2004 Agusta AW139 for sale, Kyrgyzstan

Agusta AW139 Exterior
Agusta AW139 Exterior
Agusta AW139 Exterior
Agusta AW139 Interior
Agusta AW139 Interior
Agusta AW139 Cockpit
Agusta AW139 Avionics
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Asia, Kyrgyzstan

Aircraft Description


  • One Owner Since New
  • Dual Pilot IFR Cockpit
  • 12 Passenger Layout
  • 4-Axis DAFCS

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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


Pratt & Whitney Canada PT6C-67C

Engine 1
S/N: PCE-KB0073
TSN: 2665

Engine 2
S/N: PCE-KB0119
TSN: 3018
    -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. 1 VHF Comm - 1 Mode-C diversity transponder
    2. 1 VOR/LOC/GS/MB
    3. 1 ADF
    4. 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

    -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

    -Microphone and headset (2)
    -Interphone control (cyclic grip and floor switches) (2)
    -Stand-alone VHF/AM radio equipment
    -Intercommunication control panel
    -Primus Epic HF 1050 long-range system
  • Interior & Entertainment
    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
  • Additional Equipment & Information
    -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
    -Air conditioning and heating
    -EAPS - Engine Air Particle Separator
    -Slope Operation Envelope Extension to 10º
    -Cargo hook and cargo camera provision
    -Aux Fuel Tank

    -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)

    -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)

    -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

    -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
    -Engine exhausts and ejectors
    -Two independent crashworthy fuel cells
    -Pumps on engines (2) and submerged in fuel tanks (2)
    -Fuel filter assembly

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