2015 Airbus H130

Details

The helicopter in the definition, presented hereafter, meets the certification standards for day and night VFR operations, set by the following airworthiness authorities: EASA. FAA, TCCA, ANAC, CAAC, IAC-AR. This list is not restrictive and the status of approval by other airworthiness authorities must be checked. Additional equipment item may be required by the relevant operational or certification regulation (most of them are available in catalogue).

General

• The EC130 T2® is certified with a pilot being on the left side
• The baseline aircraft is delivered with left side controls and capabilities for the removable dual controls (copilot controls are optional)
• Anti-Vibration Control System with 1 controller, actuators and accelerometers
• Fuselage comprising the cabin and 3 luggage holds, with floor tie-down nets and access doors
• Tail boom with stabilizer. FENESTRON® type anti torque rotor and tail skid
• Tubular skid landing gear, with replaceable skid shoes with long footsteps (on right and on left side), profiler on rear tube. capable of taking handling wheels
• Lifting points
• Mooring fixtures
• Single colour exterior painting
• Internal paint: light grey (prevailing colour)
• Interior signs and markings: available in either French or English

Cockpit / Cabin

• Cabin floor in light-alloy sheet-metal
• 1 pilot high-back energy-absorbing seat, adjustable in reach, removable, complete with cushions, safety belts and shoulder harnesses
• 6 passengers high-back energy-absorbing seats, removable, complete with cushions safety belts and shoulder harnesses:
• 2 front right, including for 1 copilot (copilot controls are optional)
• 4 rear row
• 2 cockpit jettisonable hinged doors
• 1 LH front door fitted with a sliding window
• 1 RH front door compatible with 8 seat layout
• 1 LH rear sliding door
• 1 RH rear sliding door
• Locks on every access to cabin and luggage compartments
• Lock on fuel cap
• Lateral and upper tinted windows (windscreen excluded)
• 1 ceiling housing the cabin lighting, 7 air ventilation outlets and controls (rotor brake and fuel cut-off)
• Dynamic ventilation system
• Cabin heating
• Demisting system for front windscreens
• 2 pilot document holders
• Door map case in LH and RH front doors
• Rear bulkhead and lateral rear upholstery
• 1 fire-extinguisher
• 1 Flight Manual available in either French or English
• Interior harmony according to definition in force

Instruments

• 1 airspeed indicator
• 1 altimeter
• 1 vertical speed indicator
• 1 LCD rotor and free turbine dual indicator
• 1 stop watch
• 1 warning panel
• 1 magnetic compass
• 1 heated pilot head
• 1 external side slip indicator
• 1 control box for light and electrical generation
• 1 ICS connection to audio warning it.sued from VEMD®
• 1 cockpit imaging and flight data monitoring device
• 1 LCD dual screen Vehicle and Engine Multifunction Display (VEMD) providing the following information:
  • First Umit Indicators (FLI)
  • torquemeter
  • exhaust gas temperature (TOT)
  • gas generator tachometer (N1)
  • Engine oil temperature, pressure
  • Fuel quantity
  • Fuel flow and estimated remaining time to fly
  • Ammeter and voltmeter and battery temperature
  • Outside Air Temperature (OAT)
  • Enhanced usage monitoring functions
  • IGE/OGE performance calculations
  • engine cycles counting
  • engine power check
  • overlimits display
  • VEMD and peripheral maintenance information
  • Data downloading capability (software and connection wire as option)

AVIONICS

• 1 avionics master switch
• 1 gyro-horizon
• 1 gyro-compass with 1 Horizontal Situation Indicator
• 1 turn and bank indicator
• 1 VHF/VOR/LOC/GS
• 1 VHF/VOR/LOC/GS/GPS
• 1 transponder (mode S)
• 1 altitude encoder
• 1 Emergency Locator Transmitter
• 1 ICS + passenger interphone

POWER PLANT

• 1 Turbomeca ARRIEL 20 turbine engine complete with starting, fuel supply and dual channel digital engine control system (FADEC) and 1 back-up fuel control box that automatically controls the engine in case of a total failure of the 2 digital channels of the FADEC
• 1 crashworthy fuel system including
• 1 tank of 540 liters (143 US gal.) total capacity
• 1 twist grip on pilot side (for engine reduction in case of tan rotor failure and autorotation training)
• 1 magnetic plug and 1 chip detector
• 1 engine lubrication and oil cooling system
• 1 fire detection system
• 1 air-intake protection grids
• 1 torque-measurement pick-up

TRANSMISSION SYSTEM

• 1 main gearbox, anti-vibration mounted, with oil sight gauge, chip detector. oil temperature and pressure switches, port for endoscope and self sealing valve for oil sampling and draining
• 1 main gearbox oil cooling system
• 1 engine to main gearbox coupling shaft
• 1rotor brake
• 1 main rotor high and low r.p.m. warning device
• 1 tail drive carried by five anti-friction bearings
• 1 tail gearbox with oil sight gauge, chip detector and port for endoscopic inspection

ROTORS AND FLIGHT CONTROLS

• 1 main rotor with 3 composite-material blades around 3 STARFLEX® head fitted with spherical thrust bearings
• 1 anti-torque rotor (FENESTRONJ with 10 asymmetrical blades, integrated in vertical fin)
• 3 main rotor hydraulic servo units (duplex servos)
• Integrated back-up control valve on each body of each duplex servo

HYDRAULIC GENERATION

• 2 independent hydraulic systems feeding the duplex servos

ELECTRICAL INSTALLATION

• One 150 A. 28 VDC starter-generator
• One 15 A.h cadmium-nickel battery
• 1 ground power receptacle
• 3 position lights (LED)
• 1 flashing anti- collision light (lED)
• 2 fixed landing lights
• 2 cabin light sets, each with 2 reading lights for 2 rear passengers and 1 dome light
• 1 integrated instrument panel lighting system Integrated lighting in central console
• 1 reading map light on upper canopy strut for pilot
• 1 cockpit breaker panel
• One 28 V DC cabin power outlet

AIRBORNE KIT (1)

• 1 pilot head cover
• 2 static port stoppers
• 1 engine air-intake blanking cover
• 1 exhaust pipe blank
• 2 ground handling bogies
• 1 cargo net and rope
• 1 lifting ring
• 2 upper mooring rings
• 3 main-blade socks and pole
• 1 document holder
• 1 airborne kit stowage bag
• 1 front air-intake blanking cover
• 1 fuel tank bleeding
• 3 ballast plates

CONFIGURATION

• Basic aircraft components:
  • EC130 T2 Baseline Aircraft as per 130 T2 15.1 00.02.E, and including:
    • VEMD
    • NR & NTL indicator
    • Control Warning Panel
    • Altimeter
    • Air Speed indicator
    • Vertical Speed Indicator
    • External side slip indicator
    • Stop watch
    • Magnetic Compass
    • Cockpit camera
• Avionics
  • VFR day and night package, included in baseline definition:
    • Emergency locator transmitter- Kannad INTEGRA AP-H
    • VHFNOR/LOC/GS- Garmin GNC 255A Intercom system (ICS) - Garmin GMA 35
    • Transponder (mode S) - Garmin GTX 33H
    • VHFNOR/LOC/GS/GPS - Garmin GTN 750H
    • Gyro-horizon Thales H 321 EGM
    • Gyro Compass Honeywell KCS 55A with Horizontal Situation Indicator Honeywell Kl 525A
    • Altitude encoder- Trans-cal
    • Turn and Bank indicator Ul 9560

OPTIONAL EQUIPMENT

• General Equipment
  • Engine flushing device without removal of cowlings
  • Heavy duty blade pins
  • Tinted windows for front windscreens
  • Sun protected upper windows
  • Enhanced air conditioning system
• Specific mission equipment
  • Landing light adjustable in site and azimuth
  • Emergency floatation gear- Fixed Parts
  • Emergency floatation gear- Removable Parts
  • Additional ballast plates in tail boom
• Interior Layout
  • Cabin carpet for 7 seats layout
• Avionics
  • Radio altimeter Thales AHV16, instead of turn and bank indicator Ul9560
  • Stand-by gyro horizon Thales H321 EGM