GENERAL   EQUIPMENT   INC.                    

BRAND NEW 2018 LEONARDO AW-189 OFFSHORE VERSION delivery in 6 months.

1 AW189 STANDARD CONFIGURATION

1.1 AW189 BASELINE AIRCRAFT

1.1.1 Airframe

− Aluminium alloy and composite airframe structure including nose radome, cockpit, main cabin with flat floor and baggage compartment, tail boom, vertical fin, horizontal stabilizers, fuel tank housing

− Attachments for main gearbox and engines / APU

− Upper deck cowlings (one front forward sliding, one aft/rear, two side opening for engines access usable as maintenance platforms)

− Maintenance step for access to upper deck (LH)

− Landing gear attachments and wheeled retractable tricycle landing gear with two wheels on nose gear, one wheel with brakes on main landing gear and mooring rings

− Wheel brake parking electric module (WBPEM)

− Two Heated Pitot tubes

− Two Heated static intakes

− Forced fan ventilation

− Bleed air heater and defroster with air noise suppression

− Cockpit air adjustable outlets

− Cockpit instrument panel, overhead panel and interseat console

− Cockpit acrylic windshields

− Pilot and Co-pilot windshield wipers

− Overhead cockpit windows

− Lower cockpit windows

− Two pilot doors with emergency exit windows and "storm window" on Pilot side (RH)

− Lower Pilot/Co-pilot doors window

− Two plugs in sliding doors for passengers cabin access

− Eight cabin emergency exit windows (two on each passenger cabin door)

− Baggage compartment with 2 lockable baggage compartment doors, LH & RH side

− Baggage compartment cargo tie-down fittings

− Anti corrosion protection

1.1.2 Rotors and Controls

− Fully articulated Main Rotor (M/R) system with five composite blades, five composite tension links, five elastomeric bearings and five hydraulic dampers

− Fully articulated Tail Rotor (T/R) system with four composite blades, four elastomeric bearings and four elastomeric dampers

− Rotating M/R and T/R flight controls with elastomeric bearings

− Pilot fixed flight controls (cyclic, collective, anti-torque pedals)

− Co-pilot fixed flight controls (cyclic, collective, anti-torque pedals)

− Force trim system

− Four parallel trim actuators (4-axis autopilot)

− Two dual digital linear actuators

1.1.3 Power Plant and Fuel System

− Two General Electric GE CT7-2E1 turboshaft engines with integrated particle separator

− One Microturbo E APU 60 Auxiliary Power Unit (usable as emergency electrical generator in flight)

− Anti-ice engine heated air intakes system

− Three anti icing fuel systems and three magnetic chip detectors (one on each engine and APU)

− Three fuel filters assemblies (one for each engine and for APU)

− Two independent dual-channel FADEC systems (one on each engine) with auto-start, auto relight, engine control functions for normal, emergency and training operations

− Engines Control Panel

− One Electronic Engine Control Unit for APU

− Engine bay group (engines and APU mounts, firewalls, cowlings, drains, exhausts)

− Fire detection system (engines and APU)

− Fire extinguisher system (one bottle for each engine compartment and one independent bottle for APU compartment)

− One Fire detection and extinguisher control panel

− Two Crashworthy fuel cells (1043 kg - 2299 lb / 1304 l - 344 US Gallons)

− Filler port for gravity refueling on LH side

− Two supply pumps on engines

− Two booster pumps submerged in fuel tanks

− Engine cross-feed valves

1.1.4 Transmission drive system and hydraulic system

− Main transmission gearbox with two direct drive engine inputs, lubrication system with oil ducts integrated in the casing and oil cooling system

− Three main transmission chip detectors/debris collectors with burning capability

− Intermediate gearbox with sight gauge and magnetic drain plug/chip detector with burning capability

− Tail gearbox with sight gauge and magnetic drain plug/chip detector with burning capability

− Dual independent, redundant hydraulic systems

− Two hydraulic power control modules

− Three main transmission driven hydraulic mechanical pumps for controls and wheel brake actuation

− One electric motor driven hydraulic pump

− Three Main Rotor dual servo actuators

− One Tail Rotor servo actuator with Stability and Command Augmentation System

− One T/R actuator shut off valve

1.1.5 Electrical Systems

− DC / AC primary power generation system: 28 V DC / 115 V AC 400 Hz provided by three independent 25kVA Starter Generators (one for each engine and for APU)

− Two Starter Generator Converter Units

− One Generator Control Unit (GCU) for APU

− Three Transformer Rectifier Units (TRU)

− One battery (17 Ah)

− 28 V DC External Power Receptacle

− 115 V AC External Power Receptacle

− DC Power Distribution System

− AC Power Distribution System

− Solid-State Secondary DC Power Distribution System

− Display based Virtual Circuit Breaker Panel

− Reduced Overhead Circuit Breaker Panel

1.1.6 Lighting System

− Internal Lighting

• Instrument cockpit panel lighting

• Inter seat cockpit console lighting

• Overhead cockpit console lighting

• One cockpit dome light

• Two cockpit utility lights

• Two cockpit storm lights

• Three baggage compartment lights

− External Lighting

• One anti-collision light (tail fin)

• Navigation lights (red, white, green)

• Two retractable swivelling landing/taxiing lights

• Two external emergency lights on undercarriage cowlings

1.1.7 Standard Avionics Package

− Cockpit Display System (CDS)

• Four colour AMLCD Rockwell Collins Display Units 10" x 8" (internal dimensions) with LED backlight and NVIS compatibility, two normally used as Primary Flight Displays (PFD) and two used as Multi Function Displays (MFD)

• One Integrated Standby Instrument System (ISIS)

• Two Display Control Panels (DCP)

• Two Cursor Control Devices (CCD)

• One Reversionary Control Panel (RCP)

• One Display Dimming Panel (DDP)

• Two Master Caution Lights (MCL)

• Two Master Warning Lights (MWL)

• Two Avionics Full Duplex Ethernet switches (AFDX)

•  Aircraft Monitoring and Management System (AMMS)

• Two Aircraft Monitoring & Management Computers (AMMC)

• One Data Transfer Device (DTD)

• Two Multipurpose Control Display Units (MCDU)

− Four Axis Automatic Flight Control System (AFCS)

• One dual Flight Control Computer (FCC)

• One Flight Control System (FCS) Control Panel

− Radio Comm and Navigation System

• Two VHF-AM radios

• Two NAV (VOR/ILS/MB) receivers

• One Automatic Direction Finder (ADF)

• One Distance Measurement Equipment (DME)

• One Transponder with Enhanced Surveillance Mode (Mode S)

• One Satellite Base Augmentation System (SBAS) GPS (WAAS/EGNOS/MSAS)

− Interphone Communication System

• Two Audio Control Panels (ACP) (Pilot and Co-pilot stations)

• One Audio Management Unit (AMU) interfacing external transceivers

• One Passenger Intercom Amplifier (PIA)

− Primary Flight Instruments

• Two flux valves

• Two Attitude Heading Reference Systems (AHRS)

• Two Air Data Systems (ADS)

• One Radar Altimeter

• Two clocks

• One standby magnetic compass

− Aircraft Plants Control Integrated System

• Two Aircraft Plants Control Computers

• Two Aircraft Plants Control Display

1.1.8 Interior

− Cockpit compartment utility finishing interior

− Two cockpit panel sun-glare shields

− Pilot and Co-pilot crashworthy adjustable seats (with inertial reels and separate 5 points safety belts)

− Pilot and Co-pilot headsets

− 28V DC cockpit/cabin power outlet (interseat console)

− Interseat console extension

− Baggage compartment utility finishing interior (carbon-fibre and soft liner)

− Baggage smoke sensor

− Baggage compartment net

1.1.9 Painting

− Standard colour scheme from company, solid colour

1.2 ADDITIONAL BASELINE EQUIPMENT

− Two steps for cockpit and cabin access (on both fuselage side)

− Main rotor hub beanie

− Rotor brake system

− Provision for main rotor blade tracking (magnetic pick-up)

− 2nd radar altimeter

− 2nd anti-collision light

− 2nd GPS

− One solid state Cockpit and Voice Flight Data Recorder (CVFDR) with ULB

− One Emergency Locator Transmitter (ELT - 3 frequencies) (fixed)

− Overhead cockpit windows sun shades

− First aid kit (EU OPS 3 compliant)

− Two fire extinguishers (cockpit and cabin - EU OPS 3 compliant)

− Pilot and Co-pilot headset hooks (overhead)

− One Rotorcraft Flight Manual (RFM) holder (cockpit)

− Rotorcraft Flight Manual and Quick Reference Handbook

− Two portable flashlights (cockpit)

− Nose landing gear bay protection

− Protection for baggage compartment edge

− Baggage compartment net provision with rings on the ceiling

− Back-up battery

− Maintenance step (RH side)

1.3 ADDITIONAL NAVIGATION AND FLEET MANAGEMENT SYSTEMS

− ADS-B out (Automatic Dependent Surveillance – Broadcast)

− Health and Usage Monitoring System (HUMS)

− Flight Data Monitoring (FDM)

− Helicopter Terrain Avoidance & Warning System (HTAWS)

1.4 MISCELLANEOUS / GROUND EQUIPMENT

− Covers and flags for engines air intake and exhaust, APU air intake and exhaust and Pitot probe and connectors

− Five tie-down assemblies for main rotor blades

− One main rotor blades sock pole

− One tail rotor blades flapping block

− Two main landing gear wheel chocks

− Main rotor balance and tracking chart, tail rotor balance chart

− One nose landing gear center pin and one landing gear handle locking pin

− Jacking dome assy

− One tow bar

− One loose equipment bag

2 CUSTOMER REQUIRED CONFIGURATION

2.1 INTERIOR EQUIPMENT – CABIN

− Standard Offshore - 16 PAX

− 16-padded crashworthy comfortable seats (width 16 inches) fabric covered (with inertial reels and separate 4 points safety belts)

− Rigid liners with Passenger cabin ambient lights, reading lights, emergency lights, emergency exit signs, ventilation/AC outlets, passenger advisory lights (no smoking / safety belt chimes) and Passenger Addressing Loudspeakers

− Soundproofing

− ICS panel with plug for one headset and call button

− Floor provisions for multiple-seats layout configuration

− Environmental Control System (ECS) - Air Conditioning

− Safety card holders

− Two cabin vertical handles (both side)

2.2 INTERIOR EQUIPMENT – COCKPIT

− Windshield washing system

− Co-pilot hinged window (storm window)

− Approach plates chart holders with lights for Pilot and Co-pilot. (Required for single pilot IFR operations)

− Pilot and Co-pilot heated glass windshield

2.3 AVIONICS EQUIPMENT

− ADELT with GPS NAV interface and GPS integrated (in lieu of standard ELT)

− TCAS II (Rockwell Collins)

− Weather Radar (Telephonics RDR1600) - Provision

− Weather Radar (Telephonics RDR1600) – Removable

2.4 UTILITY EQUIPMENT

− Camera on the tail fin

− Maritime protection

− High Capacity Baggage Compartment - Nominal

− Emergency Floats - Provision

− Emergency Floats with Rigid covers - Removable

− Helicopter Emergency Exit Light System (HEELS)

− Life jacket with survivor locator light (Qty. 16)

− Life jacket stowage under seat (Qty. 16)

- Pilot and co-pilot life jacket with survivor locator light (with pockets)

− External Life Rafts (2x21) - Provision

− External Life Rafts (2x21) - Removable (including PLB JTSO-126 Standard)

− Strobe lights on the winglets

− Auxiliary fuel tank "Under Floor" - Provision

− Auxiliary fuel tank "Under Floor" - Removable (190 kg - 419lb / 238 l - 63 US Gallons)

− Auxiliary fuel tank "Transversal" - Provision

− Auxiliary fuel tank "Transversal" - Removable (418 kg - 922 lb / 522 l - 138 US Gallons)

2.5 MISSION EQUIPMENT

− Increased Gross Weight - 8,600 kg

2.6 FINISHING – PAINTING

− AgustaWestland painting scheme, metallic colour from Company selection

− Main and tail rotor high visibility painting