1.      Basic Aircraft

• Aluminum alloy fuselage
• Acrylic windshields
• Overhead cockpit windows
• Cockpit ram air adjustable outlets
• Forced fan ventilation
• Bleed air heater and defroster with air noise suppressions
• Heated Pitot tubes (2) with Pitot heat failure warning (2)
• Heated static intakes (2)
• One cockpit and one passenger cabin fire extinguisher
• Pilot doors (2) with push-out emergency exit window (with “storm window” on pilot side)
• Plug-in sliding doors (2) for passenger cabin access with four locking latches
• Passenger doors stop in fully open position (for sliding door)
• Six cabin push-out emergency exit windows (two on each passenger cabin door)
• Baggage compartment with two lockable baggage compartment doors (LH and RH)
• Baggage compartment cargo tie-down fittings
• Wheeled retractable tricycle landing gear (two wheels on nose gear and brakes on main

landing gear)

• Structural provisions for nose landing gear doors
• Landing gear mooring
• Upper deck mooring provisions
• Hoisting and jacking fittings
• Tail boom and vertical fin
• Stabilizers with composite “winglets”
• Pilot and co-pilot windshield wipers
• Maintenance steps for access to upper deck on both sides
• Upper deck cowlings (one front forward sliding, two side opening for engine access)
• Steps for cockpit access
• Anti-vibration masses (2) under cabin floor

2.      Rotors and controls

• Fully articulated Main Rotor (M/R) with five composite blades, five elastomeric bearingsand five hydraulic dampers
• Rotating M/R flight controls
• Main rotor hub beanie
• Main dual servo actuators (3)
• Fully articulated Tail Rotor (T/R) with four composite blades, four elastomeric bearingsand four elastomeric dampers
• Rotating T/R flight controls
• One T/R dual servo actuator
• Force trim system
• Pilot fixed flight controls (cyclic, collective, anti-torque pedals)
• Co-pilot fixed flight controls (cyclic, collective, anti-torque pedals)
• Dual digital 3-axis linear actuators
• Rotor brake
• Provision for main rotor tracking (magnetic pick-up)

3.      Power Plant and Fuel System

• Two Pratt & Whitney Canada PT6C-67C turboshaft engines
• Two independent FADEC systems with auto-start and engine control functions for normal, emergency and training operations
• Two magnetic chip detectors
• Two integrated and independent engine oil coolers
• Separation firewall protection for each engine
• Fire detection system
• Fire extinguisher system (2 bottles)
• Engine exhausts and ejectors
• Two independent crashworthy fuel cells
• Two supply pumps on engines
• Two submerged booster pumps in fuel tank
• Two fuel filter assemblies
• Two engine back-up controls, mechanical and electrical
• Two manual engine start and ignition systems

4.      Transmission drive system and hydraulic system

• Main transmission with two direct drive engine inputs

• Three main transmission chip detectors/debris collectors with burning capability
• Two freewheel units
• Four strut rods for upper deck attachment and one anti-torque plate
• Intermediate gearbox with sight gauge and magnetic drain plug/chip detector
• Tail gearbox with sight gauge and magnetic drain plug/chip detector
• Dual independent, redundant hydraulic systems
• Two hydraulic Power Control Modules (PCM)
• Three main transmission driven hydraulic mechanical pumps for controls, landing gearand wheel brake actuation
• One electrical pump for control checks on ground (engines off)
• Air conditioning compressor quill

5.      Electrical System

• Two Pratt & Whitney Canada PT6C-67C turboshaft engines
• DC primary power generation: 28 V DC regulated voltage provided by two independent300 A starter generators
• DC external power receptacle
• Two nickel-cadmium batteries: one 44 Ah main battery plus one 13 Ah auxiliary battery
• DC starter generator control units (2)
• Navigation lights (3)
• Anti-collision light
• External emergency landing lights on the sponsons (2)
• Fixed landing/taxing lights on the sponsons (2)
• Retractable/rotating landing light
• Baggage compartment lights (3) and smoke sensor

6.      Standard Avionic Package

• 1st PFD (Pilot Primary Flight Display 8” x 10” colour Active Matrix Liquid Crystal Display)as part of Honeywell Primus Epic System for visualization of flight and navigation data
• 2nd PFD (Co-pilot Primary Flight Display 8” x 10” colour Active Matrix Liquid Crystal Display) as part of Honeywell Primus Epic System for visualization of flight and navigationdata
• 1st MFD (Pilot Multifunction Display 8” x 10” colour Active Matrix Liquid Crystal Display)as part of Honeywell Primus Epic System for visualization of flight and navigation data
• 2nd MFD (Co-pilot Multifunction Display 8” x 10” colour Active Matrix Liquid Crystal Display) as part of Honeywell Primus Epic System for visualization of flight and navigationdata
• One Electronic Standby Instrument System (ESIS) (attitude, airspeed, altitude, vertical speed, compass, and ILS data)
• Two Attitude and Heading Reference Systems (AHRS)
• Two Air Data Modules (ADM)
• Two flux valves
• Two Display Controllers (DC)
• Two Cursor Control Devices (CCD)
• One Reversion Control Panel (RCP)
• One Display Dimming Control Panel (DCP)
• One Stability Augmentation System (SAS) control panel
• Two Remote Instrument Controllers (RIC)
• Two Modular Avionic Units (MAU) incorporating the following major subsystems and/or functions:
  • Vehicle Monitoring System – VMS (dual)

• Monitor Warning System – MWS (dual)
• Aural Warning Generator – AWG (single)
• Central Maintenance Computer – CMC (single)
• 3-Axis dual Digital Automatic Flight Control System (DAFCS) with autotrim function
• Provision for CVR/FDR data interface (single)
• Flight Director System (dual)

• Pilot and co-pilot microphone and headset
• Pilot and Co-pilot interphone control (cyclic grip and floor switches)
• Left Modular Radio Cabinet (MRC) with the following modules
  • One VHF Comm.
  • One VOR/LOC/GS/MB
• Right Modular Radio Cabinet (MRC) with the following modules:
  • One VHF Comm.
  • One S diversity transponder
  • One VOR/LOC/GS/MB
  • One ADF
  • One DME
• Two pedestal mounted MCDU (Multi Control Function Display Units)
• 1st Radar Altimeter (RT . 300)
• 2nd Radar Altimeter System (RT . 300)
• Emergency Locator Transmitter (ELT . 5/243/406 MHz)
• One Flight Guidance Controller
• Honeywell GPS module with Flight Plan Management System (FPMS)
• Pilot and co-pilot digital audio panels with remote ICS audio port for ground operation
• Pilot clock (digital)
• Co-pilot clock (digital)
• One magnetic compass
• One Outside Air Temperature indicator
• Two Master Warning Lights (MWL)
• Two Master Caution Lights (MCL)
• Engine 1 Fire Light
• Engine 2 Fire Light
• Baggage compartment smoke detector light
• Dual electrical power connection for CVR/FDR (FAA requirement compliant)
• Cockpit Voice Recorder & Flight Data Recorder (CVR/FDR) with Underwater Locator Beacon (ULB)

7.      Interior

• Cabin, cockpit and baggage compartment utility finishing interior
• Pilot and co-pilot crashworthy seats (with inertial reels and safety belts)
• Cockpit dome/storm light
• Cockpit utility lights (2)
• 28 V DC cockpit/cabin power outlet
• Cockpit panel sun-glare shields
• Overhead cockpit windows sun shades
• Fluorescent lighted emergency exit signs
• Cockpit map and data case in central console
• Two flash lights for pilot and co-pilot
• Map and data cases in pilot and co-pilot doors

• ICS panel with plug for one headset
• Air ventilation system
• First aid kit (EASA)

8.      Painting

• Standard color scheme from company paint selection, solid color

9.      Miscellaneous/ Ground equipment

• Covers and flags: engine exhaust pipes (2), engine air inlets (2) and Pitot tubes (2), battery connector warning flag (1)
• Tie-down assemblies for main rotor blades (5)
• Tail rotor blades flapping block (1)
• Tail rotor blades sock pole (1)
• Main landing gear wheel chocks (2)
• Nose landing gear centre pin (1) and landing gear handle locking pin (1)
• Jacking dome assy (1)
• Tow bar

10.  Additional Optional Equipment installed

1. Comfort and Fixed interior Equipment:

• Passenger cabin sliding doors with specific ceiling and liners
• Painted pockets in pilot & co-pilot doors
• Pilot carpet

B.   VIP Deluxe Interior:

8 Seats Layout Package

• 2 VVIP crashworthy armchair leather covered (captain chairs)
• 4 VIP crashworthy seats leather covered
• 2 additional VIP crashworthy seats leather covered
• VIP soundproofing
• hydraulic pulsation dampeners
• vibration absorber (3rd mass)
• nose landing gear door
• lighting system
• air conditioning outlets
• carpet
• extra carpet
• liners, cabin roof and covering leatherette
• standard structural and electrical provisions for interior installation
• Cabinet
• Coat hangers

C.   Additional Avionic equipment:

• Enhanced Ground Proximity Warning System (EGPWS) complete Kit
• Weather radar (Primus 660) complete Kit
• TCAS I Honeywell (KTA-970 model)

D.   Additional Mission / Utility equipment:

• Increased Gross Weight to 800 KG

• Emergency floats provision
• 4-axis Digital Automatic Flight Control System (add. to std 3-axis)
• Air Conditioning system
• VVIP ultra silent soundproofing
• Auxiliary fuel tank 132 USG provision
• Auxiliary fuel tank 132 USG removable parts
• LH and RH electrically operated passenger steps with lights
• GSM interacting with ICS
• Night curtain cabin separator
• PA Briefing System
• One ICS station in pax cabin (ICS phone able to communicate with pilots)
• Operational Software Phase 7