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.

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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.


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TABLE OF CONTENTS 1

2

INTRODUCTION ........................................................................................................... 1 1.1

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

1.2

APPLICATIONS ......................................................................................................... 1

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 2.9.2 2.9.3 2.9.4 2.9.5 2.10

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

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V

2.12.2 Internal noise level .......................................................................................... 13 3

STANDARD CONFIGURATION AND OPTIONAL EQUIPMENT LIST...................... 14 3.1 3.1.1 3.1.2 3.1.3 3.1.4 3.1.5 3.1.6 3.1.7 3.1.8 3.2

STANDARD CONFIGURATION (EASA/FAA VFR) ...................................................... 14 Basic aircraft ................................................................................................... 14 Standard additional equipment........................................................................ 18 VFR Avionic package ...................................................................................... 18 Additional installed avionic equipment ............................................................ 18 Additional utility equipment ............................................................................. 18 Interior and comfort ......................................................................................... 19 Painting ........................................................................................................... 19 Miscellaneous equipment................................................................................ 19 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 3.3.1 3.3.2 3.3.3 3.3.4 3.3.5 4

OPTIONAL EQUIPMENT ........................................................................................... 23 Interior and comfort equipment ....................................................................... 23 Utility equipment.............................................................................................. 23 Additional avionics .......................................................................................... 24 Additional mission equipment only by FAA STC ............................................. 24 Painting ........................................................................................................... 25

PERFORMANCE DIAGRAMS ................................................................................... 27 4.1 4.1.1 4.1.2 4.2 4.2.1 4.2.2

HOVERING ............................................................................................................ 28 Hovering IGE (TOP)........................................................................................ 28 Hovering OGE (TOP) ...................................................................................... 29 RATE OF CLIMB ..................................................................................................... 30 Rate of climb 2550 Kg MGW........................................................................... 30 Rate of climb 2720 Kg MGW........................................................................... 31


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4.3 4.3.1 4.3.2 4.3.3 4.3.4 5

6

7

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

SUPPORT AND MAINTENANCE ............................................................................... 36 5.1

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

5.2

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

5.3

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

DIRECT OPERATING COST (DOC)........................................................................... 39 6.1

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

6.2

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

6.3

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

SERVICE PLANS........................................................................................................ 41 7.1 7.1.1 7.1.2 7.1.3 7.2 7.2.1 7.3 7.3.1 7.3.2

8

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

AIRFRAME MAINTENANCE PROGRAMME .................................................................... 41 Global support plan (GSP)............................................................................... 41 Complete overhaul and maintenance programme (COMP)............................. 42 Component protection agreement (CPA)......................................................... 42 ENGINE MAINTENANCE PROGRAMME ........................................................................ 43 Pratt & Whitney Canada Eagle Service Plan (ESP)......................................... 43 WARRANTIES......................................................................................................... 44 Airframe warranty ............................................................................................ 44 Engine warranty............................................................................................... 44

TRAINING ................................................................................................................... 45 8.1 8.1.1 8.2

AGUSTA-WESTLAND TRAINING CENTERS................................................................... 45 The School ...................................................................................................... 45 TRAINING COURSES ............................................................................................... 45


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


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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: -

1.1

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

MAIN CHARACTERISTICS

The main characteristics of the A119 KOALA are the following: -

-

1.2

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

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


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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

Main rotor diameter

10.83 m

35.53 ft

Tail rotor diameter

1.94 m

6.36 ft

2.00 m

6.56 ft

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

ROTORS

LANDING GEAR Track OVERALL DIMENSIONS Length (rotors turning)


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3

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

3

53.33 ft3

Max length

2.10 m

6.89 ft

Max width

1.61 m

5.28 ft

Max height

1.28 m

4.20 ft

3.45 m3

121.84 ft3

Max length (with optional baggage extension)

2.30 m

7.54 ft

Max width

1.10 m

3.61ft

Max height

0.71 m

2.33 ft

0.95 m3

33.55 ft3

Volume

1.51 m

CABIN

Volume BAGGAGE COMPARTMENT

Volume1

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

2.5

kg

Lb

BASIC EMPTY WEIGHT2

1430

3153

MAX GROSS WEIGHT (internal loads)

2720

5997

MAX GROSS WEIGHT (external loads)

3150

6945

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

2

kg

Lb

Primary cargo hook

1400

3086

Secondary hook

500

1102

Rescue hoist

204

450

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∗

2.7

kg

lb

l

USG

3-CELL fuel system

484

1067

605

160

4-CELL fuel system

568

1252

711

188

5-CELL fuel system

696

1534

870

230

POWERPLANT

Manufacturer and type: Pratt & Whitney PT6B-37A

Ratings (Sea Level, ISA)

2.8

Power kW

shp

Takeoff power (5 min)

747

1002

Maximum continuous power

650

872

TRANSMISSION

Manufacturer: Agusta

Rating∗∗

∗

Power 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: Maximum sideward speed: Maximum rearward speed:

152 kts up to 2720 kg 35/40 kts 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 2800

5500 2400

5000

2200 2000

4500

1800

4000

GROSS WEIGHT (lb)

GROSS WEGHT (kg)

6000 2600

1600

3200

3300

3400

3500

3600

LONGITUDINAL STATION mm

CG longitudinal∗ envelope

GROSS WEIGHT (kg)

2800 6000 2600 5500 2400 5000 2200 4500

2000

GROSS WEIGHT (lb)

LATERAL C of G LIMITS

4000

1800 1600 -80

-60

-40

-20

0

20

40

60

80

LATERAL STATION mm

CG lateral envelope

∗

Station 0.0 mm is situated 215 mm aft the radome tip


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2.11 PERFORMANCE SUMMARY TABLES 2.11.1 Sea level Gross weight

2550 kg – 5622 lb ISA ISA+20°C

2720 kg – 5996 lb ISA ISA+20°C

kts

139

131

138

130

km/h

257

243

256

241

kts

118

121

120

122

km/h

219

224

222

226

ft/min

1980

1780

1830

1610

m/s

10.05

9.04

9.29

8.17

nm

334

335

329

329

km

619

621

609

609

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

h:min

5:22

5:16

5:11

5:06

MAXIMUM CRUISE SPEED (TAS) RECOMMENDED CRUISE SPEED3 (TAS)

RATE OF CLIMB (TOP) 3-CELL MAX RANGE

4

476 kg usable fuel – no reserve 3-CELL MAX ENDURANCE 476 kg usable fuel – no reserve

5-CELL MAX ENDURANCE 688 kg usable fuel – no reserve

2.11.2 5000 ft Gross weight

140

132

139

131

km/h

259

244

257

243

kts

121

122

122

123

km/h

224

226

226

228

ft/min

1780

1490

1640

1330

m/s

9.04

7.56

8.33

6.75

3-CELL MAX RANGE

nm

382

382

374

374


km

707

707

692

692

h:min

4:02

3:58

3:54

3:50

5-CELL MAX MAX RANGE

nm

560

560

547

548


km

1036

1036

1013

1015

h:min

5:57

5:51

5:45

5:40

RECOMMENDED CRUISE SPEED (TAS)

RATE OF CLIMB (TOP)

3-CELL MAX ENDURANCE 476 kg usable fuel – no reserve

5-CELL MAX MAX ENDURANCE 688 kg usable fuel – no reserve

4

2720 kg – 5996 lb ISA ISA+20°C

kts

MAXIMUM CRUISE SPEED (TAS)

3

2550 kg – 5622 lb ISA ISA+20°C

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. 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 Gross weight

2550 kg – 5622 lb ISA ISA+20°C

2720 kg – 5996 lb ISA ISA+20°C

14600

11900

4000

1800

m

4450

3627

1219

549

ft

10700

7800

4000

1800

m

3261

2377

1219

549

SERVICE CEILING (MCP)

ft

>20000

17500

18700

15600

(100 ft/min ROC)

m

>6096

5334

5700

4755

ft

HIGE (TOP)

HOGE (TOP) 5

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.

Soundproofing type

Standard

5

Speech Interference Level SILdB

85.2

certified up to15000 ft


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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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THF-A119-0607-1

−

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)


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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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THF-A119-0607-1

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


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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 −

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 −

AFCS 3 Axis Duplex (Honeywell SP711)

−

AC system (2 inverters)

3.1.5 Additional utility equipment

*

28.0 kg (61.7 lb)*

−

Rotor brake

−

Pilot and copilot bird resistant windshield

−

Pilot and copilot windshield wipers

−

Baggage compartment extension (1.9 m)

−

Dual control

28.7 kg (63.3 lb)

29.3 kg (64.6 lb)



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THF-A119-0607-1

3.1.6 Interior and comfort −

Heater Bleed Air

−

Primer finishing cabin walls

−

Vibration Dampers Installation

3.1.7 Painting −

20.5 kg (45.2 lb)

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


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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 −

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 −

Leather covering 6 pax seats with armrest + 2 pilot seats

3.2.2 VIP interior −

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

*

69.4 kg (152.9 lb)*

kg (lb)* tbd

78.7 kg (173.5 lb)*

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

kg (lb)*

3.2.3.1 Convertible interior optional equipment −

Foldable litter (q.ty 1). with locking mechanism

−

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

12.6 (27.8)

15.5 (34.2)

3.2.4 EMS (Emergency Medical Service) interior a.

*

Fixed parts for Single/Dual litter EMS interior −

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

77.0 kg (169.7 lb)*



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) −

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) −

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

65.8 kg (145.1 lb)*

15.8 kg (34.8 lb)*

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

Air conditioning(1)

Weight* kg lb 40.8 90.0

Upholstery leatherette covered panels

14.5

Item

31.9

3.3.2 Utility equipment

Hour meter


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

7.0

15.4

37.8

83.3

75.4

165.9

112.4

247.4

1.0

2.2

180.0

396.0

3.5

7.7

Item

DART Bearpaws

(1)

Snow skis (1)

APICAL Emergency floats, kit

(1)

APICAL Emergency floats with life rafts, kit

SIMPLEX fire fighting tank provision and antennas relocation (1)

SIMPLEX fire fighting tank & fittings Retractable landing light 450 W

*



THF-A119-0607-1

23

3.3.2 Utility equipment (continue)

Engine particle separator


Wire strike protection system

10.3

22.7

Rapelling Kit (2 LH+2RH) (Ropes Excluded)

8.5

18.7

5.2

11.5

5.2

11.5

1.0

2.2

Item

(1)

Flight step LH

Flight step RH

(1)

Mechanical retractable external rear view mirror

(1)

3.3.3 Additional avionics

VHF-COM/NAV (KX 165 A) installation


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

Item

3.3.4 Additional mission equipment only by FAA STC

*

Item

Weight* 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) Item

Weight*

SIMPLEX electrical heated external rear view mirror

kg 7.0

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

17.4 tbd

38.3 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 Item

Weight*

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

kg From 5.0 to 10.0

lb 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%. 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

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) GROSS WEIGHT - lb x 100 51

53

55

57

59

61 4500

14000 4000 12000

10000

3000

8000

2500

2000 IS A

6000

1500 A IS

4000

PRESSURE ALTITUDE - m

PRESSURE ALTITUDE - ft

3500

+

1000

20

2000

500

0

0 23

24

25

26

27

28

GROSS WEIGHT - kg x 100


28

THF-A119-0607-1

4.1.2 Hovering OGE (TOP)

HOVERING OGE - (TOP) GROSS WEIGHT - lb x 100 44

48

52

56

60

64

68 4500

14000 4000

3000

0 +2

2500

8000

2000 6000 1500

PRESSURE ALTITUDE - m

10000

3500

external load

ISA


ISA

12000

4000 1000 2000

500

0

0 20

22

24

26

28

30

32

GROSS WEIGHT - kg x 100


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) ROTOR: 100% HEATER OFF ELECTRICAL LOAD: 100A

RATE OF CLIMB - m/s 0

1

2

3

4

5

6

7

8

9

10

11 45

14 40

35

30

10

ISA

25

8

20

ISA+20 6

15

PRESSURE ALTITUDE - mX100

PRESSURE ALTITUDE - ftX1000

12

4 10 2

5

0

0 0

4

8

12

16

20

RATE OF CLIMB - ft/minX100


30

THF-A119-0607-1

4.2.2 Rate of climb 2720 Kg MGW

RATE OF CLIMB - TOP (2720 kg) ROTOR: 100% HEATER OFF ELECTRICAL LOAD: 100A

RATE OF CLIMB - m/s 0

1

2

3

4

5

6

7

8

9

10

11 45

14 40

35

30

10

ISA

8

25

20

ISA+20

6

15 4

PRESSURE ALTITUDE - mX100


12

10 2

5

0

0 0

4

8

12

16

20

RATE OF CLIMB - ft/minX100


THF-A119-0607-1

31

4.3

FUEL CONSUMPTION VS AIRSPEED

4.3.1 Fuel consumption vs Airspeed – SL (ISA)

FUEL FLOW - SL (ISA)

TRUE AIRSPEED - km/h 93

123

153

183

213

243

TOP LIMIT

273 540

240 520 500 MCP LIMIT

220

480

FUEL FLOW - kg/h

200

440 RECOMMENDED CRUISE SPEED

420 400

180

380

FUEL FLOW - lb/h

460

360

160 BEST ENDURANCE SPEED

340

2720kg

140

320

2500 kg

300

2 10 0 kg

280

120

260 240

100 50

70

90

110

130

220 150

TRUE AIRSPEED - kts


32

THF-A119-0607-1

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

FUEL FLOW - SL (ISA+20)


123

153

183

213

243

273 500

TOP LIMIT

220

480 460

200

440 MCP LIMIT

400

RECOMMENDED CRUISE SPEED

180

380 360

160

BEST ENDURANCE SPEED

340

g 272 0k 2500 kg

140

FUEL FLOW - lb/h

FUEL FLOW - kg/h

420

320 300

2 100 kg

280 120

260 240

100 50

70

90

110

130

220 150

TRUE AIRSPEED - kts


THF-A119-0607-1

33

4.3.3 Fuel consumption vs Airspeed – 5000 ft (ISA)

FUEL FLOW - 5000 ft (ISA)


123

153

183

213

243

220

273 480

TOP LIMIT

460 200

440 MCP LIMIT

420

FUEL FLOW - kg/h

380 RECOMMENDED CRUISE SPEED

160

360 340

140

320


FUEL FLOW - lb/h

400

180

300 g 2720 k kg 2500

120

280 260

2100 kg

240 100 50

70

90

110

130

220 150

TRUE AIRSPEED - kts


34

THF-A119-0607-1

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

FUEL FLOW - 5000 ft (ISA+20)


123

153

183

213

243

273 460

200

440

TOP LIMIT

420 400

180

380 360

RECOMMENDED CRUISE SPEED

160

340

140

320


g 2 72 0k

300

kg

280

2500

120

2 10

0k

g

FUEL FLOW - lb/h

FUEL FLOW - kg/h

MCP LIMIT

260 240

100 50

70

90

110

130

220 150

TRUE AIRSPEED - kts


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. 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

Item

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. 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

Item


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 -

6.3

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.

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 Hourly Op. MMH/FH Cost (USD)

Fuel and lubricants Fuel6 56 USG/h at 124 kts Lubricants 3% of fuel cost Direct Maintenance Airframe Line Maintenance Labour7: - Scheduled Maintenance - Unscheduled Maintenance Airframe Parts: - Inspections Consumables - Unscheduled - Overhaul Components - Life-Limited Parts

126.00 3.78

0.73 0.24

47.72 15.60 2.00 110.62 14.90 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 Labour at USD 65.00 per hour 8 Pratt & Whitney Engine Maintenance Cost (DMC) for PT6B-37A, 1 cycle per hour 7


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


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. 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.

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


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:

7.2

−

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

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


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