2009 Agusta AW139

General

Manufacturer

AGUSTA

Model

AW139

Serial Number

31239

Registration #

F-HHJM

Condition

Used

Airframe

Total time

2,164

• 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

• 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
• 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

• 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

Avionics

• 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)

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)

- 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)

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

Engine 1

Engine 1 Make/Model

PRATT & WHITNEY PT6C-67C

Engine 1 Serial Number

PCE-KB0513

Engine 1 Time

2,164 SNEW

Engine 2

Engine 2 Make/Model

PRATT & WHITNEY PT6C-67C

Engine 2 Serial Number

PCE-KB0493

Engine 2 Time

2,164 SNEW

Registration

Registration

F-HHJM

Registered as

Agusta S.P.A. AW139

Serial number

31239

Accidents and incidents

None on record