Avanti EVO

Specification and Description

Revision 7.1 April 2016

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TABLE OF CONTENTS

Title Page
1 INTRODUCTION .................................................................................................................................................... 4
1.1 APPLICABLE DOCUMENTS AND REFERENCES.................................................................................................................... 4
2 GENERAL DESCRIPTION ........................................................................................................................................ 5
3 SPECIFICATIONS ................................................................................................................................................... 7
3.1 EXTERNAL DIMENSIONS .............................................................................................................................................. 7
3.2 INTERNAL DIMENSIONS AND VOLUMES .......................................................................................................................... 9
3.3 WEIGHTS ................................................................................................................................................................10
3.4 PRESSURIZATION ......................................................................................................................................................11
3.5 POWERPLANT ..........................................................................................................................................................11
3.6 PERFORMANCE ........................................................................................................................................................12
3.7 OPERATING SPEEDS ..................................................................................................................................................14
3.8 PERFORMANCE CHARTS .............................................................................................................................................15
4 AIRFRAME ...............................................................................................................................................................18
4.1 FUSELAGE GROUP .....................................................................................................................................................18
4.2 WING GROUP ..........................................................................................................................................................19
4.3 EMPENNAGE GROUP .................................................................................................................................................19
5 POWERPLANT..........................................................................................................................................................21
6 SYSTEMS ..............................................................................................................................................................22
6.1 LANDING GEAR .........................................................................................................................................................22
6.2 FLIGHT CONTROLS ....................................................................................................................................................23
6.3 FUEL SYSTEM...........................................................................................................................................................26
6.4 HYDRAULIC SYSTEM ..................................................................................................................................................26
6.5 ELECTRICAL SYSTEM ..................................................................................................................................................27
6.6 LIGHTS ...................................................................................................................................................................28
6.7 PRESSURIZATION AND ENVIRONMENTAL SYSTEM ............................................................................................................29
6.8 OXYGEN SYSTEM ......................................................................................................................................................30
6.9 ICE PROTECTION.......................................................................................................................................................30
7 INSTRUMENTATION AND AVIONICS ...................................................................................................................31
7.1 GENERAL ................................................................................................................................................................31
7.2 ELECTRONIC FLIGHT DISPLAYS .....................................................................................................................................31
7.3 MULTI-FUNCTION DISPLAY (MFD) ..............................................................................................................................32
7.4 RADIO SENSOR SYSTEM .............................................................................................................................................32
7.5 FLIGHT MANAGEMENT SYSTEM...................................................................................................................................32
7.6 WEATHER RADAR SYSTEM .........................................................................................................................................33
7.7 FLIGHT CONTROL SYSTEM ..........................................................................................................................................33
7.8 STAND-BY INSTRUMENTS ...........................................................................................................................................33
7.9 ELT .......................................................................................................................................................................33
7.10 INTEGRATED FLIGHT INFORMATION SYSTEM (IFIS)..........................................................................................................33
7.11 ELECTRONIC CHARTS FOR IFIS.....................................................................................................................................33
7.12 ENHANCED MAP OVERLAY FOR IFIS.............................................................................................................................34
7.13 TCAS I ...................................................................................................................................................................34
7.14 TAWS ...................................................................................................................................................................34
7.15 IRIDIUM SATELLITE PHONE ..........................................................................................................................................34
7.16 ADDITIONAL FEATURES ..............................................................................................................................................34
7.17 PROVISIONS ............................................................................................................................................................34
8 STANDARD AIRCRAFT CONFIGURATION ............................................................................................................36
8.1 AVIONICS, INSTRUMENTS AND CONTROL PANEL .............................................................................................................36
8.2 ELECTRICAL SYSTEMS AND LIGHTS ................................................................................................................................37
8.3 POWERPLANT AND RELATED SYSTEMS ..........................................................................................................................37
8.4 SYSTEMS.................................................................................................................................................................38
8.5 EMERGENCY EQUIPMENT ...........................................................................................................................................38
8.6 MISCELLANEOUS AND GROUND SUPPORT EQUIPMENT ....................................................................................................38

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9 OPTIONAL EQUIPMENT ......................................................................................................................................42
9.1 INCREASED RANGE OPTION ........................................................................................................................................42
9.2 AVIONICS OPTIONS ...................................................................................................................................................42
9.3 MISCELLANEOUS EQUIPMENT .....................................................................................................................................46
10 INTERIORS ...........................................................................................................................................................49
10.1 GENERAL ................................................................................................................................................................49
10.2 CABIN ....................................................................................................................................................................49
10.3 CABIN NOISE ...........................................................................................................................................................50
10.4 MISCELLANEOUS COCKPIT FURNISHINGS .......................................................................................................................51
10.5 INTERIOR DESCRIPTION ..............................................................................................................................................52
10.6 STANDARD PASSENGER INTERIOR TRIM ................................................................................................................53
11 INSPECTIONS .......................................................................................................................................................73

APPENDIX A - NOTES ABOUT THE 3-LIFTING-SURFACE DESIGN .................................................................................................74

APPENDIX B – NEW AIRCRAFT WARRANTY...........................................................................................................................76
APPENDIX C – OPTIONAL EQUIPMENT LIST SUMMARY ...........................................................................................................77

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1 INTRODUCTION

Scope of this document is to provide a preliminary specification and description of the P.180
Avanti EVO configurations in order to allow the evaluation of design, performance, and
equipment.
Piaggio P.180 Avanti EVO is the brand name of the latest evolution of Piaggio P.180 aircraft
obtained applying several major updates to P.180 Avanti II configuration.
Data and information herein are supplied for general information purposes only and are subject
to change.
The Manufacturer reserves the right to substitute equipment in lieu of that specified in this
publication or modify the configuration whenever such substitution/modification is deemed
necessary to comply with technical or regulatory requirements or to improve the product.
For performance data and operating limitations, reference must be made to the approved
Flight Manual and other appropriate documentation.
Reference to manufacturers of parts and equipment herein are quoted just as general
reference, and are therefore subject to change. Specifications, Standard Equipment and
Suppliers are subject to change without notice.
All performance information herein is for the standard aircraft, prior to installation of any
optional equipment, if not explicitly declared. All diagrams and schematics are for illustrative
purposes only.
All reasonable care has been taken by PIAGGIO AERO INDUSTRIES S.p.A., from now on PIAGGIO,
to ensure the accuracy of the information contained in this document.
However, this document does not constitute a contractual commitment, nor is it to be used in
connection with the flight operation or maintenance of an aircraft.

1.1 APPLICABLE DOCUMENTS AND REFERENCES

[1] P.180 Avanti EVO – Airplane Flight Manual

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2 GENERAL DESCRIPTION

The PIAGGIO P.180 Avanti EVO is a effect of the three lifting surfaces in the
pressurized, twin-engine, three lifting Avanti EVO allows some 34% main wing
surfaces, pusher propellers, turbine- area reduction, hence a proportional
powered aircraft capable of carrying up to benefit in weight and drag.
10 people (including crew) depending on In order to improve overall performance,
interiors configuration and the selection of the P.180 Avanti EVO is equipped with
options. winglets and new forward wing tips,
The aircraft complies with the requirements perfectly integrated in the original yet
of EASA CS-23 and of FAR Part 23. It has advanced aerodynamic design.
been certified by the Authorities of the Pitch and yaw control are through a
European Union, United States, Canada and traditional T-tail arrangement and lateral
other countries in the transport category control through ailerons, thus providing
including day, night, VFR, IFR operations fully conventional handling characteristics.
and flight into known icing conditions.
All controls are fully manual and
The P.180 Avanti EVO complies with RVSM aerodynamically balanced for lightness, and
operation requirements and is approved for the ailerons have completely sealed gaps.
Cat. II approach and landing operations and All three axes have electrically - powered
for steep approaches. trim tabs.
The Avanti EVO is designed to provide jet- The airframe consists of 90% percent
like speed on turboprop fuel flows, as well aluminum alloy and 10% composite
as the spaciousness and comfort of a wide- construction. The engineer’s objective was
body, stand-up cabin. Key to the Avanti to concentrate the primary stress from the
EVO's speed and efficiency is the three wing, landing gear and aft pressurization
lifting surface configuration and no bulkhead on the “structural core” of the
aerodynamic compromise. aircraft. This allowed a noticeable weight
A low drag airfoil for the main wing was saving in that area since the same structure
designed applying a NASA developed supports different loads at different times.
methodology, taking advantage of the A variable cross-section, streamlined
pusher configuration's undisturbed airflow fuselage was developed to obtain both
over the main wing to enhance laminarity. efficiency and the greatest possible interior
Laminar flow over 50% of the wing chord volume. The fuselage is a monocoque
was achieved, which compares to a structure made of conventional aluminum
maximum of 20% of wing chord normally alloy, produced through an innovative,
obtained on tractor type propeller aircraft. "outside-in" construction process, whereby
large skin panels are held in place by
The Avanti EVO's forward wing is a fixed vacuum pressure as internal structure is
lifting surface which has flaps that move in riveted into place. The result is a fuselage
concert with main wing flaps. The forward built to extremely close external tolerances,
wing pitch angle is set so that it stalls before thus minimizing drag due to imperfections.
the main wing, producing an automatic
nose-down effect; its five degree negative Composite materials were used only where
dihedral keeps the stream wash they really made sense; in areas requiring
interference clear of the engine inlets, the maximum stiffness with minimum weight,
main wing and the stabiliser. The global such as the stabiliser, and also in areas with

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intricate complex surfaces such as the art, powerful LED TAXI & LANDING light
engine nacelles or the winglets. system, that achieve a light service life two
order of magnitude greater than current
The turboprop engines are fitted with
technology, positioned on Nose & Main
inertial particle separators and installed as
Landing Gear legs. As a matter of fact
pushers in low-drag, area-ruled nacelles.
Avanti EVO has no incandescent bulbs on
Avanti EVO is designed to minimize impact the entire aircraft.
on environment, significantly reducing
Further design optimization is achieved
community noise levels close to 1/2 of the
removing the active lights door with
Avanti & Avanti II acoustic power .
associated actuation and controls.
This ambitious goal has been obtained with
Avanti EVO incorporate a brand new
new propeller arrangement made with a
landing gear system that is designed to
state of the art pusher propeller with
maintain and improve aircraft performance
scimitar blades rotating at lower rpm
and at the same time reduce significantly
coupled with proprietary exhaust “shark
life cycle costs.
gills” ducts that optimize hot gases impact
on blades & hub and at the same type The nose gear is equipped with a SAE Class
improve thrust in cruise while reducing B steering system, providing full time use
community noise at takeoff & landing. during T/O & Landing with automatic
engagement / disengagement; the steering
As a side benefit, the new propeller
system technology used on Avanti EVO is at
arrangement provides a slight improvement
the state of the art for the business aviation
to the already best in class internal noise
and is derived from best-in-class
levels.
applications.
The five-bladed counter rotating scimitar
To provide the best possible flexibility for a
propellers do not need any anti-ice system
variety of customer needs, Avanti EVO may
since are naturally heated by the exhaust
include in its configuration an additional
gases.
fuel tank, placed in lieu of toilet cabinet,
Avanti EVO has been designed to that brings the max range up to 1,770 nm.
incorporate a state of the art digital The additional fuel tank operation is
Environmental Control System that designed to be transparent to ground and
provides a fully automatic, dual zone, flight crew.
integrated bleed air heating and vapor cycle
Aiming at further operational capability,
cooling system; automatically managing
Avanti EVO may include in its configuration
cabin and cockpit temperatures.
an advanced Anti-Skid system to improve
As an additional improvement the new ground handling qualities and reduce pilot
digital ECS has an increased cooling power workload.
to reduce cool down time in hot weather.
The ECS package is located completely
below the baggage compartment floor, thus
improving everyday use of the available
volume.
To improve efficiency and reliability Avanti
EVO has been equipped with a state of the

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3 SPECIFICATIONS

3.1 EXTERNAL DIMENSIONS

Wing
Span (without winglets) 45.41 ft 13.84 m
Aspect Ratio 11.96
Sweep (leading edge) 1° 11' 24"
Dihedral 2° 00' 00"
Area 172.22 ft2 16.00 m2
Wing Loading (w/o winglets) 70,26 lb/ft2 343.04kg/m2

Forward Wing
Span (without wing tips) 10.76 ft 3.28 m
Aspect Ratio 4.92
Sweep (@ 25% chord) 0° 00' 00"
Dihedral -5° 00' 00"
Area 23.59 ft2 2.19 m2

Horizontal Tail
Span (without fairings) 13.73 ft 4.18 m
Aspect Ratio 4.57
Sweep (@ 25% chord) 29° 48' 00"
Dihedral -5°00'00"
Area 41.27 ft2 3.83 m2

Vertical Tail
Span 7.70 ft 2.35 m
Sweep (@ 25% chord) 40° 00' 00"
Area 50.92 ft2 4.73 m2

Landing Gear
Track 9 ft 4.0 in 2.84 m
Wheelbase 19 ft 0.0 in 5.79 m
Overall Dimensions
Length (without tail tip light) 47 ft 3.2 in 14.41 m
Height 13 ft 0.7 in 3.98 m
Span 47 ft 0.9 in 14.35m

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3.2 INTERNAL DIMENSIONS AND VOLUMES

Cabin Dimensions
Height 5 ft 9 in 1.75 m
Width 6 ft 1 in 1.85 m
Cockpit Length 4 ft 9 in 1.45 m
Passenger Cabin Length 14 ft 11 in 4.55 m
including Lavatory Length 2 ft 7 in 0.79 m
Total Length 19 ft 8 in 6.00 m

Cabin Volume
Cockpit 79.81 ft3 2.26 m3
Passenger Cabin 375.00 ft3 10.62 m3
Total Volume 454.81 ft3 12.88 m3

Cabin Door Dimensions

Height 53 in 1.35 m
Width 24 in 0.61 m

Baggage Compartment Dimensions

Total Length 5 ft 7 in 1.70 m
Total Volume 35 ft3 1. m3

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 3.3 WEIGHTS

CORPORATE VIP
Maximum Ramp 12150 lb 5511 kg
Maximum Take-off 12100 lb 5489 kg
Maximum Landing 11500 lb 5216 kg
Maximum Zero Fuel 9800 lb 4445 kg
Standard Equipped Empty (1) 8150 lb 3697 kg
Standard Operating Empty (2) 8350 lb 3787 kg
Standard

Useful Load (3) 3800 lb 1724 kg

Usable Fuel (@ 6.70 lb/gal) (4) 2802 lb 1271 kg
Maximum Net Payload (5) 1450 lb 658 kg
Fuel with Max. Net Payload (6) 2350 lb 1066 kg
Net Payload with Max. Fuel (7) 998 lb 453 kg
Increased Range Equipped Empty (8) 8200 lb 3720 kg
Increased Range Operating Empty (2) 8400 lb 3810 kg
With Increased
Range Option

Useful Load (3) 3750 lb 1701 kg

Usable Fuel (@ 6.70 lb/gal) (9) 3200 lb 1451 kg
Maximum Net Payload (5) 1400 lb 635 kg
Fuel with Max. Net Payload (6) 2350 lb 1066 kg
Net Payload with Max. Fuel (7) 550 lb 250 kg

NOTES
(1) Assuming standard Corporate 4 interior configuration with De Crane seats/divan; no options included.
Does not include weight of crew. Weight may vary depending on interior configuration and options
selection. For reference only.
(2) Includes one pilot at 200 lbs.
(3) Maximum ramp weight less operating empty weight.
(4) Equal to 418.1 U.S. gallons or 1,583 litres
(5) Zero fuel weight less operating empty weight
(6) Useful load less maximum net payload.
(7) Useful load less full fuel weight.
(8) Standard Equipped Empty plus 50 lbs (net weight increased range option).
(9) Equal to 476 U.S. gallons 1802 litres

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3.4 PRESSURIZATION
The structure supports a nominal maximum cabin pressure differential 9.0 psi.
Differential 9.0 psi .62 bar
S.L. Cabin to: 24000 ft 7315 m
Cabin altitude @ certified ceiling 6600 ft 2012 m
Certified Ceiling 41000 ft 12500 m

3.5 POWERPLANT
Engines
Manufacturer PRATT & WHITNEY OF CANADA
Model PT6A-66B (1)
Power (each)
850 SHP (634 kW)
(flat rated from 1630 thermodynamic HP)
Power Loading 7.12lb/SHP (3.23 kg/SHp)
TBO 3600 hours
NOTES: (1) Equipped with torque limiter set to 2495 lb*ft.

Propellers
Manufacturer HARTZELL
Model HC-E5N
Diameter 86,5 in ( 2197 mm)
Five-blade scimitar, constant speed,
Type
fully feathering, hydraulically operated
TBO 3600 hours

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3.6 PERFORMANCE

3.6.1 TAKE-OFF, LANDING AND ALTITUDE PERFORMANCES

Take-off Distance (1), S.L., ISA 3196 ft 974 m

Landing Distance (2), S.L., ISA (*) 3282 ft 1000 m
Rate of Climb, S.L., ISA
MTOW Both Engines 2950 ft/min 899 m/min
11550 lbs One Engine Inoperative 785 ft/min 239 m/min
MTOW Both Engines 2770 ft/min 844 m/min
12100 lbs One Engine Inoperative 697 ft/min 212 m/min
Service Ceiling
Both Engines 41000 ft 12497 m
One Engine Inoperative 23800 ft 7254 m

NOTES:
(*) Distance obtained by flight testing as per the EASA/FAA rules, without propeller reversing,
distance certification pending
(1) FAR 23 runway requirement (2-engine Take-off to clear 50 feet) for turboprop aircraft.
(2) Total distance over 50 feet, full flaps, without propeller reversing. Does not include any runway
factors for destination or alternate airports.

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 3.6.2 NOISE
The aircraft is compliant with certification noise levels specified in FAR 36, Appendix G, Amdt.
16 and in ICAO Annex 16 Chapter 10.

3.6.3 CRUISE PERFORMANCE

Maximum Speed(3) 402 KTAS 745 km/h

Cruise Speed at Maximum Cruise Power (4)

At 31000 ft 400 KTAS 741 km/h
At 35000 ft 386 KTAS 715 km/h
At 39000 ft 357 KTAS 661 km/h

IFR Maximum Cruise Range (at Maximum Range Power):

Range with Corporate VIP Configuration(5) At 39000 ft

1460 nm 2704 km
Standard Configuration(6)
Standard Configuration
1620 nm 3000 km
with Increased Range Option(7)

Range with Shuttle Configuration(8) At 39000 ft

1490 nm 2760 km
Standard Configuration(6)
Standard Configuration
1770 nm 3278 km
with Increased Range Option (7)

NOTES:
(3) At 31000 feet and ISA Conditions.
(4) Typical mid-cruise weights (operating weight + 4 PAX + 1/2 full fuel) ISA conditions and IFR
reserves.
(5) Assuming standard Corporate 4 interior configuration with De Crane seats/divan; no options
included.
(6) Mission with 1 pilot + 4 PAX, ISA conditions, zero wind.
(7) Mission with 1 pilot + 4 PAX, ISA conditions, zero wind. additional fuel tank configuration
(8) Assuming Layout Option 10 interior configuration with High Density seats; no options included.

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3.7 OPERATING SPEEDS
Stall Speed, Landing Configuration
VSO 95 KIAS 176 km/h

Maximum Operating Speed Limits

VMO 260 KIAS 482 km/h
MMO 0.7 Mach

Maximum Flap Operating Speeds

VFO flaps MID 170 KIAS 315 km/h
VFO flaps DN 150 KIAS 278 km/h

Maximum Flap Extended Speeds

VFE flaps MID 183 KIAS 339 km/h
VFE flaps DN 177 KIAS 326 km/h

Maximum Landing Gear Operating Speed

VLO 181 KIAS 335 km/h

Maximum Landing Gear Extended Speed

VLE 185 KIAS 343 km/h

Minimum Control Airspeed

VMCA 100 KIAS 185 km/h

Maneuvering Speed
VA 202 KIAS 374 km/h

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 3.8 PERFORMANCE CHARTS

P.180 - Flight Envelope

Mach

0.2 0.3 0.4 0.5 0.6 0.7 0.8

50000 15240

VC 100 VC 150 VC 200

40000 12192

VC 250
1

Altitude
30000 9144
Altitude [ft]

VC 300

20000 6096

10000 3048

0 0

50 100 150 200 250 300 350 400 450 500

True airspeed [KTAS]

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 Avanti EVO Range Vs Payload with and without Extra Fuel Tank
(Chart referred to Shuttle Layout)

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 Avanti EVO Specific Range Speed
(Cruise Weight 10,000 lbs, ISA Conditions)

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4 AIRFRAME

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ft

5 ft 9” 5

6 ft 1”
3

3.74 ft

4.1 FUSELAGE GROUP

Avanti EVO's aluminum fuselage is circular left-hand side of the fuselage and is 53
in cross section and tapers both fore and inches (1346 mm) high and 24 inches (610
aft. Cabin width extends to 6 feet 1 inch mm) wide. The upper half of the door is
(1854 mm) and a dropped aisle provides a side-hinged and swings forward to open.
cabin height of 5 feet 9 inches (1753 mm). The lower cabin door, which has two steps,
is bottom-hinged and opens downward.
The two-part cabin door is located on the

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A plug-type emergency exit hatch is located are integral) with two main spars. The wing
on the right-hand side of the cabin has a third spar running from the nacelle to
immediately opposite the cabin door. the fuselage centerline. Connected to the
The aft fuselage extends from the aft main box are an aluminum leading edge
pressure bulkhead to the tail-cone and is and aluminum and composite trailing
divided into two sections: the wing/fuselage edges. The wing incorporates inboard
intersection area and the baggage single-slotted flaps, outboard Fowler flaps,
compartment area. ailerons and engine support structure
(engine cradles are made of titanium alloy).
Within the wing/fuselage intersection area,
The wing contains an integral fuel tank out
the space over the wing and between the
to 21.34 feet (6503 mm) from fuselage
forward and central bulkheads contains an
centre line. Wing leading edge anti-ice is
integral fuel tank. This tank is divided into
accomplished by directing engine bleed air
two parts by a centre panel and is
through a diffuser duct installed in the main
interlinked with the wing tanks. Located in
wing leading edge.
the fuselage beneath the wing are most
major accessories. The forward wing is an all aluminum alloy
unit. The wing main box is a working skin
The baggage compartment is located in the
type (wing panels and spars are machined,
aft part of the fuselage between the third
stiffeners are integral) with two main spars,
wing spar and the tail-cone.
like the main wing, and is attached to the
Baggage compartment length is 5 feet 7 lower fuselage at four points. The
inches (1700 mm) and total volume is 35 aluminum alloy leading edge, contains an
cubic feet (1.00 m3). The baggage door is a electrically-activated de-icing blanket.
composite part and is hinged at the top. Single-slotted forward wing flaps are full-
The tail-cone is attached to the rear depth honeycomb aluminum parts. The
fuselage and supports the empennage. forward wing tip is an Hoerner tip like
shape, it is in fiberglass and has an
4.2 WING GROUP aerodynamic re-balancing function that
Avanti EVO is a three-lifting-surface design undoes the increasing of aircraft pitching
using a forward wing, an aft fuselage, mid- moment due to the winglet installation.
mounted main wing, and a stabiliser at the
tail. 4.3 EMPENNAGE GROUP
The wing is characterized by an aspect ratio The tail group consists of a fixed vertical fin,
of 11.96, a taper ratio of .34, a dihedral of two ventral (delta) fins, a movable stabiliser
2° and a swept of 1°11' (leading edge). The with elevators, and a rudder with trim tab.
airfoil thickness varies from 13% at the tip
Aerodynamically and mass-balanced
to 14.5% at the nacelle; inboard the nacelle,
elevators are made of full-depth aluminum
the wing has an average thickness of 13.5%.
honeycomb with aluminum skins and a
The wing is provided with a carbon fiber single spar. Each elevator is actuated by
winglet which is characterized by an aspect means of an aluminum torque fitting
ratio of 1.39, a taper ratio of 0.54, a cant attached to the inboard end of the spar.
angle of 19.2°, a sweep angle of 45.33° at
The all-movable stabiliser is a two spars
leading edge, a toe angle of 1°.
sandwich construction of graphite fabric,
The high-aspect-ratio main wing is surrounding a Nomex honeycomb core.
constructed of aluminum alloy. The wing
The vertical fin is attached to the tail-cone
main box is a working skin type (wing
bulkheads by four vertical aluminum
panels and spars are machined, stiffeners
machined spars. Skins are of aluminum

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sheet chemically milled to reduce weight. adjustable weights in this horn. The rudder
The rudder is a two spars structure with is actuated by means of an aluminum
spars and skin in aluminum alloy; it has a torque fitting attached to the lower end of
trim tab located in its trailing edge. The the front spar and to the reinforced lower
rudder is aerodynamically balanced by a close-out cap.
leading edge horn and mass balanced by

Composite Components

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5 POWERPLANT

Two Pratt & Whitney Canada PT6A-66B tests to demonstrate the extinguishing
turboprop engines are mounted in titanium agent concentrations in nacelle zones have
engine cradles atop the main wing in been carried out.
composite-construction nacelles. The engines drive two Hartzell, five-bladed,
The PT6A-66B is a light-weight, free-turbine aluminum, counter-rotating, pusher
engine, with a maximum thermodynamic propellers scimitar type optimized for
rating of 1,630 (1,215 kW) horsepower and 1800rpm, with the left-engine propeller
flat rated to 850 shaft horsepower (634 turning clockwise and the right-engine
kW). Each engine utilizes two independent propeller turning counter-clockwise. The
turbine sections: one driving the left engine is equipped with a standard
compressor in the gas generator section gearbox which incorporates a modification
and the second one (a two-stage power allowing reverse prop shaft rotation. The
turbine) driving the propeller shaft through aircraft has no critical engine due to
a reduction gearbox. Fire warning is opposite-rotation propellers. Woodward
provided by a continuous-type thermal propeller governors are fitted with an
detector running through each engine integral Beta valve, permitting reverse
compartment around and along the engine. thrust operation. The propellers are also
equipped with an autofeather system.
The fire protection system installed on
P.180 Avanti EVO detects the presence of a The P180 is equipped with a propeller
fire or of a local overheat condition in the synchrophaser system as to reduce noise
engine fire zones. The engine fire during cruise, controlling the relative phase
extinguishing system discharges between propellers and, based on phase
extinguishing agent into the fire zones error, changing props RPM to restore the
when it is activated by the flight crew. selected relative phase position.
Two identical systems are installed, one for The synchrophaser system may be engaged
each engine. The fire bottles are carbon- after takeoff and automatically disengages
halon steel containers attached to the in the case of in-flight engine shut-down or
engine mounting frames. The stainless steel propeller feathering.
tubes and nozzles duct the extinguishing The P.180 is equipped with conventional
agent to the fire zones and to the propeller push-pull manual controls including, for
gearbox zones. each of the two power plants, an engine
The system is activated through two lighted power output control lever and a combined
pushbuttons installed on glareshield left propeller control and fuel condition lever.
and right sides. They are guarded to These levers are mounted together in a
prevent inadvertent discharge of the fire control box assembly located on the control
bottles. pedestal in the flight compartment, with
The engine fire extinguishing system has Power Levers on the left side and Condition
been certified on a non-dangerous basis. No Levers on the right.

Engine nacelle section

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6 SYSTEMS
Wheel Master Switches located on pilot’s
6.1 LANDING GEAR and copilot’s control wheel handles.
The system shall automatically disarm upon
The landing gear is hydraulically operated
gear retraction or failure detection.
and fully retractable. Shock absorption on
all three gear is via air-oil struts. The
double-wheel nose gear retracts forward
into the nose section, while the single- The landing gear can be extended at speeds
wheel main gear retract backwards into the up to 185 KIAS. The gear actuators
aft fuselage. Doors completely cover the incorporate both internal up and down
retracted gear. The rear door of the nose- locks. A warning horn will sound under the
gear well and the forward doors of the following circumstances:
main-gear strut wells remain open when  the landing gear is not locked down
the gear is extended. The side-hinged wheel and power is reduced below a
well doors of the nose gear and the aft setting sufficient to maintain level
doors of the main gear open with gear flight;
extension and then close when the gear is  the flaps are lowered to the down
fully extended. position without the gear locked in
The nose gear is equipped with an electro- the down position;
hydraulic Class B (according to SAE  the flaps are set to the mid position
ARP1595) steering system with an and the left power lever is retarded
integrated rack-and-pinion type steering approximately below the half-travel
actuator. position.
The nose gear is steerable through 50
degrees left and right in the TAXI mode, and The emergency landing gear extension
7 degrees left and right in the Take-Off & system consists of a hydraulic hand pump,
Landing mode. an emergency select valve and emergency
Full time use during T/O & Landing with lines from the fluid reservoir to the
automatic engagement / disengagement. actuators.
Toe-actuated BF Goodrich carbon disc
The steering system is automatically armed brakes are installed on the main gear
when nose landing gear is down-and- wheels. Brakes are hydraulically actuated
locked; when in air it will command nose through a primary system or a secondary,
wheels centered while when on ground it emergency system.
will automatically select Take-Off & Landing
mode. Pilot selection is required to operate
in Taxi mode.
The electro-hydraulically operated nose-
gear steering is controlled through the
rudder pedals.
A control-wheel-mounted push button is
used to select the steering mode.
Both pilot and copilot can disarm the
steering system at any time via the Control

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Revision 7.1 April 2016 Avanti EVO Specification and Description
 in a dual-pilot control configuration.
6.2 FLIGHT CONTROLS
Differential ailerons provide roll control. An
Control surfaces are mechanically
autopilot rotary actuator may also drive the
connected to the pilot controls via cables,
ailerons quadrants. An aileron trim tab is
pulleys, push-pull rods and bell cranks in a
installed on the right aileron.
closed loop system. Primary controls consist
of ailerons, elevators and rudder. The pilot It has to be noted that winglet has been
controls consist of a control wheel hinged carefully designed to maintain favorable
on a yoke control column and adjustable aileron behavior.
rudder pedals hinged on the cockpit floor,

Lateral (roll) Control System

The pitch control system consists of an all trim actuator and an autopilot rotary
moving stabiliser-elevator assembly. The actuator connected to the elevator. The
trim system for this control is an elevator provides primary pitch control and
electromechanical actuator which controls consists of two surfaces separately hinged
the stabiliser angle of attack. The autopilot to the stabiliser.
system may drive both the horizontal tail

Longitudinal (pitch) Control System

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Revision 7.1 April 2016 Avanti EVO Specification and Description
An up-down spring mechanism, linked to assembly connect rudder pedals quadrant
the stabiliser, is installed in the longitudinal to rudder quadrant. An autopilot rotary
control system to provide a suitable pilot actuator may also drive the pedals
column stick force through the complete quadrant. The flight control system uses no
centre-of-gravity range, to provide dampers, stick-pushers or boosted control
increased stability at high speed and to mechanisms. Secondary control is provided
improve trimmability at low speed. by the aileron and rudder trim tabs for roll
and yaw, and by the all-movable stabiliser
for pitch. All trimming surfaces are
The rudder controls the aero plane electrically operated and controlled.
directionally about its vertical axis. A cables
circuit, push-pull rods and a bell-crank

Directional (yaw) Control System

Pitch trim is accomplished by repositioning The Avanti EVO flap system consists of
the stabiliser to the desired trim setting three mechanically independent sets of
through actuation of the horizontal pitch flaps: main wing outboard flaps, main wing
trim actuator. The three-motor, screw-jack inboard flaps and forward wing flaps. Each
type actuator has a primary and a set of left and right main wing flaps are
secondary mode of operation. Longitudinal mechanically interconnected. The operation
trim is mechanically fail-safe. of all flaps is synchronized by an electronic
control unit that controls the power supply
to the flap D.C. motors. A drive unit, located
A rudder trim tab, hinged to the trailing
in the centre of the fuselage, actuates the
edge of the rudder, is operated by an
main wing inboard and outboard flaps.
electro-mechanical actuator installed in the
Additionally, forward wing flaps are
vertical fin.
electrically driven by actuators in the
An aileron trim tab, hinged to the right forward wing.
aileron, is operated by an electro-
mechanical actuator installed in the wing.

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There are three discrete flap positions Flaps retract simultaneously to the mid
controlled by micro-switches: up, mid- position in five seconds. From the mid
takeoff position, down-landing position flaps retract simultaneously to the
configuration. From the up- to the mid- up position in 16 seconds.
setting, flap deployment takes 16 seconds.
Flap travel is sequenced to minimize pitch The flap position indicator, shown on the
change through flap deployment. From the central Multi Function Display, provides the
mid setting, all flaps descend crew with visual indication of flap surface
simultaneously to the down setting in five positions.
seconds.

Flap System

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Revision 7.1 April 2016 Avanti EVO Specification and Description
6.3 FUEL SYSTEM
The fuel system has a baseline
total fuel capacity of 421.9 U.S. Fuel System
gallons (2,848 lbs, 1,597 liters),
with a usable fuel of 418.1 U.S.
gallons (2,802 lbs, 1,583 liters).

Each engine is fed by its own

fuel system made up of four
interconnected tanks: an
integral fuselage tank just
above the wing, a wet-wing
tank, one fuselage under-wing
collector tank and one
auxiliary collector tank also
located in the fuselage below
the wing.
The aircraft can be optionally equipped with switches on in the event of main pump
an additional fuel tank to improve aircraft failure.
flight range by increasing the available fuel A capacitance-type fuel gauging system is
volumes without affecting present MTOW. used to indicate the fuel quantity, which is
shown in pounds. The fuel tanks have been
The tank add 58 U.S. gallons (390 lbs, 220
coated to provide corrosion resistance and
litres), for a total fuel capacity of 480 US
protection against micro-organism damage.
Gallons, with usable fuel system capacity of
476 U.S. gallons (3218 lbs, 1,802 litres). 6.4 HYDRAULIC SYSTEM
The additional fuel tank has been designed The hydraulic system provides hydraulic
to avoid any extra work to the crew both in power for nose wheel steering, wheels
air and on ground, since refueling and braking, landing gear extension and landing
unloading operations remain unchanged gear retraction.
(ref. § 9.1 for further details). Hydraulic power is generated by a hydraulic
The left and right fuel systems are package whose main components are a
independent except during pressure variable displacement pump, a reservoir, a
refueling operations, during which a valve- low pressure filter and a landing gear
controlled interconnecting duct connects selector valve. Two master cylinders with
the left and right collector tanks. A single independent lines are provided to allow
point pressure refueling adapter is provided normal and emergency braking.
on the right side of the fuselage under the The hydraulic power package operates in
wing. three modes. High Duty Mode (HDM) is
All the fuel is supplied to the engine from selected for landing gear extension and
the fuselage collector tank. Two electrically- retraction. The HDM pressure range is
driven submerged boost pumps, located at 1,800 to 3,000 psig (124 to 207 bar). Low
the bottom of the collector tank, are Duty Mode (LDM) is selected when landing
connected to the fuel low pressure line to gear extension has been completed and is
the engine. The main boost pump normally the normal operating mode for steering and
supplies fuel to the engine driven fuel braking. The LDM pressure range is 800 to
pump; the stand-by pump automatically 1,200 psig (55 to 83 bar). Non Operating

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Revision 7.1 April 2016 Avanti EVO Specification and Description
Mode is selected automatically when the in parallel provide torque for engine
landing gear is retracted or the pilot has starting and generate D.C. electrical power.
switched the power unit off. One 25.2 Volt, 38 Ampere-hour nickel-
An electrical depressurizing valve cadmium battery, located in the front
automatically selects HDM or LDM. The section of the rear baggage compartment,
hydraulic system uses a hydraulic fluid provides power for starting and also serves
according to MIL-H-5606 specification and as a reserve source of emergency electrical
is pressurized by bleed air. power in case of dual generator failure. A
5Ah@24VDC Emergency Power Unit is
provided to supply a subset of emergency
6.5 ELECTRICAL SYSTEM systems (Standby, COM1, ..).
A dual parallel main bus distribution system Generator control units are able to
is laid out so that, in the event of failure of a maintain the output voltage of the
single power source or of a distribution generators at a constant level during
system, power is maintained to essential variation in engine speed and electrical
equipment by the essential bus. The load. The electrical system is automatically
essential bus is energized by three paths, protected from over-voltage and reverse
each equipped with one circuit breaker and current.
one reverse current blocking diode. This
No AC power is required for the avionics
ensures that the essential bus remains
systems. Two small dual voltage inverters,
active with two independent faults in the
located in the cockpit, are used for
feed cables.
powering and dimming both the
The distribution function is ensured by a
electroluminescent AC panels and the
dual (internally segregated Lh and Rh side)
incandescent DC panels/bezels.
Main Junction Box, located in the
equipment section forward to the baggage An external power receptacle, located on
volume, and by two (Pilot and Copilot side) the left side of the fuselage just above the
Circuit Breakers Panel, located in the main gear well and provided with
cockpit. overvoltage protection, allows the use of an
The new Main Junction Box provides auxiliary power source to either start the
improved reliability and enhancements on engines or perform an extended ground
segregation and growth capacity. Two 28 check of the electrical equipment.
Volt, 400 Ampere D.C. starter / generators

DC power distribution

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6.6 LIGHTS
The aircraft is equipped with the
following lights:
‐ two winglet (red and green,
forward facing) position lights,
one vertical fin top fairing
(white, rear facing) position
light ;
‐ two anti-collision strobe lights
(one on top of the vertical fin
and one on the bottom
fuselage);
‐ two landing lights (one each
on the legs of the main
landing gear) and one taxi
light (on the nose landing gear
leg);
‐ one wing inspection light on
the left outboard nacelle TAXI LIGHT
surface;
‐ one recognition/approach
light located on the top of the
vertical fin leading edge. External Lights

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Revision 7.1 April 2016 Avanti EVO Specification and Description
6.7 PRESSURIZATION AND ENVIRONMENTAL SYSTEM
The environmental control system utilizes passed and then mixed to the colder flow
engine bleed air for heating, cooling, and through the two mixing valves.
pressurizing the cabin; one engine is The already mixed airflow is provided to
capable of sustaining the operation of the passenger cabin and cockpit through two
entire system. Two outflow valves located separated check valves.
on the rear pressure bulkhead regulate The airflow is distributed in the passenger
cabin pressurization. The pressurization area through overhead and floor diffusers,
controller provides both an auto-schedule and in the cockpit area through adjustable
mode and a manual control. outlets, lateral and floor diffusers.
The 9.0 psi (.62 bar) system provides a The controller is primarily managed by a
6,600 feet (2012 m) cabin altitude at 41,000 dedicated ECS Control Panel, installed in the
feet (12500 m) and maintains a sea-level
cockpit on pilots side instrument panel,
cabin up to 24,000 feet (7315 m). providing both full Auto and Manual control
The new Environmental Control System possibility.
provides a fully automatic, dual zone, In the passenger cabin, a RH and a LH LCD
integrated bleed air heating and vapor cycle control panels, used in conjunction with RH
cooling system (VCCS) ECS controller; it will and LH cabin evaporator, will provide
automatically and independently manage advanced control to obtain different outlet
the cabin and cockpit temperatures in both temperatures between the left outlets and
cooling and heating modes with an increase the right outlets and give the passengers a
in cooling power of about 25%. semi-zone control within the limits of the
The integrated Environmental Control Unit cabin zone set-points.
is packaged to fit into the area below the Manual modes are also provided to allow
P.180 baggage compartment.
manual control of mixing valves position,
Bleed air from the engine first enters a pre- evaporator blower speeds and air-
cooler which reduces the temperature to an conditioning compressor operation.
adequate level, then through a shut-off The controller and cockpit control panel will
valve, a check valve and a pressure
also be designed to ensure adequate
regulator reaches the ECS Gate valve. manual control in the event of a controller
The bleed air is divided into two flows; one logic failure.
enters the air to the air heat exchangers to
produce a colder flow; the other one is by-

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Revision 7.1 April 2016 Avanti EVO Specification and Description
6.8 OXYGEN SYSTEM flight.
A 40 cubic feet (1.13 m3) storage cylinder is Main wing leading edge anti-ice is
installed on the left side of the fuselage accomplished by directing engine bleed air
under the cabin floor aft of the cabin door. through a diffuser duct installed in the main
Oxygen is supplied to pilot and co-pilot wing leading edge.
positions through quick-donning The forward wing contains an electrically-
diluter/demand masks. Automatic drop-out, activated de-icing blanket on the aluminum
constant flow oxygen masks are provided at alloy leading edge.
each passenger position. Nacelle inlets are de-iced by pneumatic
boots. To avoid ice ingestion, an inertial
separator is installed inside each nacelle.
6.9 ICE PROTECTION
Moreover, the cycling of the nacelle boots
An ice detector probe is located on the right is automatically controlled by the Ice
side of the aeroplane nose. When a 0.5 Detector System in its primary mode of
millimeter thickness of ice accumulates on operation. A timer is provided to cycle the
the probe, an amber ice caution light is boots for secondary operations.
illuminated on the instrument panel. A
Electric heating of the windshield on both
visual ice accretion probe, located adjacent
pilot and co-pilot sides is used to guard
to the pilot's windshield, is provided as a
against or alleviate icing and fogging.
back-up to the ice detector. A wing
inspection light is installed on the outboard No ice protection is provided or required on
side of the left engine nacelle to allow the the horizontal and the vertical tail.
pilot to check icing conditions during night

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Revision 7.1 April 2016 Avanti EVO Specification and Description
7 INSTRUMENTATION AND AVIONICS

7.1 GENERAL configured as a Multi-Function Display

The cockpit layout of the Standard (MFD) shared by the pilots.
Configuration includes two complete crew Each PFD provides attitude, heading,
stations equipped with dual controls, airspeed, altitude, vertical speed, Flight
including control columns, adjustable Control System (FCS) annunciation, and
rudder pedals and brakes. Crew seats are navigation data on a single, integrated
fully adjustable and include four-point display.
restraint harness. An emergency oxygen
system provides two diluter/demand masks The PFDs also display Engine Indication
for the crew members.
System (EIS) information if selected in
Cockpit lighting includes dome LED lights, reversionary mode. EIS information is
instrument panel flood lights, internally- always displayed on the MFD.
lighted instruments and dual map lights. The PFDs can display a full Compass Rose, a
Two heated Pitot tubes and two heated partial Compass Arc, or a flat Compass Tape
static ports (each one with two immediately beneath the attitude ball.
independent sources) provide Current heading is read opposite the lubber
dynamic/static pressure to flight line. This display incorporates a pilot
instruments. controllable Selected Heading Bug. The
Independent sources are used to drive the heading bug is controlled by the HDG rotary
pilot's and co-pilot's flight instruments. knob on the Flight Guidance Panel (FGP).
7.2 ELECTRONIC FLIGHT DISPLAYS The PFDs also provide a Track Pointer, wind
data, lateral navigation course and
The Rockwell-Collins Pro Line 21 Electronic
deviation data, distance data, Marker
Flight Instrument System (EFIS) is an
Beacon information, ILS information,
integrated system able to gather,
vertical deviation data, VNAV deviation
concentrate, and display aircraft
data, radio altitude, Decision Height and
information to the flight crew.
Minimum Descent Altitude, map display
The EFIS includes the following units: and a Flight Management System (FMS)
 Three 8”x10” colour Liquid Crystal Message Window.
Adaptive Flight Displays (AFD) with
LED backlight
 Two Display Control Panels (DCP)
 One Cursor Control Panel (CCP)
 An Integrated Avionics Processor
System (IAPS)
 Four Data Concentrator Units (DCU)

Three AFDs with identical shape are

arranged on the instrument panel as shown
in Figures at pages 40 and 41. Under normal
conditions the two lateral displays are
configured as Primary Flight Displays (PFD)
and the central display, Ethernet capable, is

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Revision 7.1 April 2016 Avanti EVO Specification and Description
 configuration), Electronic Charts (optional)
7.3 MULTI-FUNCTION DISPLAY (MFD)
or video display (optional).
The MFD includes three major display
The ProLine 21 system may include an
areas: the Engine Indication System (EIS)
optional File Server Unit (FSU) providing
region and the upper and lower Multi-
electronic charts, enhanced map features
Function Windows (MFW) below it. The EIS
(e.g., rivers, lakes, geopolitical boundaries,
region is displayed across the upper portion
airspaces and airways) and uplinked
of the MFD. The area below the engine
graphical weather. The FSU is connected to
instruments is divided into upper and lower
the Ethernet-capable MFD providing a
format windows. The contents of both
control interface to these enhanced
format windows can be separately
features using the Cursor Control Panel
controlled by the pilot.
(CCP); both Ethernet capable MFD and CCP
The EIS area continuously shows engine are installed as standard features. Further
parameters. The engine display format information is provided in the Options
consists of a full time window showing: ITT section of this document.
and Torque, both in digital form and on a
shared analogue gauge (one for each 7.4 RADIO SENSOR SYSTEM
engine), Propeller RPM and NG, both in
digital form and on individual smaller The Radio Sensor System (RSS) is made up
analogue gauges (one for each engine). of a single CDU-3000 display unit and a
single RTU-4200 tuning unit providing a
Digital only displays for Fuel Flow, Fuel primary LCD-based integrated display
Quantity, Oil Pressure and Oil Temperature system for communication and navigation
are located on the right part of the EIS operations within the Air Traffic Control
window. There are two independent environment.
sources for the primary engine parameters
(ITT, Torque, NG and Prop RPM) for each The basic communication system includes
engine: one is the Data Concentrator Unit two VHF-4000 Communication
(DCU) and the other is the Engine Data Transceivers, two TDR-94D ATC Enhanced
Concentrator (EDC). The DCU is normally Mode-S Diversity Transponders, one DME-
the source of all displayed engine data and 4000 transceiver (a second receiver is
the EDC is a secondary source of all optional), one NAV-4000 VOR/ILS/MKR/ADF
displayed engine data. receiver and one NAV-4500 VOR/ILS/MKR
Receiver.
The Upper MFW can display either a
Checklist or a FMS Text Window. 7.5 FLIGHT MANAGEMENT SYSTEM
The Lower MFW can show either a compass
The FMS-3000 satellite-based navigation
rose, a compass arc, a present position map
system provides the capability to perform
(PPOS), a plan map, TCAS only information
en route, terminal, and non-precision
(with option installed), the Systems Page,
approach lateral navigation with provision
Enhanced Maps (optional; over the PPOS or
for LPV approaches upgrade (optional). The
Plan Map) or Graphical Weather data
system contains an advanced GPS-4000S
(optional). The turbulence radar images are
Global Positioning System SBAS (Satellite
displayed on the arc or PPOS data
Based Augmentation System) receiver
The Upper MFW and Lower MFW can be which processes the transmissions from
merged into a Full Format window showing multiple GPS satellites simultaneously to
either the FMS remote text, the Status calculate navigation solutions based on
menu (including Database effectiveness, information from all satellites in view.
Charts Subscription, Maintenance Main
The Attitude Heading Reference System
Menu, FCS Diagnostic, optional File Server

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Revision 7.1 April 2016 Avanti EVO Specification and Description
(AHRS), Air Data Computer (ADC), DME and 7.8 STAND-BY INSTRUMENTS
VOR data are also used by the FMS. The An L-3 Communication integrated stand-by
FMS provides necessary controls for all instrument located on the top of the centre
input sensors, if appropriate. instrument panel and supplied by an
A Coupled VNAV interface with the FCS emergency battery provides essential flight
allows the FMS VNAV function to select parameters in case of loss of primary
various FCS vertical modes of navigation. sensors or displays.
The FMS interfaces with the Data Base Unit
(DBU) to update, through a USB drive, its 7.9 ELT
internal Data Base and with the EFIS
An Artex C406 3-frequency Emergency
Displays to provide conventional navigation
Locator Transmitter transmits on the two
information and state-of-the-art map
Emergency Frequencies of 121.5 and 243.0
presentation.
MHz as well as on the satellite frequency of
7.6 WEATHER RADAR SYSTEM 406.025 MHz.
The system is activated either automatically
The Rockwell-Collins RTA-852 Turbulence by a g-switch or by the crew through a
Detection Radar is a stabilized, solid state, switch located in the cockpit.
X-band color radar system. The weather
and map information can be overlaid on 7.10 INTEGRATED FLIGHT INFORMATION SYSTEM
either or both PFDs and MFDs on most of (IFIS)
the navigation display formats.
The IFIS provides capability to display maps
The Control Panels provide the radar mode (airways, airspace boundaries, geopolitical
menu selection, range select knob, tilt knob data), Jeppesen charts (airport charts,
and ground clutter suppression button. approach charts, en-route charts) or
With two PFDs operational, each display is weather graphical information on the Multi
controlled separately by its own Display Function Display. It includes the following:
Control Panel (DCP) and updated on
 Rockwell-Collins FSU-5010 File
alternate antenna sweeps.
Server Unit (FSU)
7.7 FLIGHT CONTROL SYSTEM  Rockwell-Collins FSA-5000 File
Server Application software
The fail safe Flight Control System (FCS) is
made up of a dual Flight Guidance System  Rockwell-Collins ECU-3000 External
and of a 3 axis Autopilot, including Yaw Compensation Unit
Damper and Pitch Trim control.
7.11 ELECTRONIC CHARTS FOR IFIS
The pilot selects the Flight Guidance
Computer (FGC) in control with the Flight Jeppesen charts (airport charts, SID and
Guidance Panel’s (FGP) coupling (CPL) STAR charts, Instrument procedure charts,
switch. en-route charts) Rockwell-Collins ECH-5000
are installed on the FSU for visualization in
Each PFD displays the Flight Director (FD)
the Multi Function Display.
commands from the Flight Guidance
Computer selected with the CPL switch, The Chart image files are stored in the FSU
except for Go Around (GA) and Approach and are selected for display via the Chart
(APPR) modes. The GA and APPR modes are Main Menu. The Cursor Control Panel
Independent Modes, and only the on-side provides an interface with the Chart Main
Flight Guidance Computer guidance is used Menu and is also used to manipulate the
by the associated PFD for Independent displayed chart. The chart feature also
Modes. provides a depiction of the aircraft's current

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Revision 7.1 April 2016 Avanti EVO Specification and Description
position on all charts that have been Proximity Warning System (GPWS)
geographically referenced. functionality to prevent Controlled Flight
It requires subscription to the Jeppesen Into Terrain, enhanced by a stored
Charts Update Service. worldwide database including terrain,
airport and obstacle data. TAWS provides
7.12 ENHANCED MAP OVERLAY FOR IFIS the pilot with predictive warnings based on
comparison between stored obstacle data
It provides the capability to display
and a prediction of the aircraft’s flight path
geopolitical data, airways and airspace
derived from FMS and GPS data and current
maps on the Multi Function Display. It
flight parameters. TAWS provides aural and
includes the installation of the following
visual warnings to alert the pilot in case a
additional software:
hazardous condition is detected and
 Rockwell-Collins OVL-5000 Enhanced includes the possibility to represent terrain
Map Overlays elevation features on the AFDs graphically.
Map displays are controlled via the Cursor
Control Panel or via line select keys to
access the Map Menu. In order to prevent 7.15 IRIDIUM SATELLITE PHONE
display clutter, each of the enhanced map
An AirCell ST3100 Iridium Satcom system
overlays is automatically removed as map
(optional kit), installed as standard
range is increased. The airways and airspace
equipment provides worldwide access to
depictions are removed when range is
the Iridium global satellite network. It
increased over 100nm. The geopolitical map
includes:
data is removed when map range is
 An ST3100 transceiver unit located
increased over 300nm. It requires
in the passenger cabin and a patch
subscription to the Rockwell-Collins Map
antenna located on the top fuselage
Service.
 A cordless base station located on
7.13 TCAS I the top of the forward right hand
side partition cabinet in the
An L-3 Communications Skywatch HP model passenger cabin, in position also
SKY899 TCAS I airborne Traffic Alert and accessible from the cockpit.
Collision Avoidance System (optional kit) is  A cordless handset providing voice
provided as standard equipment. The TCAS communications, control functions
I system interrogates ATC transponders in and programming
nearby aircraft and uses computer  Two RS232 data ports in the
processing to identify and display potential passenger cabin for data (fax/email)
and predicted collision threats along with transfer through the Iridium Satellite
an aural warning when requested. TCAS I phone network.
traffic information can be selected for
pictorial display on the PFD and/or the MFD 7.16 ADDITIONAL FEATURES
to indicate the presence of other aircraft
The standard ProLine 21 avionics system of
within a selected range around the aircraft.
the P.180 provides the capability to operate
7.14 TAWS in RVSM-airspace and to perform Category
II approaches and steep approaches.
An L-3 Communications Landmark Class-B
The flight envelope extension to Mach 0.7
model TAWS 8000 Terrain Awareness and
Mmo is also a standard feature.
Warning System (optional kit) is provided as
standard equipment.
The system provides traditional Ground 7.17 PROVISIONS

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Revision 7.1 April 2016 Avanti EVO Specification and Description
 7.17.1 PROVISION FOR XM/WSI SATELLITE 7.17.2 AUXILIARY CABIN POWER KIT
SYSTEM RECEPTION This kit provides two sockets (40Amps max
Structural and electrical provisions for @28VDC) under cabin compartment floor,
XM/WSI Satellite Weather Graphical to provide electrical power either to
Information functionality. The provision sanitary or other equipment (if approved).
includes XM antenna, Wiring harness, The power is provided both on ground or in
Structural provision for XM weather flight (at least one generator is properly
receiver. operating and set on line).

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Revision 7.1 April 2016 Avanti EVO Specification and Description
8 STANDARD AIRCRAFT CONFIGURATION

8.1 AVIONICS, INSTRUMENTS AND CONTROL PANEL

 Radio Management System – Rockwell-Collins RTU-4200, CDU-3000
 Dual VHF COM - Rockwell-Collins VHF-4000 Transceiver with Antenna with 8.33 kHz spacing
 VHF NAV1+ADF - Rockwell-Collins NAV-4000 VOR/ILS/MKR/ADF Receiver with Antennae
 VHF NAV 2 - Rockwell-Collins NAV-4500 VOR/ILS/MKR Receiver with Antennae
 Single DME - Rockwell-Collins DME-4000 (3 channel) with Antenna
 Dual Mode S Flight ID Diversity Transponder - Rockwell-Collins TDR-94D
 Radio Altimeter - Rockwell-Collins ALT-4000 (Operation to 2500 ft) with Antennae
 Turbulence Detection Weather Radar - Rockwell-Collins RTA-852 Color Radar with 12" Antenna
 Dual Audio Panel - Baker B1045
 Dual Cockpit Speaker
 Dual hand-held Microphone
 Dual Boom/Microphone/Headset – Telex 850 ANR
 EFIS with EIS – Two Rockwell-Collins displays AFD-3010 with two DCP-3030,
One Rockwell-Collins display AFD-3010E with CCP-3000
 Flight Guidance System - Rockwell-Collins Dual FGC-3003 (A/P,YD and dual Flight Director
included), three SVO-3000 Servos, single FGP-3000 Flight Guidance Panel
 Single FMS - Rockwell-Collins FMC-3000 (NAV to NAV and VNAV), CDU-3000 (used also for radio
tuning), DBU-5000
 GPS Sensor Unit - Rockwell-Collins GPS-4000S
 Dual ADS - Rockwell-Collins ADC-3000
 Dual AHRS - Rockwell-Collins AHC-3000 and FDU-3000
 Maintenance Diagnostic System - Rockwell-Collins MDC-3110
 Four Data Concentrator Unit - Rockwell-Collins DCU-3001
 Stand-by Cluster Instrument – L-3 Communications GH-3100
 Emergency Locator Transmitter – Artex C406 (3 frequency)
 Dual Digital Clock (Chronometer included)
 Dual Master Annunciator
 Dual Turn&Slip Indicator (shown on the displays)
 Reversionary/Miscellaneous Panel
 Hobbs meter
 Integrated Flight Information System (IFIS) including:
- Rockwell-Collins FSU-5010 File Server Unit (FSU)
- Rockwell-Collins FSA-5000 File Server Application software
- Rockwell-Collins ECU-3000 External Compensation Unit
 Rockwell-Collins ECH-5000 Electronic Charts installation in the FSU
 Rockwell-Collins OVL-5000 Enhanced Map Overlays installation
 TCAS I – L-3 Communications SkyWatch HP model SKY899
 TAWS Class B with Worldwide Database – L-3 Communications Landmark model TAWS8000
 AirCell ST3100 Iridium Satcom

NOTE: RVSM, Mach 0.7, Category II Landings and Steep Approach capabilities are included as
standard.

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8.2 ELECTRICAL SYSTEMS AND LIGHTS
 Two 400A, 28V Starter Generators
 Two Solid State Generator Control Unit
 Nickel-Cadmium Battery (38 Ah)
 Emergency Power Unit (5Ah)
 External Power Receptacle with Overvoltage Protection
 Main Junction Box with self test (rear non pressurized volume)
 Two Circuit Breakers Panels (Lh & Rh side cockpit) providing nine busses DC Distribution System
with Auto Load Sharing
 Dual Solid State Master Warning and Caution Panels with Self Test
 Solid State Warning and Caution Annunciator Panel with Self Test and Dimmer System
 Pitot Heating Monitor
 Static Wicks
 Heated Stall Warning System with Pre-flight Self Test System
 One LED Taxi and two LED Landing Lights
 Two LED Left & Right Position Lights (red & green on each winglet leading edge)
 One LED Rear Position Light (white, rear facing on vertical fin top fairing)
 LED Anti-Collision Strobe System (top and bottom)
 LED Recognition Light (On top of Vertical Fin)
 LED Wing Ice Inspection Light
 Cockpit Dome Lights
 Flood Lights
 Instrument Lighting System
 Dual Map Lights in Cockpit Area
 Cabin Floor LED lighting
 LED lighting in the passenger cabin and in the toilet area
 Two 28 VDC Auxiliary Cabin Power Outlets (underneath the cabin floor).
 110 VAC power outlets in cockpit (Qty. 2) and passenger cabin (Qty. 4)
 Two RS232 data ports in the passenger cabin for data (fax/email) transfer capabilities through
the Iridium Satellite phone network only.

8.3 POWERPLANT AND RELATED SYSTEMS

 Two PRATT & WHITNEY model PT6A-66B Free Turbine Engines flat rated at 850 Shaft Horse
Power and Engine Accessories, equipped with Torque Limiter
 Two HARTZELL HC-E5N 86,5" diameter, five metal blades, scimitar type, fully feathering and
reversible, hydraulically controlled, constant speed propellers
 Magnetic Chip Detector
 Oil Quantity Dipstick Indicator
 Primary Propeller Governor
 Overspeed Propeller Governor
 N1 and N2 Magnetic Pick-up Speed Sensors
 Two Power Levers for Forward and Reverse Power
 Two Condition Levers for Propeller speed, High/Low Idle, Feather and Engine Cut-off
 Auto Ignition System
 Submerged electric main and standby Fuel Boost Pumps
 Fuel Control Unit
 Fuel Heater System
 Fuel Crossfeed System
 Low Fuel Quantity Warning System

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 Two Fuel Quantity Indicators (on the Multi Function Display)
 Two Fuel Flow Indicators (on the Multi Function Display)
 Fuel Drain System
 Fuel Tank Interconnect
 Pressure and Gravity Refueling
 Low Oil Quantity Warning System
 Propellers Auto-feather
 Complete Engine Anti-Icing System with Ice Protected Engine Inlet
 Engine Parameter Indication on Multi Function Display
 Engine Fire Detection System
 Engine Fire Extinguishing System

8.4 SYSTEMS
 Oxygen System for Pilots (Two Diluter / Demand Masks) and Passengers (Ten Masks)
 Digital Cabin Pressure Control System with manual back-up
 Mixed Air Environmental Control System with Freon cooling system
 Forward Wing Anti-Ice System (Electrical)
 Main Wing Anti-Ice System (bleed air)
 Windshield Electrical Anti-Ice and Defogging
 Hydraulic Power Pack
 Dual heated Pitot and Static Ports with heating monitor
 Alternate Heated Static Source
 Propeller Synchrophaser
 Steerable Dual Wheel Nose Landing Gear – MAGNAGHI
‐ Electro-Hydraulic Class B Steering, full time use - EATON
 Single Wheel Main Landing Gear - MAGNAGHI
 Main Wheel and Tires (6.50 - 10) - GOODRICH
 Nose Wheels and Tires (5.00 - 5) - GOODRICH
 Carbon Brakes on each Main Wheel
 Landing Gear Position Lights, Down and Locked
 Landing Gear Warning Horn and In-Transit Light
 Dual Conventional 3-Axis Aircraft Control System
 Dual Adjustable Rudder Pedals and Toe-Operated Brakes
 Parking Brake
 Emergency Landing Gear Extension System (Hand Pump)
 Electric Aileron Trim Tab (Roll)
 Electric Rudder Trim Tab (Yaw)
 Electric Stabiliser Trim Actuator (Pitch)
 Electric Flap System with Electronic Control Unit and Four Motors

8.5 EMERGENCY EQUIPMENT

 Portable fire extinguisher
 Crew and passenger oxygen
 Emergency flashlight
 First Aid kit provision

8.6 MISCELLANEOUS AND GROUND SUPPORT EQUIPMENT

 Cabin baggage straps

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  Pitot covers
 TAT sensor cap
 Anti-ice detector cap
 Engine intake blanks
 Oil cooler inlet blanks
 Starter generator and inertial separator blanks
 Air conditioning scoop cap
 Engine stack caps
 AOA transducer cap
 Static wick covers
 Telescoping tow bar
 Jack pads
 Lifting brackets
 Mooring pads with rings
 Wheel chocks
 Gust locks
 Propeller restrainers
 Fuel drain tool
 Tool case
 Windshield sun shades
 Access panel for air conditioning service
 Cockpit pedestal guard
 Cockpit glare shield check list holder
 Cockpit seat shoulder belt guide plate assembly
 Cockpit lower sidewall panels
 Cockpit control column leather boots
 Cockpit glare shield
 Cockpit seats
 Baggage compartment finishing
 Baggage compartment protective flap

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 Standard Instrument Panel

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 ECS CONTROL
PANEL

Standard Instrument Panel

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9 OPTIONAL EQUIPMENT

9.1 INCREASED RANGE OPTION

This option will provide the installation of an additional fuel tank providing a usable fuel
capacity of about 58 U.S. gallons (390lbs, 220litres); the tank is divided in two separated parts
(29 US Gallons, 195lbs, 110litres each) interconnected respectively to baseline left and right
side fuel systems; each part is equipped with a dedicated probe interfaced with aircraft fuel
quantity measurement system.
As before mentioned, the total usable fuel system capacity with the additional fuel tank will
becomes 476 U.S. gallons (3,218 lbs, 1,802litres).
Refueling and fuel unload operations remain unchanged.

9.2 AVIONICS OPTIONS

9.2.1 “ENHANCED SAFETY OF FLIGHT PACKAGE”: ACAS II + EGPWS (TAWS CLASS A)

Rockwell Collins TCAS 4000 and Honeywell EGPWS Mark VIII replacing standard TCAS I L-3 SKY
899 and TAWS B BF Goodrich Landmark 8000.

9.2.2 ACAS II 7.1

The Rockwell Collins TCAS-4000 (compliant with ICAO ACAS II Change 7 requirements) improves
safety with total situational awareness of impending traffic conflicts, including the display of
resolutionary information for immediate threats.
The system tracks all Mode C and Mode S transponders within 35nm and provides range,
relative bearing and altitude information for the up to 30 aircraft that representing the highest

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collision threat.
Traffic Alerts (TAs) and Resolution Advisories (RAs) are given aurally through the aircraft audio
system and visually on the PFDs.
When other TCAS II-equipped aircraft are encountered, complementary RA maneuvers are
coordinated by each system.
Resolution Advisory commands appear on the two vertical speed indicators or the vertical
speed display fields of integrated electronic flight display systems.
NOTE: If requested ACAS II system can be installed also in conjunction with TAWS Class B.

9.2.3 EGPWS
The MK VIII version of Honeywell's EGPWS is a Class A TAWS that helps to prevent accidents
caused by Controlled Flight into Terrain (CFIT).
The system achieves this by using a number of aircraft inputs, applying proprietary alerting
algorithms, and alerting the crew with aural messages, visual indications, and a display of
terrain in the event the boundaries of the alerting envelope have been exceeded.
System configuration is controlled via a programmable module. The MK VIII offers a worldwide
terrain database. Databases are loaded via a convenient ATA format PCMCIA card using
Honeywell's SmartCable interface.
Note: EGPWS installation is incompatible with SBAS LPV (§ 9.2.13) option.

9.2.4 HF WIRING PROVISIONS

It provides wiring and mounting provisions for later installation of the HF system.

9.2.5 HF RADIO SYSTEM

The Rockwell Collins HF 9000 Radio Communication System can be added to the two VHF
Communication Systems to perform long-distance voice communications. High Frequency radio
communications allow reliable long range transmission and reception over distances of
thousands of miles. This makes HF radio particularly useful when flying over vast surfaces
where VHF communications, limited to line of sight transmission, are out of reach.

9.2.6 INMARSAT SATELLITE PHONE

A Thrane & Thrane Aviator 200 Inmarsat Satcom system can be installed in alternative to above
Aircell ST3100 Iridium Satcom one.
The Aviator 200 using Inmarsat’s SwiftBroadband (SB) services can provide an IP connection to
ground with a maximum bandwidth of 200 kbit/s to allow, virtually anywhere in the world, a
wide range of in-flight capability including E-mail, Internet Browsing, Smart Phone Connectivity
and Voice Services; it offers also a Built-in wireless connection.
The Aviator 200 Swiftbroadband system includes:
 A SwiftBroadband Unit (SBU) located in the passenger cabin with a configuration
module holding the SIM card
 A low gain antenna located on the top fuselage with a HLD unit (High Power Amplifier,
Low Noise Amplifier and Diplexer in one unit).
 A wired handset/cradle located on the top of the forward right hand side partition
cabinet in the passenger cabin, in position also accessible from the cockpit.

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  A wireless handset/cradle located on the top of the aft left hand side cabinet in the
passenger cabin
Note: Aviator 200 installation is not feasible with current ADASd/DTU kit installation (same location)

9.2.7 PROVISION FOR IPAD MINI AS EFB

This optional provision shall install the means needed for the operation of two Apple iPad mini
(not part of the kit) as optional Class 2 / Type B Electronic Flight Bags (EFB).
The kit will add, on both pilot and co-pilot side, a device mounting mean in place of the control
wheel map holder and a dedicated power supply socket.
9.2.8 FULL PROVISION FOR CVR INSTALLATION
Structural and electrical provisions (wiring and connections) for the L-3 Communications
FA2100 Cockpit Voice Recorder.

9.2.9 COCKPIT VOICE RECORDER

The L-3 Communications FA2100 Cockpit Voice Recorder allows recording of all audio signals:
 signals transmitted or received by the pilot and the co-pilot,
 cabin page announcements,
 cockpit conversations, through the cockpit area microphone
All audio inputs are fed into 120-minutes recording channels. The FA2100 is provided with an
Underwater Locator Beacon (ULB) and a g-switch enables to stop the record in case of impact.
The kit includes:
 A CVR recording unit located in the baggage compartment
 A CVR control unit located in the pedestal
 A g-switch located in the vanity area close to the aircraft C.G.
 A cockpit microphone located on the pedestal top on the RH side
The CVR is mandatory in the US and Canada for aircraft equipped with 6 or more passenger
seats operating under FAR 135.

9.2.10 COCKPIT VOICE RECORDER PORTABLE INTERFACE UNIT

The L-3 Communications Cockpit Voice Recorder Portable Interface Unit allows the download of
recorded data as well as maintenance and operational checks on the FA2100 Cockpit Voice
Recorder unit. During normal operations, it is not usually carried on board of the aircraft.
The Portable Interface unit is fully interchangeable and can be used in connection with any L-3
Communications FA2100 Cockpit Voice Recorder unit.

9.2.11 COCKPIT VOICE AND DATA RECORDER COMBO UNIT (CVDR)

In lieu of above Cockpit Voice Recorder a L-3 FA2100 Solid-State Cockpit Voice and Data
Recorder (CVDR) can be installed, integrating CVR and FDR in a Combo Unit.
FA2100 CVDR provides four channel, 2 hour or 30 minute high quality audio recording and
64/128/256/512 words per second flight data for a minimum of 25 hours recording of Air Data,
Acceleration, Attitude, AoA, flaps position, Engines Power & Prop Reverse Condition, Radio
Transmission Keying, A/P Modes and Engagement Status, Selected Altitude, Speed, Mach,
Heading, Display Format.

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 9.2.12 LIGHTNING DETECTION SYSTEM (STORMSCOPE)
It provides a L-3 Communications WX-1000E Stormscope lightning detection system able to
detect various levels of lightning activity and to process that information into ARINC 429 format
to be displayed on the AFDs.
Lightning detection is generally limited to approximately 200 NM from the aircraft. Lightning
data from the lightning detection system may be superimposed with weather radar data on
those PFD and MFD formats which are weather radar compatible.

9.2.13 SATELLITE BASED AUGMENTATION SYSTEM - SBAS LPV

This option provides the Localizer Performance with Vertical Guidance (LPV) approach
capability to the P.180 Avanti EVO Flight Management System.
LPV (Localizer Performance with Vertical guidance) is a type of approach procedure where both
the lateral and the vertical profile guidance is computed upon SBAS augmented GPS signals.
LPV enables descent to 200-250 feet above the runway, and can only be flown with a SBAS
receiver under WAAS / EGNOS / MSAS signal coverage; the embodiment of this modification
enables full IFR precision approach availability even at small airports.
The Temperature Compensation enhances the performances of APV-Baro (Approach Procedure
with Barometric Vertical guidance) approach procedures that can be safely flown even below
the prescribed cold temperature limit.
Note: SBAS LPV option installation is incompatible with EGPWS (§9.2.3) option.

9.2.14 VIDEO CAPABILITY FOR THE MFD

The Rockwell Collins VID-3000 option allow to receive on the MFD video signals from Cameras
and or other video systems.

9.2.15 ENGINE DATA - ACQUISITION AND MONITORING SYSTEM ADASD

The ADAS (Aircraft Data Acquisition System - digital) manufactured by P&WC/Altair provides
optional maintenance information, enabling the operator to control, qualify and manage
engine maintenance operations. Recorded engine data can be downloaded and then uploaded
to Altair TurbineTracker™ web service, an Internet-based data management system software
for remote engine data management, to track the usage and the engine performance trend in
real-time.
The system performs the following primary functions:
 Exceedance Events Recording
 Engine Trend Monitoring
 Built-in Test Capability (Trend/Fault Illuminated Pushbutton)
The ADAS system main components are:
 System Processor Unit (provided with a dedicated mount),
 Trend Switch/Fault illuminated pushbutton (on the instrument panel),
 Serial connection for data upload/download with Monitor Link Program.
Note: ADASd installation is not feasible with Aviator 200 installation (same location)

9.2.16 ENGINE DATA – TRANSFER UNIT DTU

In conjunction with ADAS (Aircraft Data Acquisition System), the Data Transmission Unit (DTU)
provides the communication capabilities through which the engine performance data can
stream to the maintenance organization without pilot/operator intervention. This equipment

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requires the installation of the ADAS, as the source of data.
On landing, the DTU automatically collects data from the ADAS and establishes a cellular
connection (utilizing GSM/GPRS) with the Altair TurbineTracker™ web service, an Internet
based data management service for review and remote engine trouble-shooting.
Note: DTU installation is not feasible with Aviator 200 installation (same location)

9.2.17 ANTISKID OPTION

Avanti EVO may install an Antiskid system on its Brake system with the main purpose to
increase ground handling qualities and reduce pilot workload.
This system will provide skid control envelope from 10 to 154 kts, locked wheel protection,
touch-down protection and spin-up override.
The Antiskid system control unit, depending on the wheel speeds provided by dedicated
transducers installed in the MLG axles, will drive hydraulic pressure (through a dedicated Dual
Skid Valve -DSV) to the brakes avoiding skidding conditions.
The system is designed to minimize installation & weight impacts.

9.3 MISCELLANEOUS EQUIPMENT

9.3.1 FIRST AID OXYGEN SYSTEM

The First Aid Oxygen System consists of an additional outlet valve connected to the pilot main
oxygen line. It is placed in a convenient location in the airplane cabin, depending on the type of
airplane interior configuration.
A medical oxygen mask with a metered two-flow selector provides oxygen flow at 2 lpm or at 4
lpm. It is available at any time during flight, by connecting the appropriate oxygen mask to the
outlet valve.

9.3.2 PORTABLE OXYGEN CYLINDER

The portable oxygen cylinder provides a supplementary oxygen source for crew and passengers
use, if requested. The oxygen cylinder is installed inside the wardrobe, located in the vanity
section. It is attached to the right side of the forward wall of the wardrobe.
It supplies a constant flow of oxygen to the masks up to 16500 ft cabin altitude. The oxygen unit
is provided with 2 masks, each equipped with a flow indicator.
The table below gives the average duration in hours of a cylinder fully charged to 1800 psig,
with respect to the cabin altitude.

CABIN ALTITUDE (Feet) 1 passenger 2 passengers

0 2.75 1.38
12500 3.03 1.52
16500 3.13 1.57
Oxygen Cylinder Duration (hours).

Use of supplementary oxygen is allowed only when the cabin is pressurized or when the cabin
altitude is below 16500 ft.

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 9.3.3 EU OPS 1 /FAR 135 KIT
Loose supplies for Public Transport Operators in compliance with EU OPS 1 requirement.
The kit includes:
 Protective breathing equipment (PBE) (qty 1), including an emergency escape hood for
automatic oxygen flow and smoke protection for crew members
 Smoke goggles (qty 2)
 Live vests (qty. 10)
 One additional electric torch
 Templates for typical Safety Briefing Card and Equipment Location Card.

9.3.4 GRAVEL KIT

The kit is installed on the nose landing gear to protect the aircraft lower fuselage and wings
from small debris that may be thrown up by the nose landing gear during operations on
unpaved runways.
The kit is designed to allow operation on grass or compacted gravel runways with CBR > 15; it
is not designed to allow operation on rough or unprepared strips with loose gravel.
Performance degradation for take-off and landing are defined in the relevant sections of the
Flight Manual. Operation from unpaved runways implies application of a factor 4 for the
purpose of calculating the operational cycles of the landing gear.

9.3.5 LEAD ACID BATTERY

Installation of a 38 Ampere hours Concorde lead Acid Battery in lieu of the standard nickel-
cadmium battery.

9.3.6 NICKEL-CADMIUM BATTERY

Installation of a 43 Ampere hours SAFT Nickel Cadmium battery in lieu of the standard 38Ah
Marathon nickel-cadmium battery with updated maintenance intervals.

9.3.7 PROVISION FOR PORTABLE ELT STOWAGE

This interior provision shall allow the stowage, in the cockpit, of a portable ELT (PARM-406A
type, customer supplied) together with its containing box.

9.3.8 LIFE RAFT

One Winslow Life Raft, stored in the lower part of the lavatory cabinet featuring a standard
capacity of 7 persons and an overload capacity of 10 people.
The life raft features twin buoyancy tubes, light weight canopy, triple frequency ELT and
survival equipment in compliance with EU.OPS or FAR Part 91&121

9.3.9 14VDC AUXILIARY POWER

Installation of two sockets powered with 14VDC installed close to the left & right tables in the
typical club configuration.

9.3.10 230VAC POWER OUTLETS

In lieu of baseline 110VAC power supply capability, a KGS 230 VAC@50Hz power
source can be provided, with the same purpose of supplying the power outlets in cockpit (Qty. 2)

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and passenger cabin (Qty. 4), intended to be used by the cabin passengers and by the flight crew
for supplying portable electronic devices (PEDs) like portable computers, tablets, smartphone,
etc.
Polished Leading Edge
In lieu of standard painted wing leading edge, an optional polished leading edge can be selected.
The polished leading edge is unpainted and uncoated by current traditional protective processes
with the ALCLAD surface directly in view to the external environment.

9.3.11 MAXIMUM TAKE-OFF WEIGHT @ 11550LBS

If requested, the aircraft can be delivered with a Maximum Take-Off Weight (MTOW) of
11550lbs.
Dedicated labels and AFM supplement will be provided.

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10 INTERIORS

10.1 GENERAL
The cabin is separated from the cockpit by dividers. The fuselage is shaped to minimize drag,
while providing the maximum possible interior volume. Thus the Avanti EVO fuselage has a
tapering cabin cross section, with maximum height and width achieved in the middle of the
cabin.
Cabin length, including lavatory, is 14.9 feet (4.55 m), width is 73 inches (1.854 m) and height is
69 inches (1.753 m) from the 6.5 inches (165 mm) dropped aisle to the cabin ceiling.
The cabin may be configured with interior arrangements for six to nine passengers. The aircraft
has an externally accessible baggage compartment of 35 cubic feet (1 m3).
The interior has been designed with a composite honeycomb constructed shell for maximum
strength, durability and acoustically quiet environment. The interior has also been designed to
allow individual owners to select the finished surfaces according to their own desires.
Passenger seats track fore and aft, track laterally outward from the sidewall, swivel 180
degrees, and recline. All passenger seats are equipped with a shoulder harness for take-off and
landing.
Constant flow oxygen masks automatically deploy for each passenger when a sudden change in
cabin pressure is detected by the cabin pressurization system.
10.2 CABIN
The P.180 Avanti EVO interiors can be configured according to four Corporate floor plan layouts
(7 or 6 seats VIP style), a “shuttle” layout (7 seats airline style) or even “Special Missions” layout
to be adapted for MEDEVAC, Surveillance or Flight Inspection operations.

The Corporate interior configurations

include the following:

 Four seats in a club arrangement in the rear cabin.
 Two side-facing divans or one side-facing divan and a forward-facing seat or two
forward-facing seats in the forward cabin.
 A toilet seat approved for take-off and landing.
 One or more refreshment cabinets, depending on the seat configuration, containing
storage areas for food and beverages, compartments for ice, soda cans and small
bottles. On certain configurations, a dedicated compartment can hold hot beverages
carafes or electrically heated dispensers (optional); storage space for glasses, cups,
condiments and miscellaneous items is also available.
 Two folding tables located between the club seats.
 An armrest console running the length of the main cabin including dual figure drink
holders and closed storage compartments for miscellaneous objects at each club seat
location.
 110 VAC power outlets (Qty. 4) located inside the storage compartment.

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Passenger windows have opaque privacy shades and a reflective outer surface to reduce heat
build-up on the ground.
The cabin lighting system (Corporate versions) include:
 Downwash LED lighting
 Upwash LED lighting
 Floor lighting
 Accent lighting
 Individual Reading Lights

The LED lights can be switched on and off and dimmed by conveniently located push buttons.
Ordnance signs (“Fasten Seat Belts” and “No Smoking” signs) are located on the partitions and
inside the toilet compartment.
The rear part of the cabin houses a full privacy lavatory module, which can be completely
closed by a sliding pocket door.
It is equipped with an electrically flushing toilet on the left hand side, featuring a Teflon bowl
for ease of maintenance. It has a fully secured, removable tank for servicing.
A cosmetic mirror covers the top portion of the aft partition of the lavatory module.
The right hand toilet cabinet is provided with several different compartments which can house
towels, facial tissue, soap and toilet tissue dispensers. A stainless steel waste container is
provided for solid or liquid waste.
When the aircraft is equipped with Increased Range option, the upper section of the right hand
cabinet is no more available. The lower section could provide a limited storage capacity if not
already used for life raft housing.
A self-containing water system including a fresh water tank, a spring actuated tap, a drainable
sink and a waste water tank is available as an optional.
A rear coat closet inside the lavatory module has the capacity for all passenger coats as well as
brief case storage. A removable coat rod is located at the top; a removable shelf is also
provided at mid-height of the cabinet to allow for a higher flexibility of use.
A removable drawer is provided at the bottom of the closet for supply storage.

10.3 CABIN NOISE

The internal cabin noise is significantly lower than in other turboprop aircraft and compares
also favorably with noise of typical jet aircraft.
As a side benefit, the new propeller arrangement provides a slight improvement to the already
best in class internal noise levels.
As reference, table below details the internal noise measured on the ground and in flight using
a Precision Sound Level Meter in various ground and flight conditions.
Taxiing 70 dB(A)
Take-off 81 dB(A)
Climb 76 dB(A)
Cruise 74 dB(A); 65 SIL (dB) (350 KTAS, 23000 ft, 1800 rpm)

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10.4 MISCELLANEOUS COCKPIT FURNISHINGS
 Two crew storage cabinets;
 Dual adjustable sun visors
 Assist handles;
 Dual cup holders;
 Two cockpit speakers;
 Cockpit dome lights (white/red);
 Instrument panel flood lights;
 Internally lighted instruments;
 Dual map lights;
 Yoke mounted chart holders;
 Portable fire extinguisher.
 Cockpit pedestal guide
 Cockpit glare shield check list holder
 Cockpit control column leather boots

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10.5 INTERIOR DESCRIPTION
The available Avanti EVO interior configurations are detailed in the following including:
 Common interior trim shared by all available layout configurations,
 Five different floor plans available
 Applications other than corporate/VIP
 Interior accessories and furnishing to applicable Corporate layouts,
 Styling, colors and materials as applicable.

Interior configurations and individual element design can be changed by Piaggio Aero Industries
without notice.

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10.6 STANDARD PASSENGER INTERIOR TRIM
All passenger interior configurations share the following elements:

Interior liners and paneling

The Avanti EVO interior liners are manufactured using light weight composite panels that line the
interior ceiling and windows, providing lighting and systems to the passengers. These panels may
be covered in a variety of standard decorative fabrics, leathers and veneers. The interior paneling
consist of the following components:
 Headliner
 Passenger Service Panels (PSU), featuring continuous dimmable LED lights for up wash and
down wash lighting, drop-out oxygen masks at each seat location, air outlets and reading
lights at each seat location, speakers)
 Window Panels, featuring manually operated pleated window shades
 Windows shades encapsulated between two transparent sheets
 Side ledge and Dado panels, featuring club tables, dual drink holders, light switches and
storage compartments with standard universal electrical outlets and optional data port

Forward partitions and cabinetry

The flight deck is separated from the cabin seating area by two partitions and a pair of cabinets
which act as a divider and provide storage for passengers and crew.
The Left and Right Hand partitions consist of the following features:
Left Hand Forward Partition
 Entry Assist Hand Rail
 Entry Switch Panel (Entry, Cabin and Crew Lights)
 Entry Light
 Advisory Lighted Sign (No Smoking / Fasten Seatbelts)
 Drawer for fire extinguisher
 Chart stowage provisions (flight deck side)
 (FMS) Flight Management System Data Loader

Right Hand Forward Partition

 Upper Storage Drawer for airplane flight manuals and Jeppesen manuals
 Lower Storage Drawer for miscellaneous storage or smoke hood storage compartment
 Aircell Satellite Phone
 Dual drink holder and Switch Panel (Read Light)

An annex cabinet (to be installed just aft) is available as an option for the Corporate 2 to provide
further refreshment stowage.

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 Aft Partition and Sliding Door
The aft partition and sliding door separates the cabin seating area from the lavatory. The
partitions feature a single sliding door that pockets into the right hand partition and slides across
the aisle to provide privacy in the lavatory.
The aft partitions incorporate the following features:
 Advisory Lighted Sign on the right hand side (No Smoking / Fasten Seatbelts)
 Sliding door with privacy latch with pop up header and drop down footer
 One air vent

Aft Lavatory
The lavatory is located in the aft most portion of the cabin and occupies both sides of the cabin.
The aft lavatory includes the following features:

Right Hand Closet and Vanity

 Advisory Lighted Sign (No Smoking / Fasten Seatbelts)
 General Storage Compartment
 Illuminated Hanging storage (with curtain or bi-fold closing door), which can be fitted with
Increased Range Option

a removable shelf and a bottom drawer

Not available with

 Toilet Paper dispenser

 Trash Compartment
 Switch Panel
 Hand Towel Stowage
 Counter Top Area
 Provisions for optional water tap and drainable sink

A water system including a sink with tap, fresh water container and waste water container is
available as an option.

Aft Bulkhead Facial

 Mirror (installed on removable panel for access to avionics and service related
components)
 Stair Stepped back splash and lower panel covered in standard materials

Left Hand Toilet Seat

 Self Contained Electric Flushing Toilet
 Toilet Seat (certified to be occupied during Take-Off and Landing) including lap belt and
shoulder harness with inertia reel
 Seat bottom and back cushions upholstered in leather or fabric
 Indirect LED “up wash and down wash” lighting behind seat back

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VIP Seats
Each individual VIP seat (Iacobucci) includes:
 Back recline (full recline where available)
 180° swivelling
 Fore/aft and lateral translation
 Lowerable inboard armrest (optional)
 Provision for under-seat life vest stowage
 Extendable headrest
 Seat restraint system including lap belt, shoulder harness with
inertia reel
 Fire resistant leather upholstering and multi-layer foam
cushioning Example of Iacobucci seat
PAC or De Crane seats can also be selected.

Two-place Divan
The side facing two-place divan available in the Corporate 1 and
Corporate 3 floor plan includes:
 Under-seat life vest stowage provision
 Seat restraint system including lap belt, shoulder harness with
inertia reel
 Fire resistant leather upholstering and multi-layer foam
cushioning
A dual floor drawers kit is available as an option.

LH & RH One-Place Divan

The side facing one-place divan is available in the Corporate 1 (1) and
Corporate 4 (2) configurations and includes:
 Underseat lifevest stowage provision
 Restraint system including lap belt and dual shoulder harness
with inertia reel
 Fire resistant leather upholstering and multi-layer foam
cushioning
A single floor drawer kit is available as an option.

Folding tables
The Club section includes one table on each side, foldable and stowable
within sideledge.

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Lightweight Seats (“Shuttle” only)

Each seat includes:

 10° back recline
 Ashtray in armrest
 Under-seat life vest stowage pocket
 Folding In-arm table (front row seats)
 Rear tables
 Seat restraint system including lap belt, shoulder harness
with inertial reel .
 Seat back pocket
 Fire-resistant fabric upholstering

Mid Cabin Refreshment Cabinet (available only on Corporate 1 and 4)

The mid cabin refreshment cabinet is available only on the Corporate 1 and 4 floorplan and is the
largest refreshment cabinet available on the Avanti EVO. This low height cabinet’s features may be
configured in a several different ways. The features are as following:
 Storage for (2) hot beverage carafes
 Miniature liquor bottle stowage
 Ice Chest or Ice Drawer
 Glass Stowage
 Work Surface and Cutting board
 Napkin and Condiment stowage
 General Stowage
 Trash Compartment
 Internal Lighting
A heated liquid container is available as an option. Smaller cabinets are available for the other
floor plan configurations:

Midship Pyramid Cabinets (available only on Corporate 2 & 3)

The midship pyramid cabinets are designed to utilize the triangular space created between the
two single seat backs. This cabinet can be selected on floorplan Corporate 2 and 3 and will provide
additional stowage and refreshment items either by two or three drawers. The cabinet can be
placed on both sides in Corporate 2 and only on left hand side on Corporate 3. The cabinet can
contain the following features:
 Glass Stowage
 Ice Chest
 Carafe Stowage
 General Stowage

LH & RH (Left Hand & Right Hand) Aft Pyramid Cabinets(Evaporator Covers)
Pyramid Cabinets are located adjacent to aft partitions on the cabin side. They provide storage in
the space left between the forward facing seat and the partition and closure for the LH & RH Air
Conditioning Evaporator Units.
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 10.6.1 STANDARD CABIN LAYOUTS / FLOOR PLANS
The Avanti EVO is available in several different floor plans, all the floor plans feature an aft
lavatory with closet and a forward set of cabinets dividing the flight deck from the cabin seating
area.
The floor plans’ in the Corporate feature (4) four single seats arranged in an aft club grouping just
forward of the lavatory divider.
The cabin area forward of the club grouping can be arranged with a combination of single seats or
side facing divans and cabinets to create different floor plans with an emphasis on number of
passengers and galley amenities.

The Floor plans are as follows:

 Corporate Option 1, (7) passengers with (8th) including lavatory seat

 Corporate Option 2, (6) passengers with (7th) including lavatory seat
 Corporate Option 3, (7) passengers with (8th) including lavatory seat
 Corporate Option 4, (6) passengers with (7th) including lavatory seat
 Shuttle Option, (7) passengers all fwd facing with (8th) including lavatory seat

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10.6.1.1 CABIN LAYOUTS - CORPORATE OPTION 1 – “ARMONIA”

Corporate Option 1 – “Armonia”

FLOOR PLAN
1. Divan (2 place)
2. Single seat
3. Storage closet
4. Divan (1 place)
5. Refreshment cabinet
6. Fold out executive table
7. Belted toilet seat
8. Optional sink
9. LH & RH pyramid cabinets

Passenger capacity of (8) including lavatory seat.

Main Features:
 Four single seats arranged in an aft club grouping
 Two place side facing divan (right hand)
 Single side facing divan
 Refreshment cabinet (left hand) with stowage and drawers
 Aft Lavatory with closet
 Optional aft divan cabinet
Corporate ”Armonia” layout
Seating: VIP seats:
 Full recline where available
 180° swivel and fore/aft and lateral translation
 Sliding / drop down inboard (outboard optional) armrest (only on certain type of seats)
 Life vest storage compartment in seat base

One place & two places divans:

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  Storage compartment under divans
Optional for 2-place divan:
 End cabinet for storage and general stowage
 Floor drawers
Optional for 1-place divan:
 General stowage floor drawers

Armledge and Shell

 Headliner
 Passenger Service Panels (PSU), featuring continuous LED lights for up wash and down
wash lighting
 Window Panels, featuring manually operated, encapsulated window shades
 Sideledge and Dado, featuring club tables, dual drink- holders, light switches and storage
compartments with universal electrical outlets

LH Refreshment Cabinet
 Miniature liquor bottle stowage
 Ice chest or ice drawer
 Glass stowage
 Napkin stowage
 Miscellaneous stowage
 Trash container
Optional:
 Hot beverage container/dispenser

LH & RH Aft Pyramid Cabinets (Evaporator Covers)

 Closure for Air Conditioning Evaporator Units
 Stowage compartment

Aft Lavatory
 Illuminated wardrobe area for hanging storage
 Vanity mirror with valance lighting
 Toilet seat belted for taxi, take-off and landing
 General storage
 Self contained electronic flushing toilet
Optional:
 Vanity Module including sink with water faucet

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10.6.1.2 CABIN LAYOUTS - CORPORATE OPTION 2 – “ARIA”

Corporate Option 2 – “Aria”

FLOOR PLAN
1. Cabinet
2. Single seat
3. Storage closet
4. Fold out executive table
5. Belted toilet seat
6. Optional sink
7. LH & RH pyramid cabinets
8. Mid-ship pyramid cabinet

Passenger capacity of (7) including lavatory seat.

Main Features:
 Four single seats arranged in an aft club grouping
 Two single seats facing forward
 Optional pyramid cabinets located between seats
 Optional removable annex cabinet for refreshments (optional)
 Aft Lavatory with closet

Seating: VIP seats:

 Full recline where available
 180° swivel and fore/aft and lateral translation
 Sliding / drop down inboard (outboard optional) armrest (only on certain type of seats)
 Life vest storage compartment in seat base

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Armledge and Shell
Features:
 Headliner
 Passenger Service Panels (PSU), featuring continuous LED lights for up wash and down
wash lighting
 Window Panels, featuring manually operated, encapsulated window shades
 Sideledge and Dado, featuring club tables, dual drink- holders, light switches and storage
compartments with universal electrical outlets and data port (optional)

Mid ship Pyramid Cabinets

Features:
 Two or three general stowage drawers

LH & RH Aft Pyramid Cabinets (Evaporator Covers)

Features:
 Closure for Air Conditioning Evaporator Unit
 Stowage compartment

Aft Lavatory
 Illuminated wardrobe area for hanging storage
 Vanity mirror with valance lighting
 Toilet seat belted for taxi, take-off and landing
 General storage
 Self contained electronic flushing toilet

Optional:
 Vanity Module including sink with water faucet

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10.6.1.3 CABIN LAYOUTS - CORPORATE OPTION 3 – “ATMOSFERA”

Corporate Option 3 – “Atmosfera”

FLOOR PLAN
1. Divan (2-places)
2. Single seat
3. Storage closet
4. Fold out executive table
5. Belted toilet seat
6. LH & RH aft pyramid cabinets
7. Optional sink
8. Mid-ship pyramid cabinet
Passenger capacity of (8) including lavatory seat.
Main Features:
 Four single seats arranged in an aft club grouping
 Single seat forward facing (left hand)
 Two place side facing divan (right hand)
 Pyramid cabinet located between seats (left hand)
 Aft Lavatory with closet
Seating: VIP seats:
 Full recline where available
 180° swivel and fore/aft and lateral translation
 Sliding / drop down inboard (outboard optional) armrest (only on certain type of seats)
 Life vest storage compartment in seat base
Two places Divan:
 Storage compartment under divan
Optional:
 End cabinet for storage and general stowage
 Floor drawers
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Armledge and Shell
Features:
 Headliner
 Passenger Service Panels (PSU), featuring continuous LED lights for up wash and down
wash lighting
 Window Panels, featuring manually operated, encapsulated window shades
 Sideledge and Dado, featuring club tables, dual drink- holders, light switches and storage
compartments with universal electrical outlets and data port (optional)

LH Midship Pyramid Cabinet

Features:
 Two or three general stowage drawers

LH & RH Aft Pyramid Cabinets (Evaporator Covers)

Features:
 Closure for Air Conditioning Evaporator Unit
 Stowage compartment

Aft Lavatory
 Illuminated wardrobe area for hanging storage
 Vanity mirror with valance lighting
 Toilet seat belted for taxi, take-off and landing
 General storage
 Self contained electronic flushing toilet

Optional:
 Vanity Module including sink with water faucet

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10.6.1.4 CABIN LAYOUTS - CORPORATE OPTION 4 – “AMBIENTE”

FLOOR PLAN Corporate Option 4

1. RH Divan (1-place)
2. Single seat
3. Storage closet
4. LH Divan (1 place)
5. LH Pyramid Cabinet
6. Fold out executive table
7. Belted toilet seat
8. Optional sink
9. RH aft pyramid cabinet
10. LH aft pyramid cabinet
11. RH Refreshment cabinet
Passenger capacity of (7) including lavatory seat.
Main Features:
 Four single seats arranged in an aft club grouping with
increased distance between aft /fwd seats (club area).
 Single seat forward facing (left hand)
 Two single place side facing divans (left & right hand)
 Refreshment cabinet between RH single divan and RH aft seat
 Pyramid cabinet located between LH single divan and LH aft seat
 Aft Lavatory with closet
Seating: VIP seats:
 Full recline where available (PAC only)
 180° swivel and fore/aft and lateral translation
 Sliding / drop down inboard (outboard optional) armrest (only on certain type of seats)
 Life vest storage compartment in seat base
One place divans:
 Storage compartment floor drawers under divans

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Armledge and Shell
Features:
 Headliner
 Passenger Service Panels (PSU), featuring continuous LED lights for up wash and down
wash lighting
 Window Panels, featuring manually operated, encapsulated window shades
 Sideledge and Dado, featuring club tables, dual drink- holders, light switches and storage
compartments with universal electrical outlets and data port (optional)

RH Refreshment Cabinet
Features:
 Stowage compartments

LH Pyramid Cabinets
Features:
 Two or three general stowage drawers

LH & RH Aft Pyramid Cabinet (Evaporator Cover)

Features:
 Closure for Air Conditioning Evaporator Unit
 Stowage compartment

Aft Lavatory
 Illuminated wardrobe area for hanging storage
 Vanity mirror with valance lighting
 Toilet seat belted for taxi, take-off and landing
 General storage
 Self contained electronic flushing toilet

Optional:
 Vanity Module including sink with water faucet

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10.6.1.5 CABIN LAYOUTS – SHUTTLE LAYOUT – SEVEN AIRLINE TYPE SEATS

Shuttle Layout

FLOOR PLAN
1. Single seat
2. Storage closet
3. Belted toilet seat
4. In arm tray table (first row only)
5. Flip down tray table (typical all other seats)

Passenger capacity of (8) including lavatory seat.

Main Features:
 Seven forward facing airline style seats
 Flat arm ledge
 Aft Lavatory with closet

Seating: Lightweight seats

LH & RH Aft Pyramid Cabinet (Evaporator Cover)

Features:
 Closure for Air Conditioning Evaporator Unit
 Stowage compartment

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 10.6.2 OPTIONAL AERO-AMBULANCE CONFIGURATION

10.6.2.1 STRETCHERS FOR MEDEVAC QUICK CONVERSION

The interiors of the P.180 Avanti EVO can be easily (approx. 2 h work) converted into a one or two
stretchers MEDEVAC configuration cabin, by removing some of the VIP seats and installing one or
two LIFEPORT TM Basic Life Support (BLS) systems.
For weight saving reasons and for convenience of MEDEVAC operations (i.e. more room available
for the medical personnel), it is recommended to replace the remaining VIP seats with lighter
seats equipped with lowerable armrests available as a special option.
Each LIFEPORT TM BLS system includes:
 One or two 6-foot Patient Loading Utility
System (PLUS) equipped with power supply
outlets and with oxygen, air and vacuum
outlets
 One or two 6-foot AEROSLED stretcher with
restraint system
 One patient load ramp with stowage
compartment

10.6.2.2 CABIN LAYOUT – AERO AMBULANCE

The P.180 Avanti EVO cabin can be configured as a EASA/FAA certified Aeroambulance.
Two different layout versions are available:
 1 stretcher configuration, with seating for 4+1 medical crew / attendants
 2 stretchers configuration, with seating for 2+1 medical crew / attendants

Single Stretcher Layout

Double Stretcher Layout

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 10.6.3 SURVEILLANCE VERSION
The P.180 Avanti EVO can be configured as a surveillance aircraft equipped with a FLIR/TV Camera
system, the SeaFLIRII manufactured by FLIR SYSTEMS, thus enabling a wide range of mission
capabilities, including self-protection, counter-terrorism, drug interdictions, fisheries patrol and
environmental monitoring, mine detection, reconnaissance, surveillance, and Search and Rescue
operations.
The Surveillance version is equipped with a dedicated console installed in the passenger cabin.

10.6.4 CARGO & COMBI VERSION

A CARGO Kit and a COMBI Kit are available for installation in the cabin compartment, after total or
partial removal of passenger accommodations, to allow for full cargo or combined
cargo/passenger operations.
The maximum permissible number of seats is two (i.e. Flight Crew only) for the Cargo
configuration and four (i.e. Flight Crew plus two passengers in the foremost row) for the Combi
configuration. The kit includes:
 Protections to prevent damage during cargo handling for the lower sidewalls and for the
inflatable door seal
 Cargo restraint system, including:
 Cargo nets
 Restraint straps
 Tiedown fittings
 Floor carpet made of fire-resistant material over the entire floor area.

CARGO Layout

COMBI Layout

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 10.6.5 FLIGHT INSPECTION VERSION
The P.180 Avanti EVO can be equipped with a full Flight
Inspection capability or with a provision only; up to today these
version are available with “Shuttle” cabin layout but can be
developed also for the other cabin layouts.
When equipped with the Flight Inspection Provision only, the
aircraft will retain the standard cabin layout and will install an
additional set of antennas, dedicated to the Flight Inspection
System, with all the harnesses/cables and the means necessary to
stow/isolate them.
When equipped with the Full Flight Inspection capability:
 One RH seat in the aft side of the A/C is substituted by the FIS
Operator console(FIOC);
 One LH seat in the aft side of the A/C could be substituted by
a FIS Rack (FIDAR) to host additional equipment if needed by
the applicable Flight Inspection capabilities requirements;
Moreover, if requested, a dedicated operator seat (a copilot seat
with an adapter) can be installed in lieu of the latest RH seat.
Aside, the certified layout (console/rack/operator seat) applied to
the “Shuttle” configuration.
The “Full Flight Inspection” will provide the aircraft with the
capability to inspect:
 Navigation & Communication Aids/facilities,
 Radar facilities,
 Visual Approach Aids,
 Combined Procedures (approach/enroute)
 Instrument Flight Procedure (Dep., Enroute, Arrival)
Below a pictorial of a “single” console with operator seat applied to a “Corporate “2” configuration

When in Flight Inspection configuration, P.180 Avanti EVO shall NOT be equipped with Community
Noise reduction package (new Hartzell propellers with scimitar blades and torque limiter). The
aircraft shall retain previous Hartzell propellers in order to allow operation at 2000 rpms.

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 10.6.6 INTERIOR OPTIONS
10.6.6.1 RIGHT-HAND DIVAN END CABINET (CORPORATE 1, 3 & 4)
This optional cabinet is designed for installation on the forward
right side of the cabin, at the aft end of the two place divan, to
provide armrest comfort and additional storage space. It
features:
 Two storage drawers
 Dual drink holder

10.6.6.2 WATER SYSTEM FOR THE LAVATORY MODULE

Optional Vanity Sink with Faucet including fresh water tank and
waste water collection tank to be installed on the right hand aft
corner of the lavatory module.
The system include a water tank, an electrical pump (power
supplied with 28 VDC) and relevant pipings, installed inside the
lower part of vanity closet assy.

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10.6.6.3 HOT BEVERAGE DISPENSER
Heated liquid container/dispenser to be installed in place of the standard carafes in the top part of
the mid cabin refreshment cabinet.

10.6.6.4 FLOOR DRAWER FOR THE ONE & TWO PLACE DIVAN
Single or dual drawers kit for installation in the base of the one place left hand side divan and two
place right hand side divan.

Corporate 1 & 4 Corporate 2 & 3

10.6.6.5 SHEEP SKIN FOR PILOT AND CO-PILOT SEATS

Sheep skin cover to provide Pilots with a better comfort both in the hot and the cold season.

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 10.6.7 CABIN MATERIALS AND FINISHING
Standard upholstery materials include:
 carpet, 8 mm (0.3 in.) thick, 1,750 Kg/m2 (0,35 lbs./ft2)
 leather, 0.8-1.2 mm (0.03-0.05 in.) thick, 0,890 Kg/m2 (0.18 lbs./ft2)
 foam, 150 kg/m3 (9,35 lbs./ft3)

Premium materials and/or finishes are available on Customer’s request with lead times to be
defined on a case-by-case basis.

NOTE:
Non standard materials may cause extra weight and a subsequent reduction of useful payload.

All upholstery materials shall comply with the requirements of specification PS180-25-021
“Materials for aircraft furnishing”.

10.6.8 EXTERNAL PAINTING

10.6.8.1 STANDARD PAINTING SCHEME

The standard painting scheme is fully white color.

10.6.8.2 FULLY CUSTOMIZED PAINTING SCHEME (SOLID COLORS)*

Non standard paint scheme featuring solid colors may be selected as option. Logo and drawing
scheme according to customer’s specific requirements.

10.6.8.3 FULLY CUSTOMIZED SPECIAL MICALIZED / METALIZED PAINTING SCHEME*

Non standard paint scheme with special micalised / metalized colors may be selected as option.
Logo and drawing scheme according to customer’s specific requirements.

*NOTE:
Painting customization is subject to technical feasibility in accordance to the Maintenance Manual
limitations (absorption of radiation limitations) and will have a not negligible payload reduction
that has to be considered by the customer.

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11 INSPECTIONS

The inspection schedule consists of individual maintenance checks, performed at 200, 600, 1800,
3600 flight hour intervals, and of other flight hour and calendar scheduled inspections:

 200FH Tasks – Every 200 Flight Hours except when B, C, D inspections occur
 B Check – Every 600 Flight Hours except when D inspection occurs
 C Check – Every 1800 Flight Hours except when D inspection occurs
 D Check – Every 3600 Flight Hours

P.180 Inspection Schedule

The PT6A-66B engine requires Hot Section Inspection at 1800 hrs and Overhaul at 3600 hrs.
Engine routine checks shall be performed during the airplane preflight check and minor checks
shall be performed in conjunction with “200 FH” Interval Inspection.
The checks must be complied within the limits specified by P&WC if not otherwise specified by
Piaggio Maintenance Schedule.

The Hartzell HC-E5N propellers require overhaul every 6 years or 3600 hrs whichever occurs first.

The Main Landing Gear shall requires overhaul every 10.000 landings or 15 years whichever occurs
first.

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APPENDIX A - NOTES ABOUT THE 3-LIFTING-SURFACE DESIGN

Some additional information is given here about the Avanti EVO 3-Lifting-Surface design.
The Avanti EVO’s distinctive shape is not simply due to a styling research but was dictated by the design
goals set for the aircraft: a wide body, stand-up cabin, jet-like performance and turboprop fuel efficiency.
After an intensive aerodynamic analysis and several hundreds of hours of wind tunnel tests, PIAGGIO
AEROSPACE engineers concluded that these goals could not be achieved with conventional aircraft
configurations.
Thus the AVANTI EVO project evolved to include:
 PIAGGIO’s patented Three-Lifting-Surface Configuration (3LSC), which permits a 34-percent
reduction in total wing area over conventional designs, thereby reducing weight and drag;
 A non-cylindrical, low-drag fuselage shape, developed through extensive wind tunnel testing to
allow a large cabin cross section without a large drag penalty;
While its surface appearance is radically different from other aircraft, there is much to the Avanti EVO that
pilots and maintenance personnel will find conventional and familiar:
 Well known and widely used systems;
 90-percent aluminium construction;
 Conventional flight controls.
Thanks to this unique combination of the innovative and the conventional, you can enjoy the EVO’s
exhilarating performance and exceptional comfort, while flying with confidence in the Avanti’s proven
technologies and systems.
The AVANTI EVO’s unique 3LSC design utilises a small forward wing, a high-aspect-ratio main wing and a
small horizontal stabiliser atop the conventional vertical stabiliser.
This combination reduces drag by minimising the amount of downward force the horizontal stabiliser must
produce to balance the nose-down pitching moment created by the main wing lift and pressure distribution
acting aft of the centre of gravity.
In a conventional 2-surface configuration, this nose-down pitching moment, neutralised (trimmed) by a
downward force created by the “negative” lift, can be as much as 10% of the aircraft’s weight at cruise and
as much as 20% during approach. The result is that the main wing must provide the lift to support 110% to
120% of the aircraft’s weight. The net effect is that the main wing must be larger than a wing required to
support only the aircraft’s weight.

Conventional aircraft

ML = Nose down pitching moment created by the main wing’s lift

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LT = Negative trim lift required to neutralise main wing’s pitching moment
The extra lift required by the main wing and the “negative” lift generated by the horizontal stabiliser
produces additional induced drag (the drag associated with the generation of lift). This additional drag
would be not present if the aircraft’s weight were supported by the main wing only and the “negative” lift
was not required. A larger wing also results in additional structural weight and profile drag (the drag
associated with size).
With the AVANTI EVO’s 3LSC design, the small forward wing produces “positive” upward lift required to
trim the nose-down pitching moment created by the main wing. The horizontal stabiliser, in cruise
configuration, is producing negligible “positive” or “negative” lift.
The total lift produced by the forward and main wing is basically only that required to support the
aircraft’s weight. This lower lift requirement results in less wing area, hence, lower profile drag, lower
induced drag and lower structural weight.

3-Lifting-Surface design

W = Aircraft weight LM = Main wing lift

L = Lift = LF +LM + LT T = Lift to trim aircraft (negligible)
LF = Forward wing lift

Although the horizontal tail, in some configurations, can produce a small amount of “negative” lift, the drag
and weight penalty are minimal and the benefits to controllability are substantial. When the main wing’s
flaps are lowered for takeoff and landing the centre of lift moves even further aft, creating a large nose-
down pitching moment. The flap on the Avanti’s forward wing is programmed to extend the exact amount
to provide the additional up-lift to balance out the nose-down moment created by the main wing flaps.
The horizontal stabiliser with its conventional elevator allows the pilot precise pitch control.
With the pure canard (2-surface) configuration, pitch control is far more difficult and may require the
weight and complexity of variable sweep plus elevators or flaps on the forward wing.
The Avanti’s pitch control and stall characteristics are so conventional that the aircraft does not require a
stick-pusher or stick-shaker as some conventional aircraft design.

Flap effect

Main wing centre of lift moves aft with flap deflection. Forward wing flaps are programmed to provide
additional lift required to balance the increased nose-down pitching moment.
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APPENDIX B – NEW AIRCRAFT WARRANTY

A. Aircraft Manufacturer’s Limited Warranty

Manufacturer warrants that the Aircraft, at the time of its delivery from Manufacturer, shall be
free from all defects in material and workmanship and from defects inherent in its design
relative to the known state of the art at the time of such design. This warranty does not apply
to Aircraft operated or maintained contrary to Manufacturer's service and flight manuals, as
they may be in effect from time to time.
Upon receipt of prompt written notification from the Customer, including satisfactory evidence
of the defects and return of the defective part when possible, Manufacturer shall:
1. if the failure occurs either within the first 1,000 flight hours or 24 months after
delivery to Buyer, whichever occurs earlier, either repair or replace any defective item
(except engines referenced in paragraph B below).
2. if the failure occurs either within the first 1,000 flight hours or 24 months after
delivery to Buyer, whichever occurs earlier, either repair or replace all defective items
which are manufactured by Manufacturer or those which are manufactured by vendors
to Manufacturer's detailed design specifications.
3. if the failure occurs both within the first 5,000 flight hours and within 60 months after
delivery of the Aircraft to Buyer, either repair or replace any defective fuselage,
empennage, wing, or control surface.

B. Engines Warranted by Pratt & Whitney

Engine warranty will start from the day of the final delivery of the aircraft by the Manufacturer
to the Buyer and will be provided and administered by the engine manufacturer (Pratt &
Whitney Canada Inc.). Specific details for the implementation of such warranty will be furnished
to the Buyer by the Manufacturer upon delivery of the Aircraft.

C. Avionics Warranted by Applicable Manufacturers

Rockwell Collins avionics equipment and components are warranted by the manufacturers for a
period of 5 years. Buyer will receive any remaining life of those warranties in accordance with
each respective manufacturer's warranty program starting from the date of final delivery of the
aircraft by the Manufacturer to the Buyer.

D. Labour Statement
With regard to paragraphs A(1), A(2), and A(3) above, the repair or replacement of defective
parts under this warranty will be made by or through any Avanti Authorised Service Centre
without charge for parts and/or labour for removal, installation and/or actual repair of such
defective parts.

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APPENDIX C – OPTIONAL EQUIPMENT LIST SUMMARY

C.1 Aircraft configurations

Option Id. Description Estimated Estimated
Weight Weight (kg)
(Lbs)
XR-001 Extended Range Option 64 29
C.2 Cabin layouts
Aircraft Option Id. Description Estimated Estimated
Weight Weight Weight (kg)
(lbs) (includes (Lbs)
P-001 painting)
8220 I-001 Corporate option 1 “Armonia”, 380 172
featuring seven VIP seats
(Iacobucci IHF):
4 Club seats
1 side facing, two-place divan
1 side facing, one-place divan
LH Refresment Cabinet
8220 I-001a Same as above with 4 Club 380 172
seats by PAC (Full recline,
lowerable inboard armrest)
8160 I-001b Same as above with 4 Club 320 145
seats by De Crane

8200 I-002 Corporate option 2 “Aria”, 360 163

featuring six VIP seats
(Iacobucci IHF):
4 Club seats,
2 forward facing seats
8190 I-002a Same as above with 6 PAC 350 159
armchairs (Full recline,
lowerable inboard armrest)
8110 I-002b Same as above with 6 Club 270 122
seats by De Crane
8210 I-003 Corporate option 3 370 168
“Atmosfera”, featuring five VIP
seats (Iacobucci IHF):
4 Club seats,
1 side facing, two-place divan,
1 forward facing VIP seat
Two Drawers Pyram. Cab. (LH)
8210 I-003a Same as above with 5 PAC 370 168
armchairs (Full recline,
lowerable inboard armrest)

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 8140 I-003b Same as above with 5 De 300 136
Crane armchairs

8200 I-004 Corporate option 4 350 159

“Ambiente”, featuring seven
VIP seats (Iacobucci IHF):
4 Club seats
2 side facing, one-place divan

RH Refreshment Cabinet
Two Drawers Pyram. Cab. (LH)
8200 I-004a Same as above with 4 Club 350 159
seats by PAC (Full recline,
lowerable inboard armrest)
8150 I-004b Same as above with 4 Club 300 136
seats by De Crane

7850 I-010 Shuttle layout, featuring seven 210 95

seats:
7 forward facing lightweight
seats (airline style)
C.3 Interior options
Option Id. Description Estimated Estimated
Weight Weight
(Lbs) (Lbs)
I-110 Kit of seven lightweight seats 208 94,3
airline style (loose supply)
I-120 Ambulance kit (Single 195 88,4
Stretcher)
I-121 Ambulance kit (Two 357 161,9
Stretchers)
I-011 Floor drawer for the one place 4,1 1,9
divan (Corporate 1 & 4)
I-012 Floor drawers for the two 10,67 4,8
place divan (Corporate 1 & 3)
I-013 Right-hand divan end cabinet 16,76 7,6
(for Corporate 1 and 3 layouts)
I-014 RH Aft 1 Drawer Cabinet (for 9,75 4,4
Corporate 2 and 4 layouts)
I-015 RH Aft 2 Drawers Cabinet (for 13,12 6,0
Corporate 2 and 4 layouts)
I-016 Hot Beverage Dispenser for 4,4 2,0
the Refreshment Cabinet (for
Corporate 1 )
I-017 Pyramid 2 Drawers Cabinet (LH 13,98 6,3
or RH)

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 I-018 Pyramid 3 Drawers Cabinet (LH 18,35 8,3
or RH)
I-019 Vanity sink and water system 20 9,1
for the Lavatory Module
I-020 Sheep skin for Pilot and Co- 4 1,8
pilot seats
C.4 Avionics Options
Option Id. Description Estimated Estimated
Weight Weight (kg)
(Lbs)
A-001 HF Wiring Provisions 24 10,9
A-002 HF Radio System (1) 24,5 11,1
A-011 Full Provision for CVR/CVDR 7,4 3,4
installation
A-012 Cockpit Voice Recorder (2) 12,2 5,5
A-013 CVR System Portable Interface N/A N/A
Unit for Data Retrieval
A-014 Cockpit Voice & Flight Data 19 8,6
Recorder Combo Unit
A-015 ACAS II 7.1 (Exchange – 24 10,9
Replacing TCAS I) (delta
weight)
A-016 “Enhanced Safety of Flight” 28 12,7
Package TCAS II + EGPWS
(Exchange)(delta weight) (3)
A-017 Lightning Detection System 14,8 6,7
(Stormscope)
A-018 Satellite Based Augmentation 0 0,0
System (SBAS/LPV) capability
(3)
A-019 VHF Datalink Universal 10 4,5
Graphical Weather (Requires
installation of a third Collins
Nav/Com and Antenna)
A-024 Inmarsat Satellite phone and 17,2 7,8
Wi-Fi Cabin Connectivity
System (4)
A-025 EFB (iPad Mini) Provisions 0,74 0,3
A-028 Video Capability for the MFD 0 0,0
A-030 Engine Data Acquisition & 5 2,3
Monitoring System – P&WC /
Altair(4)
A-031 Engine Data Transfer Unit – 5 2,3
P&WC / Altair (5)

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 C.5 Systems and Miscellaneous equipment
Option Id. Description Estimated Estimated
Weight Weight (kg)
(Lbs)
S-001 First Aid Oxygen 3,8 1,7
S-002 Portable Oxygen Cylinder 9 4,1
S-003 Nose Landing Gear Gravel kit 2 0,9
(6)
S-004 JAR OPS 1 / FAR 135 KIT 14 6,3
S-006a-c Lead Acid Battery 10 4,5
(Exchange)(delta weight)
S-006b Low maintenance Battery Ni- 2 0,9
Cd (Exchange)(delta weight)
S-007 14VDC Auxiliary Power 2 0,9
S – 008 Provision for Portable ELT - -
stowage
S-009 Life Raft (7 Person / overload 46 20,8
10 Persons, triple frequency
ELT, JAR-OPS compliant SEP
kit)
S-011 Modular IFE – Flight Display - To be defined after
(plug-in monitors, CD/DVD Customer selection
player w/ Moving map,
wireless headsets audio, iPod
connector)
C.6 Painting options
Option Id. Description Estimated Estimated
Weight Weight (kg)
(Lbs)
P-001 Fully Customized Painting 100 45,4
Scheme (Non Micalized Colors)
(7)
P-002 Fully Customized Special 150 68,0
Micalized Painting Scheme (7)

Note (1): Requires the installation of the HF wiring provision (A-001)

Note (2): Requires the installation of the full provision for CVR installation (A-004)
Note (3): EPGWS and SBAS/LPV cannot be installed together for operating technical reason
Note (4) Inmarsat Satellite phone and ADAS cannot be installed together.
Note (5) Requires the installation of the provision for Engine Data Acquisition & Monitoring System (A-030)
Note (6): Required for operation on unpaved runways in accordance with the AFM supplements.
Note (7): Painting weight may according the customer selected scheme; it is about 100 lbs for solid color and 150
lbs for micalized colors (from green)

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