2009 AGUSTA AW139

Description

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 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

Modifications

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) MISCELLANEOUS / GROUND EQUIPMENT - Cargo net in baggage compartment - Covers and flags: engine exhaust pipes (2), engine air inlets (2) and Pitot tubes (2), Manuals: flight and maintenance and overhaul, illustrated parts catalogue - Tie-down assemblies for main rotor blades (5) - Tail rotor blades flapping block (1) - Main rotor blades sock pole (1) - Main landing gear wheel chocks (2) - Main rotor balance and tracking chart, tail rotor balance chart - Nose landing gear centre pin (1) and landing gear handle locking pin (1) - Tow Bar - Loose equipment bag (1)

Avionics

STANDARD AVIONIC PACKAGE - 1st PFD (Pilot Primary Flight Display) 8" × 10" (external) 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" × 10" (external) colour Active Matrix Liquid Crystal Display as part of Honeywell Primus Epic System for visualization of flight and navigation data - 1st MFD (Pilot Multi-Function Display) 8" × 10" (external) colour Active Matrix Liquid Crystal Display as part of Honeywell Primus Epic System for visualization of flight and navigation data - 2nd MFD (Co-pilot Multi-Function Display) 8" × 10" (external) colour Active Matrix Liquid Crystal Display as part of Honeywell Primus Epic System for visualization of flight and navigation data - 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 – Provision for CVR/FDR data interface (single) - Pilot and co-pilot headsets - 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 VOR/LOC/GS/MB – One ADF – One DME - Two pedestal mounted Multifunction Control Display Units (MCDU) - Emergency Locator Transmitter (ELT) - One flight guidance controller - 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)