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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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.


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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

2.10

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

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


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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

3.2

3.3

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

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

OPTIONAL EQUIPMENT....................................................................................... 29 3.3.1

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


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4

4.2

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

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

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

7

6.1.1

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

6.1.2

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

6.1.3

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

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


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7.1

7.2

7.3

7.4

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

ENGINE MAINTENANCE PROGRAMME.............................................................. 56 7.2.1

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

7.2.2

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

WARRANTIES ....................................................................................................... 57 7.3.1

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

7.3.2

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

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


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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.


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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,

•

Law Enforcement,

• VIP and Corporate transportation,

•

Offshore passenger transportation,

• Emergency medical service (EMS),

•

Harbour pilot shuttle,

• Search And Rescue (SAR) operations,

•

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


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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

EUROPE USA AUSTRIA ENGLAND FRANCE GERMANY SPAIN SWITZERLAND POLAND BRAZIL RUSSIA SOUTH AFRICA CHINA PHILIPPINES INDIA VENEZUELA AUSTRALIA JAPAN

ENAC EASA FAA ACAA CAA DGAC LBA DGAC FOCA ULC CTA ARIAC SACAA CAAC ATO DGCA INAC CAA JCAB

Ente Nazionale per l'Aviazione Civile European Aviation Safety Agency Federal Aviation Administration Austrian Civil Aviation Authority Civil Aviation Authority Direction Generale de l' Aviation Civile Luftfahrt – Bundesamt Dirección General de Aviación Civil Federal Office for Civil Aviation Civil Aviation Authority of Poland Centro Técnico Aerospacial Aviation Register of the Interstate Aviation Committee South African Civil Aviation Authority Civil Aviation Administration of China Air Transportation Office Directorate General Civil Aviation Istituto Nacional de Aviación Civil Civil Aviation Authority Japan Civil Aviation Bureau


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3

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

Main rotor diameter

11.00 m

36 ft 1 in

Tail rotor diameter

1.94 m

11 ft 7 in

Wheel track

2.15 m

7 ft 1 in

Wheel base

3.53 m

12 ft

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

ROTORS

LANDING GEAR

OVERALL DIMENSIONS Length (rotors turning)


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A109 Power External dimensions


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5

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

1.65 m3

58.3 ft3

Max length

2.10 m

6 ft 11 in

Max width

1.61 m

5 ft 03 in

Max height

1.28 m

4 ft 02 in

3

123.6 ft3

Max length (with optional baggage ext.)

2.30 m

7 ft 07 in

Max width

1.10 m

3 ft 07 in

Max height

0.71 m

2 ft 04 in

3

33.55 ft3

Volume CABIN

Volume

3.50 m

BAGGAGE COMPARTMENT

Volume

0.95 m


6

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Internal dimensions (m/ft)


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7

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 BASIC EMPTY WEIGHT (Weight tolerance ±2%) 1 MAX GROSS WEIGHT (internal loads) 2

lb

1585

3494

2850/3000 6283/6614

MAX GROSS WEIGHT (external loads)

2.5

kg

3000

6614

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) 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). 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 starboard side of the fuselage. Total capacity∗

2.7

kg

lb

l

USG

3-CELL fuel system

484

1067

605

160

4-CELL fuel system

559

1232

699

185

5-CELL fuel system

668

1473

835

221

ENGINE RATINGS

Rating (Sea level, ISA)

2.8

Turbomecca Arrius 2K1 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

TRANSMISSION RATINGS

Rating∗∗

∗

Pratt&Whitney P&W206C kW shp

Power 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)

∗∗


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9

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


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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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11

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.

22000 20000

16000 14000 12000 ISA

10000 8000

5 +3

ISA

Pressure Altitude - ft

18000

6000 4000 2000 0 -50

-40

-30

-20

-10 0 10 20 30 Temperature (OAT) - °C

40

50

60

Temperature – Altitude operational envelope


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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 FUSELAGE STA - in 126 127 128 129 130 131 132 133 134 135 136 137 138 139 140 141 31

68 3000 kg

30

66

sta 3350 29

64

2850 kg

62

28

2720 kg 60

27

sta 3245

MAST

2600 kg

26

58 56

25 54 24 52

sta 3550

23

50

22

48

sta 3220 21

GROSS WEIGHT - lb x 100

GROSS WEIGHT - kg x 100

sta 3521

46

2100 kg 20

44

19

sta 3458

42 1850 kg

18 3200

3250

3300

3350

3400

3450

3500

3550

40 3600

FUSELAGE STA - mm

CG LATERAL ENVELOPE LATERAL STA - in -3.5

-2.5

-1.5

-0.5

0.5

1.5

2.5

3.5 68

31 3000 kg

30

66 bl 40

bl -40

64

29

2850 kg


60

CENTRELINE

27

58

26

56 25 2450 kg

54

24 52 23

50

22

48

bl 80

bl -80 21

GROSS WEIGHT - lb x 100

62

28

46

20

44

19

42

1850 kg

40

18 -90

-70

-50

-30

-10

10

30

50

70

90

LATERAL STA - mm

Longitudinal and lateral CoG limits 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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13

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

km/h

291

276

289

272

285

271

263

266

RECOMMENDED CRUISE 4 SPEED (TAS)

kts

141

142

140

142

140

141

140

140

km/h

261

163

159

163

259

161

259

259

RATE OF CLIMB (TOP)

ft/min

2370

2400

2080

2100

1930

1950

1500

1520

nm

325

324

321

323

318

323

315

315

km

601

601

594

598

590

598

584

584

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

h:min

4:29

4:29

4:22

4:21

4:17

4:16

4:12

4:10

MAXIMUM CRUISE SPEED (TAS)

3-CELL MAX RANGE

5

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

5-CELL MAX ENDURANCE 668 kg usable fuel–no reserve

2.10.4 TWIN ENGINE OPERATION (5000 Ft) Gross weight

2500 kg – 5512 lb

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

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

km/h

293

272

291

269

287

265

281

261

kts

137

140

137

140

137

140

139

137

km/h

254

259

254

259

254

259

258

254

ft/min

2430

2110

2130

1830

1970

1690

1530

1250

nm

378

381

371

372

365

367

359

361

km

700

706

687

690

677

679

666

669

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

h:min

5:06

5:05

4:56

4:54

4:51

4:48

4:45

4:42

RATE OF CLIMB (TOP) 3-CELL MAX RANGE

4

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

5-CELL MAX ENDURANCE 668 kg usable fuel–no reserve

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. 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.

14

THF-A109E-0607-1

2.10.5 Twin Engine Operation AEO – (Altitude Performance) 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

ft

>20000

17900

18000

14300

16600

12700

15000

11000

m

>6100

5456

5486

4359

5059

3871

4572

3352

ft

15900

11700

13400

8700

11800

6900

9200

4600

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

HIGE (TOP)

HOGE (TOP)

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

2500 kg – 5512 lb

2720 kg – 5997 lb

ISA

ISA+20°C

ISA

ft

7000

2000

4000

m

2134

610

1220

ft/mi

1200

870

1000

700

m/s

6.1

4.4

5.1

SERVICE CEILING

ft

16400

13200

(100 ft/min ROC)

m

4998

ft m

HIGE

RATE OF CLIMB (SL)

VTOL CAT A

2850 kg – 6283 lb

3000 kg – 6614 lb

ISA+20°C

ISA

ISA+20°C

ISA

ISA+20°C

(5)

2600

(6)

(6)

(6)

900

610

760

620

3.6

4.6

3.1

3.9

3.1

14200

10900

13100

9500

11700

7700

4023

4328

3322

3993

2895

3567

2347

7500

3000

4200

0

2800

(7)

(6)

(8)

2285

914

1280

0

853

792

2.10.7 One Engine Inoperative MCP Power 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

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


THF-A109E-0607-1

15

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):

EPNdB

ICAO noise limits EPNdB

Takeoff

91.3

94.6

Fly-over

90.9

93.6

Approach

91.4

95.6

Flight condition

POWER

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

EPNdB

ICAO noise limits EPNdB

Takeoff

91.7

94.8

Fly-over

91.3

93.8

Approach

91.7

95.8

Flight condition

POWER

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 dB(A)

Speech Interference Level SILdB

Standard comfort

92

84

Silent

89

81

Paulstra - Ultra Silent

85

77

Soundproofing type

(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


16

THF-A109E-0607-1

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 a.

1585 Kg (3494 Lb)*

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


THF-A109E-0607-1

17

b.

Rotors and controls -

-

c.

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

Power plant and fuel system -

d.

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

Transmission drive system -

e.

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)

Electrical -

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


18

THF-A109E-0607-1

-

f.

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

Flight instruments – pilot -

g.

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

Instrumentation (on IDS displays) -

h.

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

Caution & Warning advisory -

i.

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

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


THF-A109E-0607-1

19

-

j.

Ventilation ram air inlets Anti reflection instrument panel

Exterior finishing -

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

3.1.2 Standard Additional Equipment -

(Installed in Current Production Aircraft) Increased internal gross weight (3 tonnes MTOW)(10 ) 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) 7

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 -

20.6 kg (45.3 lb)*

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 )

Not available on Turbomeca Arrius 2K1 equipped helicopter Weight tolerance ±2% 7

*


20

THF-A109E-0607-1

-

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 -

Airframe hour meter Dual control Rotor brake ** Retractable landing light( ) Windshield wipers (pilot/copilot) with wiper switch on cyclic grip ** Engine compartment fire extinguishers( ) Radio master switch with ground function Baggage compartment extensions (1.9 m) VLE & VLO extension up to 140 KIAS 8

8

3.1.6 Interior -

** *

15.0 Kg (33.1 Lb)*

Agusta colour scheme, from Agusta paint selection solid colour series 300

STANDARD CONFIGURATION WEIGHT

8

45.7 Kg (100.8 Lb)*

Air conditioning Garret ECU Primer finished cabin walls Vibration dampers installation

3.1.7 Painting -

35.0 kg (77.1 lb)*

1835 kg (4046 lb)*

Installations required for “CAT. A” operation

Weight tolerance ±2%


THF-A109E-0607-1

21

STANDARD CONFIGURATION INSTRUMENT PANEL

Typical IFR Dual Pilot Instrument Panel (King Avionic Package) 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18.

• MASTER WARNING push-button • MASTER CAUTION push-button ATTITUDE REVERSIONARY SWITCH ALTIMETER VHF/AM2CTRL PNL ADF CTRL PNL NAV 2 CTRL PNL MOVING MAP DISPLAY DME IND. CPLT MARKER BEACON IND ADI STAND-BY FLIGHT DIRECTOR MODE SEL VHF/AM1 CTRL PNL • AIRSPEED IND. NAV 1 CTRL PNL TRANSPONDER CTRL PNL ATTITUDE REVERSIONARY SWITCH • MASTER CAUTION push-button

19. 20. 21. 22. 23. 24. 25. 26. 27. 28. 29. 30. 31. 32. 33. 34. 35.

• MASTER WARNING push-button EADI • ENCODING ALTIMETER • VERTICAL SPED IND. ICS AUDIO CONTROL PNL • CLOCK ICS CONTROL PNL PILOT EHSI • #1 IDS • #2 IDS EMERGENCY LOCATOR CONTROL VERTICAL SPEED IND CPLT EHSI ICS CONTROL PNL PLACARD EADI AIR SPEED IND.

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


22

THF-A109E-0607-1

1. 2. 3. 4. PNL

HELIPILOT CTRL PNL MISCELLANEOUS PANEL GYROCOMPASS CTRL PNL FUEL MANAGEMENT CTRL

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

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)


THF-A109E-0607-1

23

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)


24

THF-A109E-0607-1

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 -

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 -

99.3 kg (219.0 lb)*

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



THF-A109E-0607-1

25

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

*



26

THF-A109E-0607-1

-

b.

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

“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

*



THF-A109E-0607-1

27

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

Fixed parts -

b.

3.2.6

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

H.P.S. (Harbour Pilot Shuttle) 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 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

Removable parts -

50.1 kg (110.4 lb)*

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



28

THF-A109E-0607-1

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

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

✓

-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

✓

13.0

28.7

✓ ✓

6.5

14.3

✓

Paulstra soundproofing (in lieu of Silent type)**

5/6 pax conversion kit ** (seating module replacing the aft cabinet)

Foldable litter Oxygen bottles (2)

***

9

*

H.P.S.

lb

ELITE

E.M.S.

kg

V.I.P.

CORPORATE

Item

CONVERTIBLE

✓ Suggested Applicability

Weight*

✓ ✓ ✓

✓ ✓ ✓

STD

Weight tolerance ±2% Delta Weight

** * 9

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


THF-A109E-0607-1

29

Single foldable forward facing seat 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 Six pax seats cushions (seat, backrest and headrest) with leather covering (in lieu of fabric covering) Six pax seats cushions with fabric covering (additional loose equipment) Sliding and rotating operator seat with rails ICS 3rd Station - AG 06 - Agusta/Gemelli Central Bench, 3 places, fabric covered with Shoulder harness with inertia reels and Safety belts 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 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

2.7

6.1

✓

40.4

89.1

✓

15.0

33.1

✓

12.0

26.5

✓

15.2

33.5

✓ ✓ ✓

3.1

6.8

28.7

63.3

✓

31.2

68.8

✓ ✓ ✓ ✓ ✓ ✓

34.8

76.6

✓ ✓ ✓

STD

✓ ✓

✓

3.3.2 External Painting ✓ Suggested Applicability

Customised painting scheme, solid colour series 300**

*

From 0 to 11.0

Customised Painting Scheme, Metallic Colour Series 500**

5.0

11.0

Main Rotor Blades High Visibility Painting

1.0

2.2

✓ ✓ ✓ ✓

✓ ✓ ✓ STD

✓ ✓ ✓

✓ ✓ ✓ ✓ ✓ ✓


**


30

H.P.S.

From 0 to 5.0

E.M.S.

lb

ELITE

kg

V.I.P.

Item

CORPORATE

Weight

CONVERTIBLE

*

THF-A109E-0607-1

3.3.3 Mission Equipment and Variants

H.P.S.

E.M.S.

ELITE

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

✓ ✓ ✓ ✓ ✓ ✓

113.0 249.1

✓ ✓ ✓ ✓ ✓ ✓

Emergency floats (removable parts, including 2 life rafts) RH electrically operated passenger step

4.5

9.9

✓ ✓

185 USG fuel system

6.8

15.0

✓ ✓

221 USG fuel system

13.2

29.1

✓ ✓

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

✓ ✓ ✓ ✓ ✓ ✓

4.7

10.3

✓ ✓ ✓

12.3

27.1

✓ ✓ ✓

Provisions for snow skis/slump protection pads**

Cargo hook provision (1000 kg) Cargo hook (1000 kg) (remov.parts) and rear view mirror

*

lb

V.I.P.

kg

CORPORATE

Item

CONVERTIBLE


Weight*

STD

✓ ✓ ✓ STD

✓ ✓

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


**


THF-A109E-0607-1

31

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

✓ ✓ ✓ ✓ ✓ ✓

10.4

23.0

MGB vibration isolator struts - Lord

✓ ✓

STD


32

THF-A109E-0607-1

3.3.4 Avionic Equipment a.

Collins Proline II single pilot IFR/FAA avionic package ** 10

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

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

H.P.S.

E.M.S.

ELITE

lb

V.I.P.

kg

CORPORATE

Item

CONVERTIBLE


Weight*

✓ ✓ ✓ ✓ ✓ ✓

AC system (2 inverters) Pilot navigation instruments (EADI & EHSI LCD, Standby 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%


THF-A109E-0607-1

33

b.

Additional Avionic Equipment

Weather Radar RDR 2000 (displayed on Plt/Cptl EHSI) Moving Map Observer Structural Provision (in lieu of KMD 550 installation Moving Map (in lieu of KMD Oberver MK 550 installation) III

✓ ✓

H.P.S.

ELITE

E.M.S.

✓ ✓ ✓

6.6

14.6

2.4

5.3

✓ ✓ ✓ ✓ ✓ ✓

Skyforce** or equiv.

2.3

5.0

✓ ✓ ✓ ✓ ✓ ✓

Bendix/King

STD

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

✓ ✓ ✓ ✓ ✓ ✓

10.0

22.1

✓ ✓ ✓ ✓ ✓ ✓

1.5

3.3

✓ ✓

CVR/FDR

L3

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

*

lb

V.I.P.

kg

CORPORATE

Item

CONVERTIBLE


Weight*

✓ ✓

✓


**


34

THF-A109E-0607-1

3.3.5 Special Mission Equipment

H.P.S.

E.M.S.

ELITE

6.0

13.2

✓ ✓ ✓

Bendix/King

22.0

48.5

✓ ✓ ✓

V/UHF AM-FM (analog or Flexcomm II digital)

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

21.7

47.8

✓ ✓ ✓


Sea Flir II or III

8.8

19.4

✓ ✓ ✓

FLIR installation

Sea Flir II or Flir System III

26.0

57.3

✓ ✓ ✓


LEO II A-3

11.0

24.3

✓ ✓ ✓

FLIR installation

LEO II A-3

60.0 132.3

✓ ✓ ✓

VHF/FM

NTX 138/TH250

Nat

HF/SSB

HF 1050


FLIR installation

ULTRA FORCE II/LEOII- A5 ULTRA FORCE II/LEOII- A5

Flir System

Denel

17.4

✓ ✓ ✓

52.0 114.7

✓ ✓ ✓

7.9

Flir System

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

✓ ✓ ✓

4.0

8.8

✓ ✓ ✓ ✓ ✓

Fast ropes system (rope excluded)

*

lb

V.I.P.

kg

CORPORATE

Item

CONVERTIBLE


Weight*



THF-A109E-0607-1

35

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)


36

THF-A109E-0607-1

4.1.1 Hovering IGE – AEO (TOP)

HOVERING IGE - AEO (MCP) GROSS WEIGHT - lb x 100 44

48

52

56

60

64

68

20000

6000

18000

A IS 5000

A IS

16000

0 +2

PRESSURE ALTITUDE - ft

5 +3

4000

12000

10000

3000

8000

PRESSURE ALTITUDE - m

A IS

14000

2000

2850 kg

3000 kg

6000

4000

1000

2000

0

0 18

20

22

24

26

28

30

32



THF-A109E-0607-1

37

4.1.2 Hovering IGE – AEO (MCP)

HOVERING IGE - AEO (MCP)

20000

18000

A IS

16000

A IS 0 +2

12000

A IS 5 +3


14000

10000

8000

6000

2000

3000 Kg

2850 Kg

4000

0 20

22

24

26

28

30

32



38

THF-A109E-0607-1

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

HOVERING IGE - OEI (2'30" POWER)

20000

18000

16000

12000

10000

8000

A IS


14000

ISA

6000

0 +2

ISA

4000

5 +3

2000

0 20

22

24

26

28

30

32



THF-A109E-0607-1

39

4.1.4 Hovering OGE – AEO (TOP)

HOVERING OGE - AEO (TOP)

20000

18000

16000

IS A

A IS

12000

0 +2

10000

A IS 5 +3

8000

2850 Kg

6000

4000

3000 Kg


14000

2000

0 20

22

24

26

28

30

32



40

THF-A109E-0607-1

4.1.5 Hovering OGE – AEO (MCP)

HOVERING OGE - AEO (MCP)

20000

18000

16000

A IS

12000

A IS 0 +2

10000

ISA

2850 Kg

6000

3000 Kg

8000

5 +3


14000

4000

2000

0 20

22

24

26

28

30

32



THF-A109E-0607-1

41

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

HOVERING OGE - OEI (2'30" POWER)

20000

18000

16000


14000

12000

10000

8000

A IS

6000

ISA

ISA

0 +2

4000

+35

2000

0 18

20

22

24

26

28

30

32



42

THF-A109E-0607-1

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

12000

8000

6000

ISA


10000

4000

ISA +20

ISA +35

2000

0 20

22

24

26

28

30

32



THF-A109E-0607-1

43

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

FUEL FLOW - AEO - SL (ISA) TRUE AIRSPEED - km/h 93

133

173

213

253

293

333

280

585 260 XMSN Limit 545 240

465 200

425

3000 Kg

180

2850 Kg

FUEL FLOW - lb/h

220

Vne Limit

FUEL FLOW - kg/h

505 RECOMMENDED CRUISE SPEED

385

160

345 2500 Kg

Best Range Speed

140

305

120 50

70

90

110

130

150

170

265 190

TRUE AIRSPEED - kts


44

THF-A109E-0607-1

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

FUEL FLOW - AEO - SL (ISA+20) TRUE AIRSPEED - km/h 93

133

173

213

253

293

333

280 585 260 545

MCP Limit 240

465

RECOMMENDED CRUISE SPEED

200

3000 Kg 2850 kg

180

425

FUEL FLOW - lb/h

220

VNE LIMIT

FUEL FLOW - kg/h

505

385 160

345

2500 kg BEST ENDURANCE SPEED

140

305

120

265 190

50

70

90

110

130

150

170

TRUE AIRSPEED - kts


THF-A109E-0607-1

45

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

FUEL FLOW - AEO - 5000m (ISA) TRUE AIRSPEED - km/h 93

133

173

213

253

293

333

280

585 260 545 240

XMSN Limit

465 200

425

RECOMMENDED CRUISE SPEED

180

FUEL FLOW - lb/h

220

VNE LIMIT

FUEL FLOW - kg/h

505

385 3000 kg 160

2850 kg

345

140 BEST ENDURANCE SPEED

305

2500 kg

120 50

70

90

110

130

150

170

265 190

TRUE AIRSPEED - kts


46

THF-A109E-0607-1

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

FUEL FLOW - AEO - 5000m (ISA+20) TRUE AIRSPEED - km/h 93

133

173

213

253

293

333

280

585 260 545 240

MCP Limit

465

200 425 RECOMMENDED CRUISE SPEED

180

2850 kg 160

FUEL FLOW - lb/h

220

VNE LIMIT

FUEL FLOW - kg/h

505

385

3000 kg 345

140

305 BEST ENDURANCE 2500 kg SPEED

120 50

70

90

110

130

150

170

265 190

TRUE AIRSPEED - kts


THF-A109E-0607-1

47

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


48

THF-A109E-0607-1

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. 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-A109E-0607-1

49

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. Quantity RETIREMENT LIFE (FH) per A/C

PART NUMBER

Item

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


50

THF-A109E-0607-1

PART NUMBER

Item (Continue)

Quantity RETIREMENT LIFE (FH) per A/C

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


THF-A109E-0607-1

51

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.


52

THF-A109E-0607-1

b. 6.1.3

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.

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

Hourly Op.

MMH/FH

Cost (USD)

Fuel and lubricants Fuel11

65 USG/h at 138 kts

Lubricants

3% of fuel cost

146.25 4.39

Direct Maintenance Airframe Line Maintenance Labor12: - Scheduled Maintenance

0.90

58.36

- Unscheduled Maintenance

0.44

28.89

Airframe Parts: - Inspections Consumables - Unscheduled - Overhaul Components - Life-Limited Parts

3.87 157.87 15.23 2.36

Powerplant Parts: - Line Maintenance & Overhaul Incl. Accessories13 TOTAL DOC PER FH

130.12 547.34

11

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


THF-A109E-0607-1

53

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. 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.

54

THF-A109E-0607-1

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


THF-A109E-0607-1

55

−

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:

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

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


56

THF-A109E-0607-1

−

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.


THF-A109E-0607-1

57

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:

7.6

•

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.

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


58

THF-A109E-0607-1

7.7

•

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).

STANDARD TOOLS

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


THF-A109E-0607-1

59

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

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

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: agusta@it.agusta.com AGUSTAWESTLAND UK Yeovil, Somerset BA20 2YB United Kingdom Tel. +44 (0) 1935 475222 Fax +44 (0) 1935 702131 e-mail: info@whl.co.uk AGUSTA AEROSPACE SERVICES S.A. Liège Aéroport, Bldg 60 B–4460 Grace – Hollogne Belgium Tel. +32 4 2342323 Fax +32 4 2341945 e-mail: aas@be.agusta.com 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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