2009 Agusta AW139

Airframe: Aluminium Alloy Fuselage Acrylic Windshields Overhead Cockpit Transparent Windows Lower Cockpit Transparent Windows Cockpit Ram Air Adjustable Outlets 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 Six Cabin Push-out Emergency Exit Windows (two on each passenger cabin door) Baggage Compartment with Two Lockable Baggage Compartment Doors (LH and RH) 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 Horizontal 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

Rotors and Controls: Fully Articulated Main Rotor (M/R) with Five Composite Blades, Five Elastomeric Bearings and 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 Bearings and 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 Provision for Main Rotor Tracking (magnetic pick-up)

Power Plant and Fuel System: Two Pratt & Whitney Canada PT6C-67C Turbo-shaft 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) Steel 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

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 Gear and Wheel Brake Actuation One Electrical Pump for Control Checks on Ground (Engines off) Air Conditioning Compressor Quill

Electrical System: DC Primary Power Generation: 28 V DC Regulated Voltage Provided by Two Independent 300 A Starter Generators DC External Power Receptacle Two Nickel-cadmium Batteries: One 44 Ah (20 cells) Main Battery Plus One 27 Ah Auxiliary Battery DC Starter Generator Control Units (2) Navigation Lights (3) Anti-collision Light External Emergency Landing Lights on the Sponsons (2) Retractable/Rotating Landing/Taxing Light Baggage Compartment Lights (3) and Smoke Sensor

AW Premium Equipment: Forced Fan Ventilation Bleed Air Heater and Defroster with Air Noise Suppressions Cockpit Air Ventilation System Baggage Compartment Cargo Tie-down Fittings Rotor Brake 1st Radar Altimeter RT-300 2nd Radar Altimeter RT-300 4-Axis Dual Digital Automatic Flight Control System (DAFCS) Basic Incorporated into Modular Avionic Units (MAUs) Flight Director System (dual) Incorporated into the Modular Avionic Unit (MAU) Two Honeywell GPS Modules (GNSS/SBAS – Global Navigation Satellite System/Satellite Based Augmentation System) with Flight Plan Management System (FPMS) One Mode S diversity transponder with Extended Squitter (ADSB-Out 1090 MHz) incorporated into the Modular Radio Cabinet (MRC) Cockpit Voice Recorder & Flight Data Recorder (CVR/FDR) with Underwater Locator Beacon (ULB)

Mission Equipment: Increased Gross Weight - 6,800 Kg (14,991 lb) Approach Plates Chart Holders with Lights for Pilot and Co-pilot Pilot and Co-pilot Adjustable Seats (in lieu of standard seats) Heated Glass Windshield 4-Axis DAFCS (Digital Automatic Flight Control System) Enhanced with Hover Mode (HOV) Enhanced Ground Proximity Warning System (EGPWS) Provision Enhanced Ground Proximity Warning System (EGPWS) Removable TCAS I KTA-970 Honeywell Bendix/King Provision TCAS I KTA-970 Honeywell Bendix/King Removable (