Technical Data 2016 Technical Data

Helionix® Technical Data 2016 Technical Data

H135 (Civil Version)

H135M (Military Version) Technical Data

3 Baseline Aircraft Definition

GENERAL

• Energy absorbing fuselage • Cowlings for main transmission and engine • Tail boom with fixed horizontal stabilizer • Skid-type landing gear with skid protectors, capable of • Vertical fin with faired-in Fenestron® taking ground-handling wheels • Upper deck with fittings for main gearbox, engines, • Long boarding steps, LH and RH hydraulic and cooling system • Maintenance built-in steps and grips • Exterior painting (single color)

COCKPIT, CABIN AND CARGO COMPARTMENT

• One-level cabin and cargo compartment floor with • Covers for copilot collective lever & cyclic stick integrated rails • Engine controls with manual engine back-up system at • Glazed canopy pilot's collective pitch lever • Two hinged cockpit doors with sliding window • Instrument panel with extension and glare shield on pilot's • Map case in pilot's door side and slant console • Two wide passenger sliding doors • Ram-air and electrical ventilating system for cockpit and cabin • Two rear hinged clam-shell doors • Headset holder in the cockpit • Longitudinally adjustable energy absorbing pilot and copilot seats with head rest and 4-point safety belts with • Headset holder in the cabin automatic locking system • Portable fire extinguisher • Cabin boarding grips LH and RH • Stowage net for first aid kit at the LH rear clam-shell door • Interior paneling with integrated basic sound insulation • Flash light (torch) for pilot side • Flight controls for pilot side; fixed provisions of flight controls for copilot side

BASIC INSTRUMENTATION

• Flight Display Subsystem (FDS) composed of 2 smart • Usage Monitoring System (UMS) multifunction displays (6 x 8 inch) providing the following • "One hundred feet" alert functions: • Flight Navigation Display (FND) format • Directional Gyro Free Steering Mode • Vehicle Monitoring Display (VMD) format • Warning unit: • Vehicle Management Subsystem (VMS) including: • Engine fire warning with fuel emergency shut-off • 2 duplex Aircraft Management Computer (AMC) • Warning lights • Fire extinguishing system warning • Reference sensors: • 2 Inertial Measurement Units • Cockpit Control Panel (CCP) for FDS • Air Data sensor pilot side (electrically heated pitot tube • Data Transfer Device (DTD) and static port) • Engine switch panel • 1 Magnetometer • Standby instruments: • Integrated Electronic Standby Instrument (IESI) • Standby compass

POWER PLANT

• Two Pratt & Whitney PW206B3 turbine engines or Two • Twin-engine OEI-training mode plus Turbomeca ARRIUS 2B2 turbine engines These two • Oil cooling and lubricating system with thermostatic valve engines are equipped with: • Fire detectors • Crash resistant fuel system with a flexible bladder-type fuel main tank and supply tank (split into two sections) • Full Authority Digital Engine Control (FADEC) • Chip detectors with quick-disconnect plugs • Automatically controlled variable rotor speed system • Overspeed protection system • Fuel tank filler flap, lockable • Cycle indication on FDS • Drain system •Fire walls

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TRANSMISSION SYSTEM

• Flat-shaped main gearbox with two stages • Free wheel assemblies in the engine input drives • Chip detector system with quick-disconnect plug (main • Tail rotor drive shaft gearbox) • Tail rotor gearbox with splash lubrication and oil level sight • Redundant oil cooling and lubrication system gauge • Main gearbox attachment with Anti-Resonance Isolation • Chip detector system with quick-disconnect plug (tail rotor System (ARIS) gearbox)

ROTOR AND FLIGHT CONTROLS

• Bearingless Main Rotor system (BMR) with improved • Basic provisions for an easy integration of a track and dynamic characteristics, consisting of: balance system • Rotor head / mast in one piece • Fenestron®-type tail rotor with ten metal blades • Four fiber-reinforced composite main rotor blades with (asymmetric blade spacing) and stator anti-erosion strips, control cuff, elastomeric lead-lag • Tail rotor gearbox cover dampers and special blade tip painting • Main rotor control system with dual hydraulic boost • Tail rotor control system with flexball cable and single hydraulic booster system • Digital 3-axis SAS (Stability Augmentation System) • Electrical trim system (cyclic) • Mast moment system

ELECTRICAL INSTALLATION

• Two starter / generators (2x200 A, 28 VDC) • One utility receptacle in LH side of cargo compartment • Nickel-Cadmium battery, (24 V, 27 Ah) (28 VDC, 10 A) • External power connector (STANAG 3302, LN9064, SAE • Lighting: AS 25018, SAE AS 35061) • Anti-collision warning light (red flashing), LED • Power distribution system: • Fixed, nose-mounted landing light • Two primary busbars • Three position lights (red, green, white), LED • Two shedding busbars • Adjustable instrument lighting • Two essential busbars • One utility light in the cockpit • Two high load busbars (80 A) - for optional equipment • 5 spot-lights in the cabin only • One light in cargo compartment RH side • Two high power busbars (200 A) • Radio: • Battery bus • Two radio master switches

GROUND HANDLING KITa

• Two ground-handling wheels • Fuel tank drain device • Basic aircraft covers (short term) • Keys for cockpit doors, cabin doors, baggage • Main rotor blade tie-down lash bags compartment doors and tank flap (one-key system) • Oil drain kit • Battery key • Lifting points

a. Weight not included in the standard helicopter empty weight.

DOCUMENTATION (in English)

• One Flight Manualab (on paper) • List of Applicable Publications (LOAP)a online via ® • One Pilots Checklistc (on paper) KEYCOPTER portal e • One Master Minimum Equipment List (MMEL)a online via • One Avionics Manual (for avionics installed by Airbus T.I.P.I. Helicopters) (on CD-ROM) c • One Logbook (on paper, CD-ROM on demand) • One ECMM (Electronic Component Maintenance Manuals) for vendor manuals • One Historical Record (on paper, CD-ROM on demand) • One Engine Documentationf (format depends on engine • Technical Documentationad incl. AMM, SDS, WDM, IPC, ® manufacturer), furnished by supplier, including: MSM, CECG, SRM online via KEYCOPTER portal • Maintenance Manual • Service Bulletin Catalogue (SB) online via T.I.P.I. • Illustrated Parts Catalogue

a. Revision service included as long as the aircraft is operational b. One Flight Manual included in the standard helicopter empty weight c. Revision service for 3 years d. Customized AMM, SDS, WDM and IPC versions available on request e. Customized documentation f. Revision service for 5 years for TM, 2 years for PWC

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The data set forth in this document is general in nature and for information purposes only. For performance data and operating limitations, reference shall be made to the approved flight manual and all appropriate documents. This document is the property of Airbus Helicopters®; it, as well as the information it contains, shall not be disclosed to third parties and/or reproduced in whole or in part, without express prior written authorisation of Airbus Helicopters®. © Airbus Helicopters® 2016 – All rights reserved. © AIRBUS HELICOPTERS, Aeroport International Marseille Provence - 13725 Marignane Cedex - France 2016 - All rights reserved Airbus Helicopters’ logo and the names of its products and services are registered trademarks. Airbus Helicopters reserves the right to make configuration and data changes at any time without notice. The facts and figures contained in this document and expressed in good faith do not constitute any offer or contract with Airbus Helicopters.

135T3H/P3H 16.100.01 E