CN 235 Aircraft Definition

AIRCRAFTDEFINITION

AIRCRAFT DEFINITIONAIRCRAFT DEFINITIONAIRCRAFT DEFINITIONAIRCRAFT DEFINITION

This document contains EADS-CASA proprietary information and shall not be used or disclosed without the prior written permission of EADS-CASA, Sociedad Unipersonal

MCM - Marketing 0


Military Transport Aircraft July, 2007

AIRCRAFTDEFINITION

Contents Contents

CN-235-300 Basic Equipment

Three View Drawing

Cargo Cabing

Cockpit

Communications and Navigation System

Flight Controls

Landing Gear

Power PlantPower Plant

Fuel System

Hydraulic System

Electrical System

Environmental Control System and Pressurisation

Ice Protection System

Fire Protection System

Oxygen System

Lighting System

Performance

Soft Field Capability

Manoeuvrability

Ground Performance

Payload – Range

The CN 235 in NumbersThe CN-235 in Numbers


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AIRCRAFTDEFINITION

17 m

(26

ft 1

0 in

)Three View Drawing

21.40 m (70 ft 2 in)

8.1

6.92 m (22 ft 9 in)

7.0 m (22 ft 11 in)

3.9 m (12 ft 8 in)


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AIRCRAFTDEFINITION

Cargo Cabin

In its basic configuration, the CN-235 can efficiently transport bulky cargo, personnel or

paratroops. The cargo cabin can be quickly reconfigured to fulfil each required mission.

The main cabin is furnished with a lining covering the entire interior to ensure thermo-

acoustical insulation and a comfortable interior finish; the lining covers the control cables, air

conditioning ducts and electric wiring and provides protection against damage from cargo or

passengers.

For bulky cargo transport such as fighter engines or artillery, the cargo is secured to hard

points on the floor structure by means of cargo straps and cargo chains.

9 65 (31 6 ft) 3 04m (9 9 ft)

CREW DOOR(1.27m x 0.70m)(4.1 ft x 2.3 ft)

PARATROOP DOOR(1.75m x 0.90m)(5.7 ft x 2.9 ft)

MAIN CABIN 48 m3 (1,695 cu ft) RAMP AREA

9.65 m (31.6 ft) 3.04m (9.9 ft)

EMERGENCY DOOR(0.91m x 0.50m)(2.9 ft x 1.6 ft)

PARATROOP DOOR(1.75m x 0.90m)(5.7 ft x 2.9 ft)

WINCH

t

Constant Cross Section along the Cabin

1.90

m /

6.2

ft


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2.36 m / 7.7 ft

2.70m / 8.8 ft

AIRCRAFTDEFINITION

Troop Transport Configuration

The normal seating configuration accommodates 36 troops in lateral sidewall seats; four

easily foldable seats are attached to the rear doors, without interfering with the door operation.

In high density configuration, a central seat row provides 15 more places.

The central row seats are stowed in easily accessible underfloor compartments, while the

lateral seats are simply stowed against the cabin sidewalls.

36 Fully yEquipped Troops

51 Training

Paratroops Dropping Configuration

The CN-235 accommodates up to 35 fully equipped paratroops plus one loadmaster.

Troops

Two anchor cables run along the cabin and the ramp and allow jumping either through the

side doors or the ramp. Retrieval of a hung-up parachutist can be safely achieved with the help

of the cargo winch.


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AIRCRAFTDEFINITION

Medevac Configuration

The cargo cabin can be configured for medical evacuation (Medevac) missions. Structural

provisions are permanently installed in both the sidewall and the ceiling. The fittings are

compatible with standard NATO stretchers (*).

The aircraft can accommodate up to 18 NATO standard stretchers (*) located at six stations,

each one with a capacity of three stretchers; moreover, up to four seated medical attendants

can be accommodated.

The Medevac kit includes the sidewall hook supports, floor fittings supports and

harnesses.

Up to 18 Stretchers (*)


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(*) Stretchers are Customer Furnished Equipment (CFE), not included in the proposed configuration

AIRCRAFTDEFINITION

Cockpit

The CN-235-300 cockpit allows all types of operations to be performed by a crew of two.

Pilot workload has been reduced by the use of an advanced avionics system with five

multifunctional displays. A foldable observer seat can be provided in case a third member

should be required.

The cockpit controls and displays are distributed in the main instrument panel, the left and

right consoles, the central pedestal panel and in the overhead panels.

The cockpit is equipped with smoke goggles, portable oxygen bottle, portable

extinguishers of Halon/water type, one full face mask, portable spotlight and lifejackets.


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AIRCRAFTDEFINITION

Communications and Navigation Systems

The Communications and Navigation System have been designed to support present and

future communication, surveillance and navigation requirements for operations in civil and

military environments. The systems use Commercial-off-the-Shelf (COTS) equipment

providing high reliability and performance in a cost effective solution. Adequate growth

provisions have been made to allow addition of new systems and new functions that may be

required in the future.

The following description applies to the basic CN-235-300 configuration.

COMMUNICATIONS SYSTEM EQUIPMENT

Equipment Model Manufacturer Qty

U/VHF AN/ARC-210 Rockwell-Collins 2

HF HF-9000 Rockwell-Collins 1

IFF APX-119 Raytheon 1

TCAS TCAS 4000 Rockwell-Collins 1

Interphone DADS AVTECH 1

Public Address PACIS AVTECH 1

ELT A06 CEIS 1

NAVIGATION SYSTEM EQUIPMENT

Equipment Model Manufacturer QtyEquipment Model Manufacturer Qty

Air Data Computer 90040 B&D 2

AHRS AHC-3000A Rockwell-Collins 2

EFIS EFIS-85 B14 Rockwell-Collins 1

FMS UNS-1F Universal 2

WXR Radar WXR 350 Rockwell Collins 1WXR Radar WXR-350 Rockwell-Collins 1

RADALT ALT-4000 Rockwell-Collins 1

VOR/ILS/MB VIR-32 Rockwell-Collins 2

DME DME-42 Rockwell-Collins 2

ADF ADF-462 Rockwell-Collins 1

FDR SSFDR H ll 1


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FDR SSFDR Honeywell 1

Autopilot APS-65F Rockwell-Collins 1

The above equipment models (current models) are proposed subject to the availability from the manufacturers by thetime that the purchase order is placed.

AIRCRAFTDEFINITION

Flight controls

The Flight Control System is a conventional mechanical system; the primary control

surfaces are mechanically operated by means of push-pull rods and closed-loop cables.

Control system separation between redundant control paths minimises the probability of total

failure from a single cause. There is also routing segregation between Primary Flight Controls

systems and Trim Control systems.

– Longitudinal control: dual interconnected mechanical control paths move both elevators.Each elevator surface is provided with an electrically operated trim tab and a geared tab.

– Lateral Control: dual interconnected mechanical control paths move both ailerons. Eachaileron has an electrically operated trim tab and a geared tab.

– Directional Control: a single control chain moves the rudder from the pilot and copilotpedals. The rudder has a geared tab and an electrically powered trim tab.

The Flap System is hydraulically powered : there are two flap surfaces on each wing;

each flap panel is supported on two tracks attached to the wing structure by two carriages.

The flap setting is achieved by selecting one of four predetermined positions on the flap

control lever: Up, Take Off, Approach, Landing.control lever: Up, Take Off, Approach, Landing.

The Ground Gust Lock System prevents damage of the flight controls when the aircraft

is on the ground.

Landing Gear

The main landing gear has two interconnected levered legs in tandem configuration on

each side, with independent oleo-pneumatic type shock-absorber units. The legs retract

rearwards into a fuselage nacelle. Retraction and extension is effected by an hydraulic

actuator.

The nose landing gear is located in a non-pressurised wheel bay under the cockpit and is

equipped with a single wheel levered type leg with oleo-pneumatic shock absorber. The nose

gear steering system is hydraulically powered with mechanical controlgear steering system is hydraulically powered, with mechanical control.

The brake system is hydraulically operated and incorporates an anti-skid control system. An

independent emergency/park brake system is operated through a hand lever and is powered

by an hydraulic accumulator.

The nose gear has one tubeless tyre 8.50-10/12PR. Inflation pressure is 76 psi. Twin-

wheel nose landing gear is an option in CN-235.


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The main landing gear has two tubeless 11.00 - 12 /10PR tyres inflated to 58 psi.

AIRCRAFTDEFINITION

Engine

The CN-235-300 is powered by two General Electric CT7-9C3 turboprop engines, driving

Hamilton Sundstrand 14 RF-37 four bladed propellers.

The guaranteed performance for the General Electric CT7-9C3 engine (installed, static)

with 100% propeller rpm at Sea Level, ISA conditions, is:

– Engine rating SHP Up to ambient temperature of

– Take-off 1,750 38.5OC

– APR 1,870 38.5OC

– Maximum continuous 1,750 41OC

– Maximum cruise 1,700 15OC

The CT7-9C3 engine incorporates modular construction; each engine is made up of two

main assemblies: the Power Unit Assembly or Gas Generator and the Propeller Gearbox.

The right engine is fitted with a propeller brake; with the propeller stopped, the engine gas

generator can be used as an Auxiliary Power Unit, for ground operation. The APU mode

delivers DC electrical power and bleed air for the aircraft systems.

The engine inlet has an “S” shaped air intake duct in order to prevent ‘FOD’ (Foreign Object

Damage)

Propeller

The CN-235-300 is equipped with two Hamilton Sundstrand Type 14RF-37 four-bladed

propellers with hydraulically controlled variable pitch, feathering and reverse capability.propellers with hydraulically controlled variable pitch, feathering and reverse capability.

The propellers have a diameter of 3.66 meters (12 ft) and maximum rotation speed is 1,384

rpm.


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AIRCRAFTDEFINITION

Fuel System

Fuel is carried in four integral tanks in the wings. The usable fuel capacity of each tank is:

– Inboard tanks(Main): 1.020 litres each

– Outboard tanks (Auxiliary): 1 590 litres eachOutboard tanks (Auxiliary): 1.590 litres each

– Total usable fuel: 5.220 litres

In normal operating conditions, fuel is fed to each engine by a jet pump from the collector

tank located within the corresponding main tank.

Pressure refuelling of all four tanks is done through a standard single point valve in the

refuel/defuel panel on the right main landing gear fairing nacelle. The tanks can also be filledrefuel/defuel panel on the right main landing gear fairing nacelle. The tanks can also be filled

by gravity through a lightning safe cap on each tank.

Defuelling can be forced or by gravity.

Hydraulic System

The Hydraulic System is a closed-centre, airless type system with a nominal operating

pressure of 207 bar (3000 psi). Hydraulic fluid is stored in a bootstrap type reservoir with a

capacity of 10 litres at a nominal working pressure of 50 psi.

The hydraulic system powers to the following subsystems:

– Wing Flaps

– Landing Gear normal extraction and retraction.

– Brakes (Normal and Emergency/Parking Brake)

– Nose Wheel Steering

– Rear Cargo Door and Ramp

– Propeller Brake

Hydraulic pressure is supplied by two DC Electrical Motor Pumps On the ground theHydraulic pressure is supplied by two DC Electrical Motor Pumps. On the ground, the

hydraulic system can be powered from an external GPU or from a hydraulic cart.


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AIRCRAFTDEFINITION

Electrical System

The primary electrical power for the EADS CASA CN-235 is provided by two engine-driven

DC starter-generators. Additionally, the aircraft is equipped with two fully independent AC

systems:

– The constant frequency system, provided by three DC driven inverters.

– The wild frequency system powered by two engine driven generators.

Two batteries are also provided for limited ground use, engine starting on the ground or in

flight, and as source of DC power in emergency conditions.

A connector for external DC ground power is located in the right landing gear fairing.

Environmental Control System and Pressurisation

The Environmental Control System, which provides temperature control in the flight deck

area, the main cabin and the avionics bays, obtains the compressor bleed air from high

pressure and low pressure ports in each engine. When the aircraft is on the ground, air

conditioning is provided by the left engine operating in APU modeconditioning is provided by the left engine operating in APU mode.

The Pressurisation System, of electro-pneumatic type, is able to maintain a positive

differential pressure of 5.5 psi corresponding to a cabin altitude of 7,900 ft with aircraft flying

at 25,000 ft altitude.


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AIRCRAFTDEFINITION

Ice Protection System

The Ice Protection System for the Aerodynamics Surfaces is made up of conventional

pneumatic de-icing system with inflatable rubber boots, bonded to the leading edges of the

wing, stabiliser and fin, using engine bleed air. The engine air intake is also protected with

rubber inflatable boots.

Propellers blades, windshield and AOA sensors are protected against ice formation by

means of electrically heating.

Fire Protection System

The Power Plant is protected against fire consequences with an electrical detection systemThe Power Plant is protected against fire consequences with an electrical detection system

and a extinguishing system consisting of two Halon dischargeable extinguishers. The cabin is

provided with photoelectric smoke detectors; additionally, two Halon portable extinguishers

are located in the cargo cabin and one in the cockpit.

Oxygen System

The oxygen system consists of a fixed installation of high pressure gaseous type, made up

of two interconnected pressurized cylinders, for the crew and three portable oxygen bottles

for use by the passengers.

Lighting System

The CN-235-300 Lighting System provides the required external and internal illuminationThe CN 235 300 Lighting System provides the required external and internal illumination

for all flight/ground environments.

The exterior lighting subsystem consists of the Navigation Lights; Anti-collision Lights;

Wing Inspection Lights; Landing/Taxi Lights; Runway Turn-Off Lights and Emergency Lights.


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AIRCRAFTDEFINITION

CN-235-300 PERFORMANCECN 235 300 PERFORMANCE

Soft Field Capability

The impressively strong landing gear of the CN-235 is designed for routine operations from

rough, unprepared surfaces.

The flotation characteristics of the undercarriage, which uses low-pressure tyres, allows

operation from soft field surfaces, with a CBR index (California Bearing Ratio) lower than 3, at

its MTOW, allowing more than 200 passes of operations in a field with CBR4.

Manoeuvrability

Excellent handling qualities, fast engine response times and outstanding manoeuvrabilityallow safe operations at very low level close to the ground The sustained turn radius of theallow safe operations at very low level close to the ground. The sustained turn radius of theCN-235-300 is only 380 metres (1,246 ft) (at 90% of MTOW, 160 Kts).

Small turning radius allows the CN-235 to operate at ease from remote airfields with verynarrow runways and limited apron space for parking.

R1 = 4.28 m (14 ft)

R2 = 8.18 m (26.8 ft)

R3 = 9.50 m (31.2 ft)

R4 = 18.98 m (62.3 ft)


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AIRCRAFTDEFINITION

Ground Performance

The CN-235-300 has been designed to operate in short and unpaved runways; STOL

techniques have been certified.

– TAKE-OFF at MTOW (16.500 kg; 36,380 lb) ISA, S/L (Short Field Technique)g q

– Take-off run 404 m (1,325 ft)

– Take-off run to 50 ft 633 m (2,075 ft) 50 ft

– LANDING at MLW (16.500 kg; 36,380 lb) ISA, S/L (Short Field Technique)

Landing run 378 m (1 240 ft)– Landing run 378 m (1,240 ft)

– Landing run from 50 ft 50 ft 617 m (2,025 ft)

Payload-Range

PL (lb)PL (kg)

7.000

6.000

5.000

15,000

12,5005.950 kg /13,120 lb

5.000

4.000

3.000

2 000

10,000

5,000

7,500

2.838 kg /6,250 lb

2.000

1.000

00 500 1000 1500 2000 2500 3000

02233

Range (nm)

2,500

393 2730


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AIRCRAFTDEFINITION

Overall Length: 21.40 m 70 ft 2 in

Wing Span: 25.81 m 84 ft 8 in

Overall Height: 8.17 m 26 ft 10 in

The Cn-235 in Numbers

Wing aspect ratio 10.16

Gross Wing Area: 60 m2 646 ft2

Wheel Base: 6.92 m 22 ft 9 in

Wheel Track: 3.90 m 12 ft 8 in

Cargo Hold Length (excluding ramp): 9.65 m 31 ft 8 ing g g p

Ramp Length: 3.04 m 10 ft

Cargo Hold Height: 1.90 m 6 ft 3 in

Cargo Hold maximum Width: 2.70 m 8 ft 10 in

Cargo Hold Volume: 45.22 m3 1,597 ft3

M i T k Off W i ht (2 5 ) 16 500 k 36 380 lbMaximum Take Off Weight (2.5g): 16,500 kg 36,380 lb

Maximum Take Off Weight (3 g): 14,100 kg 31,084 lb

Maximum Landing Weight (9 ft /s): 16,500 kg 36,380 lb

Maximum Payload (2.5g): 5,950 kg 13,120 lb

Maximum Payload (3 g): 3,550 kg 7,826 lb

Usable Fuel Capacity: 5220 litres 1380 USg

Maximum Cruise Speed (TAS): 454 km/h 245 kts

Normal Operating Altitude: 7,620 m 25,000 ft

Ferry Range: 5,055 km 2730 nm

Take Off run (ISA, S/L, MTOW): 404 m 1325 ft

Landing roll (ISA, S/L, MLW): 378 m 1240 ft

Load factor limits 3.0 g / -1.0 g


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AIRCRAFTDEFINITION

OPTIONAL EQUIPMENT


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AIRCRAFTDEFINITION

OPTIONAL EQUIPMENTOPTIONAL EQUIPMENT

Palletised Cargo Transport Configuration

The CN-235 Cargo Handling Aerial Delivery System (CHADS) is completely compatible with the

463L cargo pallet system which is widely used in the C-130 and other airlifters.

This configuration allows the transport of up to:

– Four 88”x108” pallets (one on the ramp), or

– Eight 88” x 54” pallets (two on the ramp).

The Cargo Handling Aerial Delivery System includes:

– Two side rail rows, to provide upward and lateral restraint, equipped with manual and automatic

locks that provide the forward and rearward restraint

– Four roller tray rows, located along the whole length of the main cabin and the ramp.

– Ramp transport kit, consisting of side rails with locks

- .


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AIRCRAFTDEFINITION


Cargo Air Delivery Configuration

The cargo cabin can be configured for Cargo Air Delivery missions with the CHADS (Cargo

Handling Aerial Delivery System), adding two anchor cables, a tow plate assembly and a pendulum

release assembly.

The CN-235 is approved for the following cargo dropping modes:

– EXTRACTION using either HAD (Heavy Drop Altitude) or LAPES (Low Altitude Parachute

Extraction System):

– GRAVITY using either GEP (gravity Ejected Platform) or CDS (Containers Delivery System):


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AIRCRAFTDEFINITION


Communications and Navigation System

COMMUNICATION SYSTEM EQUIPMENT (Optional)


Transponder TDR-94 Rockwell-Collins 1

CVR SSCVR Honeywell 1

NAVIGATION SYSTEM EQUIPMENT (Optional)


IRS LTN-101 Northrop Grumman 2

TACAN TCN-500 Rockwell-Collins 1

GPWS MARK VIII Honeywell 1

DF DF-430 Rockwell-Collins 1


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AIRCRAFTDEFINITION


Survivability

Survivability enhancing options available in the CN-235-300 include a Radar Warning Receiver

(RWR) and a Counter Measures Dispenser System (CMDS).

Radar Warning Receiver

– The ALR-400(V2)R Radar Warning Receiver system, from Indra, receives, identifies and classifies

radar emissions in a dense electronic environment in the frequency range from 0.5 GHz to 18 GHz.

Counter Measures Dispenser System

– The ALE-47Counter Measures Dispenser System , from BAeS, is capable of dispensing expendable

countermeasure decoys such as chaff, flares and others to enhance the aircraft survivability against

Tailcone E/J Band antennas

y , y g

radar-directed anti-aircraft artillery (AAA), radar command-guided missiles, radar homing guided

missiles and infrared (IR) guided missiles.

Chaff/Flares dispensers locationin aircraft tailcone


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AIRCRAFTDEFINITION

Military Transport Aircraft Divisiony pAVDA. ARAGÓN, 404 – 28022 MADRID – SPAIN

TELEPHONE +34 (91) 585 70 00 FAX +34 (91) 585 76 66

www.eads.com

© EADS CASA S.L.. Unipersonal 2006ALL RIGHTS RESERVED

This document and all information contained herein is the sole property of EADS CASA S.L.. Unipersonal. No intellectual property rights are granted by the provision of this document or disclosure of its content. This

document shall not be reproduced or disclosed to a third party without the express written consent of EADS CASA S.L.. Unipersonal. This document and its content shall not be used for any other purpose other than for

which it is supplied.The pictures used in this document are intended to show the aircraft capabilities and may include some elements (I.e. ground support equipment, optional items) which are not included in the proposed aircraft.


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CN 235 Aircraft Definition