H145 Technical Description

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H145Technical Description 2020 HELICOPTERS 145 D-3 20.100.01 E 25 Technical Description The data set forth in this document are general in nature and for information purposes only. For performance data and operating limitations, reference must be made to the approved flight manual and all appropriate documents. This document is the property of Airbus Helicopters ®; no part of it shall be reproduced or transmitted without the express prior written authorization of Airbus Helicopters® and its contents shall not be disclosed. © Airbus Helicopters® 2020 – All rights reserved. 3 Baseline Aircraft Definition GENERAL • Energy absorbing fuselage • Tail boom with fixed horizontal stabilizer and vertical fin with faired-in Fenestron ® • Upper deck with fittings for main gearbox, engines, hydraulic and cooling system • Cowlings for main transmission and engines • Improved engine cowling heat protection • Skid-type landing gear with skid protectors, capable of taking ground-handling wheels • Long boarding steps, LH and RH • Cold weather kit • Built-in maintenance steps and grips • Exterior painting (single color) COCKPIT, CABIN AND CARGO COMPARTMENT • One-level cabin and cargo compartment floor with integrated rails • Two hinged cockpit doors with sliding window • Map case in pilot´s door • Two wide passenger sliding doors with window of push-out type • Two rear hinged clam-shell doors • Longitudinally adjustable energy absorbing pilot and copilot seats with head rest and 4-point safety belts with automatic locking system • Cabin & cockpit boarding grips (LH and RH) • Flight controls (pilot side) • Single pilot instrument panel with glare shield • Interior paneling • Ram-air and electrical ventilating system for cockpit and cabin • Bleed air heating system • Ventilation for avionics deck a • Helmet holder in the cockpit, rotatable • Portable fire extinguisher • Stowage net for first aid kit at the LH rear clam-shell door • 2 flashlights (torches) • Slant console • Center console • Windscreen wiper for pilot and copilot • Door open warning • Pilot‘s and copilot‘s collective control guards b a. If required by final configuration. b. Installed or delivered as loose part depending on final configuration. INSTRUMENTS • Flight Display Subsystem (FDS) composed of 2 smart multifunction displays (6 x 8 inch) providing the following functions: • Flight Navigation Display (FND) format (incl. PFD, FLI, Master list, NAV, RPM, mast moment & fuel indication) • Vehicle Monitoring System (VMS) format (incl. engine, gearbox, hydraulic, fuel, electrical system, RPM and clock indication) • Vehicle Management System (VMS) including: • 2 duplex Aircraft Management Computer (AMC) • Reference sensors: • 3 Attitude and Heading Reference Systems (AHRS) • 2 Air Data sensors (electrically heated pitot tube and static port) • 2 Three Axis Magnetometers (TAM) • Stand-by instruments: • Integrated Electronic Standby Instrument (IESI) • Stand-by compass • Usage Monitoring System (UMS) • „One hundred feet“ alert • Directional Gyro Free Steering Mode • Warning unit: • Engine fire warning with fuel emergency shut-off • Warning lights • Fire extinguishing system warning • Cockpit Control Panel (CCP) for FDS • Wireless Airborne Communication Server (wACS) • Engine switch panel: • Digital engine control (FADEC) • Radar altimeter POWER PLANT • Two Safran Helicopter Engines ARRIEL 2E turbine engines with electronic engine control (double channel FADEC) • Crash resistant fuel system with a flexible bladder-type fuel main tank and supply tank (split into two sections) • Two independent oil cooling and lubrication systems of the engines • Fire detection and extinguishing system • Chip detectors with quick-disconnect plugs • Twin-engine OEI-training mode • Automatically controlled variable rotor speed system • Cycle counter • Drain system • Fire walls TRANSMISSION SYSTEM • Main transmission including an independent redundant lubrication system and monitoring sensors • Chip detector system with quick-disconnect plug (main transmission) • Free wheel assemblies in the engine input drives • Rotor brake system • Tail rotor transmission system with splash lubrication and oil level sight gauge • Chip detector system with quick-disconnect plug (tail rotor gearbox) 26 145 D-3 20.100.01 E The data set forth in this document are general in nature and for information purposes only. For performance data and operating limitations, reference must be made to the approved flight manual and all appropriate documents. This document is the property of Airbus Helicopters ®; no part of it shall be reproduced or transmitted without the express prior written authorization of Airbus Helicopters® and its contents shall not be disclosed. © Airbus Helicopters ® 2020 – All rights reserved. Technical Description ROTOR AND FLIGHT CONTROLS • Bearingless Main Rotor system (BMR), consisting of: • Rotor head / mast in one piece • Five glass and carbon fiber reinforced blades with erosion protection strip, control cuff, detachable outer blade, elastomeric lead-lag dampers • Fenestron ® -type tail rotor with ten composite blades (asymmetric blade spacing) and stator • Tail rotor gearbox cover • Basic provisions for an easy integration of a track and balance system • Dual hydraulic boost system for cyclic and collective blade control of the main rotor • Tail rotor control system with flexball cable and dual hydraulic booster • Main rotor blade tip painting (yellow) • Vector Mast Moment System (VMMS) • Dual Duplex 4-axis Digital Automatic Flight Control System including upper modes • Electrical hydraulic pump for main rotor ELECTRICAL INSTALLATION • Power generation system: • Two starter/generators (2 x 200 A, 28 VDC) • Nickel-Cadmium battery, (24 VDC, 40 Ah) • External power connector (STANAG 3302) • Power distribution system: • Two main busbars • Two essential busbars • Two shedding busbars • Two non-essential busbars (80 A) for optional equipment only • Battery bus