THF-A109E-0706-1.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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THF-A109E-0607-1 III

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.


IV THF-A109E-0607-1

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THF-A109E-0607-1 V

TABLE OF CONTENTS

1 INTRODUCTION.................................................................................... 1

1.1 MAIN CHARACTERISTICS ...............................................................................................2

1.2 APPLICATIONS........................................................................................................2

2 LEADING FEATURES........................................................................... 3

2.1 CERTIFICATION ......................................................................................................3

2.2 EXTERNAL DIMENSIONS .......................................................................................4

2.3 INTERNAL DIMENSIONS AND VOLUMES ...........................................................................6

2.4 WEIGHTS .................................................................................................................8

2.5 SLING LOAD CAPACITY .................................................................................................8

2.6 FUEL CAPACITY......................................................................................................9

2.7 ENGINE RATINGS ...................................................................................................9

2.8 TRANSMISSION RATINGS......................................................................................9

2.9 OPERATIONAL ENVELOPE ..................................................................................10

2.9.1 Never Exceed Speed Vne ........................................................................10

2.9.2 Wind Envelope .........................................................................................10

2.9.3 Load Factors at MGW ..............................................................................11

2.9.4 Slope Landing...........................................................................................11

2.9.5 Ground Handling ......................................................................................11

2.9.6 Temperature and Altitude .........................................................................12

2.10 CG ENVELOPE ......................................................................................................13

2.10.1 Longitudinal And Lateral Envelope ...........................................................13

2.11 PERFORMANCE SUMMARY TABLE..........................................................................14

2.11.1 Twin Engine Operation (Sea Level)..........................................................14


VI THF-A109E-0607-1

2.11.2 TWIN ENGINE OPERATION (5000 Ft).................................................... 14

2.11.3 Twin Engine Operation AEO – (Altitude Performance) ............................ 15

2.11.4 One Engine Inoperative (OEI – 2’30” Contingency Power) ...................... 15

2.11.5 One Engine Inoperative MCP Power ....................................................... 15

2.11.6 Cat. A takeoff and landing performance................................................... 15

2.12 ENVIRONMENTAL IMPACT.................................................................................. 16

2.12.1 External Noise Level ................................................................................ 16

2.12.2 Internal Noise Level ................................................................................. 16

3 STANDARD CONFIGURATION AND OPTIONAL EQUIPMENT LIST ....... 17

3.1 STANDARD CONFIGURATION (EASA/FAA IFR) ................................................. 17

3.1.1 Basic Aircraft............................................................................................ 17

3.1.2 Standard Additional Equipment................................................................ 20

3.1.3 EASA-FAA Single Pilot IFR Avionic Package .......................................... 20

3.1.4 Additional Installed Avionic equipment..................................................... 20

3.1.5 Additional Auxiliary Equipment................................................................. 21

3.1.6 Interior...................................................................................................... 21

3.1.7 Painting .................................................................................................... 21

3.1.8 Miscellaneous/ground equipment ............................................................ 24

3.2 COMPLETIONS ..................................................................................................... 25

3.2.1 Corporate/De Luxe Interior....................................................................... 25

3.2.2 VIP Interior ............................................................................................... 25

3.2.3 CONVERTIBLE Interior............................................................................ 25

3.2.4 “ELITE” interior........................................................................................ 26

3.2.5 E.M.S. interior (Single Litter) .................................................................... 28

3.2.6 H.P.S. (Harbour Pilot Shuttle) interior ...................................................... 28

3.3 OPTIONAL EQUIPMENT....................................................................................... 29

3.3.1 Interior Optional Equipment ..................................................................... 29


THF-A109E-0607-1 VII

3.3.2 External Painting ......................................................................................30

3.3.3 Mission Equipment and Variants ..............................................................31

3.3.4 Avionic Equipment....................................................................................33

3.3.5 Special Mission Equipment.......................................................................35

4 PERFORMANCE DIAGRAMS ............................................................ 36

4.1.1 Hovering IGE – AEO (TOP)......................................................................37

4.1.2 Hovering IGE – AEO (MCP) .....................................................................38

4.1.3 Hovering IGE – OEI (2’30’’ Power) ...........................................................39

4.1.4 Hovering OGE – AEO (TOP) ....................................................................40

4.1.5 Hovering OGE – AEO (MCP) ...................................................................41

4.1.6 Hovering OGE – OEI (2’30’’ Power) .........................................................42

4.2 TAKEOFF AND LANDING PERFORMANCE (CATEGORY A) .............................................43

4.2.1 Weight – Altitude limitations (back-up procedure from helipad)................43

4.2.2 Fuel consumption vs Airspeed – AEO – SL (ISA).....................................44

4.2.3 Fuel consumption vs Airspeed – AEO – SL (ISA+20 °C)..........................45

4.2.4 Fuel consumption vs Airspeed – AEO – 5000 ft (ISA) ..............................46

4.2.5 Fuel consumption vs Airspeed – AEO – 5000 ft (ISA+20 °C) ...................47

5 SUPPORT AND MAINTENANCE ....................................................... 48

5.1 INSPECTION PROGRAMMES...............................................................................48

5.2 OVERHAUL COMPONENTS .....................................................................................50

5.3 RETIREMENT LIFE COMPONENTS .....................................................................50

6 ESTIMATED DIRECT OPERATING COST AND RELATED DATA ... 52

6.1 GENERAL INFORMATION.....................................................................................52

6.1.1 FUEL AND LUBRICANTS ........................................................................52

6.1.2 Airframe Direct Maintenance ....................................................................52

6.1.3 POWERPLANT MAINTENANCE .............................................................53

7 SERVICE PLANS ................................................................................ 54


VIII THF-A109E-0607-1

7.1 AIRFRAME MAINTENANCE PROGRAMMES....................................................... 54

7.1.1 Global support plan (GSP) ....................................................................... 54

7.1.2 Complete overhaul and maintenance programme (COMP) ..................... 55

7.1.3 Component Protection Agreement (CPA) ................................................ 55

7.2 ENGINE MAINTENANCE PROGRAMME.............................................................. 56

7.2.1 Pratt & Whitney – Eagle Service Plan (ESP) ........................................... 56

7.2.2 Turbomeca – Support By the Hour (SBH)................................................ 57

7.3 WARRANTIES ....................................................................................................... 57

7.3.1 Airframe Warranty.................................................................................... 57

7.3.2 Engine Warranty ...................................................................................... 57

7.4 EXCHANGE PROGRAMME .................................................................................. 58

7.4.1 Agusta Exchange Programme ................................................................. 58

7.4.2 Pratt & Whitney Rental/Exchange Programme ........................................ 58

7.5 RECOMMENDED GROUND SUPPORT EQUIPMENT (GSE) .............................. 58

7.6 TECHNICAL PUBLICATIONS................................................................................ 58

7.7 STANDARD TOOLS .............................................................................................. 59

8 TRAINING ............................................................................................60

8.1 AGUSTA TRAINING CENTRE............................................................................... 60

8.1.1 The School............................................................................................... 60

8.1.2 The Simulator........................................................................................... 60

8.2 TRAINING COURSES ........................................................................................... 60

9 USEFUL INFORMATION.....................................................................61


THF-A109E-0607-1 1

1 INTRODUCTION

The A109POWER is the latest model of the A109 family incorporating advanced technologies to fulfil the new Civil Aviation rules. It has been developed to provide a high level of power and excellent performance, as well as:

• maximum operational capability for the operator,

• safe use both over city areas and in extreme environmental conditions,

• high versatility, from passenger transport to EMS,

• low operating costs.

The A109POWER is a lightweight, twin engine, multipurpose helicopter with eight seats. The helicopter has a four composite blades, fully articulated main rotor with elastomeric bearings and a semi–rigid two composite–bladed tail rotor system. Each engine has its separate input to the main transmission. The twin–engine reliability is assured by a dual fully separated fuel system, dual hydraulic system, dual electric system, and dual redundant lubricating system for the main transmission and the engines. The fuselage and the empennage are of aluminium alloy for the primary structure and of fibre composite material for the secondary structure. The landing gear is a three–wheel, retractable, tricycle type.


2 THF-A109E-0607-1

1.1 MAIN CHARACTERISTICS

The main characteristics of the A109POWER are the following:

• Functional cabin layout designed for high operational flexibility and for quick and easy reconfiguration possibility (2 pilots with 6 passengers or with 2 litters and 2 medical attendants).

• Large separate baggage compartment with a max length of 2.3 m.

• Second multipurpose baggage compartment accessible from the cabin to be used also as accommodation for two longitudinal litters or for the additional fuel tanks.

• New design retractable landing gear, with high clearance for operation from unprepared terrain.

• IFR package for single or dual pilot operation including 3 axes duplex autopilot with Flight Director.

• Engine monitoring and aircraft warnings (with voice annunciation) on dual liquid crystal multifunction displays (IDS).

• Titanium main rotor hub with composite grips and blades and with elastomeric bearings.

• Steel rotor hub with two composite blades, individually interchangeable.

• New generation Pratt & Whitney PW206C or Turbomeca Arrius 2K1 engines with FADEC.

• Excellent performance including full CAT A up to maximum weight.

• Excellent flying qualities, high controllability and manoeuvrability.

• Operative from – 40°C up to + 50°C

• Great safety, "fail safe" design and redundancy of all systems.

• Reduced maintenance requirements due to the wide use of reliable and on condition components.

• Improved availability through different inspection programme options.

• Maintenance programmes at guaranteed cost available either for the airframe or the engines.

1.2 APPLICATIONS

The great flexibility of the cabin lay–out and the wide range of optional equipment available make the A109POWER suitable for different applications such as:

• Passenger transportation,

• VIP and Corporate transportation,

• Emergency medical service (EMS),

• Search And Rescue (SAR) operations,

• Law Enforcement,

• Offshore passenger transportation,

• Harbour pilot shuttle,

• Utility operations (fire fighting, sling load carrying, news gathering, etc.


THF-A109E-0607-1 3

2 LEADING FEATURES

2.1 CERTIFICATION

The certification is in accordance with:

• FAR PART 27 Amendment 1 to 8 included and from 11 to 28 where applicable

• A109 No. 27–54–EU–17 Special Condition for helicopter,

• Exemption N. 6518 dated Oct. 9, 1996 from sec. 27.1(a) of title 14, Code of Federal Regulation,

• FAR PART 29 sec. 29.903 (b) for Category A engine isolation,

• JAR 29 and FAR 29 where applicable for Category A operation.

The helicopter is certified for single and /or dual Pilot IFR operations. The helicopter has been certified by the Civil Aviation Authorities of more than 30 countries, including:

ITALY ENAC Ente Nazionale per l'Aviazione Civile EUROPE EASA European Aviation Safety Agency USA FAA Federal Aviation Administration AUSTRIA ACAA Austrian Civil Aviation Authority ENGLAND CAA Civil Aviation Authority FRANCE DGAC Direction Generale de l' Aviation Civile GERMANY LBA Luftfahrt – Bundesamt SPAIN DGAC Dirección General de Aviación Civil SWITZERLAND FOCA Federal Office for Civil Aviation POLAND ULC Civil Aviation Authority of Poland BRAZIL CTA Centro Técnico Aerospacial RUSSIA ARIAC Aviation Register of the Interstate Aviation Committee SOUTH AFRICA SACAA South African Civil Aviation Authority CHINA CAAC Civil Aviation Administration of China PHILIPPINES ATO Air Transportation Office INDIA DGCA Directorate General Civil Aviation VENEZUELA INAC Istituto Nacional de Aviación Civil AUSTRALIA CAA Civil Aviation Authority JAPAN JCAB Japan Civil Aviation Bureau


4 THF-A109E-0607-1

2.2 EXTERNAL DIMENSIONS

FUSELAGE

Length 11.45 m 37 ft 7 in

Width (elevator) 2.88 m 9 ft 5 in

Width (passengers cabin door) 1.62 m 5 ft 4 in

Height (tail fin) 3.50 m 11 ft 6 in

Fuselage ground clearance 0.40 m 1 ft 4 in

ROTORS

Main rotor diameter 11.00 m 36 ft 1 in

Tail rotor diameter 1.94 m 11 ft 7 in

LANDING GEAR

Wheel track 2.15 m 7 ft 1 in

Wheel base 3.53 m 12 ft

OVERALL DIMENSIONS

Length (rotors turning) 13.04 m 42 ft 9 in

Width (main rotor blade at 45°) 7.78 m 25 ft 6 in

Height (top of tail fin) 3.50 m 11 ft 6 in

Main rotor clearance (rotor turning, controls in neutral position) 2.45 m 8 ft

Tail rotor clearance (rotor turning) 0,95 m 3 ft 12 in


THF-A109E-0607-1 5

A109 Power External dimensions


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2.3 INTERNAL DIMENSIONS AND VOLUMES

COCKPIT

Max length 1.38 m 4 ft 06 in

Max width 1.59 m 5 ft 03 in

Max height 1.36 m 4 ft 06 in

Volume 1.65 m3 58.3 ft3

CABIN

Max length 2.10 m 6 ft 11 in



Volume 3.50 m3 123.6 ft3

BAGGAGE COMPARTMENT

Max length (with optional baggage ext.) 2.30 m 7 ft 07 in



Volume 0.95 m3 33.55 ft3


THF-A109E-0607-1 7

Internal dimensions (m/ft)


8 THF-A109E-0607-1

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 3.1.1.

Weights kg lb

BASIC EMPTY WEIGHT (Weight tolerance ±2%) 1 1585 3494

MAX GROSS WEIGHT (internal loads) 2 2850/3000 6283/6614

MAX GROSS WEIGHT (external loads) 3000 6614

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 1000 2205

Primary cargo hook with secondary hook3 500 1102

Rescue hoist 272 600

1 Basic empty Weight with A/C equipped with Turbomecca Arrius 2K1 engines is 1596 kg (3519) 2 3000 kg MGW with the application of Increased Internal Gross Weight mod. 109-0823-22 3 the secondary cargo hook can be used only in conjunction with the primary one, for higher safety. The secondary cargo

hook utilizes the same structural provisions and supports as the principal one, with independent and dedicated wiring and jettison mechanism (electrical and manual).


THF-A109E-0607-1 9

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 starboard side of the fuselage.

Total capacity∗ kg lb l USG

3-CELL fuel system 484 1067 605 160



2.7 ENGINE RATINGS

Pratt&Whitney

P&W206C Turbomecca Arrius 2K1 Rating (Sea level, ISA)

kW shp kW shp AEO Takeoff power (5 min) 2 x 477 2 x 640 2 x 500 2 x 670

AEO Maximum continuous power 2 x 423 2 x 567 2 x 425 2 x 570

OEI 2’ 30’’ Contingency power 546 732 560 750

OEI Maximum continuous power 500 670 500 670

2.8 TRANSMISSION RATINGS

Power

Rating∗∗ kW shp

AEO Takeoff power (5 min) 671 900

AEO Maximum continuous power 671 900

OEI 2’ 30’’ Contingency power 478 640

OEI Maximum continuous power 417 560

∗ Unusable fuel: 8 kg – 18.0 lb for all three tank configurations. Fuel density is assumed at 0.8 kg/l ∗∗ Rating applicable at 100% rotor speed (384 rpm)


10 THF-A109E-0607-1

2.9 OPERATIONAL ENVELOPE

2.9.1 Never Exceed Speed Vne

Never exceed speed VNE up to 2850 kg 168 kts (IAS);

Never exceed speed VNE from 2850 kg up to 3000 kg 140 kts (IAS);

Maximum sideward speed: 30/40 kts;

Maximum rearward speed: 30 kts.

2.9.2 Wind Envelope

Satisfactory stability and control in rearward and sideward flight has been demonstrated, at all loading conditions for hover in ground effect up to takeoff power, from –1000 ft to 8000 ft HD, in the following wind/ground speed azimuth envelopes.

APPLICABILITY FROM 4000 TO 8000 ft HD – 2850 kg GW

UP to 4000 ft HD FROM 4000 to 8000 ft HD


THF-A109E-0607-1 11

2.9.3 Load Factors at MGW

2.5 g POSITIVE

0.5 g NEGAIVE

2.9.4 Slope Landing

Takeoff and landing on terrain with slopes is possible, for the entire weight envelope, up to the following limits:

8° LONGITUDINAL

10° LATERAL

2.9.5 Ground Handling

The space required for the ground handling of the helicopter and its ground clearances are presented in the following picture:

Turning Radius


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2.9.6 Temperature and Altitude

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

ISA +35ISA

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

22000

-50 -40 -30 -20 -10 0 10 20 30 40 50 60Temperature (OAT) - °C

Pres

sure

Alti

tude

- ft

Temperature – Altitude operational envelope


THF-A109E-0607-1 13

2.10 CG ENVELOPE

The A109POWER is approved for flight within Longitudinal and Lateral Centre of Gravity range limits according to the following diagrams:

2.10.1 Longitudinal And Lateral Envelope

CG LONGITUDINAL ENVELOPE

1850 kg

2600 kg

2100 kg

2720 kg

3000 kg

MAST

18

19

20

21

22

23

24

25

26

27

28

29

30

31

3200 3250 3300 3350 3400 3450 3500 3550 3600

FUSELAGE STA - mm

GR

OSS

WEI

GH

T - k

g x

100

40

42

44

46

48

50

52

54

56

58

60

62

64

66

68126 127 128 129 130 131 132 133 134 135 136 137 138 139 140 141

FUSELAGE STA - in

GR

OSS

WEI

GH

T - l

b x

100

sta 3220

sta 3245

sta 3350 sta 3521

sta 3550

2850 kg

sta 3458

CG LATERAL ENVELOPE

1850 kg

2850 kg

CENTRELINE

18

19

20

21

22

23

24

25

26

27

28

29

30

31

-90 -70 -50 -30 -10 10 30 50 70 90

LATERAL STA - mm

GR

OSS

WE

IGH

T - k

g x

100

40

42

44

46

48

50

52

54

56

58

60

62

64

66

68-3.5 -2.5 -1.5 -0.5 0.5 1.5 2.5 3.5

LATERAL STA - in

GR

OSS

WEI

GH

T - l

b x

100

bl -80

bl 40

bl 80

3000 kgbl -40

2450 kg

Longitudinal and lateral CoG limits


14 THF-A109E-0607-1

2.10.2 PERFORMANCE Summary Table

2.10.3 Twin Engine Operation (Sea Level)

Gross weight 2500 kg – 5512 lb 2720 kg – 5997 lb 2850 kg – 6283 lb 3000 kg – 6614 lb

ISA ISA+20°C ISA ISA+20°C ISA ISA+20°C ISA ISA+20°

kts 157 149 156 147 154 146 142 144 MAXIMUM CRUISE SPEED (TAS) km/h 291 276 289 272 285 271 263 266

kts 141 142 140 142 140 141 140 140 RECOMMENDED CRUISE SPEED4 (TAS) km/h 261 163 159 163 259 161 259 259

RATE OF CLIMB (TOP) ft/min 2370 2400 2080 2100 1930 1950 1500 1520

3-CELL MAX RANGE5 nm 325 324 321 323 318 323 315 315

484 kg usable fuel- no reserve km 601 601 594 598 590 598 584 584

3-CELL MAX ENDURANCE 484 kg usable fuel-no reserve

h:min 3:12 3:11 3:06 3:05 3:03 3:02 2:59 2:58

5-CELL MAX RANGE nm 453 458 447 463 444 447 440 443

668 kg usable fuel–no reserve km 838 849 828 857 822 828 814 821

5-CELL MAX ENDURANCE

668 kg usable fuel–no reserve h:min 4:29 4:29 4:22 4:21 4:17 4:16 4:12 4:10

2.10.4 TWIN ENGINE OPERATION (5000 Ft) Gross weight 2500 kg – 5512 lb 2720 kg – 5997 lb 2850 kg – 6283 lb 3000 kg – 6614 lb

ISA ISA+20°C ISA ISA+20°C ISA ISA+20°C ISA ISA+20°C

kts 158 147 157 145 155 143 152 141 MAXIMUM CRUISE SPEED (TAS) km/h 293 272 291 269 287 265 281 261

kts 137 140 137 140 137 140 139 137 RECOMMENDED CRUISE SPEED3 (TAS) km/h 254 259 254 259 254 259 258 254

RATE OF CLIMB (TOP) ft/min 2430 2110 2130 1830 1970 1690 1530 1250

3-CELL MAX RANGE4 nm 378 381 371 372 365 367 359 361

484 kg usable fuel- no reserve km 700 706 687 690 677 679 666 669

3-CELL MAX ENDURANCE 484 kg usable fuel-no reserve

h:min 3:38 3:37 3:31 3:29 3:28 3:25 3:23 3:20

5-CELL MAX RANGE nm 528 533 519 522 512 514 503 505

668 kg usable fuel–no reserve km 978 988 961 966 948 952 932 936

5-CELL MAX ENDURANCE

668 kg usable fuel–no reserve h:min 5:06 5:05 4:56 4:54 4:51 4:48 4:45 4:42

4 The Recommended cruise speed is the speed corresponding to the 99% of the lowest specific fuel consumption for given

environmental condition and weight. 5 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.


THF-A109E-0607-1 15

2.10.5 Twin Engine Operation AEO – (Altitude Performance)



ft >20000 17900 18000 14300 16600 12700 15000 11000 HIGE (TOP)

m >6100 5456 5486 4359 5059 3871 4572 3352

ft 15900 11700 13400 8700 11800 6900 9200 4600 HOGE (TOP)

m 4846 3566 4084 2652 3596 2103 2804 1402

SERVICE CEILING (MCP) ft >20000 19500 >20000 17400 19600 16100 18400 14800

(100 ft/min ROC) m >6100 5943 6100 5303 5974 4907 5608 4511

2.10.6 One Engine Inoperative (OEI – 2’30” Contingency Power)



ft 7000 2000 4000 2600 HIGE

m 2134 610 1220 (5)

792 (6) (6) (6)

ft/mi 1200 870 1000 700 900 610 760 620 RATE OF CLIMB (SL)

m/s 6.1 4.4 5.1 3.6 4.6 3.1 3.9 3.1

SERVICE CEILING ft 16400 13200 14200 10900 13100 9500 11700 7700

(100 ft/min ROC) m 4998 4023 4328 3322 3993 2895 3567 2347

ft 7500 3000 4200 0 2800 VTOL CAT A

m 2285 914 1280 0 853 (7) (6) (8)

2.10.7 One Engine Inoperative MCP Power



SERVICE CEILING ft 14700 10200 12500 7300 11000 5600 9500 4000

(100 ft/min ROC) m 4480 3109 3810 2225 3353 1707 2895 1220

2.10.8 Cat. A takeoff and landing performance

See Section 4.2 herein.

(5) Up to 2650 kg at sea level (6) Up to 2950 kg at sea level (7) Up to 2720 kg at sea level (8) Certification Pending


16 THF-A109E-0607-1

2.11 ENVIRONMENTAL IMPACT

2.11.1 External Noise Level

The external noise level on the ground does not exceed the values specified herein in the following conditions:

At 2850 kg MGW with Pratt & Whitney PW206C engines(9):

POWER ICAO noise limits Flight condition

EPNdB EPNdB

Takeoff 91.3 94.6

Fly-over 90.9 93.6

Approach 91.4 95.6

At 3000 kg MGW with Pratt & Whitney PW206C engines (9):

POWER ICAO noise limits Flight condition

EPNdB EPNdB

Takeoff 91.7 94.8

Fly-over 91.3 93.8

Approach 91.7 95.8

2.11.2 Internal Noise Level The internal noise level does not exceed the values specified herein for the different applicable soundproofing type referring to the following flight conditions:

• Cruise Speed at 140 kts • 2720 kg Average Weight • 3000 ft Altitude

Weighted Level

Speech Interference LevelSoundproofing type

dB(A) SILdB

Standard comfort 92 84

Silent 89 81

Paulstra - Ultra Silent 85 77

(9) External noise figure refer to the A109 POWER With Metal Tail Rotor Blades, Noise Reduction Certification For The Current Composite Blades Installation Is Pending


THF-A109E-0607-1 17

3 STANDARD CONFIGURATION AND OPTIONAL EQUIPMENT LIST

This section provides information on the aircraft standard configuration and optional interior and equipment available for the A109POWER and is organised as follows:

Section 3.1: Description of the A109POWER Standard configuration Section 3.2: Interior completions Section 3.3: Optional equipment, available to customise the aircraft for specific applications

3.1 STANDARD CONFIGURATION (EASA/FAA IFR)

In this section the standard helicopter configuration is described in detail, and includes the main following subsystems:

Basic Aircraft,

Standard Additional Equipment,

EASA-FAA Single Pilot IFR Avionic Package,

Additional Installed Avionic equipment,

Additional Auxiliary Equipment,

Interior

Miscellaneous/ground Equipment.

3.1.1 Basic Aircraft 1585 Kg (3494 Lb)*

a. Airframe

- Aluminium alloy and bonded panel fuselage - Semi-monocoque aluminium alloy tail boom - Two hinged jettisonable high crew doors (LH & RH) - Two passenger sliding doors (LH & RH) with jettisonable window - Acrylic windshield and side windows - Acrylic overhead windows - Removable fibreglass tail rotor gearbox fairing - Quick removable tail rotor drive shaft cover - Three wheel retractable landing gear - Interchangeable landing gear tires - Separate baggage compartment with hinged door - Three jacking points - Removable fairing and cowlings providing complete accessibility to the controls and drive

components - Swivelling front wheel provided with tow bar attachment - Quick opening hinged inspection doors to allow visual check of engine oil levels and

maintenance inspection points - Grounding point


18 THF-A109E-0607-1

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, corrosion protected, delta hinged type, semi–rigid, 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 stop mechanism

c. Power plant and fuel system

- Pratt & Whitney PW206C engine (2) or Turbomeca Arrius 2K1 engine (2) - Engine mounted fuel pump and filter assembly - Engine mounted oil pump and filter assembly - Engine mounted fuel control and governor (FMU) - Full Authority Digital Electronic Control (FADEC) - Lubrication and cooling system - Engine oil chip detectors (2) - Engine control panel - Fuel system control panel - RH refuelling point - Airframe mounted easy access fuel filter - Three fuel cells (160 USG) - Submerged fuel boost pump (2) - Ground fuel drains

d. Transmission drive system

- 900 SHP for take off and continuous operation main transmission - Two stage transmission - Two free wheeling units - 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 (engines to transmission, transmission to tail rotor, engines to

blowers)

e. Electrical

- 27 Ah, 24 volt DC nickel cadmium battery with temperature probe - 160 Ampere self cooled starter generators (2) - Voltage regulators (2) - Battery relay


THF-A109E-0607-1 19

- Interconnecting bus relay (2) - External power relay - Distribution buses (1 battery, 2 essential, 2 main) - External power receptacle - Position lights - Anti collision lights (2) - Taxing lights (2) and landing lights (2) on landing gear sponsons - Utility cockpit lights (2) - Instrument lights with dimming switch - Radio master switch

f. Flight instruments – pilot

- Air speed indicator - Instantaneous vertical speed indicator - Barometric encoding altimeter - Magnetic compass indicator - Clock, 8 days and elapsed time

g. Instrumentation (on IDS displays)

- Dual gas generator speed (N1%) - Dual turbine outlet temperature (TOT °C) - Dual torque meter (TRQ%) - Dual power turbine speed (N2%) - Rotor speed (NR%) - Transmission oil temperature (°C) and pressure (PSI) - Two engine oil temperature (°C) and pressure (PSI) - Two fuel pressure (PSI) - Two fuel quantity (kg) - Two engine fuel flow (kg/hr) - Two flight controls hydraulic system pressure (PSI) - Two utility hydraulic system pressure (PSI) - Outside air temperature (°C) - Dual DC ammeter - Dual DC voltmeter - Dual AC voltmeter

h. Caution & Warning advisory

- Master warning lights (MWL) - Master caution lights (MCL) - Warning, caution & advisory messages (on IDS displays) - Engine fire detection system with remote fire warning lights - Aural Warning Generator with female voice annunciations

i. Interior arrangement

- Reclined rear cabin bulkhead - Two individual pilot seats, fore and aft adjustable, with lap belts - Aluminium alloy honeycomb reinforced floor with anti skid finish


20 THF-A109E-0607-1

- Ventilation ram air inlets - Anti reflection instrument panel

j. Exterior finishing

- Finishing in accordance with manufacturer specification NTA 893 A - Primer exterior painting

3.1.2 Standard Additional Equipment 20.6 kg (45.3 lb)*

(Installed in Current Production Aircraft) - Increased internal gross weight (3 tonnes MTOW)(10

7

) - Internal Structural provision for utility equipment (cargo hook, rescue hoist, search light,

AFCS, etc.) - Cabin Fire Extinguisher - Crew open door actuators - First aid kit - Pilot/copilot shoulder harness with inertial reel - Quick disconnecting chip detectors - Baggage compartment lights - Tail boom strake - Fuel drain electrical valves - Pilot/copilot headsets (2)

3.1.3 EASA-FAA Single Pilot IFR Avionic Package 100.7 kg (222.1 lb)*

- AC system (2 inverters) - Pilot navigation instruments including:

• 5-ATI AMLCD EADI & EHSI • Stand-by ADI

- Gyrocompass C14 (Honeywell) - Vertical gyro (N.1) 46060-11 (Flightline) - Vertical gyro (N.2) VG-208 (JET Electronics) - AFCS 3 Axis Duplex SP-711 (Honeywell) - ADF KR 87 (King) - Mode-S Transponder KT-70 (King) - VHF-COM/NAV KX-165 King (2) - ICS pilot/copilot AG-06-1U (Agusta/Gemelli) - DME KDM-706A (King) - Marker Beacon Receiver KMR 675 (King)

3.1.4 Additional Installed Avionic equipment 33.2 kg (73.2 lb)*- Copilot flight/navigation instruments including:

• 5-ATI AMLCD EADI & EHSI • Barometric altimeter • Air speed indicator • Vertical speed indicator

(10

7

) Not available on Turbomeca Arrius 2K1 equipped helicopter * Weight tolerance ±2%


THF-A109E-0607-1 21

- Flight Director & autotrim FZ-702 (Honeywell) - Radio altimeter AA-300 (Honeywell) - 3-frequency E.L.T. C 406-2HM (Artex) - GPS interfaced with EFIS and B-RNAV function 2101 I/O (Free Flight/Trimble) - EFIS pilot/copilot on command switch - Moving Map KMD-550 (Bendix/King)

3.1.5 Additional Auxiliary Equipment 35.0 kg (77.1 lb)*- Airframe hour meter - Dual control - Rotor brake - Retractable landing light(8

**) - Windshield wipers (pilot/copilot) with wiper switch on cyclic grip - Engine compartment fire extinguishers(

8

**) - Radio master switch with ground function - Baggage compartment extensions (1.9 m) - VLE & VLO extension up to 140 KIAS

3.1.6 Interior 45.7 Kg (100.8 Lb)*- Air conditioning Garret ECU - Primer finished cabin walls - Vibration dampers installation

3.1.7 Painting 15.0 Kg (33.1 Lb)*- Agusta colour scheme, from Agusta paint selection solid colour series 300

STANDARD CONFIGURATION WEIGHT 1835 kg (4046 lb)*

8

**Installations required for “CAT. A” operation * Weight tolerance ±2%


22 THF-A109E-0607-1

STANDARD CONFIGURATION INSTRUMENT PANEL

Typical IFR Dual Pilot Instrument Panel (King Avionic Package)

19. • MASTER WARNING push-button 20. EADI 21. • ENCODING ALTIMETER 22. • VERTICAL SPED IND. 23. ICS AUDIO CONTROL PNL 24. • CLOCK 25. ICS CONTROL PNL 26. PILOT EHSI 27. • #1 IDS 28. • #2 IDS 29. EMERGENCY LOCATOR CONTROL 30. VERTICAL SPEED IND 31. CPLT EHSI 32. ICS CONTROL PNL 33. PLACARD 34. EADI 35. AIR SPEED IND.

1. • MASTER WARNING push-button 2. • MASTER CAUTION push-button 3. ATTITUDE REVERSIONARY SWITCH 4. ALTIMETER 5. VHF/AM2CTRL PNL 6. ADF CTRL PNL 7. NAV 2 CTRL PNL 8. MOVING MAP DISPLAY 9. DME IND. 10. CPLT MARKER BEACON IND 11. ADI STAND-BY 12. FLIGHT DIRECTOR MODE SEL 13. VHF/AM1 CTRL PNL 14. • AIRSPEED IND. 15. NAV 1 CTRL PNL 16. TRANSPONDER CTRL PNL 17. ATTITUDE REVERSIONARY SWITCH 18. • MASTER CAUTION push-button

ONLY INSTALLATION MARKED WITH “•” ARE INCLUDED IN THE BASIC INSTRUMENT


THF-A109E-0607-1 23

Central and front console

Typical IFR Dual Pilot Instrument Panel

(KING Avionics Package with Pilot/Copilot EADI & EHSI and Bendix/King KMD 550 Moving Map)

1. HELIPILOT CTRL PNL 2. MISCELLANEOUS PANEL 3. GYROCOMPASS CTRL PNL 4. FUEL MANAGEMENT CTRLPNL

1. LANDING GEAR SEL 2. ARKING BRAKE HANDLE 3. COVER 4. CABIN VENTILATION KNOB 5. GPS 6. NOSE WHEEL LOCK LEVER 8. HYDRAULIC SYSTEM SWITCH 9. LANDING GEAR POSITION IND


24 THF-A109E-0607-1

Typical IFR Dual Pilot Instrument Panel

(COLLINS Avionics Package with Pilot/Copilot EADI & EHSI and Observer MKII Moving Map)

3.1.8 Miscellaneous/ground equipment − Air intake/exhaust covers

− Pitot tubes covers

− Tie-down fittings provisions

− Rotorcraft Flight Manual and technical publications

− Ground tools kit (including tow bar, lifting tool, wheel chocks)


THF-A109E-0607-1 25

3.2 COMPLETIONS

The following completions are available as option to customise the specific helicopter. Each completion weight has to be added to the weight of the “Standard Configuration” described in Section 3.1.

3.2.1 Corporate/De Luxe Interior 99.3 kg (219.0 lb)*- Silent soundproofing - Painted liners or tinted - 3 seats, central bench - 3 seats, aft bench - 3 points shoulder harness with inertia reels and safety belts for all pax seats - All seats covered with fabric - Reading lights - Advisory lights - Floor carpeting - Floor courtesy lights

3.2.2 VIP Interior 112.1 kg (247.2 lb)*- Silent soundproofing - Leatherette covered liners or painted - All seats VIP model covered with leather or fabric/leather - 3 seats, central bench with foldable armrest - 3 seats, aft bench with foldable armrest - 3 points shoulder harness with inertia reels and safety belts for all pax seats - Reading lights - Advisory lights - Floor carpeting - Floor courtesy lights - Leather bellows on flight controls - Carpeting protection - Seat covers - Customised finishing

3.2.3 CONVERTIBLE Interior 98.3 kg (216.8 lb)*- Standard Soundproofing - Painted liners - All seats covered with fabric - 3 seats, central bench with individually foldable back panel - 3 seats, aft bench with individually foldable back panel - Locking system for litters on back panel seats, aft and central bench - 3 points shoulder harness with inertia reels and Safety belts for all pax seats - Reading lights - Advisory lights - Floor Carpeting

* Weight tolerance ±2%


26 THF-A109E-0607-1

3.2.4 “ELITE” interior

“Elite” completion is available with both King Silver Crown or Collins Proline II avionics, and it includes the ‘Single pilot IFR/EASA-FAA avionic package’ plus a list of dedicated items for VVIP transport. Depending on the selected avionics, the relevant delta weight has to be considered.

a. “ELITE” COMPLETION – KING AVIONICS 171.8 kg (378.8 lb)* KING SILVER CROWN AVIONICS – SINGLE/DUAL PILOT IFR/EASA-FAA

- AC system (2 inverters) - Pilot navigation instruments (LCD EADI & EHSI, Stand-by ADI) - Gyrocompass C14 A Honeywell - Vertical gyros (N. 1) 46060-11 Flightline system - Vertical gyros (N. 2) VG 208 Jet Electronics - AFCS 3 Axis Duplex SP 711 Honeywell - Gyrocompass C14 Honeywell - Vertical gyro (N.1) 46060-11 Flightline system - Vertical gyro (N.2) VG 208 JET Electronics - AFCS 3 Axis Duplex SP 711 Honeywell - ADF KR 87 King - Transponder (Mode S) KT 70 King - VHF-COM/NAV KX 165 King (2) - ICS pilot/copilot AG-06-1U Agusta/Gemelli - DME KDM 706A King - Marker Beacon KMR 675 King

INTERIOR - Paulstra soundproofing - Leatherette covered liners - VVIP 3 seats aft facing bench with see-through armrest - VVIP 2 seats fwd facing with rear cabinet bar - Central single refrigerated drawer - Coordinated VVIP pilot/copilot seats with headrest - Pilot multipurpose holder - Pilot console tray - 6 Active Noise Reduction headsets - Pax ICS ‘on/off’ light - Reading light - Advisory light - Floor carpeting - Floor courtesy light - Leather bellows on flight controls - Carpeting protection - Seat covers

ADDITIONAL EQUIPMENT - Weather radar RDR 2000 Bendix/King (presented on pil./copil. EHSI) - 221 USG fuel system (in lieu of 160 USG) - RH electrically operated passenger step



THF-A109E-0607-1 27

- Pulsed chip detectors (transmission & engines) - Baggage compartment extension (2.3 m) - MGB vibration isolator struts – Lord

b. “ELITE” COMPLETION – COLLINS AVIONICS 189.1 kg (416.8 lb)*

COLLINS PROLINE II AVIONICS – SINGLE/DUAL PILOT IFR/EASA-FAA - AC system (2 inverters) - Pilot navigation instruments (LCD EADI & EHSI, Stand-by ADI) - Gyrocompass C14 A Honeywell - Vertical gyros (N. 1) 46060-11 Flightline system - Vertical gyros (N. 2) VG 208 Jet Electronics - AFCS 3 Axis Duplex SP 711 Honeywell - ADF ADF 60 Collins - Transponder (Mode S) TDR 94 Collins - VOR/ILS 1 (with MKR-BCN) VIR 32 Collins - VOR/ILS 2 (with MKR-BCN) VIR 32 Collins - VHF/AM 1 VHF 22 A Collins - VHF/AM 2 VHF 22 A Collins - ICS pilot/copilot AG 06 1U Agusta/Gemelli - DME DME 42 Collins

INTERIOR - Paulstra soundproofing - Leatherette covered liners - VVIP 3 seats aft facing bench with see-through armrest - VVIP 2 seats fwd facing with rear cabinet bar - Central single refrigerated drawer - Coordinated VVIP pilot/copilot seats with headrest - Pilot multipurpose holder - Pilot console tray - 6 Active Noise Reduction headsets - Pax ICS ‘on/off’ light - Reading light - Advisory light - Floor carpeting - Floor courtesy light - Leather bellows on flight controls - Carpeting protection - Seat covers

ADDITIONAL EQUIPMENT - Weather radar RDR 2000 Bendix/King (presented on pil./copil. EHSI) - 221 USG fuel system (in lieu of 160 USG) - RH electrically operated passenger step - Pulsed chip detectors (transmission & engines) - Baggage compartment extension (2.3 m) - MGB vibration isolator struts - Lord



28 THF-A109E-0607-1

3.2.5 E.M.S. interior (Single Litter)

a. Fixed parts 50.1 kg (110.4 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 EMS provisions - EMS electrical system - Electrical outlets (12 & 28 VDC) - 3rd ICS station in pax cabin - Medical oxygen system provisions (single bottle) - Sliders on pilot/copilot and cabin doors windows

b. Removable parts 70.2 kg (155.0 lb)*

- Doctor, sliding/rotating seat - Primary litter platform with front lock mechanism - Litter (q.ty 1) - Two foldable aft, fwd facing seats with headrests - Safety-belts with shoulder harness - Storage compartment - Oxygen bottle (in baggage compartment) - Special rubber floor carpet - Interior cargo net

3.2.6 H.P.S. (Harbour Pilot Shuttle) interior 89.1 kg (196.5 lb)*

- Standard soundproofing - Tinted liners - Floor with rails for hoist operator seat & drains - Special rubber floor carpet - 3-place forward looking aft bench - 3 points shoulder harness with inertia reels and safety belts for aft seats - Hoist operator seat (sliding & rotating) - Sliders on pilot/copilot/pax and cabin doors windows



THF-A109E-0607-1 29

3.3 OPTIONAL EQUIPMENT

The following optional equipment are available to customise the specific helicopter (each optional equipment weight has to be added to the weight of the “STANDARD CONFIGURATION (EASA/FAA IFR)” described in Section 3.1).

3.3.1 Interior Optional Equipment

✓ Suggested Applicability Weight*

Item

kg lb

CO

RPO

RA

TE

V.I.

P.

ELIT

E

E.M

.S.

CO

NV

ERTI

BLE

H.P

.S.

Paulstra soundproofing (in lieu of Silent type)** 12.0 26.5 ✓ STD

Central single refrigerated drawer (under the aft facing seat) 5.0 11.0 ✓ STD

Central single drawer 3.1 6.7 ✓ ✓

Chest of three drawers (under the aft facing seat, in lieu of ‘central single drawer’) 5.7 12.7 ✓ ✓

Active Noise Reduction headset 0.6 1.3 ✓ ✓ STD ✓ ✓ ✓

Pilot multipurpose holder 2.9 6.4 ✓ ✓ STD

Pilot console tray 2.5 5.5 ✓ ✓ STD

2 pilot seats headrests 0.5 1.1 ✓ ✓ STD ✓ ✓ ✓

Central bench with see-through modification** 1.5 3.3 ✓ STD

Rear cabinet 7.0 15.4 ✓ ✓

Rear cabinet with bar 7.5 16.5 ✓ STD

5/6 pax conversion kit ** (seating module replacing the aft cabinet) -4.0 -8.8 ✓ ✓ ✓

Second litter provision & rear lock mechanism 1.5 3.3 ✓

Second litter platform with front lock mechanism 6.2 13.7 ✓

Foldable litter 13.0 28.7 ✓ ✓

Oxygen bottles (2)9

*** 6.5 14.3 ✓

* Weight tolerance ±2% **Delta Weight 9

* In lieu of ‘Oxygen bottle (in baggage compartment)’


30 THF-A109E-0607-1

Single foldable forward facing seat 2.7 6.1 ✓

Pax conversion kit, including: Central bench 3 places, fabric covering Single foldable forward facing seat Cushions and back for 3 foldable fwd facing seats 3 headrest Additional floor carpet

40.4 89.1 ✓

Six pax seats cushions (seat, backrest and headrest) with leather covering (in lieu of fabric covering) 15.0 33.1 ✓

Six pax seats cushions with fabric covering (additional loose equipment) 12.0 26.5 ✓

Sliding and rotating operator seat with rails 15.2 33.5 ✓ ✓ ✓

ICS 3rd Station - AG 06 - Agusta/Gemelli 3.1 6.8 STD ✓ ✓

Central Bench, 3 places, fabric covered with Shoulder harness with inertia reels and Safety belts 28.7 63.3 ✓

Survival equipment install. kit, consisting of: 2 Individual Life rafts 1 life raft for 6 men or 1 life raft for 4 men

8 life vests

31.2 68.8 ✓ ✓ ✓ ✓ ✓ ✓

E.M.T. (Emergency Medical Transport) Single litter configuration including: Fixed provision

Aft. Panel structural Modification Provision for litter support

Removable equipment Bench panel with litter platform provision and litter

rear lock mechanism Litter platform with litter front lock mechanism

One foldable litter

34.8 76.6 ✓ ✓ ✓ ✓

3.3.2 External Painting ✓ Suggested Applicability

Weight*

Item

kg lb

CO

RPO

RA

TE

V.I.

P.

ELIT

E

E.M

.S.

CO

NV

ERTI

BLE

H.P

.S.

Customised painting scheme, solid colour series 300** From 0 to 5.0

From 0 to 11.0 ✓ ✓ ✓ ✓ ✓

Customised Painting Scheme, Metallic Colour Series 500** 5.0 11.0 ✓ ✓ STD ✓ ✓ ✓

Main Rotor Blades High Visibility Painting 1.0 2.2 ✓ ✓ ✓ ✓ ✓ ✓

* Weight tolerance ±2% **Delta Weight


THF-A109E-0607-1 31

3.3.3 Mission Equipment and Variants


Item

kg lb

CO

RPO

RA

TE

V.I.

P.

ELIT

E

E.M

.S.

CO

NV

ERTI

BLE

H.P

.S.

Reinforced pilot/copilot windshield 2.7 6.0 ✓ ✓ ✓ ✓ ✓ ✓

Sliders on pilot/copilot doors windows 0.5 1.1 ✓ ✓ ✓ STD ✓ STD

Sliders on pax cabin doors -1.6 -3.6 ✓ ✓ STD ✓ STD

Emergency floats provisions 12.0 26.3 ✓ ✓ ✓ ✓ ✓ ✓

Emergency floats (removable parts) 60.4 133.1 ✓ ✓ ✓ ✓ ✓ ✓

Emergency floats (removable parts, including 2 life rafts) 113.0 249.1 ✓ ✓ ✓ ✓ ✓ ✓

RH electrically operated passenger step 4.5 9.9 ✓ ✓ STD

185 USG fuel system 6.8 15.0 ✓ ✓ ✓ ✓ ✓

221 USG fuel system 13.2 29.1 ✓ ✓ STD ✓ ✓

Provisions for snow skis/slump protection pads** 3.8 8.4 ✓ ✓ ✓ ✓ ✓ ✓

Snow skis kit (removable parts) 31.9 70.3 ✓ ✓ ✓ ✓ ✓ ✓

Slump protection pads kit (removable parts) 14.2 31.3 ✓ ✓ ✓ ✓ ✓ ✓

Engines particle separator 14.8 32.6 ✓ ✓ ✓ ✓ ✓ ✓

Cargo hook provision (1000 kg) 4.7 10.3 ✓ ✓ ✓

Cargo hook (1000 kg) (remov.parts) and rear view mirror 12.3 27.1 ✓ ✓ ✓

Dual cargo hook provision (1000 kg / 500 kg) 6.0 13.2 ✓ ✓ ✓

Dual cargo hook kit (1000 kg / 500 kg) (removable parts) 3.6 7.9 ✓ ✓ ✓

Bambi Bucket provision (when cargo hook is installed) 0.5 1.1 ✓ ✓ ✓

Bambi Bucket kit (removable parts) 54.0 119.1 ✓ ✓ ✓

External hoist (272 kg) provision (including step bar) 21.9 48.2 ✓ ✓ ✓



32 THF-A109E-0607-1

External hoist (272 kg) kit (removable parts) 56.5 124.6 ✓ ✓ ✓

External loudspeaker provision 2.3 5.1 ✓ ✓ ✓

External loudspeaker kit (removable parts) 8.5 18.7 ✓ ✓ ✓

Rappelling hooks (2 LH + 2 RH) 8.5 18.7 ✓ ✓

SX-5 Starbust searchlight provision 6.9 15.1 ✓ ✓ ✓

SX-5 Starbust searchlight kit (removable parts) 11.9 26.3 ✓ ✓ ✓

SX-16 Nightsun searchlight provision 6.9 15.2 ✓ ✓ ✓

SX-16 Nightsun searchlight kit (removable parts) 20.6 45.4 ✓ ✓ ✓

Wire strike protection (cable cutters) 7.8 17.2 ✓ ✓ ✓ ✓ ✓ ✓

Pulsed chip detectors (transmission and engines) 1.0 2.2 ✓ ✓ STD ✓ ✓ ✓

Baggage compartment extension (2.3 m) 1.6 3.5 ✓ ✓ STD ✓ ✓ ✓

All weather covers (ground equipment) 6.0 13.2 ✓ ✓ ✓ ✓ ✓ ✓

Strobe lights on horizontal stabilizer 3.2 7.0 ✓ ✓ ✓ ✓ ✓ ✓

Fuel cap with keylock 0.5 1.1 ✓ ✓ ✓ ✓ ✓ ✓

2nd landing/search light (under baggage comp.) 3.2 7.1 ✓ ✓ ✓ ✓ ✓ ✓

MGB vibration isolator struts - Lord 10.4 23.0 ✓ ✓ STD


THF-A109E-0607-1 33

3.3.4 Avionic Equipment

a. Collins Proline II single pilot IFR/FAA avionic package10

**

(in lieu of Garmin – Bendix/King avionics Ref. Para 3.1.3


Item

kg lb

CO

RPO

RA

TE

V.I.

P.

ELIT

E

E.M

.S.

CO

NV

ERTI

BLE

H.P

.S.

COLLINS PROLINE II AVIONICS – SINGLE/DUAL PILOT IFR/EASA-FAA 14.0** 30.9** ✓ ✓ ✓ ✓ ✓ ✓

AC system (2 inverters)

Pilot navigation instruments (EADI & EHSI LCD, Stand-by ADI)

Gyrocompass C14 A Honeywell

Vertical gyros (N. 1) 46060-11 Flightline system

Vertical gyros (N. 2) VG 208 Jet Electronics

AFCS 3 Axis Duplex SP 711 Honeywell

ADF ADF 60 Collins

Mode-S Transponder TDR 94 Collins

Transponder (Mode S) TDR 94 Collins

VOR/ILS 1 (with MKR-BCN) VIR 32 Collins

VOR/ILS 2 (with MKR-BCN) VIR 32 Collins

VHF/AM 1 VHF 22 A Collins

VHF/AM 2 VHF 22 A Collins

ICS Pil/Copilot AG 06 1U Agusta/Gemelli

DME DME 42 Collins

10

** Special order. Availability subject to lead time. * Weight tolerance ±2%


34 THF-A109E-0607-1

b. Additional Avionic Equipment


Item

kg lb

CO

RPO

RA

TE

V.I.

P.

ELIT

E

E.M

.S.

CO

NV

ERTI

BLE

H.P

.S.

Weather Radar (displayed on Plt/Cptl EHSI) RDR 2000 Bendix/King 6.6 14.6 ✓ ✓ STD ✓ ✓ ✓

Moving Map Observer Structural Provision (in lieu of KMD 550 installation 2.4 5.3 ✓ ✓ ✓ ✓ ✓ ✓

Moving Map (in lieu of KMD 550 installation)

Oberver MK III

Skyforce** or equiv. 2.3 5.0 ✓ ✓ ✓ ✓ ✓ ✓

Stormscope WX-1000 BF Goodrich 8.0 17.6 ✓ ✓ ✓ ✓ ✓ ✓

TAS SKY 497 BF Goodrich 9.7 21.5 ✓ ✓ ✓ ✓ ✓ ✓

TCAS (integrated into EFIS) SKY 791 BF Goodrich 12.5 27.6 ✓ ✓ ✓ ✓ ✓ ✓

IRIDIUM satellite telephone AIRSAT 1 Icarus Instr. or equiv. 4.5 10.0 ✓ ✓

GSM/SATCOMM telephone Telit 155 Telit 3.2 6.9 ✓ ✓ ✓ ✓ ✓ ✓

CVR/FDR L3 10.0 22.1 ✓ ✓ ✓ ✓ ✓ ✓

NVG compatibility (Collins Proline II only, int. and ext. lights) 1.5 3.3 ✓ ✓ ✓



THF-A109E-0607-1 35

3.3.5 Special Mission Equipment


Item

kg lb

CO

RPO

RA

TE

V.I.

P.

ELIT

E

E.M

.S.

CO

NV

ERTI

BLE

H.P

.S.

VHF/FM NTX 138/TH250 Nat 6.0 13.2 ✓ ✓ ✓

HF/SSB HF 1050 Bendix/King 22.0 48.5 ✓ ✓ ✓

V/UHF AM-FM (analog or digital) Flexcomm II Wulfsberg 17.5 38.6 ✓ ✓ ✓

Direction Finder (DF) 931-6/-16 Chelton 12.0 26.5 ✓ ✓ ✓

GPS/VOR/VHF-AM GNS-430 GARMIN 5.1 11.3 ✓ ✓ ✓

FLIR complete provision UF 275 6.0 13.2 ✓ ✓ ✓

FLIR installation UF 275 Flir System 21.7 47.8 ✓ ✓ ✓

FLIR complete provision Sea Flir II or III 8.8 19.4 ✓ ✓ ✓

FLIR installation Sea Flir II or III Flir System 26.0 57.3 ✓ ✓ ✓

FLIR complete provision LEO II A-3 11.0 24.3 ✓ ✓ ✓

FLIR installation LEO II A-3 Denel 60.0 132.3 ✓ ✓ ✓

FLIR complete provision ULTRA FORCE II/LEOII- A5

7.9 17.4 ✓ ✓ ✓

FLIR installation ULTRA FORCE II/LEOII- A5

Flir System 52.0 114.7 ✓ ✓ ✓

Analog Video downlink system ECS 9.0 19.8 ✓ ✓ ✓

Digital Video downlink system ECS 12.0 26.5 ✓ ✓ ✓

Digital Video uplink system ECS 6.0 13.2 ✓ ✓ ✓

Digital Video recorder (DVR) DVFAR-II DUAL

AERO OPTICAL, or equiv.

1.3 2.9

✓ ✓ ✓

Fast ropes system (rope excluded) 4.0 8.8 ✓ ✓ ✓ ✓ ✓



36 THF-A109E-0607-1

4 PERFORMANCE DIAGRAMS

This Section contains the A109 Power flight performance charts illustrating:

4.1 HOVERING

Hovering IGE – AEO (TOP)

Hovering IGE – AEO (MCP)

Hovering IGE – OEI (2’30” Power)

Hovering OGE – AEO (TOP)

Hovering OGE – AEO (MCP)

Hovering OGE – OEI (2’30” Power)

4.2 TAKEOFF AND LANDING PERFORMANCE (CATEGORY A)

Weight – Altitude limitations (back-up procedure from helipad)

4.3 FUEL CONSUMPTION VS AIRSPEED

Fuel consumption vs Airspeed – AEO – SL (ISA °C)

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

Fuel consumption vs Airspeed – AEO – 5000 ft (ISA)

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


THF-A109E-0607-1 37

4.1.1 Hovering IGE – AEO (TOP)

HOVERING IGE - AEO (MCP)

ISA+20ISA +35

2850

kg

3000

kg

ISA

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

18 20 22 24 26 28 30 32

GROSS WEIGHT - kg x 100

PRE

SSUR

E A

LTIT

UDE

- ft

0

1000

2000

3000

4000

5000

6000

44 48 52 56 60 64 68

GROSS WEIGHT - lb x 100

PRE

SSUR

E A

LTIT

UDE

- m


38 THF-A109E-0607-1

4.1.2 Hovering IGE – AEO (MCP)

HOVERING IGE - AEO (MCP)

2850

Kg

3000

Kg

ISA +35 ISA +20

ISA

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

20 22 24 26 28 30 32


PRE

SSUR

E A

LTIT

UDE

- ft


THF-A109E-0607-1 39

4.1.3 Hovering IGE – OEI (2’30’’ Power)

HOVERING IGE - OEI (2'30" POWER)

ISA +35

ISA +20ISA

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

20 22 24 26 28 30 32


PRES

SURE

ALT

ITU

DE -

ft


40 THF-A109E-0607-1

4.1.4 Hovering OGE – AEO (TOP)

HOVERING OGE - AEO (TOP)

ISAISA +20

ISA +35

3000

Kg

2850

Kg

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

20 22 24 26 28 30 32


PRE

SSU

RE A

LTIT

UDE

- ft


THF-A109E-0607-1 41

4.1.5 Hovering OGE – AEO (MCP)

HOVERING OGE - AEO (MCP)

2850

Kg

3000

Kg

ISA +35

ISA +20

ISA

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

20 22 24 26 28 30 32


PRES

SURE

ALT

ITU

DE -

ft


42 THF-A109E-0607-1

4.1.6 Hovering OGE – OEI (2’30’’ Power)

HOVERING OGE - OEI (2'30" POWER)

ISA +35ISA +20

ISA

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

18 20 22 24 26 28 30 32


PRE

SSUR

E A

LTIT

UDE

- ft


THF-A109E-0607-1 43

4.2 TAKEOFF AND LANDING PERFORMANCE (CATEGORY A)

The following diagram refers to preliminary Cat. A performance capabilities of the POWER, for back-up procedure from helipad.

4.2.1 Weight – Altitude limitations (back-up procedure from helipad)

CAT. A WEIGHT - ALTITUDE LIMITATIONS GROUND BASED / ELEVATED HELIPAD

ISA +35

ISA +20

ISA

0

2000

4000

6000

8000

10000

12000

20 22 24 26 28 30 32


PRE

SSUR

E A

LTIT

UDE

- ft


44 THF-A109E-0607-1

4.2.2 Fuel consumption vs Airspeed – AEO – SL (ISA)

FUEL FLOW - AEO - SL (ISA)

Best Range Speed

2500 Kg

2850 Kg3000 Kg

Vne

Lim

it

RECOMMENDED CRUISE SPEED

XMSN Limit

120

140

160

180

200

220

240

260

280

50 70 90 110 130 150 170 190

TRUE AIRSPEED - kts

FUE

L FL

OW

- kg

/h

265

305

345

385

425

465

505

545

585

93 133 173 213 253 293 333

TRUE AIRSPEED - km/h

FUE

L FL

OW

- lb

/h


THF-A109E-0607-1 45

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

FUEL FLOW - AEO - SL (ISA+20)

BEST ENDURANCE SPEED

2850 kg

2500 kg

V NE L

IMIT

3000 Kg


MCP Limit

120

140

160

180

200

220

240

260

280

50 70 90 110 130 150 170 190

TRUE AIRSPEED - kts

FUE

L FL

OW

- kg

/h

265

305

345

385

425

465

505

545

585

93 133 173 213 253 293 333


FUE

L FL

OW

- lb

/h


46 THF-A109E-0607-1

4.2.4 Fuel consumption vs Airspeed – AEO – 5000 ft (ISA)

FUEL FLOW - AEO - 5000m (ISA)

BEST ENDURANCE SPEED

2500 kg

2850 kg

V NE L

IMIT

3000 kg


XMSN Limit

120

140

160

180

200

220

240

260

280

50 70 90 110 130 150 170 190

TRUE AIRSPEED - kts

FUE

L FL

OW

- kg

/h

265

305

345

385

425

465

505

545

585

93 133 173 213 253 293 333


FUE

L FL

OW

- lb

/h


THF-A109E-0607-1 47

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

FUEL FLOW - AEO - 5000m (ISA+20)

BEST ENDURANCE SPEED 2500 kg

2850 kg

V NE L

IMIT

3000 kg


MCP Limit

120

140

160

180

200

220

240

260

280

50 70 90 110 130 150 170 190

TRUE AIRSPEED - kts

FUEL

FLO

W -

kg/h

265

305

345

385

425

465

505

545

585

93 133 173 213 253 293 333


FUEL

FLO

W -

lb/h


48 THF-A109E-0607-1

5 SUPPORT AND MAINTENANCE

This Chapter includes information about the helicopter maintenance and support. Further information on the specific subjects are available through the pertinent publications herein indicated and in the Pratt & Whitney “PW200 Customer Support Handbook” publication as far as the engines are concerned.

5.1 INSPECTION PROGRAMMES

The operator may choose from three inspection programmes, as indicated in the schemes below, 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, 100, 400, 800, 3200 hour inspection and 12 months inspection.

Standard Inspection Programme scheme


THF-A109E-0607-1 49

b. Extended Programme

The scheduled inspections consist of a basic 50 hours/30 days inspection, standard 200, 400, 800 3200 hours inspection and 12 months inspection

Extended Inspection Programme scheme

c. Progressive Programme

The scheduled inspections consist of a basic 50 hours/30 days inspection, progressive 200 and 400 hours inspection (both divided into four phases), 800 hours and 3200 hours inspection plus 12 months inspection (divided into three phases).

Progressive Inspection Programme scheme

The operator may also decide to shift in the programme according to a defined procedure.


50 THF-A109E-0607-1

5.2 OVERHAUL COMPONENTS

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

PART NUMBER Item Quantity per A/C TBO (FH)

160SG139Q2-1 Starter Generator 2 1,000

109-0900-39-103 Main Landing Gear actuator 2 4,000 LND

109-0500-10-107 Nose Landing Gear actuator 1 4,000 LND

109-0400-03-109 Main Transmission Assy 1 4,800

109-0440-01-121 Tail Rotor Gearbox Assy 1 3,000

109-0110-42-124/5/6 Main Rotor Servo Actuator Assy 3 1,800

109-0040-51-103 Tail Rotor Servo Actuator Assy 1 1,800

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, are available through the Agusta “Dynamic Components Overhaul Policy & Price List”. Engine components subject to overhaul are listed in PW206C engine maintenance Manual.

5.3 RETIREMENT LIFE COMPONENTS

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

PART NUMBER Item Quantity per A/C

RETIREMENT LIFE (FH)

109-0503-44-103 NOSE LANDING GEAR 1 9,000 Lnd

109-0503-45-101/-102 MAIN LANDING GEAR 1 8,000 Lnd

109-0200-02-93 ELEVATOR, LH 1 4,400

109-0210-03-13 FITTING 1 5,000

109-0322-69-101 PIN 1 3,000

109-0111-05-121 GRIP ASSY 4 10,000

109-0405-76-107 SHAFT ASSY 1 8,100


THF-A109E-0607-1 51

PART NUMBER Item (Continue) Quantity per A/C

RETIREMENT LIFE (FH)

109-0325-08-109 FITTING LOWER 4 19,000

109-0455-09-103 BELT, TOOTHED 2 600 or 2 Years

109-0325-08-1 FITTING, LOWER 4 19,000

109-8131-07-1 RETENTION STRAP ASSY 2 1,800

109-8131-08-1 STRAP PIN 2 5,000

109-8131-06-1 STRAP PLUG 2 5,000

709-0160-47-101 BOLT, RETENTION STRAP 2 5,000

709-0160-48-101 T/R BLADE 2 15,000

109-0131-06-101 HUB ASSEMBLY 2 3,000

109-0110-90-103 BOLT 2 5,000

109-0110-05-101 SWASHPLATE SUPPORT 1 17,000


52 THF-A109E-0607-1

6 ESTIMATED DIRECT OPERATING COST AND RELATED DATA

6.1 GENERAL INFORMATION

This chapter provides information on the Direct Operating Costs (DOC) connected with the typical operation of the A109POWER helicopter. It is assumed that the helicopter is civil certified and operates in a temperate climate and in a non-corrosive environment (recommended anti-corrosive measures must be observed for offshore 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. The DOCs may vary depending upon parameters such as flight hours per year, operational life, engine cycle, etc.; a typical usage spectrum for a corporate configuration has been analysed with the following assumptions:

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

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

- Fuel & Lubricants - Airframe Direct Maintenance - Powerplant Maintenance

The following sections provide additional rationale for the data reported in this chapter.

6.1.1 FUEL AND LUBRICANTS

The data shown reflects the average fuel consumption assuming operation at the optimum range speed, at 1,000 ft altitude, and ISA conditions. The 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.

6.1.2 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-A109E-0607-1 53

b. Parts

- Inspections consumables: the data shown refers to the cost of the parts replaced during scheduled inspections;

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

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

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

6.1.3 POWERPLANT MAINTENANCE

The Powerplant direct operating cost estimate includes costs for periodic inspections and overhauls as per P&WC Engine Maintenance Cost for PW206C engines. Since the engine overhaul interval is bound by both operating hours and engine cycles, the engine cycles assumed are 1 engine cycle per flight hour, as stated above. Additionally, it is assumed that the aircraft Powerplant overhaul is performed by the engine manufacturer. The table below reports detailed information about estimated DOCs. Further information is available through AgustaWestland Company Customer Support and Marketing Organizations.

Economic Conditions 2005 Operator

MMH/FH

Hourly Op.

Cost (USD)

Fuel and lubricants

Fuel11 65 USG/h at 138 kts 146.25

Lubricants 3% of fuel cost 4.39

Direct Maintenance

Airframe Line Maintenance Labor12:

- Scheduled Maintenance 0.90 58.36

- Unscheduled Maintenance 0.44 28.89

Airframe Parts:

- Inspections Consumables 3.87

- Unscheduled 157.87

- Overhaul Components 15.23

- Life-Limited Parts 2.36

Powerplant Parts:

- Line Maintenance & Overhaul Incl. Accessories13 130.12

TOTAL DOC PER FH 547.34

11 Fuel at USD 2.25 per USG 12 Labor at USD 65 per hour 13 Pratt & Whitney Engine Maintenance Cost (DMC) for PW206C, 1 cycle per hour


54 THF-A109E-0607-1

7 SERVICE PLANS

Several maintenance programmes are available at guaranteed cost either for the airframe or for the engine with different coverage in order to better meet the Customer requirements.

7.1 AIRFRAME MAINTENANCE PROGRAMMES

The airframe maintenance programme available through Agusta are:

GSP (Global Support Plan)

COMP (Complete Overhaul and Maintenance Programme)

CPA (Components Protection Agreement)

7.1.1 Global support plan (GSP)

Global Support Plan (GSP) is specifically designed 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. 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)

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

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


THF-A109E-0607-1 55

7.1.2 Complete overhaul and maintenance programme (COMP)

Complete Overhaul and Material Program (COMP) is specifically designed 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. 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)

COMPONENTS PROTECTION AGREEMENT (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 CPA provides repair, overhaul and replacement for the parts covered under this Plan at a fixed rate for every flight hour.

MAIN COVERED COMPONENTS: − Main Gearbox

− Tail Rotor Gearbox

− Main & Tail Rotor Servos


56 THF-A109E-0607-1

− Swashplate Assembly

− Main & Tail Rotor Hub Assembly

− Main & Tail Rotor Blades

− Hydraulic Pumps

− Starter Generators

− Nose Landing Gear

− Main Landing Gear.

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

The PW206C engines can take advantage of a guaranteed maintenance programme named ESP™ (Eagle Service Plan), managed directly by Pratt & Whitney. The Arrius 2K1 engines can take advantage of a guaranteed maintenance programme named SBH™ (Support by the Hour) service, managed directly by Turbomeca.

7.2.1 Pratt & Whitney – Eagle Service Plan (ESP)

ESP™ is a “pay–by–the–hour” budgeted maintenance plan designed to cover major scheduled and unscheduled (due to P&W material or workmanship defect) engine and LRU/accessory maintenance, where Pratt & Whitney becomes responsible for expenses resulting from:

− Scheduled Engine Overhaul

− Basic unscheduled engine maintenance

− Basic unscheduled LRU/accessory maintenance

− Required Product Support improvements at engine shop visit

− It includes:

− Parts

− Labour

− Freight

− Life Limited Parts

− Plus allowance for


THF-A109E-0607-1 57

− Removal/Installation

− Troubleshooting

− Support Spare Engine

− Required Hot Section Inspection

For this coverage the operator pays a monthly fee based on the number of hours flown in a given month multiplied by a specified US dollar rate per hour ($/h).

Detailed information about ESP are available through the PRATT & WHITNEY “ESP – Eagle Service Plan” publication.

7.2.2 Turbomeca – Support By the Hour (SBH)

SBH™ is a global support service offered to operators, to enable them to maintain the best availability of their engine fleet through a contract arrangement paid by running hours only. Turbomeca classic SBH includes: Parts and labour for:

− Overhaul

− Unscheduled repairs

− Life limited parts. Standard exchange for engine and LRU (repairable) through Turbomeca engine and LRU’s pool

Embodiment of mandatory and recommended modifications

For this coverage, the operator pays a monthly fee based on the number of hours flown during the month multiplied by the SBH rate.

More information about the SBH programme can be obtained directly through TURBOMECA Operators Support Department.

7.3 WARRANTIES

7.3.1 Airframe Warranty

The A109POWER 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 PW206C engine is covered by Pratt & Whitney warranty. For an outline of Pratt & Whitney warranty see the “PW200 Customer Support Handbook” publication. The Arrius 2K1 engine is covered by Turbomeca warranty. Detailed information about Turbomeca is available through the Turbomeca applicable documentation.


58 THF-A109E-0607-1

7.4 EXCHANGE PROGRAMME

7.4.1 Agusta Exchange Programme

The Agusta Exchange Programme offers reconditioned components at special price while recognizing a credit for turn–in components thereby reducing to a minimum the helicopter down–time and additionally contributes to minimize the operating costs. Detailed information about AGUSTA EXCHANGE PROGRAMME are available through the Agusta Customer’s Support.

7.4.2 Pratt & Whitney Rental/Exchange Programme

Further information about PRATT & WHITNEY RENTAL/EXCHANGE PROGRAMME are available through the Pratt & Whitney “PW200 CUSTOMER SUPPORT HANDBOOK” publication.

7.5 RECOMMENDED GROUND SUPPORT EQUIPMENT (GSE)

Each helicopter is supplied with a set of Ground Support Equipment including:

• Main Rotor Blade Anchoring Equipment

• Pitot Tube Covers

• Engine Air Intake Cover, RH LH

• Wheel Chocks

• Engine Exhaust Cover, RH & LH

• Mooring And Lifting Plate

• Lifting Hook

• All–Weather Protective Covers Kit.

7.6 TECHNICAL PUBLICATIONS

Each helicopter is supplied with a set of technical publications, including

Helicopter Log Book

• Flight Manual – A109POWER

• Manufacturer's Data

• Maintenance Manual – A109POWER

• Overhaul Manual – A109POWER

• Illustrated Parts Breakdown – A109POWER

• A109 Technical Bulletin Set

• A109 Information Letter Set

• General Information Letter Set


THF-A109E-0607-1 59

• Maintenance Manual – Turboshaft Pratt & Whitney PW206C or Turbomeca Arrius 2K1

• Illustrated Parts Catalog –Turboshaft Pratt & Whitney PW206C or Turbomeca Arrius 2K1

• A set of: Service Bulletins, Spare Parts Bulletins, Service Information Letters for Pratt & Whitney PW206C or Turbomeca Arrius 2K1

• Vendor Equipments Publications (as received from the Vendors themselves).

7.7 STANDARD TOOLS

Detailed information about Agusta standard tools are available through the Agusta “A109POWER maintenance manual” publication.

THE DATA SET FORTH ON THIS DOCUMENT ARE GENERAL IN NATURE. 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

60 THF-A109E-0607-1

8 TRAINING

8.1 AGUSTA TRAINING CENTRE

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 available courses range from basic training for unskilled personnel to the specialized training for skilled personnel, depending on the particular requirements of the Customer.

8.1.2 The Simulator

In order to enhance effectiveness of training and provide successful means towards increasing flight safety, AgustaWestland has joined forces with CAE in the ROTORSIM consortium, a joint venture owned equally by CAE and AgustaWestland to carry out integrated training solutions for a range of AgustaWestland helicopters. The A109POWER “full flight simulator” (STD-1H Level D), available from the 2nd quarter of 2006, will be EASA/FAA certified, and will provide training for a range of operations including, but not limited to, search and rescue, offshore, emergency medical services, and night vision, allowing for training of A109POWER operators worldwide.

8.2 TRAINING COURSES

− Pilot Ground Course

− Pilot Transition Course (VFR/IFR)

− Airframe Maintenance Course

− Engine Line Maintenance Course

− Avionic Course


THF-A109E-0607-1 61

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 AgustaWestland 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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