumed the static pressure is
equal
to the pressure inside the cabin.
WARNING: biowing into the Pitot tube may results in an airspeed indicator damage.
1.17 BAGGAGE COMPARTMENT
An open space behind the seats is provirled 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, for every configuration, that the weight and balance ofthe aircraft
are within the allowed limits.
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Apr. Ol
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FLIGHT CONTROLS
Issue l/Revision l
Apr. Ol
Savannah FLIGHT MANUAL
1
1 J
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Figure nr.3
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l Pag. 16j
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Paragraph
2.1
2.2
2.3
2.4
2.5
2.6
2.7
2.8
Savannah FLIGHTMANUAL
Speed limits
Load factors
Engine operating limits
Weight !imitations
C of G !imitations
Kind of operations
Kind of maneuverings
TABLE OF CONTENTS
SECTION2
LIMITATIONS
Max crosswind for T/0 and landing
lPag. 171
Page
18
18
18
19
19
19
19
19
Issue l/Revision l
Apr. Ol
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FLIGHT MANUAL
l Pag.181
2.1 SPEED LIMITS
NOTE h ti U: t e o owmg spee 1m1ts
d r · (IAS)
Stall
SQ_eed, full flaps, Vso
Flaps range (white arc)
Stall speed, no flaps, Vs
Normal operating range (green arc)
Max. maneuvering speed
(l)
Attention zone (yellow arc) (2)
Vmo
Never exceeding speed, Vne (red line)
Flaps speed limit
NOTES:
are set a a max1mum a e o we
t t k
ff ight of 1000 lbs/454 kg
30 mph l 48 km/h
30-60 mph l 48-96 km/h
35
mph l 56 km/h
'Y, j /-1.
~.J l) .j
40-85 mph l 64-137 km/h
70 mph l 112 km/h
85-125 mph l 137-201 km/h
100 mph l 160 km/h
125 mph l 201 km/h
60 mph l 96 km/h
2
·~ 6
l>
~
,_ 70
l
'"6c-11.2
~
9
-'/
2
.":}
(1): the maximum maneuvering speed is the maximum speed at which the flight controls may be
fully operated (maximum movable surfaces detleetion angles);
(2): when flying
in turbulence conditions this speed range has to be avoided.
2.2 LOAD FACTORS
Fia s retracted + 4
Fia s full extended + 2
NOTE: the maximum load factors (limit load factors) are obtained multiplying theabove indicated
values
by the coefficient 1,5.
2.3 ENGINE OPERATING LIMITS
•
Maximum RPM for T/0 and climb
• Caution range
• Normal range
• Maximum continuous power
• Idle speed
• Oil pressure
• Oil temperature
• Fuel pressure
• Air-box temperatures (Only 912 ULS)
5800 RPM (5 min.) (red line)
5500-5800 RPM (yellow arc)
1400-5500 RPM (green arc)
5500 RPM
around 1400 RPM
normal range 2-5 bar (29-73 psi) (green arc)
caution
range5-7 bar (73-102 psi) (yellow arc)
min. 0.8
bar (12 psi) (red line), max 7 bar (102 psi) (red
line)
normal range 90-11Ooc (green arc)
caution range 50-90 l 110-140
oc (yellow arc)
max 140 °C (red line)
max 0.4 bar (5.8 PSI)
Min 0.15 bar (2.2 PSI)
Caution range 18 oc- 20 °C (yellow arc)
Caution range 24 oc- 35 °C (yellow arc)
Normal range 20 oc-24 °C (green arc)
Minimum air
box temp. 18 °C
Maximum air-box temp. 35 °C (red line)
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Savannah FLIGHT MANUAL
2.4 WEIGHT LIMITATIONS
Maximum take off weight:
Minimum take
offweight (minimum pilot weight 86 kg and~ h flight fuel):
2.5 C
ofG LIMITATIONS
Forward C of G limit:
Rear C
ofG limit:
See also section
6.
2.6 KIND OF OPERATIONS
30%MAC
38.5%MAC
The airplane can be operated only in day-VFR conditions.
2. 7 KIND OF MANEUVERINGS
The airplane is intended for non-aerobatic operations only.
2.8
MAX CROSSWIND FOR T/0 AND LANDING
'1s-o Is
-454 kg
367 kg
The maximum cross-wind component allowed during take-offand landing is 30/48 mph/km/h.
Jssue I/Revision l
Apr. Ol
---
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Paragraph
3.1
3.2
3.3
3.4
3.5
3.6
3.7
3.8
Savannah FLIGHT MANUA~
Emergencylanding
Fire
on the ground
TABLE OF CONTENTS
SECTION 3
EMERGENCYPROCEDURES
Fire on the ground, engine operating
In flight fire
Cabin fire
Unintentional spins
Engine failure during
T/0 (on the ground) or immediately after T/0
(low altitude)
Engine start during flight
lPag. 20 1
Page
21
21
21
21
21
21
22
22
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