thf-a119-0607-1.pdf

THE DATA CONTAINED IN THIS DOCUMENT ARE GENERAL IN NATURE AND MAY VARY WITH CONDITIONS. FOR PERFORMANCE DATA AND OPERATING LIMITATIONS FOR ANY SPECIFIC FLIGHT MISSION, REFERENCE MUST BE MADE TO THE APPROVED FLIGHT MANUAL. THIS SPECIFICATION IS SUBJECT TO CHANGE WITHOUT NOTICE.

THF-A119-0607-1 III


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II THF-A119-0607-1

This document contains data related to aircraft description, specification and performance that are supplied for general information purposes only. The exact description, characteristics, and performance capabilities of any particular aircraft may vary and are wholly dependent on the final configuration requested by the Customer and on the specific aircraft usage, operation and maintenance. For performance data and operating limitations reference must be made to the approved Flight Manual and other appropriate documentation.

THE INFORMATION CONTAINED IN THIS DOCUMENT IS SUBJECT TO CHANGE WITHOUT NOTICE AND IN ANY CASE IT DOES NOT CONSTITUTE AN OFFER NOR A CONTRACTUAL COMMITMENT, UNLESS SPECIFICALLY AGREED IN WRITING BY AGUSTAWESTLAND COMPANIES.


THF-A119-0607-1 III

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IV THF-A119-0607-1

TABLE OF CONTENTS 1 INTRODUCTION ...........................................................................................................1

1.1 MAIN CHARACTERISTICS ..........................................................................................1

1.2 APPLICATIONS .........................................................................................................1

2 LEADING FEATURES ..................................................................................................2

2.1 CERTIFICATION (TYPE AND OPERATIONAL APPROVAL)..................................................2

2.2 EXTERNAL DIMENSIONS ............................................................................................3

2.3 INTERNAL DIMENSIONS AND VOLUMES........................................................................5

2.4 WEIGHTS ................................................................................................................7

2.5 SLING LOAD CAPACITY..............................................................................................7

2.6 FUEL CAPACITY........................................................................................................8

2.7 POWERPLANT..........................................................................................................8

2.8 TRANSMISSION ........................................................................................................8

2.9 OPERATIONAL ENVELOPE .........................................................................................9

2.9.1 Maximum operational flight speed – ISA Sea level............................................9 2.9.2 Wind envelope...................................................................................................9 2.9.3 Flight load factors ............................................................................................10 2.9.4 Slope landing...................................................................................................10 2.9.5 Temperature and altitude.................................................................................10

2.10 CG ENVELOPE ......................................................................................................11

2.10.1 CG longitudinal and lateral envelope ...............................................................11

2.11 PERFORMANCE SUMMARY TABLES...........................................................................12

2.11.1 Sea level ..........................................................................................................12 2.11.2 5000 ft..............................................................................................................12 2.11.3 Altitude performance........................................................................................13

2.12 ENVIRONMENTAL IMPACT........................................................................................13

2.12.1 External noise level..........................................................................................13


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2.12.2 Internal noise level .......................................................................................... 13

3 STANDARD CONFIGURATION AND OPTIONAL EQUIPMENT LIST...................... 14

3.1 STANDARD CONFIGURATION (EASA/FAA VFR) ...................................................... 14

3.1.1 Basic aircraft ................................................................................................... 14 3.1.2 Standard additional equipment........................................................................ 18 3.1.3 VFR Avionic package...................................................................................... 18 3.1.4 Additional installed avionic equipment ............................................................ 18 3.1.5 Additional utility equipment ............................................................................. 18 3.1.6 Interior and comfort ......................................................................................... 19 3.1.7 Painting ........................................................................................................... 19 3.1.8 Miscellaneous equipment................................................................................ 19

3.2 COMPLETIONS ...................................................................................................... 20

3.2.1 Corporate interior ............................................................................................ 20 3.2.1.1 Corporate interior optional equipment ............................................................. 20 3.2.2 VIP interior ...................................................................................................... 20 3.2.2.1 VIP optional equipment ................................................................................... 20 3.2.3 Convertible interior .......................................................................................... 21 3.2.3.1 Convertible interior optional equipment........................................................... 21 3.2.4 EMS (Emergency Medical Service) interior..................................................... 21 3.2.4.1 EMS optional equipment ................................................................................. 22

3.3 OPTIONAL EQUIPMENT ........................................................................................... 23

3.3.1 Interior and comfort equipment ....................................................................... 23 3.3.2 Utility equipment.............................................................................................. 23 3.3.3 Additional avionics .......................................................................................... 24 3.3.4 Additional mission equipment only by FAA STC ............................................. 24 3.3.5 Painting ........................................................................................................... 25

4 PERFORMANCE DIAGRAMS ................................................................................... 27

4.1 HOVERING ............................................................................................................ 28

4.1.1 Hovering IGE (TOP)........................................................................................ 28 4.1.2 Hovering OGE (TOP) ...................................................................................... 29

4.2 RATE OF CLIMB ..................................................................................................... 30

4.2.1 Rate of climb 2550 Kg MGW........................................................................... 30 4.2.2 Rate of climb 2720 Kg MGW........................................................................... 31


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4.3 FUEL CONSUMPTION VS AIRSPEED...........................................................................32

4.3.1 Fuel consumption vs Airspeed – SL (ISA) .......................................................32 4.3.2 Fuel consumption vs Airspeed – SL (ISA + 20°C) ...........................................33 4.3.3 Fuel consumption vs Airspeed – 5000 ft (ISA).................................................34 4.3.4 Fuel consumption vs Airspeed – 5000 ft (ISA + 20°C).....................................35

5 SUPPORT AND MAINTENANCE ...............................................................................36

5.1 INSPECTION PROGRAMMES .....................................................................................36

5.2 OVERHAUL COMPONENTS .......................................................................................37

5.3 RETIREMENT LIFE ..................................................................................................38

6 DIRECT OPERATING COST (DOC)...........................................................................39

6.1 FUEL AND LUBRICANTS ...........................................................................................39

6.2 AIRFRAME DIRECT MAINTENANCE ............................................................................39

6.3 POWER PLANT MAINTENANCE..................................................................................40

7 SERVICE PLANS........................................................................................................41

7.1 AIRFRAME MAINTENANCE PROGRAMME ....................................................................41

7.1.1 Global support plan (GSP)...............................................................................41 7.1.2 Complete overhaul and maintenance programme (COMP).............................42 7.1.3 Component protection agreement (CPA).........................................................42

7.2 ENGINE MAINTENANCE PROGRAMME........................................................................43

7.2.1 Pratt & Whitney Canada Eagle Service Plan (ESP).........................................43

7.3 WARRANTIES.........................................................................................................44

7.3.1 Airframe warranty ............................................................................................44 7.3.2 Engine warranty...............................................................................................44

8 TRAINING ...................................................................................................................45

8.1 AGUSTA-WESTLAND TRAINING CENTERS...................................................................45

8.1.1 The School ......................................................................................................45

8.2 TRAINING COURSES ...............................................................................................45


THF-A119-0607-1 VII

9 USEFUL INFORMATION ........................................................................................... 46


VIII THF-A119-0607-1

1 INTRODUCTION

The A119 KOALA is an 8 seats, light single turbine helicopter. It has been developed to provide a high power level and excellent performance, as well as:

- maximum operational capability for the operator - high versatility, from passenger transport to aerial work and EMS operations - low operating costs

1.1 MAIN CHARACTERISTICS The main characteristics of the A119 KOALA are the following:

- Functional cabin layout designed for high operational flexibility and for rapid and easy reconfiguration possibility (7 passengers and 1 pilot or 1/2 litters and 4/2 medical attendants in addition to 2 pilots)

- Large separate baggage compartment with up to 2.3 m of max length - Second multipurpose baggage compartment accessible from the cabin to be used also as

accommodation for the two longitudinal litters or for additional fuel tanks - Skid type landing gear - Titanium main rotor hub with composite grips and blades and with elastomeric bearings - Steel tail rotor hub with two composite blades, individually interchangeable - Pratt & Whitney PT6B-37A turbo shaft engine - Excellent flying qualities, high controllability and manoeuvrability. - Operative from - 35°C up to + 50°C - Great safety, "fail safe" design and redundancy of all main systems - Reduced maintenance requirements due to the wide use of reliable and on condition

components - High availability through different inspection program options - Maintenance programs at guaranteed cost available either for the airframe or the engine

1.2 APPLICATIONS The great flexibility of the cabin lay-out and the wide range of optional equipment available make the A119 KOALA suitable for different applications such as:

- Passenger transport - VIP and Corporate transportation - Aerial Work (fire fighting, sling load carrying, news gathering, etc) - Emergency Medical Service - Law Enforcement - Off-Shore - Training


THF-A119-0607-1 1

2 LEADING FEATURES

The A119 KOALA is a lightweight, multipurpose helicopter with eight seats. The helicopter has a four composite blades, fully articulated main rotor with elastomeric bearings and a teetering two bladed tail rotor system. The fuselage and the empennage are of aluminum alloy for the primary structure and of fibre composite material for the secondary structure. The landing gear is of skid type.

2.1 CERTIFICATION (TYPE AND OPERATIONAL APPROVAL) The helicopter is designed and certified in compliance with:

► FAR PART 27 Amendment 1 to 8 included and from 11 to 29 where applicable

► JAR PART 27 Base Minus

► A109 Nr. 27-54-EU-17 Special Conditions for helicopter


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2.2 EXTERNAL DIMENSIONS

FUSELAGE

Length 11.17 m 36.65 ft

Width (elevator) 2.88 m 9.45 ft

Height (tail fin) 3.77 m 12 37 ft

Fuselage ground clearance 0.54 m 1.77 ft

ROTORS

Main rotor diameter 10.83 m 35.53 ft

Tail rotor diameter 1.94 m 6.36 ft

LANDING GEAR

Track 2.00 m 6.56 ft

OVERALL DIMENSIONS

Length (rotors turning) 13.02 m 42.70 ft

Width (main rotor blade at 45°) 7.66 m 25.13 ft

Main rotor clearance (rotor turning, controls in neutral position) 2.54 m 8.33 ft

Tail rotor clearance (rotor turning) 1.32 m 4.33 ft


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External dimensions (m/ft)


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2.3 INTERNAL DIMENSIONS AND VOLUMES

COCKPIT

Max length 1.38 m 4.53 ft

Max width 1.59 m 5.22 ft

Max height 1.36 m 4.46 ft

Volume 1.51 m3 53.33 ft3

CABIN

Max length 2.10 m 6.89 ft

Max width 1.61 m 5.28 ft


Volume 3.45 m3 121.84 ft3

BAGGAGE COMPARTMENT

Max length (with optional baggage extension) 2.30 m 7.54 ft

Max width 1.10 m 3.61ft


Volume1 0.95 m3 33.55 ft3

1 Max load: 150 kg – 330 lb


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Internal dimensions (m/ft)


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2.4 WEIGHTS The Basic Empty Weight takes account of the main aircraft structure and all the essential equipment. The complete description of the basic configuration is given in Section 3.1 (Para. 3.1.1a to 3.1.1j included). The Maximum Gross Weight, relating to internal loads is 2720 kg (5997 lb).

Weights kg Lb

BASIC EMPTY WEIGHT2 1430 3153

MAX GROSS WEIGHT (internal loads) 2720 5997

MAX GROSS WEIGHT (external loads) 3150 6945

2.5 SLING LOAD CAPACITY On request, the helicopter can be equipped with a single/dual cargo hook and/or a rescue hoist. The maximum sling load capabilities are shown in the table below.

Lifting capacity kg Lb

Primary cargo hook 1400 3086

Secondary hook 500 1102

Rescue hoist 204 450

2 Weight tolerance ±2%


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2.6 FUEL CAPACITY

The fuel system is of modular-type with different capacities. The basic system is made of 3 cells, while other two optional configurations are available with the addition of the fourth and the fifth fuel cell. Refuelling is performed by gravity through a single point positioned on the right of the fuselage.

Total capacity∗

kg lb l USG

3-CELL fuel system 484 1067 605 160



2.7 POWERPLANT

Manufacturer and type: Pratt & Whitney PT6B-37A

Power Ratings (Sea Level, ISA)

kW shp Takeoff power (5 min) 747 1002

Maximum continuous power 650 872

2.8 TRANSMISSION

Manufacturer: Agusta

Power Rating∗∗

kW shp Takeoff power (5 min) 671 900

Maximum continuous power 671 900

∗ Unusable fuel: 8 kg – 17.6 lb for all three tank configurations. Fuel density is assumed at 0.8 kg/l ∗∗ Rating applicable at 100% rotor speed (384 rpm)


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2.9 OPERATIONAL ENVELOPE

2.9.1 Maximum operational flight speed – ISA Sea level

Never exceed speed VNE: 152 kts up to 2720 kg Maximum sideward speed: 35/40 kts Maximum rearward speed: 40 kts

2.9.2 Wind envelope

The wind/ground speed azimuth envelope depicted below is applicable to all loading conditions for hover in ground effect up to takeoff power.

Wind/ground speed azimuth envelope (from sea level to 3000 ft)


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2.9.3 Flight load factors

The flight load factor limits that apply to the A119 KOALA operations at MGW are:

► 2.5 g POSITIVE

► 0.5 g NEGATIVE

2.9.4 Slope landing

Takeoff and landing on terrain with slope is possible, within the weight envelope, up to the following limits:

► 12° LONGITUDINAL (nose-up)

► 2° LONGITUDINAL (nose-down)

► 10° LATERAL

2.9.5 Temperature and altitude

The helicopter and its components are designed to operate in the air temperature and altitude range defined below.

− Temperature: from -35°C to +50°C

− Maximum operating pressure altitude: 15000 ft (4572 m)

− Maximum pressure altitude for takeoff and landing: 15000 ft (4572 m)


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2.10 CG ENVELOPE The following charts show the centre of gravity range limits.

2.10.1 CG longitudinal and lateral envelope

LONGITUDINAL C of G LIMITS

4000

4500

5000

5500

6000

1600

1800

2000

2200

2400

2600

2800

3200 3300 3400 3500 3600

LONGITUDINAL STATION mm

GR

OSS

WEG

HT

(kg)

GR

OSS

WEI

GH

T (lb

)

CG longitudinal∗ envelope

LATERAL C of G LIMITS

5500

5000

4500

4000

6000

1600

1800

2000

2200

2400

2600

2800

-80 -60 -40 -20 0 20 40 60 80

LATERAL STATION mm

GR

OSS

WEI

GH

T (k

g)

GR

OSS

WEI

GH

T (lb

)

CG lateral envelope

∗ Station 0.0 mm is situated 215 mm aft the radome tip


THF-A119-0607-1 11

2.11 PERFORMANCE SUMMARY TABLES

2.11.1 Sea level

Gross weight 2550 kg – 5622 lb 2720 kg – 5996 lb

ISA ISA+20°C ISA ISA+20°C

kts 139 131 138 130 MAXIMUM CRUISE SPEED (TAS)

km/h 257 243 256 241

kts 118 121 120 122 RECOMMENDED CRUISE SPEED3 (TAS)

km/h 219 224 222 226

ft/min 1980 1780 1830 1610 RATE OF CLIMB (TOP)

m/s 10.05 9.04 9.29 8.17

3-CELL MAX RANGE4 nm 334 335 329 329 476 kg usable fuel – no reserve km 619 621 609 609

3-CELL MAX ENDURANCE

476 kg usable fuel – no reserve h:min 3:38 3:34 3:31 3:28

5-CELL MAX RANGE nm 488 490 480 481 688 kg usable fuel – no reserve km 904 907 889 891



2.11.2 5000 ft



kts 140 132 139 131 MAXIMUM CRUISE SPEED (TAS)

km/h 259 244 257 243

kts 121 122 122 123 RECOMMENDED CRUISE SPEED (TAS)

km/h 224 226 226 228

ft/min 1780 1490 1640 1330 RATE OF CLIMB (TOP)

m/s 9.04 7.56 8.33 6.75

3-CELL MAX RANGE nm 382 382 374 374 476 kg usable fuel – no reserve km 707 707 692 692



5-CELL MAX MAX RANGE nm 560 560 547 548 688 kg usable fuel – no reserve km 1036 1036 1013 1015

5-CELL MAX MAX ENDURANCE


3 The recommended cruise speed is the speed corresponding to the 99% of the lowest specific fuel consumption (nm/kg

of fuel) for given environmental condition and weight. 4 The maximum range is evaluated at the Best range speed, that is the speed corresponding to the lowest specific fuel

consumption for given environmental condition and weight.


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2.11.3 Altitude performance



ft 14600 11900 4000 1800 HIGE (TOP)

m 4450 3627 1219 549

ft 10700 7800 4000 1800 HOGE (TOP)

m 3261 2377 1219 549

SERVICE CEILING (MCP)5 ft >20000 17500 18700 15600 (100 ft/min ROC) m >6096 5334 5700 4755

2.12 ENVIRONMENTAL IMPACT

2.12.1 External noise level

The external noise level does not exceed the values specified by the last amendment 7 (2002) to the ICAO International Standards and Recommended Practices, Environmental Protection, Annex 16, Vol. I – Aircraft Noise, Ch. 8.

Corrected Noise Level SEL dB(A)

83.5

2.12.2 Internal noise level

The internal noise level may vary according to the internal soundproofing configuration. Standard soundproofing type noise level is shown below.

Speech Interference

Level Soundproofing type

SILdB

Standard 85.2

5 certified up to15000 ft


THF-A119-0607-1 13

3 STANDARD CONFIGURATION AND OPTIONAL EQUIPMENT LIST

This section provides information on the aircraft standard configuration and optional interior and equipment available for the A119 KOALA and includes the following:

Section 3.1: Description of the A119 KOALA Standard configuration Section 3.2: Completions Section 3.3: Optional equipment, available to customise the aircraft for specific applications

3.1 STANDARD CONFIGURATION (EASA/FAA VFR) The helicopter Standard configuration incorporates the following main subsystems described in detail in this section:

Basic aircraft

Standard additional equipment

VFR Avionic package

Additional installed avionic equipment

Additional utility equipment

Interior and comfort

Painting

Miscellaneous equipment

3.1.1 Basic aircraft 1430 kg (3153 lb)*

The A119 Koala basic configuration, which the BASIC EMPTY WEIGHT refers to (see Para.2.4 is inclusive of all the equipment listed in this section, from point (a) to (j).

a. Airframe

− Aluminum alloy and bonded panel fuselage

− Semimonocoque aluminum alloy tail boom

− Skid type landing gear

− Two jettisonable crew doors (LH & RH)

− Two passenger sliding doors (LH & RH) with jettisonable window

− Acrylic windshield and side windows

− Acrylic overhead windows

− Removable fiberglass tail rotor gearbox fairing

− Quick removable tail rotor drive shaft cover

− Separate baggage compartment with hinged door

* Weight tolerance ±2% - Basic aircraft weight includes transmission and engine oil as well as unusable fuel.


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− Three jacking points

− Removable fairing and cowlings providing complete accessibility to the controls and drive components.

− Quick opening hinged inspection doors to allow visual check of engine oil levels and maintenance inspection points

− Grounding points

b. Rotors and controls

− Titanium metal main rotor hub, corrosion protected, fully articulated with four composite grips, four elastomeric bearings, four individually interchangeable composite blades, swept tips, and dampers

− Steel metal tail rotor hub, teetering, delta-3, hinged type, with two composite blades, individually interchangeable

− Cyclic and collective controls powered by two hydraulic systems

− Hydraulically powered anti torque system

− Adjustable friction devices on cyclic and collective system

− Force trim and artificial feel system

− Adjustable directional control pedals

− Dynamic flapping limitator mechanism

c. Power plant and fuel system

− Pratt & Whitney PT6-B37A turboshaft engine

− Engine mounted fuel pump and filter assembly

− Engine mounted oil pump and filter assembly

− Engine mounted fuel control and governor

− Electronic engine control (EEC)

− Lubrication and cooling system

− Engine oil chip detector (1)

− Engine mounted fuel heater

− RH refueling point

− Fuel system control panel

− Three fuel cells (605 l)

− Submerged fuel pumps (2 boost and 1 transfer pump)


THF-A119-0607-1 15

d. Transmission drive system

− 900 SHP for take off and continuous operation main transmission

− Two stage transmission

− Two transmission mounted hydraulic pumps with separate reservoir

− Internal dry sump transmission lubrication with pressure and scavenge pump, and oil filter

− Transmission oil chip detectors (2)

− Single stage, bevel gear T/R 90° gear box including oil level sight glass and chip detector

− Transmission cooling and lubrication system

− Transmission shafts (engine to main transmission, engine to tail transmission, transmission to blower)

e. Electrical system

− 28 volt DC 22 Ah nickel cadmium battery with temperature probe

− 200 Ampere self cooled starter generator

− Voltage regulator

− Battery relay

− Interconnecting bus relay

− External power relay

− Distribution buses (2)

− External power receptacle

− Position lights

− 250 W landing lights (2)

− Utility lights (2)

− Anti collision lights (2)

− Instrument lights with dimming knob

f. Flight instruments – pilot

− Barometric encoding altimeter

− Air speed indicator

− Vertical speed indicator

− Magnetic compass indicator

− Clock, 8 days and elapsed time

− Dual tachometer backup instrument


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g. Instrumentation (on IDS display)

− Inter Turbine Gas Temperature (ITT °C)

− Engine Torque (TQ %)

− Compressor Speed (N1 %)

− Turbine Speed (N2 %)

− Rotor Speed (NR %)

− Engine Oil Pressure (PSI) and Temperature (°C)

− Transmission Oil Pressure (PSI) and Temperature (°C)

− Fuel Pressure (PSI) and Fuel Quantity (kg)

− Hydraulic pressure (PSI) system 1 & 2

− DC current (Amp)

− DC voltage (VDC)

− AC voltages (VAC 1 & 2)

h. Warning/caution advisory and maintenance system

− Master caution lights

− Master warning lights

− Aural warning generator

i. Interior arrangement

− Two individual pilot seats, fore and aft adjustable, with lap belts

− Aluminum alloy honeycomb reinforced floor with anti skid finish

− Ventilation ram air inlets

− Anti reflection instrument panel

j. Exterior finishing

− Finishing in accordance with manufacturer specification NTA893A

− Primer exterior painting


THF-A119-0607-1 17

3.1.2 Standard additional equipment 15.2 kg (33.5 lb)*

(Installed in current production aircraft) − Cabin Fire extinguisher

− Crew Open Door Actuators

− First Aid Kit

− Pilot/copilot shoulder harness with inertial reel

− Quick disconnecting Chip Detectors

− Baggage Compartment Light

− Tail Boom Strake

− Fuel Drain Electrical Valves

− Radio Master Switch

− 27 Ah Battery (in lieu of 22 Ah battery)

3.1.3 VFR Avionic package 28.0 kg (61.7 lb)*

− VHF-COM/GPS (Garmin 250XL) Installation & Provision

− ICS Pilot (AG06 – 1U) Installation & Provision (incl. 1 Control panel and 2+4 Headsets)

− Gyrocompass (Honeywell C14A) Installation & Provision

− Pilot navigation instruments including the following instruments or equivalent: ADI & HSI

− Transponder (KT 70) Mode (S) Installation & Provision

− ADF (KR 87) Installation & provision

3.1.4 Additional installed avionic equipment 28.7 kg (63.3 lb)

− AFCS 3 Axis Duplex (Honeywell SP711)

− AC system (2 inverters)

3.1.5 Additional utility equipment 29.3 kg (64.6 lb)

− Rotor brake

− Pilot and copilot bird resistant windshield

− Pilot and copilot windshield wipers

− Baggage compartment extension (1.9 m)

− Dual control

* Weight tolerance ±2%


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3.1.6 Interior and comfort 20.5 kg (45.2 lb)− Heater Bleed Air

− Primer finishing cabin walls

− Vibration Dampers Installation

3.1.7 Painting 10.0 kg (22.0 lb)− Single colour painting. Solid colour series 300

STANDARD CONFIGURATION WEIGHT 1562 kg (3443 lb)*

(Para. 3.1.1 to 3.1.7)

3.1.8 Miscellaneous equipment − Air intake/exhaust covers

− Pitot tubes covers

− Tie-down fitting provisions

− Ground tools kit (including tow bar, lifting tool, ground wheels)

− Rotorcraft Flight Manual and technical publications


THF-A119-0607-1 19

3.2 COMPLETIONS Versatility of the A119 KOALA is reflected by the number of roles in which it can be employed. The following interior layout configurations and optional equipment are available as additional installation or alternatives to the standard interior as detailed in section 3.1.

3.2.1 Corporate interior 69.4 kg (152.9 lb)*

− All seats covered with fabric

− 3-seat central bench

− 3-seat aft bench

− 3 points shoulder harness with inertia reels and safety belts for all pax

− Reading lights

− Advisory lights

− Floor carpeting

− Upholstery tinted panels

− Soundproofing

3.2.1.1 Corporate interior optional equipment kg (lb)*

− Leather covering 6 pax seats with armrest + 2 pilot seats tbd

3.2.2 VIP interior 78.7 kg (173.5 lb)*

− All Seats covered with leather

− 3 Seats. central bench

− 3 Seats. aft bench

− 3 Points shoulder harness with inertia reels and safety belts for all pax

− Reading lights

− Advisory lights − Floor carpeting

− Upholstery leatherette covered panels

− Soundproofing

3.2.2.1 VIP optional equipment kg (lb)*

− Chest of single drawer 3.1 (6.8)

− Chest of three drawers 8.8 (19.4)


THE DATA CONTAINED IN THIS DOCUMENT ARE GENERAL IN NATURE AND THEY MAY VARY WITH CONDITIONS. FOR PERFORMANCE DATA AND OPERATING LIMITATIONS FOR ANY SPECIFIC FLIGHT MISSION, REFERENCE MUST BE MADE TO THE APPROVED FLIGHT MANUAL. SPECIFICATION SUBJECT TO CHANGE WITHOUT NOTICE.

20 THF-A119-0607-1

− Pilot console tray 1.5 (3.3)

− Pilot multipurpose holder 2.9 (6.4)

− Rear cabinet 7.0 (15.4)

− 5/6 Pax conversion kit (seating module replacing the aft cabinet) -4.0 (-8.8)

3.2.3 Convertible interior 64.4 kg (141.9 lb)*− All Seats covered with fabric

− 3 seats central bench with 3 individually foldable back panel

− 3 seats aft bench with 3 individually foldable back panel

− Provision for locking system for litters on back panel seats. aft & cent. bench

− 3 points shoulder harness with inertia reels and safety belts for all pax

− Reading lights

− Advisory lights

− Floor carpeting


− Soundproofing

3.2.3.1 Convertible interior optional equipment kg (lb)*

− Foldable litter (q.ty 1). with locking mechanism 12.6 (27.8)

− 6 Pax seats cushions (seat, backrest and headrest) with Leather covering (in lieu of fabric covering) tbd

− 6 Pax seats cushions (seat, backrest and headrest) with fabric covering tbd

− Sliding and rotating operator seat with rails 15.5 (34.2)

3.2.4 EMS (Emergency Medical Service) interior

a. Fixed parts for Single/Dual litter EMS interior 77.0 kg (169.7 lb)*

− Head liner with EMS provisions

− Side liners LH/RH with EMS provisions

− Aft EMS liners with rails

− Bench panel with rear EMS provisions

− Provision for litter platform

− Cargo net provisions

− Floor equipped with rails and provisions



THF-A119-0607-1 21

− EMS electrical system

− EMS copilot reversible seats

− Electrical outlets (12 VDC / 28 VDC)

− 3rd ICS station in pax cabin − Medical oxygen system provision(2)

− Sliders on cabin doors


− Soundproofing

b. Single litter installation (removable parts) 65.8 kg (145.1 lb)*− Doctor sliding and rotating seats

− Primary litter platform with front lock mechanism

− Litter (q.ty 1)

− Two foldable aft. fwd facing seats with head rest

− Safety-belts with shoulder harness

− Storage compartment

− Oxygen bottle in baggage compartment (2) − Special rubber floor carpet

− Interior cargo net

bb.1 Dual litter installation (additional parts) 15.8 kg (34.8 lb)*− Second litter provision & rear lock mechanism (installed)

− Second litter platform with front lock mechanism

− Foldable litter (q.ty 1)

3.2.4.1 EMS optional equipment 40.4 kg (89.1lb)*

− Pax. conversion Kit. including: Central bench 3 places. fabric covering Cushions and back for 3 foldable forward facing seats Headrest. q.ty 3 Additional floor carpet Single foldable fwd facing seat



22 THF-A119-0607-1

3.3 OPTIONAL EQUIPMENT The interior and comfort, utility, avionic and mission equipment listed below is available to satisfy specific role requirements. The list is provisional and subject to change, and also some incompatibilities of installation may apply. AgustaWestland should be contacted to ensure a consistent configuration build-up.

3.3.1 Interior and comfort equipment

Weight*

Item kg lb Air conditioning(1) 40.8 90.0

Upholstery leatherette covered panels 14.5 31.9

3.3.2 Utility equipment

Weight*

Item kg lb Hour meter 0.4 1.0 Baggage extension (2.3 m) 4.9 10.8 188 US Gall Fuel System 6.8 15.0 230 US Gall Fuel System 13.0 28.7 Cargo Hook, complete provision 3.5 7.7 Cargo Hook 1400 Kg & Rear view mirror 11.6 25.6 Cargo Hook 500 Kg (available if 1400 kg cargo hook is installed) 6.0 13.2 Provision for Bambi bucket 1.5 3.3 Bambi bucket kit (Model 2024 – 910 l) – removable parts 65.0 143.3 External Hoist, complete provision 6.2 13.7 External Hoist 450 lbs 40.1 88.4 DART Bearpaws (1) 7.0 15.4 Snow skis 37.8 83.3 APICAL Emergency floats, kit(1) 75.4 165.9 APICAL Emergency floats with life rafts, kit(1) 112.4 247.4 SIMPLEX fire fighting tank provision and antennas relocation 1.0 2.2 SIMPLEX fire fighting tank & fittings(1) 180.0 396.0 Retractable landing light 450 W 3.5 7.7



THF-A119-0607-1 23

3.3.2 Utility equipment (continue)

Weight*

Item kg lb Engine particle separator 8.6 19.0 Wire strike protection system 10.3 22.7 Rapelling Kit (2 LH+2RH) (Ropes Excluded) 8.5 18.7 Flight step LH(1) 5.2 11.5 Flight step RH(1) 5.2 11.5 Mechanical retractable external rear view mirror(1) 1.0 2.2

3.3.3 Additional avionics

Weight*

Item kg lb VHF-COM/NAV (KX 165 A) installation 5.1 11.2 DME (KN 62A) installation and provision 1.6 3.5 Marker Beacon (KR 21) installation and provision 1.6 3.5 Radio Altimeter (AA 300) installation and provision 4.2 9.3 ELT (EBC 502 H) 1.3 2.9 ELT C406-2HM Artex (3 frequencies) 3.4 7.5 ICS Pilot (2nd Control panel) AGU-06-1U 1.8 4.0 Active noise reduction headsets (each) 0.6 1.3 Stand-by artificial horizon 3.0 6.6

3.3.4 Additional mission equipment only by FAA STC

Weight*

Item kg lb

Super Night Scanner Search Light 3.5 7.7

SX-5 Search light (provision) 5.0 11.0

SX-5 Search Light (removable parts) 10.0 22.0

Spectrolab Nightsun SX-16 Search Light (provision) 8.3 18.3

Spectrolab Nightsun SX-16 Search Light (removable parts) 22.0 48.5

External Loudspeakers (provision) 4.0 8.8 External Loudspeakers installation (removable parts) 6.8 15.0



24 THF-A119-0607-1

3.3.4 Additional mission equipment only by FAA STC (continue)

Weight*

Item kg lb SIMPLEX electrical heated external rear view mirror 7.0 15.4 FLIR Ultra 7500 (provision) 4.5 10.0

FLIR Ultra 7500 (installation) 18.4 40.5

FLIR WESCAM M12DS200 24.0 53.0 WESCAM Antenna Skypod V airborne microwave system tbd tbd WULFSBERG FLEXCOM II Multiband VHF/UHF – AM/FM 17.4 38.3

TYLER LH–RH Tactical Platform installed on skid landing gear tbd tbd

DEVORE Recognition Lights tbd tbd

DEVORE Tel-Tail vertical tail and tail rotor flood lighting 1.6 3.5

ALTAIR Engine monitor system for Koala with IDS tbd tbd

AFS Engine barrier filter tbd tbd

KEYESTONE liquid oxygen system, 10 litres tbd tbd

Aeronautical accessories, high visibility cockpit door window tbd tbd

Pilot and copilot pedal extension tbd tbd

3.3.5 Painting

Weight*

Item kg lb Customer painting scheme with solid colour series 300. (additional to std. scheme)

From 5.0 to 10.0

From 11.0 to 22.0

Customised painting scheme with metallic colour series 500. (additional to std. scheme)

From 10.0 to 15.0

From 22.0 to 33.1

NOTES: (1) FAA STC validated by EASA (2) The E.M.S. interior may also be fitted without the Medical oxygen system provision (kg 6.0 - 13.2 lbs) and the Oxygen bottle (kg 14.0 - 30.8 lbs) installation (*) Weight Tolerance ± 2%.


THF-A119-0607-1 25

Typical instrument panel

Integrated Display System (IDS)


26 THF-A119-0607-1

4 PERFORMANCE DIAGRAMS

This Section contains the A119 KOALA flight performance charts illustrating:

4.1 HOVERING

Hovering IGE (TOP)

Hovering OGE (TOP)

4.2 RATE OF CLIMB

Rate of climb 2550 kg MTOW

Rate of climb 2720 kg MTOW

4.3 FUEL CONSUMPTION VS AIRSPEED

Fuel consumption vs Airspeed – SL (ISA)

Fuel consumption vs Airspeed – SL (ISA + 20°C)

Fuel consumption vs Airspeed – 5000 ft (ISA)

Fuel consumption vs Airspeed – 5000 ft (ISA + 20°C)


THF-A119-0607-1 27

4.1 HOVERING

4.1.1 Hovering IGE (TOP)

HOVERING IGE - (TOP)

ISA + 20

ISA

0

2000

4000

6000

8000

10000

12000

14000

23 24 25 26 27 28

GROSS WEIGHT - kg x 100

PRE

SSUR

E AL

TITU

DE

- ft

0

500

1000

1500

2000

2500

3000

3500

4000

4500

51 53 55 57 59 61

GROSS WEIGHT - lb x 100

PRES

SURE

ALT

ITU

DE -

m


28 THF-A119-0607-1

4.1.2 Hovering OGE (TOP)

HOVERING OGE - (TOP)

ISA + 20

ISA

external load

0

2000

4000

6000

8000

10000

12000

14000

20 22 24 26 28 30 32

GROSS WEIGHT - kg x 100

PRE

SSU

RE

ALT

ITU

DE

- ft

0

500

1000

1500

2000

2500

3000

3500

4000

4500

44 48 52 56 60 64 68

GROSS WEIGHT - lb x 100

PR

ESS

URE

ALT

ITU

DE -

m


THF-A119-0607-1 29

4.2 RATE OF CLIMB

4.2.1 Rate of climb 2550 Kg MGW

RATE OF CLIMB - TOP (2550 kg)

ISA

ISA+20

0

2

4

6

8

10

12

14

0 4 8 12 16 20

RATE OF CLIMB - ft/minX100

PRES

SUR

E AL

TITU

DE

- ftX

1000

0

5

10

15

20

25

30

35

40

450 1 2 3 4 5 6 7 8 9 10 11

RATE OF CLIMB - m/s

PRES

SUR

E AL

TITU

DE

- mX

100

ROTOR: 100%HEATER OFFELECTRICAL LOAD: 100A


30 THF-A119-0607-1

4.2.2 Rate of climb 2720 Kg MGW

RATE OF CLIMB - TOP (2720 kg)

ISA+20

ISA

0

2

4

6

8

10

12

14

0 4 8 12 16 20

RATE OF CLIMB - ft/minX100

PRE

SS

URE

ALT

ITU

DE

- ft

0

5

10

15

20

25

30

35

40

450 1 2 3 4 5 6 7 8 9 10 11

RATE OF CLIMB - m/s

PR

ES

SURE

ALT

ITUD

E -

mX

100

ROTOR: 100%HEATER OFFELECTRICAL LOAD: 100A


THF-A119-0607-1 31

4.3 FUEL CONSUMPTION VS AIRSPEED

4.3.1 Fuel consumption vs Airspeed – SL (ISA)

FUEL FLOW - SL (ISA)

2720kg

2500 kg

2100 kg

MCP LIMIT

RECOMMENDED CRUISE SPEED

BEST ENDURANCE SPEED

TOP LIMIT

100

120

140

160

180

200

220

240

50 70 90 110 130 150

TRUE AIRSPEED - kts

FUEL

FLO

W -

kg/h

220

240

260

280

300

320

340

360

380

400

420

440

460

480

500

520

540

93 123 153 183 213 243 273

TRUE AIRSPEED - km/h

FUEL

FLO

W -

lb/h


32 THF-A119-0607-1

4.3.2 Fuel consumption vs Airspeed – SL (ISA + 20°C)

FUEL FLOW - SL (ISA+20)

2720kg

2500 kg

2100 kg

MCP LIMIT



TOP LIMIT

100

120

140

160

180

200

220

50 70 90 110 130 150

TRUE AIRSPEED - kts

FUEL

FLO

W -

kg/h

220

240

260

280

300

320

340

360

380

400

420

440

460

480

500

93 123 153 183 213 243 273


FUEL

FLO

W -

lb/h


THF-A119-0607-1 33

4.3.3 Fuel consumption vs Airspeed – 5000 ft (ISA)

FUEL FLOW - 5000 ft (ISA)

2720 kg

2500 kg

2100 kg

MCP LIMIT



TOP LIMIT

100

120

140

160

180

200

220

50 70 90 110 130 150

TRUE AIRSPEED - kts

FUEL

FLO

W -

kg/h

220

240

260

280

300

320

340

360

380

400

420

440

460

480

93 123 153 183 213 243 273


FUEL

FLO

W -

lb/h


34 THF-A119-0607-1

4.3.4 Fuel consumption vs Airspeed – 5000 ft (ISA + 20°C)

FUEL FLOW - 5000 ft (ISA+20)

2720kg

2500 kg

2100 kg

MCP LIMIT



TOP LIMIT

100

120

140

160

180

200

50 70 90 110 130 150

TRUE AIRSPEED - kts

FUEL

FLO

W -

kg/h

220

240

260

280

300

320

340

360

380

400

420

440

460

93 123 153 183 213 243 273


FUEL

FLO

W -

lb/h


THF-A119-0607-1 35

5 SUPPORT AND MAINTENANCE

5.1 INSPECTION PROGRAMMES

In order to best suit Customer needs and to ensure the maximum helicopter availability, three different inspection programs may be selected. These are designed to provide flexibility for maximum utilization of the helicopter and to most suit the operator’s needs. The inspection programmes are identified as follows:

a. Standard Programme

The scheduled inspections consist of an airworthiness check, 300/annual inspection and 2400 hour inspection.

Standard Inspection Programme scheme

b. Extended Programme

The scheduled inspections consist of a basic 25 hours/30 days inspection, 300 flight hours/annual inspection and 2400 hour inspection.

Extended Inspection Programme scheme


36 THF-A119-0607-1

c. Progressive Programme

The scheduled inspections consist of an airworthiness check, progressive 300/annual inspection (divided into six phases) and 2400 hour inspection. The operator may decide to interrupt one program and revert to another according to defined procedure.

Progressive Inspection Programme Scheme

5.2 OVERHAUL COMPONENTS The components subject to overhaul are listed in the following table.

Item Quantity per A/C

TBO (FH)

Starter Generator 1 1000

Main Transmission Assy 1 4800

Tail Rotor Hub assembly 1 3600

Main Rotor Servo Actuator 3 1800

Tail Rotor Servo Actuator 1 1800

Co-Pilot Collective Stick assembly 1 6000

Pilot Collective Stick assembly 1 6000

Most parts are on–condition and will be inspected via the preventive maintenance program process. Detailed information about components subject to overhaul, with the relevant prices, is available through AgustaWestland Customer Support.


THF-A119-0607-1 37

5.3 RETIREMENT LIFE The components subject to retirement are listed in the following table.

Item Quantity per A/C

Retirement Life (FH)

Fwd Cross Tube Assy (Landing gear) 1 13000

Aft. Cross Tube Assy (Landing gear) 1 14000

Stabilizer (Fuselage) 1 9000

Main Rotor Blade 4 15000

Rod.Aft. (Transmission) 1 5900

Cover Assy (Transmission) 1 10000

Strap Plug (Tail rotor) 2 5000

Hub Assy (Tail rotor) 1 3000

Strap Pin (Tail rotor) 2 5000

Bolt (Tail rotor) 2 5000

Tail Rotor Blade 2 15000

Support Swashplate 1 11000

Bolt (Main rotor control) 2 2700

Control Rod (Tail rotor control) 2 1000


38 THF-A119-0607-1

6 DIRECT OPERATING COST (DOC)

This section provides information on the Direct Operating Costs (DOC) associated with typical A119 KOALA operations. It is assumed that the helicopter is civil certified and operates in a temperate climate in a non-corrosive environment (recommended anti-corrosive measures must be observed for off-shore operations and adequate protection from weather provided when not flying, etc.). The DOC reflects the aircraft operated, maintained and supported using the recommended tooling and facilities by experienced personnel in defined working conditions. It is assumed that the helicopter is in basic configuration without any optional equipment. DOC information has been estimated in accordance with the Helicopter Association International (HAI) methodology. Since the DOC may vary depending upon parameters such as FH per Year, Operational Life, Engine Cycle etc., a typical usage spectrum for a Corporate configuration has been analysed:

- 300 FH per year - 10 years as reference period - 1 Landing per FH - 1 Engine cycle per FH

Direct Costs are, by definition, those that are related directly to each hour flown covering:

- Fuel and lubricants - Airframe direct maintenance - Power plant maintenance

The following description provides the rationale of the data included within.

6.1 FUEL AND LUBRICANTS The data shown reflects the average fuel consumption assuming operation at the optimum range speed, at 1000 ft altitude, and ISA conditions. Customers' actual fuel consumption may vary depending on many factors, including: speed, temperature, weight, altitude, helicopter configuration, and mission. Depending on these factors, the average fuel consumption could increase by 10%. The cost of lubricants is estimated at 3% of the cost of the fuel.

6.2 AIRFRAME DIRECT MAINTENANCE The airframe direct maintenance cost estimates are provided in the categories of line maintenance labour and parts.

a. Labour

The estimated labour costs includes the time required to conduct scheduled inspections, perform the removal and replacement of Overhaul and Retirement Parts, and to conduct unscheduled maintenance as required.


THF-A119-0607-1 39

b. Parts

- Inspections consumables - Data shown refers to the cost of the parts replaced during scheduled inspections.

- Unscheduled - Data shown refers to components repair cost (including parts and labour) and replacement of non-repairable parts for unscheduled maintenance.

- Overhaul - Data shown refers to the average overhaul (including parts and labour) for major dynamic components with scheduled time between overhaul (TBO) intervals.

- Life Limit - Data shown refers to the replacement cost of all components with a mandatory retirement life.

6.3 POWER PLANT MAINTENANCE The powerplant direct operating cost estimate includes costs for periodic inspections and overhauls as per P&WC Engine Maintenance Cost for PT6B-37A. Since the engine overhaul interval is bound by both operating hours, and engine cycles, the engine cycles assumed in each Engine Maintenance Cost estimation are detailed in the main assumptions table to respect the different mission profiles. It is assumed that the aircraft powerplant overhaul is performed by the engine manufacturer.

The table below reports detailed information about estimated DOC. Further information is available through AgustaWestland Customer Support and Marketing Organisations.

Economic Conditions January 2006 Operator MMH/FH

Hourly Op. Cost (USD)

Fuel and lubricants Fuel6 56 USG/h at 124 kts 126.00Lubricants 3% of fuel cost 3.78 Direct Maintenance Airframe Line Maintenance Labour7: - Scheduled Maintenance 0.73 47.72 - Unscheduled Maintenance 0.24 15.60Airframe Parts: - Inspections Consumables 2.00 - Unscheduled 110.62 - Overhaul Components 14.90 - Life-Limited Parts 5.68 Powerplant Direct Maintenance: - Line Maintenance and Overhaul Incl. Accessories8 115.29 TOTAL DOC PER FH 441.59

6 Fuel at USD 2.25 per USG 7 Labour at USD 65.00 per hour 8 Pratt & Whitney Engine Maintenance Cost (DMC) for PT6B-37A, 1 cycle per hour


40 THF-A119-0607-1

7 SERVICE PLANS

Several service plans are available both for the airframe and the power plant of the A119 KOALA, at fixed hourly rates.

7.1 AIRFRAME MAINTENANCE PROGRAMME AgustaWestland airframe maintenance programmes are:

GSP (Global Support Plan) COMP (Complete Overhaul and Maintenance Programme) CPA (Components Protection Agreement)

Detailed information about all the three plans described in this section can be found in the appropriate AgustaWestland publications.

7.1.1 Global support plan (GSP)

For Civil Operators desiring complete coverage, including maintenance labour to ensure the highest level of operating cost assurance, AgustaWestland has assembled a comprehensive support plan which covers the basic helicopter and the required maintenance manpower. The Global Support Plan (GSP) provides labour to perform the maintenance and the repair, overhaul, replacement and/or exchange of spare parts at a fixed rate for every flight hour.

Covered components:

− Airframe components

− Avionics components

Components and items excluded:

− Engines and engine accessories

− Items with a unit price less than 200 USD

− Aircraft paint, upholstery, carpets, interior panels

− Fuel, and consumable materials

− Optional kits (can be included upon Customer request)

Plan provisions:

− Labour for scheduled and unscheduled inspections as per Chapter 5 of the Maintenance Manual (labour will be performed by the AgustaWestland authorized service centre nearest to the Customer)

− Spare parts for scheduled and unscheduled/on-condition maintenance

− Replacement parts, for items which have reached their mandatory retirement life limit

− Exchange components, for items which have reached their overhaul period (TBO)


THF-A119-0607-1 41

− Labour and Parts support for the application of Agusta mandatory technical bulletins

Plan exclusions: - Any costs attributable to abuse or misuse of the aircraft.

7.1.2 Complete overhaul and maintenance programme (COMP)

For Civil Operators desiring comprehensive coverage with an added level of operating cost assurance, AgustaWestland has assembled a special support plan which covers the basic helicopter configuration. The Complete Overhaul and Material Program (COMP) provides repair, overhaul and replacement and/or exchange spare parts at a fixed rate for every flight hour.

Covered components:

− Airframe components

− Avionics components

Components and items excluded:

− Engines and Engine Accessories.

− Optional kits (can be included upon Customer request)

− Items with a unit price less than 200 USD

− Aircraft paint, upholstery, carpets, interior panels

− Fuel, lubricants, and consumable materials

Plan provisions:

− Spare parts for scheduled and unscheduled/on-condition maintenance.

− Replacement parts, for items which have reached their mandatory retirement life limit

− Exchange components, for items which have reached their overhaul period (TBO)

− Parts support for the application of Agusta mandatory technical bulletins

Plan exclusions:

− Labour for scheduled and unscheduled/on-condition maintenance

− Any costs attributable to abuse or misuse of the aircraft

− Transportation charges

7.1.3 Component protection agreement (CPA)

CPA is specifically designed for Civil Operators desiring an added level of operating cost assurance, AgustaWestland has assembled a special support plan which covers the major components of the applicable helicopter type. The Components Protection Agreement (CPA) provides repair, overhaul and replacement for the parts covered under this Plan at a fixed rate for every flight hour.


42 THF-A119-0607-1

Main covered components:

− Main Gearbox

− Tail Rotor Gearbox

− Main & Tail Rotor Servos

− Swashplate Assembly

− Main & Tail Rotor Hub Assembly

− Main & Tail Rotor Blades

− Hydraulic Pumps

− Starter Generator

Plan provisions: − Interested spare parts for scheduled and unscheduled/on-condition maintenance. − Replacement parts, for items which have reached their mandatory retirement life limit. − Exchange components, for items which have reached their overhaul period (TBO). − Parts support for the application of Agusta mandatory technical bulletins.

Plan exclusions:

− Labour for scheduled and unscheduled/on-condition maintenance

− Any costs attributable to abuse or misuse of the aircraft

− Transportation charges

− Fuel, lubricants and consumables material

7.2 ENGINE MAINTENANCE PROGRAMME As regards the power plant, Customers are eligible to enrol the PT6B-37A engine in the Pratt & Whitney Eagle Service Plan (ESP).

7.2.1 Pratt & Whitney Canada Eagle Service Plan (ESP)

Pratt & Whitney Canada Eagle Service Plan (ESP) offers multiple options designed to cope with major scheduled and unscheduled engine and LRU/accessory maintenance.

Components covered by ESP are:

- Scheduled engine overhaul/refurbishment - Scheduled hot section inspections/refurbishment - Basic unscheduled engine maintenance - Basic unscheduled LRU/accessories - Required product support improvements at engine shop visit

For further information about these service levels and their rates, refer to the dedicated Pratt & Whitney publications.


THF-A119-0607-1 43

7.3 WARRANTIES

7.3.1 Airframe warranty

The A119 KOALA is covered by Agusta with the "TRIPLE 3" warranty. Detailed information about "TRIPLE 3" warranty are available through the AGUSTA “WARRANTY POLICY” publication.

7.3.2 Engine warranty

The PT6B-37A engine is covered by the standard Pratt & Whitney warranty.


44 THF-A119-0607-1

8 TRAINING

8.1 AGUSTA-WESTLAND TRAINING CENTERS AgustaWestland is an established provider of professional training services and solutions to a wide range of military and civil customers around the world. Along with the continued high quality of service provided to helicopter customers, the Company has extended its significant training capability into the wider training market place Training programs can be tailored to meet a customer's individual needs and operational environments using established analytical processes. Initial conversion training is available at AgustaWestland established and well-equipped Customer Training Centers located in the UK, USA, and Italy, and/or at a customer's choice of location. Furthermore, the Company designs, develops and delivers training solutions and services throughout a products' lifecycle as required to meet the demands of long-term operational support. Extensive use is made of multi-media tools and the ever expanding range of synthetic training devices ranging from e-learning, part-task maintenance and procedures trainers through to full mission and flight simulators.

8.1.1 The School

The flight school, with a line of various types of helicopter and with the professional level of its instructor pilots, is able to offer diversified services, ranging from private pilot license to the highest operational qualifications required by the most modern machines on the market today. The courses available range from basic training for unskilled personnel to the specialized training for skilled personnel, depending on the particular requirements of the Customer.

8.2 TRAINING COURSES Training courses available include:

- Pilot ground course - Pilot transition course - Airframe maintenance course - Engine line maintenance course

Specific and tailored training solutions are available to the Customer.


THF-A119-0607-1 45

9 USEFUL INFORMATION

The following are the offices you may contact for further information:

AGUSTAWESTLAND ITALY Via Giovanni Agusta, 520 21017 Cascina Costa di Samarate (VA) Italy Tel. +39 0331 229111 Fax +39 0331 229605 e-mail: [email protected]

AGUSTAWESTLAND UK Yeovil, Somerset BA20 2YB United Kingdom Tel. +44 (0) 1935 475222 Fax +44 (0) 1935 702131 e-mail: [email protected]

AGUSTA AEROSPACE SERVICES S.A. Liège Aéroport, Bldg 60 B–4460 Grace – Hollogne Belgium Tel. +32 4 2342323 Fax +32 4 2341945 e-mail: [email protected]

AGUSTA AEROSPACE CORPORATION 3050 Red lion road Philadelphia PA 19114 U.S.A. Tel. +1 (215) 281 1400 Fax +1 (215) 281 1366

Detailed information about Agusta world wide facilities and service centres are available through the relevant publication “Customer Support Directory – 2006”.

AGUSTAWESTLAND OFFICIAL WEBSITE

www.agustawestland.com


46 THF-A119-0607-1

thf-a119-0607-1.pdf

Documents

performance data

approved flight manual

specific flight mission

performance capabilities

specific aircraft usage

general information

aircraft description

particular aircraft