Technical Data

Contents
1 Foreword .......................................................................................................................................... 5
2 General characteristics .................................................................................................................... 9
2.1 External dimensions.................................................................................................................. 9
2.2 Internal dimensions ................................................................................................................. 10
2.3 Possible cabin arrangement (seats & equipment as option) .................................................. 10
2.4 Weight ..................................................................................................................................... 11
2.5 Fuel capacities ........................................................................................................................ 11
2.6 Engines ................................................................................................................................... 11
2.7 Main transmission ratings ....................................................................................................... 12
3 Standard aircraft definition ............................................................................................................. 13
4 Basic configuration choice ............................................................................................................. 15
4.1 Conventional instrumentation (NVG friendly) Single pilot VFR day / night package .............. 15
4.2 Glass cockpit Instrumentation (NVG friendly) Dual pilot IFR package ................................... 19
4.3 Typical antenna layout ............................................................................................................ 23
5 Mission arrangement...................................................................................................................... 24
5.1 Troop transport........................................................................................................................ 24
5.2 Military equipment: .................................................................................................................. 26
6 Optional equipment ........................................................................................................................ 31
6.1 Further available equipment ................................................................................................... 31
6.2 Avionics................................................................................................................................... 35
6.3 Observation mission ............................................................................................................... 36
7 Main performance .......................................................................................................................... 37

Manufacturer’s notes – Attention!

Eurocopter’s policy is one of on-going product enhancement which means that alterations in
definition, weights, dimensions or performance may be made at any time without notice being
included in those documents that have already been issued.
This document cannot thus be taken as an offer or serve as an appendix to a contract without a
prior check as to its validity and prior written agreement of Eurocopter.
The operational or certification regulations, as defined by the local authorities, can make
compulsory the installation of some of the equipment or recommended solutions, listed in this
document. This list does not claim to cover the whole of the worldwide operational requirements
nor the equipment not specifically related to the helicopter (for example: life jacket) or necessary
for particular missions (for example: supplemental oxygen). The operator is responsible for
ascertaining with his local authorities that the planned configuration of the helicopter complies
with regulatory requirements for the area(s) of operations and the type(s) of mission(s)
considered.
®, ® ®
EUROCOPTER, its logo, M’ARMS FENESTRON and STEADYCONTROL are trade marks of
the Eurocopter group.

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.
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 Technical Data

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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.
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 Technical Data

1 Foreword
The EC635 as a derivation from the EC135 is a light twin-engine, multi-purpose helicopter of the 2-3
ton class with up to 8 seats for pilot/s and passengers. Underlining its multi-role capabilities, it can
even be operated as single pilot IFR (optional). The helicopter combines Eurocopter’s latest
technologies, like advanced cockpit design, modern avionics. The Fenestron® anti-torque-system and
the bearingless main rotor system give the helicopter an outstanding maneuverability. Due to its
extreme simplicity, the rotor system contributes to highest safety aspects and, at the same time,
reduces scheduled maintenance to a minimum. Optimized main rotor blades with advanced tip
geometry in combination with a Fenestron® with unequal blade spacing make the EC635 the quietest
helicopter in its class, bringing it 7 dBA below the ultra-stringent ICAO limit.

The built-in anti resonance isolation system (ARIS) filters rotor-induced vibrations and thus enhances
flying comfort to a maximum. As a result, the vertical vibration level is far below 0.1g at hover with no
increase with speed. In addition to these aspects mentioned above, the rotor system together with
high TBO gearbox and airframe components grant for low maintenance costs, and on the other hand
high in-service-time of the helicopter due to low scheduled maintenance required.

Depending on the operator’s preferences, the EC635 can be equipped with either Arrius 2B2 or Pratt
& Whitney PW206B2 power plants. Both engine types feature full authority digital engine control
(FADEC) with manual engine backup as well as automatic start-up and shut-down. The powerful and
reliable engines in combination with the optimized lifting system of the EC635 provide outstanding
performance and vital power reserves even in one-engine-inoperative scenarios. Twin-engine
reliability is complemented by a fully separated fuel system, a tandem hydraulic system, dual electrical
system and redundant lubrication for the main transmission. Further positive safety aspects of the
EC635 are design elements like energy absorbing fuselage and seats, as well as crash resistant fuel
cells.

A wide range of existing optional supplemented by specialized military equipment is available for the
EC635, as for example different types of armament and military COM/NAV (IFF, HF, etc.). Together
with it’s most versatile cabin layout, the EC635 is ready to be adapted for a wide range of missions,
like utility transport, reconnaissance, armed combat support, CASEVAC, Advanced Tactical Training,
to name a few.

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.
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 Technical Data
Compared to other helicopters in its class, the EC635 offers a significantly larger cabin, featuring:
- excellent outside vision for pilot/s, crew or passengers
- roomy cabin which accommodates long or bulky freight
- unrivalled side loading (no door posts) and rear loading capability
- unobstructed and flat floor all over the cabin area

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.
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 Technical Data
The EC635 is available with a conventional cockpit layout and a glass cockpit layout, which are both
NVG friendly. All LCD screens are well arranged on the instrument panel, easy to read even if viewed
from an angle and feature perfect readability in any light conditions. The unique color coding, warning
and information concept helps the pilot/s to collect all relevant parameters while suppressing
presentation of non-relevant information. Additionally, Eurocopter’s unique first limit indicator (FLI)
dramatically simplifies engine and torque monitoring. Being relieved from the instrument scan without
missing vital information, the pilot/s can dedicate more of his/their attention to the mission.

Apart from the a.m. configuration and upon customer request, Eurocopter can provide any specific
mission suite adapted to the today’s KPPs for ‘NET Ready Interoperability/Network Centric
Operations’ including the relevant communication systems for Army, Air Force, Navy and Joint
Operations.

Typical example for a conventional cockpit layout (NVG friendly) .

Typical example of a glass cockpit layout (NVG friendly)

Latest news / highlights:

New version EC635 P2i or T2i with:
„ Increased maximum take off weight: MTOW: 2.910 kg
„ Increased useful load: 1.443 kg
„ Increased MCP TOP: 2 x 78 %
„ Improved high and hot performances: Service ceiling at 2835 kg, 12,000 ft (+2,000 ft)
HOGE, ISA+20°C at 2835 kg, 5,700 ft (+2,400 ft)
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.
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 Technical Data

Blank

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.
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 Technical Data

2 General characteristics

2.1 External dimensions

* Rotor turning, controls in neutral position

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.
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 Technical Data
2.2 Internal dimensions

Floor area Volume

Cabin & baggage compartment 4.35 m² 46.83 ft² 4.90 m³ 173.04 ft³
Cockpit (pilot side) 1.15 m² 12.38 ft² 1.00 m³ 35.31 ft³
Total (undivided) 5.50 m² 59.21 ft² 5.90 m³ 208.35 ft³

2.3 Possible cabin arrangement (seats & equipment as option)

Troop „ 1 or 2 pilots + 7 or 6 troops (“6 Troop Transport” version)

transport „ 1 or 2 pilots + 6 or 5 passengers (“5 Troop Transport” version)
Medical „ 1 pilot + 1 litter + up to 5 seats for doctor and attendants
evacuation „ 1 pilot + 2 litters + up to 4 seats for doctor and attendant
„ 2 pilots + 1 litter + up to 4 seats for doctor and attendants
„ 2 pilots + 2 litters + up to 3 seats for doctor and attendant
Cargo „ 1 pilot + 4.9 m³ (173.04 ft³) in cabin and cargo compartment
transport
Armed „ 1 pilot + 1 officer in command + 1 observer
Mission „ Gun pods 12.7mm
„ or Rocket launchers 70mm
„ or Cannon pods 20mm
„ or mixed armament configurations

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.
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 Technical Data

2.4 Weight
Note : margin ± 1.5 % kg lb
„ Empty weight, wet (in standard aircraft configuration) 1,467 3,234
„ Useful load (for standard aircraft configuration) 1,443 3,181
„ Pilot 80 176
„ Payload and / or fuel 1,363 3,005
„ Maximum take-off weight 2,910 6,415

2.5 Fuel capacities

Note: Tolerance of fuel figures: ±2% Usable fuel Unusable fuel

Fuel density used is 0.8 kg/liter.
lb kg l lb kg
„ Main tank 1033.0 468.6 585.7 7.5 3.4
„ Supply tank 186.5 84.6 105.8 9.3 4.2
„ Total 1219.5 553.2 691.5 16.8 7.6

2.6 Engines
2 Pratt & Whitney turbine engines – PW206B2
or
2 Turbomeca turbine engines - ARRIUS 2B2

Engine ratings

Thermodynamic limits per engine at SL, ISA kW ch shp

PW206B2
„ One Engine Inoperative (OEI), 30 sec power 609 828 816
„ One Engine Inoperative (OEI), 2.0 min power 580 789 777
„ One Engine Inoperative (OEI), MCP 528 718 708
„ Take-Off Power (TOP) 498 677 667
„ Maximum Continuous Power (MCP) 457 621 612

ARRIUS 2B2
„ One Engine Inoperative (OEI), 30 sec power 609 828 816
„ One Engine Inoperative (OEI), 2.0 min power 580 789 777
„ One Engine Inoperative (OEI), MCP 528 718 708
„ Take-Off Power (TOP) 473 643 634
„ Maximum Continuous Power (MCP) 442 601 592

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.
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 Technical Data

2.7 Main transmission ratings

Single engine operation kW ch shp

„ 30 sec OEI-power 1 x 526 1 x 715 1 x 705
„ 2.0 min OEI-power 1 x 513 1 x 698 1 x 687
„ Maximum Continuous OEI-Power 1 x 368 1 x 501 1 x 493

Twin engine operation

„ Take-Off Power (TOP) 2 x 320 2 x 435 2 x 429
„ Maximum Continuous Power (MCP) 2 x 283 2 x 385 2 x 380

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.
635.06.101.01 E 12
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 Technical Data

3 Standard aircraft definition

GENERAL
ƒ Energy absorbing fuselage ƒ Upper deck with fittings for main gearbox, engines, hydraulic
ƒ Reinforcement of cabin structure for roof mounted and cooling system
equipment ƒ Cowlings for main transmission and engines
ƒ Common kit LH and RH ƒ Skid-type landing gear with skid protectors, capable of taking
ƒ Reinforcement of the LH and RH fuselage side structure ground-handling wheels
with multi-purpose fittings on each side ƒ Long boarding steps, LH and RH
ƒ Tail boom with fixed horizontal stabilizer and two end- ƒ Maintenance built-in steps and grips
plates ƒ Exterior painting (single color STANDOX)
ƒ Vertical fin with faired-in Fenestron®

COCKPIT, CABIN AND CARGO COMPARTMENT

ƒ One-level cabin and cargo compartment floor with ƒ NVG friendly standard cockpit layout
integrated rails ƒ Flight controls (pilot side)
ƒ Checkered cover plates for cable tunnels, LH and RH, in ƒ Engine controls with manual engine back-up system at
the cabin/cargo compartment pilot's collective pitch lever
ƒ Glazed canopy ƒ Instrument panel with extension on pilot's side and glare
ƒ Two hinged cockpit doors with sliding windows shield
ƒ Map case in pilot’s door ƒ Ram-air and electrical ventilating system for cockpit and
ƒ Two wide passenger sliding doors cabin
ƒ Two rear hinged clam-shell doors ƒ Headset holder in the cockpit
ƒ Longitudinally adjustable energy absorbing pilot and copilot ƒ Headset holder in the cabin
seats with head rest and 4-point safety belts with automatic ƒ Portable fire extinguisher
locking system ƒ Stowage net for first aid kit at the LH rear clam-shell door
ƒ Cabin boarding grips (LH and RH) ƒ Flash light (torch)
ƒ Interior paneling with integrated basic sound insulation ƒ 4 Mobile tie-down rings

BASIC INSTRUMENTATION, NVG friendly

ƒ Central Panel Display System (CPDS), consisting of: ƒ Engine cycle counter (on flight report page)
ƒ Caution Advisory Display (CAD) with indication of: ƒ Clock (2”)
ƒ Caution and advisory information ƒ Magnetic compass
ƒ Fuel quantity indication ƒ Triple (rotor and engines) RPM-indicator (2”)
ƒ Vehicle and Engine Management Display (VEMD) with ƒ Standard instruments: (single pilot) 1
indication of: ƒ Encoding altimeter (3")
ƒ Torque ƒ Airspeed indicator (3")
ƒ Engine parameters (N1-RPM (for P&W) or ΔN1-RPM ƒ Vertical speed indicator (3")
(for TM), oil pressure, oil temperature, Turbine Outlet ƒ Warning unit:
Temperature (TOT), engine/FADEC rep EEC failure ƒ Engine fire warning with fuel emergency shut-off
and parameter code messages, self diagnoses) ƒ Warning lights
ƒ FLI (First Limit Indicator) for TQ, TOT, N1 (for P&W) ƒ Aural warning
or ΔN1 (for TM) as analogue display ƒ Main switch panel:
ƒ Main transmission parameters (oil pressure, oil temp.) ƒ DC power control
ƒ Dual ammeter (generator) ƒ Digital engine control (FADEC)
ƒ Ammeter (battery) ƒ Pitot / static system with electrical heated pitot tube, pilot
ƒ Dual voltmeter side
ƒ Outside Air Temperature (OAT) ƒ Static pressure crossover system
ƒ Parameters of optional equipment (e.g. internal long ƒ Air Data Computer
range fuel tank)

POWER PLANT
ƒ Two Pratt & Whitney PW206B2 turbine engines or ƒ Oil cooling and lubricating system with thermostatic valve
Two Turbomeca ARRIUS 2B2 turbine engines ƒ Crash resistant fuel system with a flexible bladder-type fuel
main tank and a self sealing fuel supply tank (split into two
These 2 engines are equipped with:
sections)
ƒ fire detectors
ƒ Automatically controlled variable rotor speed system
ƒ electronic engine control (FADEC-BOX)
ƒ Fuel tank filler flap, lockable
ƒ chip detectors with quick-disconnect plugs
ƒ overspeed protection system
ƒ twin-engine OEI-training mode

1
If glass cockpit instrumentation is chosen as optional equipment, these standard instruments are deleted and an altimeter (2”)
and an airspeed indicator (2”) as back-up instruments are added.
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.
635.06.100.01 E 13
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 Technical Data
TRANSMISSION SYSTEM
ƒ Flat-shaped main gearbox with two stages ƒ Free wheel assemblies in the engine input drives
ƒ Chip detector system with quick-disconnect plug (main ƒ Tail rotor drive shaft
gearbox) ƒ Tail rotor gearbox with splash lubrication and oil level sight
ƒ Redundant oil cooling and lubrication system gauge
ƒ Main gearbox attachment with Anti-Resonance Isolation ƒ Chip detector system with quick-disconnect plug (tail rotor
System (ARIS) gearbox)

ROTOR AND FLIGHT CONTROLS

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

ELECTRICAL INSTALLATION
ƒ Power generation system: ƒ Battery bus
ƒ Two starter/generators (2 x 160 A, 28 VDC) ƒ One utility receptacle in LH side of cargo compartment
ƒ Nickel-Cadmium battery, (24 V, 17 Ah) (28VDC, 15A)
ƒ External power connector (STANAG 3302) ƒ Lighting:
ƒ Power distribution system: ƒ Anti-collision warning light (red flashing); NVG friendly
ƒ Two primary busbars ƒ Three position lights (red, green, white), NVG friendly
ƒ Two shedding busbars ƒ Fixed, nose-mounted landing light (250 W)
ƒ Two essential busbars ƒ Adjustable instrument lighting, NVG friendly
ƒ Two high load busbars (80 A) - for optional equipment ƒ One utility light in the cockpit NVG friendly
ƒ Two high power busbars (200 A) ƒ 5 spot-lights in the cabin NVG friendly
ƒ One light in cargo compartment RH side

2
GROUND HANDLING KIT
ƒ Two ground-handling wheels ƒ Fuel tank drain device
ƒ Basic aircraft covers (short time) ƒ Keys for cockpit doors, cabin doors, baggage compartment
ƒ Main rotor blade tie-down lash bags doors and tank flap (one-key system)
ƒ Oil drain hoses ƒ Battery key
ƒ Lifting points

DOCUMENTATION
3
ƒ One Flight Manual ƒ One Avionics Manual (for avionics installed by
2) 2) 4
ƒ One Pilots-Checklist, revision service for five years Eurocopter) (on paper)
2) 2)
ƒ One Logbook (only paper, CD ROM on demand) ƒ Engine Documentation , furnished by supplier, including:
2)
ƒ One Historical Record (only paper, CD ROM on demand) ƒ Maintenance Manual
2) 3) 4) 4) 4)
ƒ One CD-ROM including AMM , SDS , WDM , IPC, ƒ Illustrated Parts Catalogue (IPC)
MSM ƒ Service Bulletins
3) 2)
ƒ One additional Master Servicing Manual (MSM) on ƒ Weapon delivery manual 2) , furnished by supplier
paper
3) 2)
ƒ One Service Bulletin Catalogue (SB) per contract, on
paper
3) 2)
ƒ One List of Applicable Publications (LOAP) , on paper

2
Weight not included in the standard helicopter empty weight
3
Revision service included as long as the aircraft is operational
4
Customized documentation
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.
635.06.100.01 E 14
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 Technical Data

4 Basic configuration choice

4.1 Conventional instrumentation (NVG friendly)

Single pilot VFR day / night package
4.1.1 Instrument panel overview

Additional space:
A - for 2” back-up airspeed indicator (used in MEGHAS/FCDS “glass cockpit” solutions)
5
B - for 2” standby horizon AI 803 CY
C - for 2” back-up altimeter (used in MEGHAS/FCDS “glass cockpit” solutions)
D - e.g. for 3” RMI
E - e.g. for DME or ELT remote control
G - e.g. for 2nd gyro
M - e.g. for marker lights
R - e.g. for 3” radar altimeter indicator (KNI 416)
S - e.g. for 2nd GPS/COM/NAV GNS430 or other equipment

5
US export authorization needed
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.
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 Technical Data

4.1.2 Content of Avionics Solution conventional VFR NVG friendly

Document Commercial
reference reference Title

- L2300-018-01 Avionics Solution conventional NVG friendly, consisting of

Intercom System
08-16053-A L2341-192-12 Audio / Comm. control system AS 3100-12/13 NVG (Becker), pilot,
incl. Intercom Select Panel (ICS mode selector)
08-16053-A L2341-293-01 Intercom amplifier IC 3100-4 (Becker)

Transponder
08-22026-A L2325-092-13 Transponder (Mode S) GTX 330 - NVG friendly (Garmin)

Radio Switch
08-29003-A L2480-090-01 Avionics / Radio master switches

GPS/NAV/COM
08-43018-B L3442-092-05 GPS / NAV / COM GNS 430 - NVG friendly (Garmin), pilot,
for conventional cockpit

Conventional instruments
6
08-51012-A L3425-092-03 4" artificial horizon GH14-391 - NVG friendly (Honeywell), pilot
08-52013-A L3421-092-05 Gyro magnetic heading system KCS 55 A (Honeywell), pilot
incl. KG-102A, KMT-112, KA-51B with HSI KI-525A NVG friendly 6

Miscellaneous
- L0000-150-18 Avionics solution interconnection / wiring

6
US export authorization needed
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.
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 Technical Data

4.1.3 Minimum required equipment

Minimum required equipment for Avionics Solution conventional, single pilot

Weight
(margin ± 3 %)
Document Commercial
reference reference Title kg lb
05-33001-A L3113-001-00 Slant panel 0.8 1.8
05-33002-A L3113-004-00 Center console 2.3 5.1
05-41004-B L2104-100-00 Bleed air heating system 6.6 14.6
05-44002-A L2122-001-00 Ventilation extruder without copilot I-panel 0.3 0.7
extension
05-61010-A L2433-003-00 Battery, type “Saft”, ULM, 27 Ah, 24 V 8.2 18.1
instead of standard battery
05-62010-B L2420-002-00 AC system (350 VA) 3.2 7.1
05-63003-A L2432-001-00 Starter / generators (2 x 200 A, 28 VDC) 3.6 7.9
instead of standard generators
06-45024-A L3343-006-00 Landing & search light, 400/200 W NVG 6.3 13.9
(only for VFR Night)
- L2300-018-01 Avionics Solution conventional NVG friendly 39.5 87.1

For a dual pilot solution, the following items have to be added:

Weight
(margin ± 3 %)
Document Commercial
reference reference Title kg lb
05-37016-A L6701-001-00 Copilot flight controls 6.0 13.2
05-38010-A L3111-001-00 10" copilot instrument panel with glare shield 2.8 6.2
05-39006-A L2514-003-01 Map case in copilot door 0.5 1.1
08-16053-A L2341-191-12 Audio / Comm. control system AS 3100-12/13 NVG 2.0 4.4
(Becker), copilot
08-51012-A L3425-091-03 4" artificial horizon GH14-391 - NVG friendly 2.5 5.5
(Honeywell), copilot 7
08-60003-A L3412-090-00 Copilot 3" instruments (airspeed indicator, 2.3 5.1
altimeter, vertical speed indicator
(United Instruments) NVG friendly illumination
7
08-61010-A L3166-091-05 RMI KI 229 - NVG friendly (Honeywell), copilot 2.4 5.3
7
08-61011-A L3167-091-05 CDI KI 204 - NVG friendly (Honeywell), copilot 1.3 2.9
Note: the minimum requirement equipment for Cat A certification or JAR OPS are not included.

7
US export authorization needed
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.
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 Technical Data
4.1.4 Possible add-ons

Possible add-ons for Avionics solution conventional NVG friendly

Weight
Document Commercial (margin ± 3 %)
reference reference Title
k lb
05-38010-A L3111-001-00 10” Copilot instrument panel with glare shield, 2.8 6.2
only for single pilot
06-67044-A L2563-801-06 ELT C406-N HM (Artex) incl. NAV. opt. 3.8 8.4
08-16053-A L2341-193-08 Audio / Comm. control system AS 3100-12/13 NVG 2.7 6.0
(Becker), PAX, in cabin ceiling (LH installation)
08-21014-A L3441-090-04 Radar altimeter KRA 405B (Honeywell) 5.6 12.3
L3441-092-04 Radar altimeter indicator KNI 416 - NVG friendly 1.2 2.6
(Honeywell)
08-43018-A L3442-091-05 GPS / NAV / COM GNS 430-NVG friendly (Garmin), 9.5 20.9
copilot, for conventional cockpit
08-51013-A L3425-802-51 2” std-by horizon AI 803 CY (Goodrich), 6.6 14.6
incl. back-up battery 8
08-71002-A L2217-001-10 VFR SAS 8.5 18.7
(VFR pitch/roll Stability Augmentation System)

4.1.5 Further avionics add-ons, see chapter 6 page 35

8
US export authorization needed
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.
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 Technical Data

4.2 Glass cockpit Instrumentation (NVG friendly)

Dual pilot IFR package
4.2.1 Instrument panel overview

Additional space:
V - for Video Radar Unit (brightness control for external video source e.g. moving map, FLIR, weather radar)
S – Additional space for other equipment

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.
635.06.101.01 E 19
This document is the property of EUROCOPTER; no part of it shall be reproduced or transmitted without the express prior written authorization of EUROCOPTER and its contents shall not be disclosed. © eurocopter - 01/2006
 Technical Data

4.2.2 Content of avionics solution glass cockpit, NVG friendly

Document Commercial
reference reference Title

L2300-018-02 Avionics Solution glass cockpit, NVG friendly consisting of

VHF AM
08-11022-A L2313-092-07 VHF AM/COM system VCS-40 A (Chelton/Wulfsberg), pilot
08-11022-A L2313-092-15 (Back-up) Control unit CD 402 B NVG friendly (Chelton/Wulfsberg), pilot
08-11022-A L2313-091-08 VHF AM/COM system VCS-40 A (Chelton/Wulfsberg), copilot
Intercom System
08-16061-A L2341-190-40 Digital Audio Control System - DACS (NAT), incl.
Audio Management Unit AMU50,
Audio Control Panels ACP53 - pilot and copilot
Transponder
08-22027-A L2325-092-06 Transponder (Mode S) MST 67A (Honeywell)
DME
08-25511-A L3455-090-06 DME FLITELINE CDM-451 (Chelton/Wulfsberg)
VOR/ILS/MKR receivers
08-26024-A L3432-092-07 VOR/ILS/MKR navigation system VNS-41 A (Chelton/Wulfsberg), pilot
08-26024-A L3432-092-13 (Back-up) Control unit CD 412 B NVG friendly (Chelton/Wulfsberg), pilot
08-26024-A L3432-091-06 VOR/ILS/MKR navigation system VNS-41 A (Chelton/Wulfsberg), copilot
Radio switch
08-29003-A L2480-090-01 Avionics / Radio master switches
FMS
08-44035-A L3442-022-00 Flight-, Navigation Management System CMA-9000 (CMC Electronics)
08-44035-A L3442-023-00 GPS sensor CMA-3024 (CMC ELECTRONICS), for CMA-9000
Conventional instruments
9
08-51013-A L3425-802-51 2” Stand-by horizon AI 803 CY incl. battery (Goodrich)
Display system
08-65003-A L3161-090-09 MEGHAS - Flight Control Display System (FCDS) - Dual (4xSMD45)
Miscellaneous
- L0000-150-18 Avionics solution interconnection / wiring

Note: the VHF-AM COM (VCS-40A), VHF NAV (VNS-41A), ATC transponder (MST-67A) and the GPS
sensor (CMA-3024) are controlled via CMA-9000

9
US Export authorization needed
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.
635.06.101.01 E 20
This document is the property of EUROCOPTER; no part of it shall be reproduced or transmitted without the express prior written authorization of EUROCOPTER and its contents shall not be disclosed. © eurocopter - 01/2006
 Technical Data

4.2.3 Minimum required equipment

Minimum required equipment for avionics solution glass cockpit NVG friendly

Weight
(margin ± 3 %)
Document Commercial
reference reference Title kg lb
05-33001-A L3113-001-00 Slant panel 0.8 1.8
05-33002-A L3113-004-00 Center console 2.3 5.1
05-34002-A L2576-001-00 Avionics compartment 4.2 9.3
05-37016-A L6701-001-00 Copilot flight controls 6.0 13.2
05-38010-A L3111-001-04 7“ copilot instrument panel with glare shield 2.7 6.0
05-39006-A L2514-003-01 Map case in copilot door 0.5 1.1
05-39007-A L3111-001-10 Map case on instrument panel glare shield 0.6 1.3
05-41004-B L2104-100-00 Bleed air heating system 6.6 14.6
05-61010-A L2433-006-00 Battery, type "Saft", ULM, 40 Ah, 24 V 16.8 37.0
instead of standard battery
05-62010-B L2420-005-00 AC System (50 VA) 10 1.9 4.2
05-63003-A L2432-001-00 Starter / generators (2 x 200 A, 28 VDC) 3.6 7.9
instead of standard generators
06-12008-B L3217-001-00 Reinforced rear landing gear cross tube 1.1 2.4
(standard landing gear only)
06-45023-A L3343-006-00 Landing & search light, 200/400 W, NVG friendly 6.3 13.9
L2300-018-02 Avionics Solution glass cockpit, NVG friendly 96.0 211.6
08-53002-B L2212-400-00 MEGHAS sensor kit 17.8 39.3
08-54001-A L3411-001-00 Copilot pitot static system 1.4 3.1
08-71002-B L2217-001-50 IFR pitch/roll SAS 12.2 26.9

Note: the minimum requirement equipment for Cat A certification or JAR OPS are not included.

ON REQUEST:
- Exchange of 2x SMD45 on copilot side to one SMD68

10
Alternatively the AC system L2420-002-00 (05-62010-B) (350VA; 3.2kg) can be selected
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.
635.06.101.01 E 21
This document is the property of EUROCOPTER; no part of it shall be reproduced or transmitted without the express prior written authorization of EUROCOPTER and its contents shall not be disclosed. © eurocopter - 01/2006
 Technical Data

4.2.4 Possible add-ons

Possible add-ons for Avionics Solution Glass cockpit NVG friendly

Weight
(margin ± 3 %)
Document Commercial
reference reference Title kg lb
06-67044-A L2563-801-06 ELT C406-N HM (Artex) incl. NAV. opt. 3.8 8.4
08-16061-A L2341-193-40 Digital Audio/Comm. control and intercom system 2.0 4.4
DACS (NAT), Audio Control Panel ACP53 - PAX
08-21014-A L3441-090-04 Radar Altimeter KRA 405B (Honeywell) 5.6 12.3
08-24015-A L3452-092-17 ADF system DFS-43A (Chelton/Wulfsberg), 9.6 21.2
controlled via CMA-9000
08-72001-A L2212-001-00 Digital Automatic Flight Control System - DAFCS 27.0 59,6
instead of IFR pitch/roll SAS, (radar altimeter required)
08-81018-A L2321-007-00 M’ARMS Cockpit Voice and Flight Data Recorder 17.3 38.1
(CVFDR), ground station not included (DAFCS
required)
(in combination with UMS: 18.3 kg / 40.3 lb)
08-83007-A L3171-001-00 M’ARMS Usage Monitoring System (UMS), 7.2 15.9
ground station not included (DAFCS required)

4.2.5 Further avionics add-ons, see chapter 6 page 35

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.
635.06.101.01 E 22
This document is the property of EUROCOPTER; no part of it shall be reproduced or transmitted without the express prior written authorization of EUROCOPTER and its contents shall not be disclosed. © eurocopter - 01/2006
 Technical Data
4.3 Typical antenna layout

1– ELT antenna (6 – ADF antenna (if required))

2– VHF2 antenna 7 – Radar altimeter antenna
3– VOR antennas 8 – ATC antenna
4– VHF1 antenna 9 – Marker antenna
5– GPS antenna 10 – DME antenna

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.
635.06.101.01 E 23
This document is the property of EUROCOPTER; no part of it shall be reproduced or transmitted without the express prior written authorization of EUROCOPTER and its contents shall not be disclosed. © eurocopter - 01/2006
 Technical Data

5 Mission arrangement

5.1 Troop transport

5.1.1 Six (6) Troop transport

Weight
This installation is characterized by: (margin ± 3 %)

Document Commercial
reference reference Title kg lb
07-27001-A L2522-001-00 Three (3) forward passenger seats, facing backwards 37.4 82.5

07-27004-A L2522-004-10 Utility seats for 3 rear passengers, fixed provisions 1.2 2.6

07-27004-A L2522-004-20 Utility seats for 3 rear passengers, detachable parts 33.2 73.2

3 rear passenger seats 3 forward passenger seats

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.
635.06.101.01 E 24
This document is the property of EUROCOPTER; no part of it shall be reproduced or transmitted without the express prior written authorization of EUROCOPTER and its contents shall not be disclosed. © eurocopter - 01/2006
 Technical Data

5.1.2 Five (5) Troop transport

Weight
This installation is characterized by: (margin ± 3 %)

Document Commercial
reference reference Title kg lb
07-27001-A L2522-001-00 Three (3) forward passenger seats, facing backwards 37.4 81.6

07-27001-A L2522-002-00 Two (2) rear passenger seats, facing forwards 22.2 49.0

07-60015-A L2514-014-00 Variable tie-down web for luggage securing 4.2 9.3

2 rear passenger seats

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.
635.06.101.01 E 25
This document is the property of EUROCOPTER; no part of it shall be reproduced or transmitted without the express prior written authorization of EUROCOPTER and its contents shall not be disclosed. © eurocopter - 01/2006
 Technical Data

5.2 Military equipment:

5.2.1 Rocket launcher 70mm (2.75”) on each side

Content: Weight
(margin ± 3 %)

Document Commercial
reference reference Title kg lb
11 5)
12 - tube rocket launcher FZ-Herstal FZ321 mod1,cal. 70 mm, 358 790
capacity 12 rockets (twice, one on each side)

Minimum required equipment

Document Commercial
reference reference Title kg lb
07-15016-A L2512-003-10 Height adjustable pilot seat (instead of standard pilot seat) 3.7 8.1

11-90008-A L8580-010-12 Multi-Purpose Armament System (MPAS), basic electrical part 12.0 26.5

11-90004-A L8580-200-00 Reflex Sight T100 incl. control panel and sight support 5.1 11.2

11-90005-A L8580-600-00 Gun & Rocket Control Panel GRMU 3.0 6.6

11-90007-A L8580-100-00 Master Armament Panel MAP 0.75 1.7

11-90008-A L8580-400-00 Automatic/Manual Range Select Panel AMR 0.5 1.1

11-00009-A L8513-001-20 Multi-purpose pylon, RH and LH, detachable parts incl. 25.4 56.0
aerodynamic fairings
11-00010-A L8580-200-00 Light Suspensions 325mm with release unit, LH and RH 35.8 78.9
including cabling, detachable parts

11
Weight of ammunition is included
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.
635.06.101.01 E 26
This document is the property of EUROCOPTER; no part of it shall be reproduced or transmitted without the express prior written authorization of EUROCOPTER and its contents shall not be disclosed. © eurocopter - 01/2006
 Technical Data
5.2.2 20 mm cannon pod on each side

Content: Weight
(margin ± 3 %)

Document Commercial
reference reference Title kg lb
12 )
Cannon pod GIAT NC621 cal. 20 mm, capacity 180 rounds 360 794 5
(twice, one on each side)

Minimum required equipment

Document Commercial
reference reference Title kg lb
07-15016-A L2512-003-10 Height adjustable pilot seat (instead of standard pilot seat) 3.7 8.1

11-90004-A L8580-200-00 Reflex Sight T100 incl. control panel and sight support 5.1 11.2

11-90008-A L8580-010-12 Multi-Purpose Armament System (MPAS), basic electrical part 12.0 26.5

11-90005-A L8580-600-00 Gun & Rocket Control Panel GRMU 3.0 6.6

11-90007-A L8580-100-00 Master Armament Panel MAP 0.75 1.7

11-90008-A L8580-400-00 Automatic/Manual Range Select Panel AMR 0.5 1.1

11-00009-A L8513-001-20 Multi-purpose pylon, RH and LH, detachable parts incl. 25.4 56.0
aerodynamic fairings
11-00010-A L8580-200-00 Light Suspensions 325mm with release unit, LH and RH 35.8 78.9
including cabling, detachable parts

12
Weight of ammunition is included
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.
635.06.101.01 E 27
This document is the property of EUROCOPTER; no part of it shall be reproduced or transmitted without the express prior written authorization of EUROCOPTER and its contents shall not be disclosed. © eurocopter - 01/2006
 Technical Data
5.2.3 12.7 mm gun pod on each side

Content: Weight
(margin ± 3 %)

Document Commercial
reference reference Title kg lb
13 7)
Machine gun pod FN-Herstal HMP400 cal. 12.7 mm, 276 608
capacity 400 rounds (twice, one on each side)

Minimum required equipment

Document Commercial
reference reference Title kg lb
07-15016-A L2512-003-10 Height adjustable pilot seat (instead of standard pilot seat) 3.7 8.1

11-90004-A L8580-200-00 Reflex Sight T100 incl. control panel and sight support 5.1 11.2

11-90008-A L8580-010-12 Multi-Purpose Armament System (MPAS), basic electrical part 12.0 26.5

11-90005-A L8580-600-00 Gun & Rocket Control Panel GRMU 3.0 6.6

11-90007-A L8580-100-00 Master Armament Panel MAP 0.75 1.7

11-90008-A L8580-400-00 Automatic/Manual Range Select Panel AMR 0.5 1.1

11-90006-A L8580-500-00 Command and Control Panel PC17 0.4 0.9

11-00009-A L8513-001-20 Multi-purpose pylon, RH and LH, detachable parts incl. 25.4 56.0
aerodynamic fairings
11-00010-A L8580-200-00 Light Suspensions 325mm with release unit, LH and RH 35.8 78.9
including cabling, detachable parts

13
Weight of ammunition is included
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.
635.06.101.01 E 28
This document is the property of EUROCOPTER; no part of it shall be reproduced or transmitted without the express prior written authorization of EUROCOPTER and its contents shall not be disclosed. © eurocopter - 01/2006
 Technical Data
5.2.4 Rocket launcher 70mm (2.75”) & 20 mm cannon pod

Content: Weight
(margin ± 3 %)

Document Commercial
reference reference Title kg lb
14 8)
Cannon pod GIAT NC621 cal. 20 mm, capacity 180 rounds 180 397
8) 8)
12 - tube rocket launcher FZ-Herstal FZ321 mod1,cal. 70 179 395
mm, capacity 12 rockets

Minimum required equipment

Document Commercial
reference reference Title kg lb
07-15016-A L2512-003-10 Height adjustable pilot seat (instead of standard pilot seat) 3.7 8.1

11-90004-A L8580-200-00 Reflex Sight T100 incl. control panel and sight support 5.1 11.2

11-90008-A L8580-010-12 Multi-Purpose Armament System (MPAS), basic electrical 12.0 26.5
part
11-90005-A L8580-600-00 Gun & Rocket Control Panel GRMU 3.0 6.6

11-90007-A L8580-100-00 Master Armament Panel MAP 0.75 1.7

11-90008-A L8580-400-00 Automatic/Manual Range Select Panel AMR 0.5 1.1

11-00009-A L8513-001-20 Multi-purpose pylon, RH and LH, detachable parts incl. 25.4 56.0
aerodynamic fairings
11-00010-A L8580-200-00 Light Suspensions 325mm with release unit, LH and RH 35.8 78.9
including cabling

14
Weight of ammunition is included
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.
635.06.101.01 E 29
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 Technical Data
5.2.5 Rocket launchers 70mm and 12.7 mm gun pod

Content: Weight
(margin ± 3 %)

Document Commercial
reference reference Title kg lb
15 9)
Machine gun pod FN-Herstal HMP400 cal. 12.7 mm, 138 304
capacity 400 rounds
9) 9)
12 - tube rocket launcher FZ-Herstal FZ321 mod1,cal. 70 179 395
mm, capacity 12 rockets

Minimum required equipment

Document Commercial
reference reference Title kg lb
07-15016-A L2512-003-10 Height adjustable pilot seat (instead of standard pilot seat) 3.7 8.1

11-90004 L8580-200-00 Reflex Sight T100 incl. control panel and sight support 5.1 11.2

11-90008 L8580-010-12 Multi-Purpose Armament System (MPAS), basic electrical 12.0 26.5
part
11-90005 L8580-600-00 Gun & Rocket Control Panel GRMU 3.0 6.6

11-90007 L8580-100-00 Master Armament Panel MAP 0.75 1.7

11-90008 L8580-400-00 Automatic/Manual Range Select Panel AMR 0.5 1.1

11-90006 L8580-500-00 Command and Control Panel PC17 0.4 0.9

11-00009 L8513-001-20 Multi-purpose pylon, RH and LH, detachable parts incl. 25.4 56.0
aerodynamic fairings
11-0010 L8580-200-00 Light Suspensions 325mm with release unit, LH and RH 35.8 78.9
including cabling, detachable parts

Further available military equipment on request:

ƒ Door Gunner Post cal. 7.62 mm
ƒ Defense Aids Suite (DAS):
ƒ Missile Launch Detector MILDS
ƒ Electro Chaff-Flare dispenser system (C/F-D)

15
Weight of ammunition is included
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.
635.06.101.01 E 30
This document is the property of EUROCOPTER; no part of it shall be reproduced or transmitted without the express prior written authorization of EUROCOPTER and its contents shall not be disclosed. © eurocopter - 01/2006
 Technical Data
6 Optional equipment
Due to the multi-role capabilities and the high complexity of the EC635, each configuration has
to be checked through EUROCOPTER offer department in order to define the incompatibilities
between the different options.

6.1 Further available equipment

Weight
General Equipment
(margin ± 3 %)

Document Commercial
reference reference Title kg lb
05-02016-A L1111-002-00 Two-color external painting instead of single color painting 1.5 3.3
05-02016-A L1111-004-00 Multicolor external painting instead of single color painting 2.0 4.4
05-12001-A L5232-001-00 Multifunction handle on the main gear box cowling (LH and RH) 0.6 1.3
05-12002-A L2551-003-00 Additional 4 tie-down fittings for airline attachment rails 0.6 1.3
05-21015-A L8541-001-10 Wire strike protection system, fixed provisions 3.3 7.3
05-21015-A L8541-001-20 Wire strike protection system, detachable parts 8.2 18.1
05-22014-A L5371-001-00 Engine outlet heat protection 1.2 2.7
05-22013-B L7100-001-00 Automatic in flight power check 0.0 0.0
05-22007-A L7924-001-00 Fuzz burners for engines 1.2 2.6
05-22008-A L2621-001-00 Engine fire extinguishing system 3.6 7.9
05-23006-A L7165-002-00 Engine compressor washing device 3.2 7.1
05-24017-A L6211-014-00 Sand erosion protection kit for rotor blades 0.9 2.0
05-25016-A L7161-001-10 Sand filter system, fixed provisions 10.1 22.3
05-25016-A L7161-001-20 Sand filter system, detachable parts 26.2 57.8
05-26012-A L1241-001-00 Anti-corrosion protection for high corrosive environment 2.0 4.4
05-31025-A L5211-002-00 Sliding window in sliding doors 0.9 2.0
05-31026-B L2514-002-00 Tinted sun shades for cockpit windshield roof section 1.9 4.2
05-31026-B L5621-001-00 Tinted window for cockpit doors 0.0 0.0
05-31026-B L5632-001-00 Tinted windows for passenger cabin 0.9 2.0
(incl. sliding window for sliding doors)
05-31027-A L5633-001-10 Window in clam-shell door, LH 0.6 1.3
05-31027-A L5633-001-20 Window in clam-shell door, RH 0.6 1.3
05-31028-A L2524-030-10 IFR – training screen, fixed provisions 0.1 0.2
05-31028-A L2524-030-20 IFR – training screen, detachable parts 1.6 3.5
05-31045-A L5211-001-11 Lockable sliding window in copilots' door 0.2 0.4
05-31045-A L5211-001-12 Lockable sliding window in pilots' door 0.2 0.4
05-32007-A L3042-001-00 Windshield wiper system 4.9 10.8
05-34003-A L2576-002-00 Dampers for avionics compartment 1.6 3.5
(avionics compartment required)

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.
635.06.101.01 E 31
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 Technical Data
Weight
General Equipment (contd.)
(margin ± 3 %)

Document Commercial
reference reference Title kg lb
05-37016-A L6701-001-00 Copilot flight controls 6.0 13.2
16
05-37017-A L6721-001-00 Covers for copilot flight controls -2.5 -5.5
05-39006-A L2514-003-01 Map case in copilot door 0.5 1.1
05-39007-A L3111-001-10 Map cases on instrument panel glare shield 0.6 1.3
05-39008-A L3113-004-10 Illuminated chart holder for pilot side 0.9 2.0
05-39008-A L3113-004-20 Illuminated chart holder for copilot side 0.9 2.0
05-42019-A L2105-001-00 Air conditioning system 58.7 129.4
05-42020-A L2105-001-10 Air conditioning system for tropical environment 61.9 136.5
05-61010-A L2433-003-00 Battery, type "Saft", ULM, 27 Ah, 24 V instead of standard battery 8.2 18.1
05-61010-A L2433-006-00 Battery, type "Saft", ULM, 40 Ah, 24 V instead of standard battery 16.8 37.0
05-71001-A L6351-001-00 Rotor brake system 6.3 13.9
05-81032-A L2818-100-10 Internal long range fuel tank system, fixed provisions 3.8 8.4
05-81032-A L2818-100-20 Internal long range fuel tank system, detachable parts 35.2 77.6
05-85008-A L2843-001-00 Fuel management system (Fuel flow meters) 1.0 2.2
05-92009-A L6611-001-10 Main rotor blade folding: basic kit 1.3 2.9
05-92009-A L6611-001-20 Main rotor blade folding: fixed provisions for ground handling kit 0.7 1.5
(basic kit required)
05-92009-A L6611-001-30 Main rotor blade folding: ground handling kit GSE GSE
05-93007-A L8544-002-00 Lashing points (wind speeds up to 100 kts) (weight GSE: 24.9 kg) 0.7 1.5
05-93008-A L8544-001-00 Lashing points (wind speeds up to 40 kts) 2.4 5.3
05-93011-A L8544-003-10 Additional lashing points for ship landing, fixed provisions 0.5 1.1
05-93011-A L8544-003-20 Additional lashing points for ship landing, detachable parts 0.4 0.9
05-95001-A L1321-001-00 Tie-down and covering kit (long-term outside helicopter parking) GSE GSE
05-97001-B L6201-001-30 Accelerometers (for Track & Balance system) 0.0 0.0
05-97002-B L6201-002-10 Optical tracker, fixed provisions 0.1 0.2
05-97002-B L6201-002-20 Optical tracker, detachable parts 0.7 1.5
05-97004-A L6201-001-00 VMS II (Track & Balance system) 2.7 6.0

Weight
Specific Mission Equipment
(margin ± 3 %)

Document Commercial
reference reference Title kg lb
06-11021-A L3274-001-10 Settling protectors, fixed provisions 1.9 4.2
06-11021-A L3274-001-20 Settling protectors, detachable parts 7.6 16.8
06-11022-A L3272-001-10 Snow skids, fixed provisions 0.9 2.0
06-11022-A L3272-001-20 Snow skids, detachable parts 20.8 45.9
06-12007-A L3273-001-00 Lengthened skids (standard landing gear only) 8.3 18.3
06-12009-A L3216-001-10 High landing gear (instead of standard landing gear) 26.0 57.3

16
Stick, Pitch and Pedals have to be removed - thus negative delta weight
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.
635.06.101.01 E 32
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 Technical Data
Weight
Specific Mission Equipment (contd.)
(margin ± 3 %)

Document Commercial
reference reference Title kg lb
17
06-21017-A L8512-001-10 External hoist, fixed provisions 8.6 19.0
17
06-21017-A L8512-001-20 External hoist 50m, detachable parts, 58.8 129.6
(incl. 1 week winch operator training)
17
06-21017-A L8512-001-21 External hoist 90m, detachable parts, 62.7 138.2
(incl. 1 week winch operator training)
18
06-24009-A L8534-002-22 External rope-down device for 2 persons, detachable parts RH
18
06-24009-A L8534-002-21 External rope-down device for 2 persons, detachable parts LH 13.3 29.3
06-24012-A L8534-001-10 Internal rope-down device for 4 persons, fixed provisions (for std. 6.0 13.2
landing gear only)
06-24012-A L8534-001-20 Internal rope-down device for 4 persons, detachable parts (for 8.7 19.2
std. landing gear only)
06-26011-A L8511-002-10 Cargo hook mirrors, fixed provisions 0.8 1.8
06-26011-A L8511-002-20 Cargo hook mirrors, detachable parts 3.9 8.6
06-27019-A L8511-001-10 Cargo hook system, fixed provisions 3.2 7.1
06-27019-A L8511-001-30 Cargo hook system, detachable parts (cargo hook mirrors 16.5 36.4
required)
06-27022-A L8511-005-10 Double cargo hook system, fixed provisions 4.3 9.5
06-27022-A L8511-005-20 Double cargo hook system, detachable parts 22.1 48.7
06-45024-A L3343-006-00 Landing & search light, 400/200 W, NVG friendly 6.3 13.9
06-46001-A L3344-001-00 Strobe lights, white 1.4 3.1
06-61015-A L3215-001-10 Emergency floats, fixed provisions (standard landing gear only) 7.8 17.2
06-61015-A L3215-001-21 Emergency floats, detachable parts (standard landing gear only) 64.6 142.4
06-65002-A L2566-001-00 Emergency hammer 0.2 0.4
06-65004-A L2625-003-00 2nd portable fire extinguisher 2.8 6.2
06-66009-A L3322-001-00 Boarding step illumination 0.2 0.4
HEEL System (Helicopter Emergency Egress Lighting) 5.6 12.3
06-66017-A L3353-010-00
(Emergency lights required)
06-67037-A L2563-005-00 Underwater Locator Beacon, ELP-362D 0.5 1.1
06-67047-A L2563-812-00 Automatic Deployable ELT 9.1 20.1

06-69005-A L2341-006-61 Voice alert generator 611-014 (NAT) 0.5 1.1

06-78009-A L3347-006-00 Formation lights NVG friendly 5.3 11.7
06-78006-A L3347-005-00 IR flasher 2.0 4.4
06-81009-A L8503-001-10 Fire extinguishing bucket attachment (Bambi Bucket), fixed 0.9 2.0
provisions (cargo hook or double cargo hook system required)

17
Communication via copilot audio / comm. control unit
18
Operation cannot be civil certified, L8514-002-00 ‘Multipurpose attachment hard points (3ea)
required
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.
635.06.101.01 E 33
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 Technical Data
Weight
Interior Layout
(margin ± 3 %)

Document Commercial
reference reference Title kg lb
07-15016-A L2512-003-20 Height adjustable copilot seat (instead of standard copilot seat) 3.7 8.1
07-30012-A L2581-001-00 Enhanced sound proofing kit 6.0 13.2
07-30013-A L2524-002-00 Separation curtain for cockpit / cabin 2.0 4.4
07-30014-A L2524-021-00 Separation curtain for cabin / cargo compartment incl. smoke 2.3 5.1
detector in cargo compartment (avionics compartment required)
07-30015-A L2524-001-00 Separation wall for cabin / cargo compartment incl. smoke 3.9 8.6
detector in cargo compartment (avionics compartment required)
07-30018-A L5213-003-00 Curtains for cabin windows (grey) 1.5 3.3
07-40005-A L2513-200-00 Washable floor covering for cockpit 4.1 9.1
07-40005-A L2513-210-00 Washable floor covering for cargo compartment 3.0 6.4
07-40005-A L2513-220-00 Washable floor covering for cockpit, cabin and cargo 11.8 26.0
compartment
07-50025-A L5211-004-10 Securing device for complete opening of copilot door 0.8 1.8
(copilot pitot / static system required)
07-50026-A L5231-001-00 One-hand latching system for clam-shell doors 1.0 2.2
07-50027-A L5231-002-00 Extended opening fasteners for clam-shell doors 0.3 0.9
07-50028-A L5213-001-11 Sliding door fastener, intermediate and max. position, LH 1.0 2.2
07-50028-A L5213-001-12 Sliding door fastener, max. position, LH 0.4 0.9
07-50028-A L5213-001-21 Sliding door fastener, intermediate and max. position, RH 1.1 2.4
07-50028-A L5213-001-22 Sliding door fastener, max. position, RH 0.4 0.9
07-50034-A L5212-001-00 Jettisonable cockpit doors 1.2 2.6
07-50035-A L8504-813-00 Spoiler position for cockpit doors 1.9 4.2
07-50039-A L5211-010-00 Pre catch system for pilots' doors 0.2 0.4
07-50039-A L5211-011-00 Pre catch system for sliding doors 0.2 0.4

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.
635.06.101.01 E 34
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 Technical Data

6.2 Avionics Weight

(margin ± 3 %)

08-15028-A L2319-002-41 Fixed provisions for GSM phone 2.3 5.1

(antenna, 28VDC, interfacing to ICS)
08-15507-B L2315-092-00 IRIDIUM satellite phone AEROPHONE (AERODATA) 4.6 10.1
08-17032-A L2331-003-00 Cabin loudspeaker 2.5 5.5
08-18018-A L2315-001-10 Headset H 10-76 (DAVID CLARK), 0.5 1.1
Low Impedance Spiral Wire
08-18018-A L2315-001-14 Headset H10-76 ANR/ENC (DAVID CLARK), Low Impedance 0.9 2.0
Spiral Wire
08-35007-A L2327-001-01 Traffic Advisory System TAS 9900BX 11.0 24.3
with 3" indicator (RYAN)
08-53004-A L3424-000-00 AHRS Free Steering Mode 0.4 0.9

08-83021-A L3172-001-00 STEADYCONTROL® (Track, Balance and Vibration recording tbd tbd
system)
On request DF equipment
On request IFF transponder
On request HF system
On request Moving Map system
On request Weather Radar
On request Tactical radio
On request Further Audio / Comm. Control solutions

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.
635.06.101.01 E 35
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 Technical Data

Weight
Operational Protection
(margin ± 3 %)
Document Commercial
reference reference Title kg lb
10-20009-A L8551-001-10 Light armor protection kit, cockpit and cabin, fixed provisions 1.0 2.2
(type AoA)
The detachable parts are available on request or directly by manufacturer for cockpit only or
cabin only or cabin rear bulkhead only.
The armor seat plating, complete installation, is also available on request.

EMS Equipment / CASEVAC

On request EMS cabin arrangement

6.3 Observation mission

Different equipment can be offered on request:

ƒ SMD68 on copilots’ side (6” x 8” display)

ƒ FLIR (Ultraforce II) with Operator Console and
Digital Video Downlink
ƒ SX16 with IFCO, Laserpointer and slaving unit
ƒ Loudspeaker System
ƒ (SAR-) Weather radar
ƒ Tactical radios
ƒ Spoiler position for cockpit doors
ƒ Rappelling devices for 2+2 persons
ƒ IRIDIUM satellite phone
ƒ Tactical direction finder, etc.

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.
635.06.101.01 E 36
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 Technical Data

7 Main performance
The following performance values and figures refer to an EC635, equipped with average production
engines.
Unless otherwise specified, the values and figures refer to a clean helicopter at Sea Level (SL), in
International Standard Atmosphere (ISA) and zero wind condition.

Performance on 2 engines (AEO) Pratt & Whitney PW206B2

Gross Weight kg 2,400 2,630 2,720 2,835 2,910
lb 5,290 5,800 6,000 6,250 6,415
km/h 278 278 278 259 259
„ Maximum speed (VNE)
kts 150 150 150 140 140
km/h 261 260 257 256 254
„ Maximum cruising speed (VH)
kts 141 140 139 138 137
kg/h 234.5 234.5 234.5 234.5 234.5
„ Fuel consumption at fast cruise speed
lb/h 517 517 517 517 517
km/h 224 224 226 228 230
„ Economical cruising speed
kts 121 121 122 123 124
„ Fuel consumption kg/h 193.5 198 200.5 204.5 208.5
at economical cruising speed lb/h 427 436.5 442 451 460
kg/h 149.5 156 158.5 162 164.5
„ Fuel consumption at 65 KIAS
lb/h 330 344 349.5 357 363
m/s 10.9 9.4 8.9 8.1 7.6
„ Rate of climb, TOP, SL, ISA
ft/min 2,150 1,850 1,750 1,600 1,500
1)
„ Hover ceiling IGE (4 ft AGL), TOP, m 4,570 4,450 4,140 3,6552) 3,0453)
1) 2) 3)
no wind or headwind, ISA ft 15,000 14,600 13,600 12,000 10,000
„ Hover ceiling IGE (4 ft AGL), TOP, m 3,880 3,415 3,095 2,695 2,435
no wind or headwind, ISA + 20°C ft 12,750 11,200 10,150 8,850 8,000
m 4,500 3,670 3,430 2,685 2,010
„ Hover ceiling OGE, TOP, ISA
ft 14,750 12,050 11,050 8,800 6,600
m 3,460 2,595 2,210 1,785 1,480
„ Hover ceiling OGE, TOP, ISA + 20°C
ft 11,350 8,500 7,250 5,850 4,850
2) 3)
„ Service ceiling, MCP, m 6,095 5,410 5,155 3,655 3,045
2) 3)
(climb reserve 200 ft/min), ISA ft 20,000 17,750 16,900 12,000 10,000
„ Maximum range (without fuel reserve at
economical cruise speed)
„ standard fuel tank configuration (553 kg) km 650 640 635 630 625
nm 351 346 343 340 338
„ long range fuel tank configuration (723 kg) km 860 845 835 830 825
nm 464 456 451 448 445
„ Maximum endurance (without fuel reserve at
65 KIAS
„ standard fuel tank configuration (553 kg) h:min 3:52 3:43 3:40 3:36 3:33
„ long range fuel tank configuration (723 kg) h:min 5:07 4:57 4:52 4:46 4:42
1) 15,000 ft density altitude certification limit
2) 12,000 ft pressure altitude certification limit
3) 10,000 ft pressure altitude certification limit

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.
635.06.101.01 E 37
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 Technical Data

Performance on 1 engine (OEI) Pratt & Whitney PW206B2

Gross Weight kg 2,400 2,630 2,720 2,835 2,910
lb 5,290 5,800 6,000 6,250 6,415
„ Service ceiling with 100 ft/min climb reserve, m 4,265 3,550 3,275 2,925 2,715
MCP OEI-power, ISA ft 14,000 11,650 10,750 9,600 8,900
„ Service ceiling with 100 ft/min climb reserve, m 3,505 2,695 2,375 1,965 1,710
MCP OEI-power, ISA + 20°C ft 11,500 8,850 7,800 6,450 5,600
m/s 3.4 2.3 1.9 1.4 1.1
„ Rate of climb, MCP OEI-power, SL
ft/min 665 450 375 275 215
„ Max. temperature for CAT A, take-off from
°C + 50 + 50 + 50 + 46 + 43
clear heliport at SL
„ Max. gross weight hover IGE (4ft AGL), SL, kg 2,835
ISA, no wind, 2 min OEI power lb 6,250
„ Max. gross weight hover IGE (4ft AGL), SL, kg 2,675
ISA + 20°C, no wind, 2 min OEI power lb 5,885
„ Max. gross weight hover OGE, SL, kg 2,665
ISA, no wind, 30 sec OEI power lb 5,875
„ Max. gross weight hover OGE, SL, kg 2,585
ISA + 20°C, no wind, 30 sec OEI power lb 5,687
„ Max. gross weight CAT A, VTOL, SL, kg 2,910
ISA / ISA + 20°C lb 6,415

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.
635.06.101.01 E 38
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 Technical Data

Performance on 2 engines (AEO) Turbomeca Arrius 2B2

Gross Weight kg 2,400 2,630 2,720 2,835 2,910
lb 5,290 5,800 6,000 6,250 6,415
km/h 278 278 278 259 259
„ Maximum speed (VNE)
kts 150 150 150 140 140
km/h 261 260 257 256 254
„ Maximum cruising speed (VH)
kts 141 140 139 138 137
kg/h 234.5 234.5 234.5 234.5 234.5
„ Fuel consumption at fast cruise speed
lb/h 517 517 517 517 517
km/h 237 237 237 239 240
„ Economical cruising speed
kts 128 128 128 129 130
„ Fuel consumption kg/h 209 213 215 219 221
at economical cruising speed lb/h 461 470 474 483 487
kg/h 159.0 165 167.5 170.5 173
„ Fuel consumption at 65 KIAS
lb/h 350.5 364 369 376 381
m/s 10.9 9.4 8.9 8.1 7.6
„ Rate of climb, TOP, SL, ISA
ft/min 2,150 1,850 1,750 1,600 1,500
1) 1)
„ Hover ceiling IGE (4 ft AGL), TOP, m 4,570 4,570 4,325 3,6552) 3,0453)
1) 1) 2) 3)
no wind or headwind, ISA ft 15,000 15,000 14,200 12,000 10,000
„ Hover ceiling IGE (4 ft AGL), TOP, m 3,880 3,430 3,080 2,670 2,395
no wind or headwind, ISA + 20°C ft 12,750 11,250 10,100 8,750 7,850
1)
m 4,570 3,690 3,430 2,685 2,010
„ Hover ceiling OGE, TOP, ISA 1)
ft 15,000 12,100 11,050 8,800 6,600
m 3,470 2,545 2,175 1,740 1,450
„ Hover ceiling OGE, TOP, ISA + 20°C
ft 11,400 8,350 7,150 5,700 4,750
2) 3)
„ Service ceiling, MCP, m 6,095 5,410 5,155 3,655 3,045
2) 3)
(climb reserve 200 ft/min), ISA ft 20,000 17,750 16,900 12,000 10,000
„ Maximum range (without fuel reserve at
economical cruise speed)
„ standard fuel tank configuration (553 kg) km 635 625 620 615 610
nm 343 338 335 332 329
„ long range fuel tank configuration (723 kg) km 835 825 815 810 805
nm 451 445 440 437 434
„ Maximum endurance (without fuel reserve at
65 KIAS
„ standard fuel tank configuration (553 kg) h:min 3:37 3:30 3:27 3:24 3:21
„ long range fuel tank configuration (723 kg) h:min 4:47 4:38 4:34 4:30 4:27

1) 15,000 ft density altitude certification limit

2) 12,000 ft pressure altitude certification limit
3) 10,000 ft pressure altitude certification limit

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.
635.06.101.01 E 39
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 Technical Data

Performance on 1 engine (OEI) Turbomeca Arrius 2B2

Gross Weight kg 2,400 2,630 2,720 2,835 2,910
lb 5,290 5,800 6,000 6,250 6,415
„ Service ceiling with 100 ft/min climb reserve, m 4,510 3,790 3,520 3,185 2,955
MCP OEI-power, ISA ft 14,800 12,450 11,550 10,450 9,700
„ Service ceiling with 100 ft/min climb reserve, m 3,730 2,830 2,500 2,070 1,795
MCP OEI-power, ISA + 20°C ft 12,250 9,300 8,200 6,800 5,900
m/s 3.4 2.3 1.9 1.4 1.1
„ Rate of climb, MCP OEI-power, SL
ft/min 665 450 375 275 215
„ Max. temperature for CAT A, take-off from
°C + 50 + 50 + 50 + 47 + 43.5
clear heliport at SL
„ Max. gross weight hover IGE (4ft AGL), SL, kg 2,835
ISA, no wind, 2 min OEI power lb 6,250
„ Max. gross weight hover IGE (4ft AGL), SL, kg 2,690
ISA + 20°C, no wind, 2 min OEI power lb 5,930
„ Max. gross weight hover OGE, SL, kg 2,665
ISA, no wind, 30 sec OEI power lb 5,875
„ Max. gross weight hover OGE, SL, kg 2,615
ISA + 20°C, no wind, 30 sec OEI power lb 5,765
„ Max. gross weight CAT A, VTOL, SL, kg 2,910
ISA / ISA + 20°C lb 6,415

OPERATING LIMITATIONS (valid for both versions, EC635 P2i and EC635 T2i)
The helicopter can be operated within the following altitude and temperature limitations (according to
the Flight Manual):

Gross Weight 2,720 kg 2,835 kg 2,910 kg

6,000 lb. 6,250 lb. 6,415 lb.
6,095 m PA 3,655 m PA 3,045 m PA
„ Maximum operating altitude
20,000 ft PA 12,000 ft PA 10,000 ft PA
„ Maximum operating altitude for hover in
4,570 m DA 3,655 m PA 3,045 m PA
ground effect,
15,000 ft DA 12,000 ft PA 10,000 ft PA
takeoff and landing
„ Minimum temperature -35°C (-31°F)
ISA + 39°C
„ Maximum temperature
(max. + 50°C / + 122°F)

Abbreviations
AGL Above Ground Level OGE Out Of Ground Effect
DA Density Altitude PA Pressure Altitude
IGE In Ground Effect SL Sea Level
ISA International Standard Atmosphere TOP Take-Off Power
MCP Maximum Continuous Power VNE Never-Exceed Speed
OEI One Engine Inoperative VTOL Vertical Take-Off and Landing

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.
635.06.101.01 E 40
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 Technical Data
Hover In Ground Effect (HIGE, TOP, no wind)
with two PW206B2 engines

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.
635.06.101.01 E 41
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 Technical Data
Hover In Ground Effect (HIGE, TOP, no wind)
with two ARRIUS 2B2 engines

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.
635.06.101.01 E 42
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 Technical Data
Hover Out Of Ground Effect (HOGE, TOP)
with two PW206B2 engines

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.
635.06.101.01 E 43
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 Technical Data
Hover Out Of Ground Effect (HOGE, TOP)
with two ARRIUS 2B2 engines

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.
635.06.101.01 E 44
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 Technical Data
Hover Out Of Ground Effect (HOGE, 30 sec OEI-power)
with one PW206B2 engine

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.
635.06.101.01 E 45
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 Technical Data
Hover Out Of Ground Effect (HOGE, 2.0 min OEI-power)
with one PW206B2 engine

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.
635.06.101.01 E 46
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 Technical Data
Hover Out Of Ground Effect (HOGE, 30 sec OEI-power)
with one ARRIUS 2B2 engine

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.
635.06.101.01 E 47
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 Technical Data
Hover Out Of Ground Effect (HOGE, 2.0 min OEI-power)
with one ARRIUS 2B2 engine

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.
635.06.101.01 E 48
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 Technical Data
Maximum Cruising Speed
with two PW206B2 engines

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.
635.06.101.01 E 49
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 Technical Data
Maximum Cruising Speed
with two ARRIUS 2B2 engines

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.
635.06.101.01 E 50
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 Technical Data
Maximum Rate Of Climb, TOP
with two PW206B2 engines,

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.
635.06.101.01 E 51
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 Technical Data
Maximum Rate Of Climb, TOP
with two ARRIUS 2B2 engines,

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.
635.06.101.01 E 52
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 Technical Data
Payload / Range
with two PW206B2 engines

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.
635.06.101.01 E 53
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 Technical Data
Payload / Range
with two ARRIUS 2B2 engines

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.
635.06.101.01 E 54
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