Leonardo AW139

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)

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)

STANDARD INTERIOR
- Pilot and co-pilot crashworthy seats (with inertial reels and safety belts)
- Cockpit dome/storm light
- Cockpit utility lights (2)
- 28 V DC cockpit/cabin power outlet
- Cockpit panel sun-glare shields
- Overhead cockpit windows sun shades
- Fluorescent emergency exit signs
- Cockpit map and data case in central console
- Two flash lights for pilot and co-pilot
- Map and data cases in pilot and co-pilot doors
- ICS panel with plug for one headset (LH side)
- First aid kit

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

ROTORS AND CONTROLS
- Fully articulated Main Rotor (M/R) with five composite blades, five elastomeric bearings and five hydraulic dampers
- Rotating M/R flight controls
- Main rotor hub beanie
- Main dual servo actuators (3)
- Fully articulated Tail Rotor (T/R) with four composite blades, four elastomeric bearings and four elastomeric dampers
- Rotating T/R flight controls
- One T/R dual servo actuator
- Force trim system
- Pilot fixed flight controls (cyclic, collective, anti-torque pedals)
- Co-pilot fixed flight controls (cyclic, collective, anti-torque pedals)
- Dual digital 3-axis linear actuators
- Provision for main rotor tracking (magnetic pick-up)

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

Pratt & Whitney PT6C-67C

Engine #1
S/N: PCE-KB0513
TT: 2,164

Engine #2
S/N: PCE-KB0493
TT: 2,164