2004 Leonardo AB139

Details

AIRFRAME

• Aluminum alloy fuselage
• Acrylic Windshields
• Overhead windows
• Fresh air adjustable outlets
• Forced fan ventilation (provision for)
• Bleed air header and defroster with air noise suppression
• Heated Pitot tubes w/ Pitot heat failure warning (2)
• Heated static intakes (2)
• Cargo tie-down fittings
• Pilot cabin fire extinguisher
• Pilot’s doors (2 for pilot’s cabin)
• Plug-in sliding doors (2) for PAX cabin access with emergency exit windows on each door
• Baggage compartment
• Wheeled retractable tricycle Landing Gear (2 wheels on nose gear)
• Mooring and jacking fittings
• Tail-boom and vertical fin
• Stabilizer

ROTORS & CONTROLS

• Fully-articulated main rotor with five composite blades, five elastomeric bearings and five hydraulic dampers
• Rotating main rotor flight controls
• Three main dual servo actuators
• Fully-articulated tail rotor with four composite blades, four elastomeric bearings and four elastomeric dampers
• Rotating tail rotor flight controls
• One tail rotor dual servo actuator
• Force trim system
• Pilot fixed flight controls (cyclic, collective, rudder)
• Co-pilot fixed flight controls (cyclic, collective, rudder – provisions for)
• Engine mechanical back-up control (2)
• Dual digital three-axis linear actuators (6)

ELECTRICAL SYSTEMS

• DC primary power generation: 28-volt DC regulated voltage provided by two independent 300-amp starter generators
• DC external power receptacle
• One nickel-cadmium battery 40 Ah plus one 13 Ah auxiliary battery
• DC starter generator control unit (2)
• Manual engine start and ignition system (2)
• Navigation lights
• Anti-collision lights
• Landing light/search light
• Utility lights
• Pilot cabin dome light
• PAX cabin lights (dome or reading lights according to interior configuration)
• Tritium-lighted emergency exit signs
• Seatbelt/no smoking signs
• Baggage compartment light & fire/smoke sensor
• AC static inverters system (provisions for)

TRANSMISSION / DRIVE SYSTEM & HYDRAULIC SYSTEM

• Main transmission with chip detectors/debris collectors with burning capability
• Four strut rods for upper deck attachment and anti-torque plate
• Intermediate gearbox (sight gage and magnetic drain plug/chip detector)
• Tail gearbox (sight gage and magnetic drain plug/chip detector)
• Two hydraulic power control modules (PCMs)
• Three hydraulic mechanical pumps for controls (2 independent sys) and one electrical pump for controls check on ground (engines off)
• Upper-deck cowlings
• Provisions for BCS compressor

POWER PLANT & FUEL SYSTEM

• Two Pratt & Whitney Canada PT6C-67C engines
• EEC (Electronic Engine Control)
• Overriding clutches
• Two magnetic chip detectors
• Two integrated and independent engine oil coolers
• Separate firewall protection for each engine
• Fire detecting system
• Cowlings
• Engine exhausts and ejectors
• Two independent crashworthy fuel cells
• Pumps on engines (2) and submerged in fuel tanks (2)
• Fuel filter assembly

COMMUNICATION SYSTEM

• Primus Epic HF 1050 long-range system
• Microphone and headset (2)
• Interphone control (cyclic grip and floor switches) (2)
• Stand-alone VHF/AM radio equipment
• Intercommunication control panel

FLIGHT/ENGINE INSTRUMENTATION

• PFD (Pilot Primary Flight Display 8 x 10 color Active Matrix Liquid Crystal Display) as part of Honeywell Primus Epic System for visualization of flight and navigation data
• MFD (Pilot Multifunction Display 8 x 10 color Active Matrix Liquid Crystal Display) as part of Honeywell Primus Epic System for visualization of flight and navigation data
• AHRS (Attitude and Heading Reference System)
• ADM (Air Data Module)
• Flux valve
• Display Controller
• Cursor Control Device
• Reversion Control Panel
• Display Dimming Control Panel
• Stability Augmentation System (SAS) Controller
• Modular Avionics Units (MAUs) - Vehicle Monitoring System – VMS (dual) - Monitor Warning System – MWS (dual) - Aural Warning Generator – AWG (single) - Central Maintenance Computer – CMC (single) - 4-axis Digital Automatic Flight Control System – DFACS (dual) with Autotrim function - Flight Data Acquisition Unit – FDAU (single)
• Clock (digital)
• Magnetic Compass
• Free air temperature indicator
• Master Warning Light (MWL)
• Master Caution Light (MCL)
• Engine 1 fire light
• Engine 2 fire light
• Baggage fire light

SINGLE/DUAL PILOT IFR

• Electronic Standby Instrument System (ESIS) (attitude, airspeed, altitude, vertical speed, compass and ILS data)
• Second PFD (co-pilot display)
• Second Master Warning Light
• Second Master Caution Lights
• Co-pilot clock
• Dual control
• Second display controller
• Remote Instrument Controller
• Second cursor control device
• Left modular radio cabinet with following modules: - 1 VHF Comm - VOR/LOC/GS/MB
• Right modular radio cabinet with the following modules: - 1 VHF Comm - 1 Mode-C diversity transponder - 1 VOR/LOC/GS/MB - 1 ADF - 1 DME
• Emergency communication panel
• RMU – Radio Management Units
• Radio Altimeter (RT – 300)
• Cockpit digital audio panel with remote ICS audio port for ground operation
• PAX audio panel for 1 headset

ADDITIONAL STANDARD EQUIPMENT

• Second radar altimeter system
• Flight plan management system (FPMS) and GPS module with MCDU
• Dual flight director system integrated with MAU
• Steps for passenger cabin access and cockpit access
• Rotor brake
• ELT
• Air conditioning and heating
• EAPS- Engine Air Particle Separator
• Slope Operation Envelope Extension to 10º
• Cargo hook and cargo camera provision
• Aux Fuel Tank

INTERIOR

• Standard cabin and cockpit liners with soundproofing
• Pilot/Co-pilot crashworthy seats
• 12 padded crashworthy utility passenger seats
• Windshield wipers
• Steps for cabin access
• Pilot steps for cockpit access