H135 Technical Description

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H135Technical Description 2020 HELICOPTERS Techni calDescri pti on 135 T3H/P3H 20.100.01 E 23 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 3 Baseline Aircraft Definition GENERAL • Energy absorbing fuselage • Tail boom with fixed horizontal stabilizer • Vertical fin with faired-in Fenestron • Upper deck with fittings for main gearbox, engines, hydraulic and cooling system • Cowlings for main transmission and engine • Skid-type landing gear with skid protectors, capable of taking ground-handling wheels • Long boarding steps, LH and RH • Maintenance built-in steps and grips • Exterior painting (single color) COCKPIT, CABIN AND CARGO COMPARTMENT • One-level cabin and cargo compartment floor with integrated rails • Glazed canopy • Two hinged cockpit doors with sliding window • Map case in pilot's door • Two wide passenger sliding doors • 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 boarding grips LH and RH • Interior paneling with integrated basic sound insulation • Flight controls for pilot side; fixed provisions of flight controls for copilot side • Covers for copilot collective lever, cyclic stick and pedals • Engine controls with manual engine back-up system at pilot's collective pitch lever • Single pilot instrument panel with glare shield and slant console • Ram-air and electrical ventilating system for cockpit and cabin • Helmet holder in the cockpit • Headset holder in the cabin • Portable fire extinguisher • Stowage net for first aid kit at the LH rear clam-shell door • Flash light (torch) for pilot side INSTRUMENTS • Flight Display Subsystem (FDS) composed of 2 smart multifunction displays (6 x 8 inch) providing the following functions: • Flight and Navigation Display (FND) format (incl. PFD, FLI, Master List, NAV, RPM, mast moment & fuel indication) • Vehicle Management System (VMS) format (incl. engine, gearbox, fuel, electrical system, RPM & clock indication) • Vehicle Management System (VMS) including: • 2 duplex Aircraft Management Computer (AMC) • Reference sensors: • 1 Attitude and Heading Reference System • Air Data sensor pilot side (electrically heated pitot tube and static port) • 1 Magnetometer • Standby instruments: • Integrated Electronic Standby Instrument (IESI) • Standby compass • Usage Monitoring System (UMS) • Flight Data Continuous Recorder (FDCR) • "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 • Data Transfer Device (DTD) • Engine switch panel POWER PLANT • Two Pratt & Whitney Canada PW206B3 turbine engines or two Safran Helicopter Engines ARRIUS 2B2 plus turbine engines These two engines are equipped with: • Fire detectors • Full Authority Digital Engine Control (FADEC) • Chip detectors with quick-disconnect plugs • Overspeed protection system • Cycle indication on FDS • Twin-engine OEI-training mode • Oil cooling and lubricating system with thermostatic valve • Crash resistant fuel system with a flexible bladder-type main tank and supply tank (split into two sections) • Automatically controlled variable rotor speed system • Fuel tank filler flap, lockable • Drain system • Fire walls TRANSMISSION SYSTEM • Flat-shaped main gearbox with two stages • Chip detector system with quick-disconnect plug (main gearbox) • Redundant oil cooling and lubrication system • Main gearbox attachment with Anti-Resonance Isolation System (ARIS) • Free wheel assemblies in the engine input drives • Tail rotor drive shaft • Tail rotor gearbox with splash lubrication and oil level sight gauge • Chip detector system with quick-disconnect plug (tail rotor gearbox) 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. 24 135 T3H/P3H 20.100.01 E Technical Description ROTOR AND FLIGHT CONTROLS • Bearingless Main Rotor system (BMR) with improved dynamic characteristics, consisting of: • Rotor head / mast in one piece • Four fiber-reinforced composite main rotor blades with anti-erosion strips, control cuff, elastomeric lead-lag dampers and special blade tip painting • Main rotor control system with dual hydraulic boost system • Electrical trim system • Basic provisions for an easy integration of a track and balance system • Fenestron-type tail rotor with ten metal blades (asymmetric blade spacing) and stator • Tail rotor gearbox cover • Tail rotor control system with flexball cable and single hydraulic booster • Digital 3-axis SAS (Stability Augmentation System) • Mast moment system ELECTRICAL INSTALLATION • Two starter / generators (2x200 A, 28 VDC) • Nickel-Cadmium battery, (24 VDC, 27 Ah) • External power connector (STANAG 3302, LN9064, SAE AS 25018, SAE AS 35061) • Power distribution system: • Two primary busbars • Two shedding busbars • Two essential busbars • Two high load busbars (80 A) - for optional equipment only • Two high power busbars (200 A) • Battery bus