manufacturer
Leonardo
configuration
Utility
condition
Used
year
2004
time
3477
helicopter location
Kyrgyzstan
serial number
31010
registration number
HB-ZGC
listing ID
HT12313
Description
HIGHLIGHTS
DEAL PENDING
One Owner Since New
Dual Pilot IFR Cockpit
12 Passenger Layout
4-Axis DAFCS
avionics
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 panels with remote ICS audio port for ground operation
-PAX audio panel for 1 headset
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
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
equipment
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
general characteristics
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
