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THE DATA SET FORTH ON THIS DOCUMENT ARE PRELIMINARY AND 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

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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 generalinformation purposes only. The exact description, characteristics, and performance capabilities of any particular aircraftmay vary and are wholly dependent on the final configuration requested by the Customer and on the specific aircraftusage, operation and maintenance. For performance data and operating limitations reference must be made to theapproved Flight Manual and other appropriate documentation.

THE INFORMATION CONTAINED IN THIS DOCUMENT IS SUBJECT TO CHANGE WITHOUT NOTICE AND IN ANYCASE IT DOES NOT CONSTITUTE AN OFFER NOR A CONTRACTUAL COMMITMENT, UNLESS SPECIFICALLYAGREED 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 (TYPE AND OPERATIONAL APPROVAL)..................................................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 POWERPLANT ..........................................................................................................9

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

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

2.9.1 Maximum operational flight speed ISA Sea level..........................................10

2.9.2 Wind envelope.................................................................................................10

2.9.3 Flight load factors ............................................................................................11

2.9.4 Slope landing...................................................................................................11

2.9.5 Static landing gear loading ..............................................................................11

2.9.6 Temperature and altitude.................................................................................12

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

2.10.1 CG longitudinal and lateral envelope............................................................... 13

2.11 PERFORMANCE SUMMARY TABLES ...........................................................................14

2.11.1 Twin-engine operation (AEO) Sea level........................................................14

2.11.2 Twin-engine operation (AEO) 5000 ft ...........................................................14

2.11.3 Twin-engine operation (AEO) Altitude performance ..................................... 15

2.11.4 One engine inoperative (OEI) 230 Contingency power .............................. 15

2.11.5 One engine inoperative (OEI) MCP power (3175 kg) ................................... 15




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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

2.12.3 Engine smoke and emissions.......................................................................... 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........................................................................ 21

3.1.3

EASA/FAA Single pilot IFR avionic package (Garmin Bendix/King)............. 213.1.4 Additional installed avionic equipment ............................................................ 22

3.1.5 Installed utility equipment................................................................................ 22

3.1.6 Interior............................................................................................................. 22

3.1.7 Painting ........................................................................................................... 22

3.1.8 Miscellaneous/ground equipment.................................................................... 23

3.2 COMPLETIONS ....................................................................................................... 24

3.2.1 Corporate/De Luxe interior .............................................................................. 24

3.2.2

VIP interior ...................................................................................................... 24

3.2.3 Offshore/public transport interior ..................................................................... 25

3.2.4 HPS (Harbour Pilot Shuttle) interior ................................................................ 25

3.2.5 EMS (Emergency Medical Service) interior..................................................... 26

3.2.6 Painting ........................................................................................................... 26

3.3 OPTIONAL EQUIPMENT ........................................................................................... 27

3.3.1 Interior equipment ........................................................................................... 27

3.3.2 Utility equipment.............................................................................................. 28

3.3.3 EMS equipment............................................................................................... 30

3.3.4

Avionic equipment........................................................................................... 31

3.3.5 Special mission equipment ............................................................................. 33

4 PERFORMANCE DIAGRAMS.................................................................34

4.1 HOVERING ............................................................................................................ 35

4.1.1 Hovering IGE AEO (TOP) ............................................................................ 35

4.1.2 Hovering IGE AEO (MCP)............................................................................ 36

4.1.3 Hovering IGE OEI (230 Power).................................................................. 37




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4.1.4 Hovering OGE AEO (TOP)...........................................................................38

4.1.5 Hovering OGE AEO (MCP)...........................................................................39

4.1.6 Hovering OGE OEI (230 Power) ................................................................40

4.2 TAKEOFF AND LANDING PERFORMANCE (CATEGORYA) ............................................. 41

4.2.1 Weight Altitude limitations (Vertical procedure from elevated helipad and

backup procedure from ground/elevated helipad) .......................................................41

4.3 FUEL CONSUMPTION VSAIRSPEED ..........................................................................42

4.3.1 Fuel consumption vs Airspeed AEO SL (ISA)............................................42

4.3.2 Fuel consumption vs Airspeed AEO SL (ISA+20C)..................................43

4.3.3 Fuel consumption vs Airspeed AEO 5000 ft (ISA) ..................................... 44

4.3.4

Fuel consumption vs Airspeed AEO 5000 ft (ISA + 20C) ......................... 45

5 SUPPORT AND MAINTENANCE............................................................ 46

5.1 INSPECTION PROGRAMMES .....................................................................................46

5.2 OVERHAUL COMPONENTS .......................................................................................48

5.3 RETIREMENT LIFE COMPONENTS .............................................................................48

6 DIRECT OPERATING COST (DOC) ....................................................... 50

6.1 GENERAL INFORMATION .........................................................................................50

6.1.1 Fuel and lubricants ..........................................................................................50

6.1.2 Airframe direct maintenance............................................................................ 50

6.1.3 Powerplant maintenance .................................................................................51

7 SERVICE PLANS .................................................................................... 52

7.1 AIRFRAME MAINTENANCE PROGRAMME ....................................................................52

7.1.1

Global support plan (GSP)...............................................................................52

7.1.2 Complete overhaul and maintenance programme (COMP).............................53

7.1.3 Component protection agreement (CPA).........................................................53

7.2 ENGINE MAINTENANCE PROGRAMME ........................................................................54

7.2.1 Pratt & Whitney Canada Eagle Service Plan (ESP).........................................54

7.3 WARRANTIES.........................................................................................................55




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7.3.1 Airframe warranty............................................................................................ 55

7.3.2 Engine warranty .............................................................................................. 55

8 TRAINING ................................................................................................56

8.1 AGUSTAWESTLAND TRAINING CENTRES .................................................................. 56

8.1.1 The school....................................................................................................... 56

8.1.2 The simulator .................................................................................................. 56

8.2 TRAINING COURSES ............................................................................................... 57

9 USEFUL INFORMATION.........................................................................58




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1 INTRODUCTION

The Grand is a new top-of-the-range light twin helicopter developed to meet market requirementsin a multitude of applications. Positioned at the upper end of the light twinFAR/JAR 27 segment (3175 kg 7000 lb), the Grand features high performance capabilities,providing levels of cabin space and payload previously available only on intermediate-sizecategory helicopters, whilst retaining attractive economics typical of the light twin category.

The Grands spacious, unobstructed passenger cabin (2.30 m 7 ft 7 in max length) is easilyaccessible through large sliding cabin doors (1.40 m 4 ft 7in), one on each side of the fuselage. Acomprehensive selection of interiors and mission equipment makes the Grand a suitable platformfor a multitude of roles, including Corporate/VIP transportation, EMS, Law Enforcement, Offshoreand various Utility operations. The Grands 815 shp new generation Pratt & Whitney CanadaPW207C turboshaft engines with electronic control (FADEC) ensure outstanding performance

capabilities in both hovering and cruising flight, including full Cat. A/Class 1 capability, whilstretaining low fuel burn characteristics. The payload/range characteristics and the very high cruisespeed give the Grandcapabilities which are unique in its category.

The cockpit layout provides excellent visibility and an ergonomic working space for the pilots. Theinstrument panel incorporates four LCD displays for flight and navigation together with two LCDmultifunction displays (IDS) for aircraft/engine data monitoring, crew alerting and maintenance datapages. State-of-the-art avionics for single/dual pilot IFR operation, including a three-axis duplexautopilot coupled with a Flight Director, are standard features of the helicopter and maximise safetyof operations and a low pilot workload. High passive safety is available to the flight crew and thepassengers thanks to the cocoon-type high strength airframe fitted with a crash-resistant fuelsystem and crashworthy seats for both the pilot(s) and passengers.

The Grands composite material main and tail rotor blades feature optimised geometry and tipprofile for high aerodynamic efficiency and contribute to reduce external noise to levels well belowthe ICAO noise limits.Operating economics benefit from low level of maintenance requirements, both in terms ofmaterials and man-hours required. Only a few main components are subject to overhaul, whilst alimited number of low cost parts are subject to retirement: in both cases TBOs (Time BetweenOverhaul) or retirement hours are high. In addition, an attractive Warranty Policy and, alternatively,availability of competitive Pay-by-the-hour spare parts support programmes ensure optimumoperating cost control.




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1.1 MAIN CHARACTERISTICS

The Grandsatisfies the stringent market demand, fulfilling the new Civil Aviation regulations. Itsmain features include the following:

High Maximum takeoff weight (3175 kg 7000 lb) for increased payload/range capability

New generation Pratt & Whitney Canada PW207C engines with Full Authority DigitalEngine Control (FADEC)

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

Composite tail rotor blades

Crash-resistant seats for crew and passengers, crash-resistant fuel system, fail-safe designand redundancy of all systems to ensure high safety level

Full Cat. A Class 1 performance for safe operation

Excellent flying qualities, high controllability and manoeuvrability

Spacious passenger cabin (2.30 m 7 ft 7 in long) for high comfort

Wide cabin sliding door opening (1.40 m 4 ft 7 in max length) on both sides to ensureexcellent accessibility

Large separate baggage compartment (2.30 m 7 ft 7 in max length)

Particular care to soundproofing to obtain very low levels of cabin noise

State-of-the-art avionics for single/dual pilot IFR operation, including 3 axes duplexautopilot with Flight Director, 4 LCD screens for flight and navigation instruments, 2 LCD

multifunction displays (IDS) for aircraft/engine data monitoring and aircraft warnings (withvoice annunciation)

Capability to operate in congested or hostile environment and in extreme temperature,within - 25C and + 50C

Heavy duty retractable landing gear with high clearance for unprepared terrain

Reduced maintenance requirements by the wide use of reliable and on-conditioncomponents

Low operating costs and maximum airborne availability through different inspectionprogramme options suited for the customer needs, as well as fixed hourly rate maintenanceprogrammes available both for the airframe and the engines

1.2 APPLICATIONS

The great flexibility of the cabin layout and the wide range of optional equipment make the Grandsuitable 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, slingload carrying, news gathering, etc.




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2 LEADING FEATURES

The Grand is a twin-engine light category, multipurpose helicopter with crashworthy seats foraccommodating up to eight persons. The helicopter has a four-composite blade, fully articulatedmain rotor with elastomeric bearings and a semi-rigid, two-composite blade tail rotor system. Eachengine provides separate input to the main transmission. The twin-engine reliability is furtherenhanced by a dual fully separated crash-resistant fuel system, dual hydraulic system and dualelectric system.The fuselage and the empennage are of aluminium alloy construction for the primary structure andfibre composite material for the secondary structure. The landing gear is a three-wheel, retractable,tricycle type.

2.1 CERTIFICATION (TYPE AND OPERATIONAL APPROVAL)

The helicopter is designed and certifiedin compliance with:

JAR 27 Small Rotorcraft,Amendment 2

JAR 27Appendix C (assimilating JAR 29 selected paragraphs) for Category A

FAR 27 Small Rotorcraft, Amendment 1 to 8 included and from 11 to 28 where applicable

On this basis, the rotorcraft shall be approved for:

Day/night VFR (Visual Flight Rules) Single pilot operation permitted from the right seat

Day/night IFR (Instrument Flight Rules) Single pilot operation permitted from the rightseat

Category A operations

Other special mandatory airworthiness standards are:

HIRF requirements for in accordance with RTCA DO-160D

Software certification in accordance with RTCA DO-178B

The basis of certification for noise is:

ICAO Annex 16, Vol. I, Ch. 8

The reference for FAA noise certification is:

FAR part 36, Appendix H

The Grandis type certified asA109S, with Agusta S.p.A. being the Type Certificate holder.




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2.2 EXTERNAL DIMENSIONS

FUSELAGE

Length 11.65 m 38 ft 03 in

Width (elevator) 3.29 m 10 ft 10 in

Width (passengers cabin door) 1.64 m 5 ft 05 in

Height (tail fin) 3.44 m 11 ft 03 in

Fuselage ground clearance 0.40 m 1 ft 04 in

ROTORS

Main rotor diameter 10.83 m 35 ft 06 in

Tail rotor diameter 1.94 m 6 ft 04 in

LANDING GEAR

Wheel track 2.15 m 7 ft 01 in

Wheel base 3.74 m 12 ft 03 in

OVERALL DIMENSIONS

Length (rotors turning) 12.96 m 42 ft 06 in

Width (main rotor blade at 45) 7.76 m 25 ft 06 in

Height (top of tail fin) 3.44 m 11 ft 03 in

Main rotor clearance (rotor turning, controls in neutral position) 2.45 m 8 ft 00 in

Tail rotor clearance (rotor turning) 1.00 m 3 ft 03 in




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Grand 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 2.30 m 7 ft 07 in



Volume 3.90 m3 137.7 ft3

BAGGAGE COMPARTMENT

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



Volume 0.90 m3 31.8 ft3

Max load: 120 kg 265 lb




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Grand internal dimensions




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2.4 WEIGHTS

The Basic Empty Weight takes account of the main aircraft structure and all the essential

equipment. The complete description of the basic configuration is given in Section 3.1 (Para.3.1.1a to 3.1.1j included).The Maximum Gross Weight, relating to internal loads, equals the JAR/FAR 27 certification limit(3175 kg 7000 lb).

Weights kg lb

BASIC EMPTY WEIGHT1 1655 3649

MAX GROSS WEIGHT (internal loads) 3175 7000

MAX GROSS WEIGHT (external loads) 3200 7055

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 1150 2535

Primary cargo hook with secondary hook 500 1102

Rescue hoist 272 600

1Weight tolerance 2%




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2.6 FUEL CAPACITY

The fuel system is of modular-type with different capacities. The basicsystem is made of 3 crash-resistant cells, while other two optional configurations are available with the addition of the fourth

and the fifth crash-resistant fuel cell. Refuelling is performed by gravity through a single pointpositioned on the starboard side of the fuselage.

Total capacity

kg lb l USG

3-CELL fuel system 460 1014 575 152



2.7 POWERPLANT

Manufacturer and type: Pratt & Whi tney Canada PW207C

PowerRating (Sea level, ISA)

kW shp

AEO Takeoff power (5 min) 2 548 2 735

AEO Maximum continuous power 2 466 2 625OEI 2 30 Contingency power 608 815

OEI Maximum continuous power 548 735

2.8 TRANSMISSION

Manufacturer: Agusta

PowerRating

kW shp

AEO Takeoff power (5 min) 716 960

AEO Maximum continuous power 671 900

OEI 2 30 Contingency power 545 730

OEI Maximum continuous power 448 600

Unusable fuel: 10 kg 22.0 lb for all three tank configurations. Fuel density is assumed at 0.8 kg/lRating applicable at 100% rotor speed (384 rpm)




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2.9.3 Flight load factors

The flight load factor limits that apply to the Grandoperations at MGW are:

2.3 g POSITIVE

0.5 g NEGATIVE

2.9.4 Slope landing

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

10 LONGITUDINAL

10 LATERAL

2.9.5 Static landing gear loading

The loads reported below refer to the helicopter in the Grandmid-CG configuration.

Gross weight:

3175 kg 7000 lb

LoadingContact

Area

Contact

pressure

Nose Landing Gear715 kg1578 lb

0.0115 m217.9 in2

6.10 bar88.4 psi

Main Landing Gear2 x 1230 kg2 x 2711 lb

0.0198 m230.7 in2

6.10 bar88.4 psi




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2.9.6 Temperature and alti tude

The helicopter and its components are designed to operate in the air temperature and altitude

range defined in the diagram below.

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

22000

-50 -40 -30 -20 -10 0 10 20 30 40 50 60

Temperature - C

Pressure

Altitude-

ft

0

1000

2000

3000

4000

5000

6000

Pressure

Altitud

e-mISA

des

igno

bjective

Temperature Altitude operational envelope

Maximum pressure altitude for takeoff and landing: 16000 ft (4877 m)




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2.10 CG ENVELOPE

The following charts show the centre of gravity range limits.

2.10.1 CG longitudinal and lateral envelope

CG LONGITUDINAL ENVELOPE

3175 kg

2910 kg

2050 kg

2370 kg

2970 kg

MAST

18

20

22

24

26

28

30

32

34

3200 3250 3300 3350 3400 3450 3500 3550

FUSELAGE STA - mm

GROSSWEIGHT-

kgx

100

40

44

48

52

56

60

64

68

72

126 127 128 129 130 131 132 133 134 135 136 137 138 139

FUSELAGE STA - in

GROSSWEIGHT-

lbx

100

sta 3225

sta 3249

sta 3330 sta 3430

sta 3520

sta 3415

CG LATERAL ENVELOPE

2450 kg

2050 kg

2450 kg

3175 kg

CENTRELINE

18

20

22

24

26

28

30

32

34

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

LATERAL STA - mm

GROSSWEIGHT-

kgx

100

40

44

48

52

56

60

64

68

72

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

LATERAL STA - i n

GROSSWEIGHT-

lbx

100

bl - 40.0 bl 40.0

bl - 80.0 bl 80.0

CG longitudinaland lateral envelope

Station 0.0 mm is situated 718 mm aft the radome tip




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2.11 PERFORMANCE SUMMARY TABLES

2.11.1 Twin-engine operation (AEO) Sea level

Gross weight 2900 kg 6393 lb 3175 kg 7000 lbISA ISA+20C ISA ISA+20C

kts 161 158 155 154MAXIMUM CRUISE SPEED (TAS)

km/h 298 293 287 285

kts 140 137 135 135RECOMMENDED CRUISE SPEED

3(TAS)

km/h 261 254 250 250

ft/min 2120 2110 1830 1820RATE OF CLIMB (TOP)

m/s 10.77 10.72 9.30 9.25

3-CELL MAX RANGE4 nm 310 305 295 293

450 kg usable fuel no reserve km 574 565 546 543

3-CELL MAX ENDURANCE

450 kg usable fuel no reserveh:min 2:54 2:50 2:45 2:43

5-CELL MAX RANGE nm 459 448 432 427


5-CELL MAX ENDURANCE


2.11.2 Twin-engine operation (AEO) 5000 ft

Gross weight 2900 kg 6393 lb 3175 kg 7000 lb

ISA ISA+20C ISA ISA+20Ckts 161 152 155 146

MAXIMUM CRUISE SPEED (TAS)km/h 298 282 287 270

kts 135 135 135 135RECOMMENDED CRUISE SPEED

3(TAS)

km/h 250 250 250 250

ft/min 2100 2080 1780 1730RATE OF CLIMB (TOP)

m/s 10.67 10.57 9.04 8.79

RANGE4

nm 343 342 328 323


ENDURANCE

450 kg usable fuel no reserve h:min 3:13 3:09 3:03 2:57

MAX RANGE nm 501 500 480 475


MAX ENDURANCE


3The Recommended cruise speed represents, at given environmental condition and weight, the speed corresponding tothe 99% of the best specific range (nm/kg).

4The maximum range is evaluated at the Best range speed, that is the speed corresponding to the lowest specific fuelconsumption (kg/nm) for given environmental condition and weight.




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2.11.3 Twin-engine operation (AEO) Alt itude performance


ISA ISA+20C ISA ISA+20C

ft 18200 15200 15600 12400HIGE (TOP)

m 5550 4630 4750 3780

ft 13800 10600 10000 7700HOGE (TOP)

m 4210 3230 3050 2350

SERVICE CEILING (MCP) ft 18950 16000 16200 13100

(100 ft/min ROC) m 5775 4880 4940 3995

2.11.4 One engine inoperative (OEI) 230 Contingency power



ft/min 1320 1110 1070 880RATE OF CLIMB (SL)

m/s 6.71 5.64 5.44 4.47

SERVICE CEILING ft 14400 12000 11600 9000

(100 ft/min ROC) m 4390 3660 3535 2745

2.11.5 One engine inoperative (OEI) MCP power (3175 kg)



kts 135 130 130 125CRUISE SPEED (TAS SL)

km/h 250 241 241 231

kts 133 123 126 113CRUISE SPEED (TAS 5000 ft)

km/h 246 228 233 209

ft/min 830 690 620 490RATE OF CLIMB (SL)

m/s 4.22 3.51 3.15 2.49

SERVICE CEILING ft 12400 8500 9500 5500

(100 ft/min ROC) m 3780 2590 2895 1675

2.11.6 Cat. A takeoff and landing performance

See Section 4.2 herewith.




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2.12 ENVIRONMENTAL IMPACT

2.12.1 External noise level

The external noise level does not exceed the values specified by the last amendment 7 (2002) tothe ICAO International Standards and Recommended Practices, Environmental Protection, Annex16, Vol. I Aircraft Noise, Ch. 8.

GrandICAO noise

limitsFlight condition (MGW)

EPNdB EPNdB

Takeoff 90.5 92.0Fly-over 88.4 90.0

Approach 91.2 95.0

2.12.2 Internal noise level

The internal noise level may vary according to the internal soundproofing configuration, asindicated in the table5.

WeightedLevel

SpeechInterference

LevelSoundproofing type

dB(A) SILdB

Standard comfort 92 84

Silent 89 81

Paulstra - Ultra Silent 85 77

2.12.3 Engine smoke and emissions

Engine smoke emission meets the requirements defined by ICAO Annex 16, Vol. II Aircraftengine emissions. Moreover, an ecology system is installed to prevent fuel leakage after engineshutdown, and combustion chamber drains are provided for the fuel accumulating in case of falsestart or no-light.

5Preliminary data applicable to a VIP/Corporate layout for the following flight condition: 140 KTAS cruise speed 3000kg average gross weight 3000 ft altitude




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3 STANDARD CONFIGURATION AND OPTIONAL EQUIPMENT LIST

This section provides information on the aircraft standard configuration and optional interior andequipment available for the Grandand includes the following:

Section 3.1: Description of the GrandStandard configuration

Section 3.2: Completions, available as options for the interior and the external painting

Section 3.3: Optional equipment, available to customise the aircraft for specific applications

3.1 STANDARD CONFIGURATION (EASA/FAA IFR)

The helicopter Standard configuration incorporates the following main subsystems described indetail in this section:

Basic aircraft

Standard additional equipment

EASA/FAA Single pilot IFR avionic package (Garmin Bendix/King)

Additional installed avionic equipment

Installed utility equipment

Interior

Miscellaneous/ground equipment

3.1.1 Basic aircraft 1655 kg (3649 lb)*

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

a. Airframe

Aluminium alloy and bonded panel fuselage

Semimonocoque aluminium alloy tail boom

Two hinged jettisonable wide crew doors (on both sides)

Two sliding passenger doors on both sides, 1.40 m opening, with jettisonable windows

Acrylic windshield and side windows

Acrylic overhead windows

Quick removable tail rotor drive shaft cover

Three wheel retractable landing gears

Separate baggage compartment with hinged door

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




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Jacking and hoisting points

Removable fairing and cowlings, for complete accessibility to the controls and drivecomponents

Swivelling front wheel with tow bar attachment

Quick opening hinged inspection doors, to allow visual check of engine oil levels andmaintenance inspection points

Grounding points

b. Rotors and controls

Fully articulated corrosion-protected titanium main rotor hub with 4 composite grips, 4elastomeric bearings, 4 individually interchangeable composite blades with swept tips anddampers.

Two composite tail rotor blades, semi-rigid delta hinged type, individually interchangeable Cyclic and collective controls powered by two separate hydraulic systems

Hydraulically powered anti-torque T/R control system

Adjustable friction devices on cyclic and collective system

Force trim and artificial feel system

Adjustable directional control pedals

Dynamic main rotor blade flapping lock mechanism

c. Power plant and fuel system

Two Pratt & Whitney PW207C turboshaft engines

Two independent electronic control systems (FADEC) with normal, emergency and trainingoperation modes and autostart

Engine-mounted Fuel Management Unit (FMU), fuel pump and filter assembly

Engine-mounted oil pump and filter assembly

Lubrication and cooling system

Engine oil chip detectors (one per engine)

Engine control panel

Two independent fuel systems, with cross-feeding valve and control panel

3-cell crash-resistant fuel system (460 kg 152 USG)

Submerged fuel boost pump (one per system)

Airframe mounted easy access fuel filter

RH refuelling point

Locking fuel cap

Ground fuel drains




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d. Transmission drive system

960 shp for take off and 900 shp continuous operation main transmission, with two directdrive engine inputs

Three 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

Two transmission oil chip detectors

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)

e. Electrical system

24 volt DC 27 Ah nickel cadmium battery with temperature probe

Two 160 A self-cooled starter generators

Two voltage regulators

Battery relay

Two interconnecting bus relay

External power relay

Distribution buses (1 battery bus, 2 essential buses, 2 emergency buses, 2 main buses)

External power receptacle

Position lights

Two 150 W taxing lights

Two 250 W landing lights

Two cockpit utility lights

Two anti collision lights

Instrument lights with dimming switch

Radio master switch

f. Flight instruments pilot

Airspeed indicator

Instantaneous vertical speed indicator

Barometric encoding altimeter

Magnetic compass indicator

Clock, 8 days and elapsed time




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LC Integrated Display System (IDS)

g. Instrumentation (on IDS display)

Dual gas generator speed indicator (N1 %)

Dual turbine outlet temperature indicator (C)

Dual torque meter indicator (TRQ %)

Dual power turbine speed indicator (N2 %)

Rotor speed indicator (NR %)

Transmission oil temperature (C) and pressure (PSI) indicator

Two engine oil temperature (C) and pressure (PSI) indicators

Two fuel pressure indicators (PSI)

Two fuel quantity indicators (KG)

Two flight controls hydraulic system pressure indicators (PSI)

Two utility hydraulic system pressure indicators (PSI)

Outside air temperature indicator (C)

Two fuel flow indicators (KG/HR)

Two DC voltmeters (VDC)

Two AC voltmeters (VAC)

Two DC ammeters (AMP)

h. Warning/caution advisory and maintenance system

Master Warning lights

Master Caution lights

Warning/Caution advisory (on IDS display)

Engine fire detection system

Aural Warning Generator system

Usage Monitoring System (on IDS display)

i. Interior arrangement

Two individual crash-resistant pilot seats, fore and aft adjustable, with lap belts andheadrests

Aluminium alloy honeycomb reinforced floor with anti-skid finishing

Ventilation ram air inlets

Anti reflection instrument panel

Primer finished cabin walls




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j. Exterior finishing

Finishing in accordance with manufacturer specification NTA893A

Primer exterior painting

3.1.2 Standard additional equipment 17.9 kg (39.5 lb)*

(Installed in current production aircraft)

Pilot and copilot headsets

Pilot and copilot shoulder harness with inertia reel

Baggage compartment light

Crew open door actuators

Quick disconnecting chip detectors

Portable fire extinguisher

Structural provision for utility equipment (emergency floats, rescue hoist, cargo hook,weather radar, engine fire extinguisher, flight director, AFCS)

Fuel drain electrical valves

Tail boom strake

First aid kit

Airframe hourmeter

3.1.3 EASA/FAA Single pilot IFR avionic package

(Garmin Bendix/King) 99.7 kg (219.9 lb)*

Pilot navigation instruments (LCD EADI and EHSI, stand-by ADI)

Gyrocompass C14A Honeywell

Vertical gyro #1 46060-11 Flightline System

Vertical gyro #2 VG-208 JET Electronics

3-axis duplex AFCS SP711 Honeywell

ADF KR-87 Bendix/King

Transponder (mode S) KT-73 Bendix/King

VHF #1 COM/NAV/GPS GNS530 Garmin

VHF #2 COM/NAV/GPS GNS430 Garmin

Pilot ICS (including pilot/copilot control panel, mode controller, audio cabin control)

DME KDM706A Bendix/King

Marker beacon KMR675 Bendix/King

AC power supply system (two inverters)

*Weight tolerance 2%




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3.1.4 Addi tional installed avionic equipment 33.8 kg (74.5 lb)*

Copilot flight/navigation instruments (LCD EADI and EHSI, barometric altimeter, airspeedindicator, VSI)

Flight director FZ 702 Honeywell with autotrim

Radio altimeter AA 300 Honeywell

ELT C406-2HM Artex

Moving map KMD 550 Bendix/King

Radio master switch with ground function

EFIS pilot/copilot in command switch

3.1.5 Installed uti lity equipment 38.4 kg (84.6 lb)*

Dual control

Rotor brake

Retractable/rotating landing light

Pilot and copilot windshield wipers

Wiper switch on cyclic grip (pilot)

Engine compartment fire extinguishers

Baggage compartment extension (1.9 m)

3.1.6 Interior6 40.6 kg (89.5 lb)*

Air conditioning

Primer finished cabin walls

Passive vibration absorber

3.1.7 Painting 15.5 kg (34.2 lb)*

Single colour painting scheme, solid colours, series 300

STANDARD CONFIGURATION WEIGHT 1900.9 kg (4190.8 lb)*(Para. 3.1.1 to 3.1.7)


6 This Standard Configuration does not include interior completion/mission equipment. Refer to the subsequentparagraphs for available options.




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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)

Typical Garmin Bendix/King cockpit for the standard configuration




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3.2 COMPLETIONS

Versatility of the Grandis reflected by the number of roles in which it can be employed.The following interior layout configurations and painting options are available as additional

selection to the Standard Configuration, as detailed in section 3.1.

3.2.1 Corporate/De Luxe interior 148.4kg (327.2 lb)*

Silentsoundproofing

Painted liners

3 fwd and 3 rear pax crash-resistant Clubseats facing each other, covered with fabric

4-point shoulder harness with inertia reels and safety belts on all seats

6 Active Noise Reduction (ANR) headsets

Advisory and reading lights

Floor carpeting

Cabin loudspeakers

3.2.2 VIP interior 175.1kg (386.0 lb)*

Paulstra - Ultra Silentsoundproofing

Leatherette covered liners

3-seat aft facing central bench with see-through foldable armrest

3-seat fwd facing aft bench with foldable armrest

All seats crash-resistant VIPmodel covered with leather



Leather bellows on flight controls

Floor carpeting

Cabin double layer acrylic windows


Customised pax cabin finishing

Cabin loudspeakers

Carpeting protection

Seat covers





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3.2.3 Offshore/public transport interior 117.0kg (257.9lb )*

Standard comfort soundproofing

Painted liners

2 x 3 fwd facing crash-resistant seats covered with fabric



Cabin double layer acrylic windows


Emergency floats provisions

Helicopter Emergency Egress Lighting System (HEELS)

Cabin loudspeakers

3.2.4 HPS (Harbour Pilot Shuttle) interior 102.7kg (226.4 lb)*

Standard comfort soundproofing

Painted liners

Special cabin floor with rails and drains

Sliding and rotating aft facing crash-resistant seat

3 fwd facing crash-resistant aft seats


3rdICS station in pax cabin


Sliding windows pilot/copilot and pax cabin

External hoist (272 kg) provisions including step bar

Emergency floats provisions

Helicopter Emergency Egress Lighting System (HEELS)





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3.2.5 EMS (Emergency Medical Service) interior

a. Fixed parts for Single/Dual lit ter EMS interior 60.8 kg (133.9 lb)*

EMS cabin floor with rails and drains

EMS painted liners with rails and provisions for EMS equipment

Aft bench panel (incl. inertia reels and safety belts)

EMS electrical system with 4 high-intensity patient lights

Electrical outlets (12 and 28 VDC)

3rdICS station in pax cabin

Provision for litter platform

Cargo net provisions

Medical oxygen distribution system (on LH and RH side liners) Sliding windows pilot/copilot and pax cabin

b. Single lit ter installation (removable parts) 61.8 kg (136.2 lb)*

Aft facing seat (sliding and rotating crash-resistant type)

Two fwd facing crash-resistant seats with foldable backrest and removable headrests


Primary LH litter platform with front lock mechanism and storage compartment

(inclusive of provision for up to 2 oxygen bottles installation). 1.85 m foldable litter (q.ty 1)

Cargo net

3.2.6 Painting

Weight*

Itemkg lb C

orporate

VIP

Public

transport

HPS

EMS

Metallic colour series 500(in lieu of solid colour series 300 weight)

5.0 11.0

Customised painting scheme, 2-3 colours(in lieu of solid colour series 300 weight)

up to10.0

up to22.0

Main rotor blades high visibility painting 1.0 2.2





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3.3 OPTIONAL EQUIPMENT

The interior, utility, EMS, avionic and special mission equipment listed below is available to satisfy

specific role requirements. The list is subject to change, and also some incompatibilities of specificinstallations may apply. AgustaWestland should be contacted to ensure a consistent configurationbuild-up.

3.3.1 Interior equipment

Weight*

Itemkg lb C

orporate

VIP

Public

transport

HPS

EMS

Paulstra - Ultra Silentsoundproofing (in lieu of Silentsoundproofing weight)

17.0 37.5

Pilot console tray 1.5 3.3

Pilot and copilot aft holders 3.0 6.6

2 crash-resistant aft seats (fwd facing)with central cabinet (in lieu of 3-seat bench)

tbd tbd

2 crash-resistant aft seats (fwd facing)with central cabinet/bar (in lieu of 3-seat bench)

tbd tbd

Removable rear cabinet kit(replaces aft central seat, includes modified cushions)

tbd tbd

Single drawer (under aft facing central bench) 3.5 7.7

Chest of 3 drawers (alternative to single drawer) 6.0 13.2

Refrigerated cabinet under central bench (aft facing) tbd tbd

Active Noise Reduction (ANR) headsets (1 unit) 0.6 1.3

3 crash-resistant central seats (aft facing) with armrest andsee-through modification

42.0 92.6

3 crash-resistant central seats (aft facing) (incl. inertia reelsand safety belts)

32.3 71.2

3 crash-resistant aft seats (fwd facing) with armrest 45.6 100.5

Additional fixed crash-resistant single seat (aft facing) 12.0 26.5

Additional sliding and rotating crash-resistant operator seat 18.0 39.7





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3.3.2 Utili ty equipment

Weight*

Item kg lb Corporate

VIP

Public

transport

HPS

EMS

Reinforced pilot/copilot windshield 2.7 6.0

Sliding window crew doors(in lieu of std. windows weight)

0.5 1.1

Sliding window pax doors(in lieu of std. windows weight)

-0.5 -1.1

Electrically operated passenger step (RH side) 4.5 9.9

Cargo hook provisions (1150 kg) 5.7 12.6

Double cargo hook provisions (1150 kg/500 kg) 1.7 3.6

Cargo hook kit (1150 kg) and rearview mirror removableparts

12.6 27.8

Double cargo hook kit (1150 kg/500 kg) removable parts(additional to Cargo hook kit)

3.6 7.9

Bambi bucket provision (with cargo hook installed) 1.2 2.6

Bambi bucket kit (Model 2024 910 l) 54.0 119.0

External hoist (272 kg) provisions including step bar 20.5 45.1

External hoist kit (272 kg) removable parts 56.7 124.9

Wire strike protection system (cable cutters) 8.3 18.3

Rappelling hooks (2 LH + 2 RH, ropes excluded) 8.4 18.5

Emergency floats provisions 11.2 24.7

Emergency floats kit removable parts 59.7 131.6

Emergency floats kit removable parts(including two 6/8-person rafts)

113.0 249.1

177 USG crash-resistant fuel system(in lieu of 152 USG weight)

6.0 13.2

213 USG crash-resistant fuel system(in lieu of 152 USG weight)

13.7 30.1

External loudspeakers provision 1.6 3.5

External loudspeakers kit removable parts 7.0 15.4





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3.3.2 Utility equipment (continue)

Weight*

Itemkg lb C

orpo

rate

VIP

Public

transport

HPS

EMS

SX-5 Starbust Spectrolab searchlight provision 7.2 15.9

SX-5 Starbust Spectrolab searchlight kit removable parts 12.1 26.7

SX-16 Nightsun Spectrolab searchlight provision tbd tbd

SX-16 Nightsun Spectrolab searchlight kit removable parts tbd tbd

NVG compatibility 4.8 10.6

Snow skis/slump protection pads provision 1.0 2.2

Snow skis removable parts 31.6 69.7

Slump protection pads removable parts 12.0 26.5

Particle separator engine air induction system 14.9 32.8

Pulsed chip detectors (engines, main and tail gearboxes) 1.0 2.2

Baggage compartment extension (2.3 m) 1.9 4.2

Helicopter Emergency Egress Lighting System (HEELS) 3.0 6.6

Tail flood lights (not NVG compatible) 0.2 0.4

High-intensity strobe lights 3.2 7.1

Fuel cap with key-lock 0.5 1.1

All-weather covers (ground equipment) - -





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3.3.3 EMS equipment

Weight*

Itemkg lb C

orpo

rate

VIP

Public

transp

ort

HPS

EMS

Additional fwd facing crash resistant single seat(replacing the single litter removable parts)

7.7 17.0

Additional fixed crash-resistant single seat (aft facing) 12.0 26.5

2ndlitter platform (RH) 13.0 28.7

2ndfoldable litter (1.85 m) 12.0 26.5

2 m litter (LH only) 15.0 33.1

Intubation saddle 3.0 6.6

Drawer compartment for warmer bag tbd tbd

Support for incubator (without incubator attachments) tbd tbd

Provision for up to 4 oxygen bottles(in the storage compartment)

tbd tbd

Oxygen bottle (1 unit 600 l) 6.5 14.3





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3.3.4 Avionic equipment

a. Collins Proline II single pilot IFR/FAA avionic package7 110.8 kg (244.3 lb)

*

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

Pilot navigation instruments (LCD EADI and EHSI, stand-by ADI)

Gyrocompass C14A Honeywell

Vertical gyro #1 46060-11 Flightline System

Vertical gyro #2 VG-208 JET Electronics

3-axis duplex AFCS SP711 Honeywell

ADF ADF-60A 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-22A Collins

VHF/AM #2 VHF-22A Collins

DME DME42 Collins

Pilot ICS (including pilot/copilot control panel, mode controller, audio cabin control)

GPS 2101 I/O FreeFlight

AC power supply system (two inverters)

Typical Collins Proline II Instrument Panel

7Special order. Availability subject to lead time.





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b. Additional avionic equipment

Weight*

Itemkg lb C

orpo

rate

VIP

Public

transp

ort

HPS

EMS

Moving Map MKII Observer Skyforce

(in lieu of KMD 550 Bendix/King weight)7.0 15.4

TAS SKY497 BF Goodrich(presented on GNS530/KMD 550)

12.2 26.9

Stormscope WXE 1000E BF Goodrich (presented on EFIS) 5.5 12.1

Weather radar RDR 2000 Bendix/King (presented on EFIS) 6.6 14.6

Search-weather radar Primus 700 Honeywell 19.0 41.9

GSM/SATCOMM Telit SAT 550 (ICS interfaced) 4.5 10.0

IRIDIUM telephone AIRSAT 1 4.5 10.0

CVR/FDR L3 FA2300 Madras tbd tbd


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

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3.3.5 Special miss ion equipment

Weight*

Itemkg lb C

orpo

rate

VIP

Public

transp

ort

HPS

EMS

VHF/FM NTX138/TH250 NAT 6.7 14.8

HF Primus HF1050 Bendix/King 22.0 48.5

UHF/VHF AM/FM Flexcom II Wulfsberg** 15.1 33.2

TCAS SKY791 BF Goodrich** 12.4 27.3

Homing DF 931-6 Chelton** tbd tbd

FLIR LEO II A3 Cumulus complete provision**

tbd tbd

FLIR LEO II A3 Cumulus installation** tbd tbd

FLIR UltraForce II (LEO II A5) FlirSystem complete provision**

tbd tbd

FLIR UltraForce II (LEO II A5) FlirSystem installation** tbd tbd

FLIR SeaFlir II FlirSystem complete provision**

tbd tbd

FLIR SeaFlir II FlirSystem installation** tbd tbd

Mission console(incl. 10 display and digital video recorder)**

tbd tbd

Video downlink** tbd tbd

Video up/downlink** tbd tbd


**Equipment not covered by T.S.O., installation will be approved by EASA/FAA as No hazard




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4 PERFORMANCE DIAGRAMS

This Section contains the Grandflight performance charts illustrating:

4.1 HOVERING

Hovering IGE AEO (TOP)

Hovering IGE AEO (MCP)

Hovering IGE OEI (230 Power)

Hovering OGE AEO (TOP)

Hovering OGE AEO (MCP)

Hovering OGE OEI (230 Power)

4.2 TAKEOFF AND LANDING PERFORMANCE (CATEGORY A)

Weight Altitude limitations (Vertical procedure from elevated helipad and

backup procedure from ground/elevated helipad)

4.3 FUEL CONSUMPTION VS AIRSPEED

Fuel consumption vs Airspeed AEO SL (ISA)

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

Fuel consumption vs Airspeed AEO 5000 ft (ISA)

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



WITHOUT NOTICE

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4.1 HOVERING

4.1.1 Hovering IGE AEO (TOP)

HOVERING IGE - AEO (TOP)

ISA+20

ISA

ISA+35

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

20 22 24 26 28 30 32

GROSS WEIGHT - kg x 100

PRESSUREALT

ITUDE-ft

0

1000

2000

3000

4000

5000

6000

44 48 52 56 60 64 68

GROSS WEIGHT - lb x 100

PRESSUREALT

ITUDE-m




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4.1.2 Hovering IGE AEO (MCP)

HOVERING IGE - AEO (MCP)

ISA+20

ISA

ISA+35

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

20 22 24 26 28 30 32


PRESSURE

ALTITUDE-

ft

0

1000

2000

3000

4000

5000

6000

44 48 52 56 60 64 68


PRESSURE

ALTITUDE-m



WITHOUT NOTICE

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4.1.3 Hovering IGE OEI (230 Power)

HOVERING IGE - OEI (2'30" POWER)

ISA+20

ISA

ISA+35

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

20 22 24 26 28 30 32


PRESSURE

ALTITUDE-ft

0

1000

2000

3000

4000

5000

6000

44 48 52 56 60 64 68


PRESSURE

ALTITUDE-m




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4.1.4 Hovering OGE AEO (TOP)

HOVERING OGE - AEO (TOP)

ISA+20

ISA

ISA+35

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

20 22 24 26 28 30 32


PRESSURE

ALTITUDE-ft

0

1000

2000

3000

4000

5000

6000

44 48 52 56 60 64 68


PRESSUREALTITUDE-m



WITHOUT NOTICE

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4.1.5 Hovering OGE AEO (MCP)

HOVERING OGE - AEO (MCP)

ISA+20

ISA

ISA+35

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

20 22 24 26 28 30 32


PRESSUREALTITUDE-ft

0

1000

2000

3000

4000

5000

6000

44 48 52 56 60 64 68


PRESSUREAL

TITUDE-m




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4.1.6 Hovering OGE OEI (230 Power)

HOVERING OGE - OEI (2'30" POWER)

ISA+20

ISA

ISA+35

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

20000

20 22 24 26 28 30 32


PRESSUREA

LTITUDE-ft

0

1000

2000

3000

4000

5000

6000

44 48 52 56 60 64 68


PRESSUREA

LTITUDE-m



WITHOUT NOTICE

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4.2 TAKEOFF AND LANDING PERFORMANCE (CATEGORY A)

The following diagram refers to preliminary Cat. A performance capabilities of the Grand, for theVertical procedure from elevated helipad and Backup procedure from ground/elevated helipad.

4.2.1 Weight Alt itude limitations (Vertical procedure from elevated helipad and

backup procedure from ground/elevated helipad)

CAT. A WEIGHT - ALTITUDE LIMITATIONS

Vertical Procedure from Elevated Helipad and

Backup Procedure from Ground/Elevated Helipad

(15 m x 15 m)

ISA

ISA+20IS

A+35

0

2000

4000

6000

8000

10000

12000

20 22 24 26 28 30 32


PRESSUREALTITUDE-

f

0

500

1000

1500

2000

2500

3000

3500

44 48 52 56 60 64 68


PRESSUREALTITUDE-

m




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4.3 FUEL CONSUMPTION VS AIRSPEED

4.3.1 Fuel consumpt ion vs Ai rspeed AEO SL (ISA)

FUEL FLOW - AEO - SL (ISA)

BEST

ENDURANCE

SPEED

3175kg

2900k

g

2600k

gVNE

LIMIT

XMSN LIMIT

RECOMMENDED

CRUISE SPEED

120

140

160

180

200

220

240

260

280

50 70 90 110 130 150 170 190

TRUE AIRSPEED - kts

FUELFLOW

-

kg

/h

265

305

345

385

425

465

505

545

585

93 133 173 213 253 293 333

TRUE AIRSPEED - km/h

FUELFLOW-

lb/h



WITHOUT NOTICE

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

FUEL FLOW - AEO - SL (ISA+20C)

3175kg

2900kg

2600kg

VNE

LIMIT

MCP LIMIT

RECOMMENDED

CRUISE SPEED

BEST

ENDURANCE

SPEED

120

140

160

180

200

220

240

260

280

50 70 90 110 130 150 170 190

TRUE AIRSPEED - kts

FUELFLOW

-kg

/h

265

305

345

385

425

465

505

545

585

93 133 173 213 253 293 333


FUELFLOW

-lb/h




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4.3.3 Fuel consumption vs Airspeed AEO 5000 ft (ISA)

FUEL FLOW - AEO - 5000 ft (ISA)

3175kg

2900kg

2600k

g

VNE

LIMIT

MCP LIMIT

RECOMMENDEDCRUISE SPEED

BEST

ENDURANCESPEED

120

140

160

180

200

220

240

260

280

50 70 90 110 130 150 170 190

TRUE AIRSPEED - kts

FUELF

LOW

-kg

/h

265

305

345

385

425

465

505

545

585

93 133 173 213 253 293 333


FUELF

LOW

-lb/h



WITHOUT NOTICE

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

FUEL FLOW - AEO - 5000 ft (ISA+20C)

3175k

g

2900kg

2600k

g

VNE

LIMIT

MCP LIMIT

RECOMMENDED

CRUISE SPEED

BEST

ENDURANCESPEED

120

140

160

180

200

220

240

260

280

50 70 90 110 130 150 170 190

TRUE AIRSPEED - kts

FUELFL

OW

-kg

/h

265

305

345

385

425

465

505

545

585

93 133 173 213 253 293 333


FUELFL

OW

-lb/h




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5 SUPPORT AND MAINTENANCE

5.1 INSPECTION PROGRAMMES

In order to best suit Customer needs and to ensure the maximum helicopter availability, threedifferent inspection programs may be selected.These are designed to provide flexibility formaximum utilization of the helicopter and to most suit the operators needs. The inspectionprogrammes are identified as follows:

a. Standard Programme

The scheduled inspections consist of an airworthiness check, 100, 400, 800, 3200 hour inspectionand 12 months inspection.

Standard Inspection Programme scheme



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b. Extended Programme

The scheduled inspections consist of a basic 50 hours/30 days inspection, standard 200, 400, 8003200 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 and400 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.




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5.3 RETIREMENT LIFE COMPONENTS (continue)

ItemQuantityper A/C

RETIREMENT LIFE(FH)

Lower fixed half-scissor 1 3400

Rotating swashplate 1 2300

Bolt 2 1000

Locking ring 1 1200

Spherical sleeve 1 1000

Upper fixed half-scissor 1 17000

Rod, aft 2 12000

Forward road 1 14000

Lower fixed half-scissor support 1 15000

Main rotor shaft 1 10000

Tail rotor blade 2 10000

Hub assembly 1 12000 landings

Retention strap assembly 2 7200 landings

Bolt, retention strap 2 22000 landings

Strap plug 2 20000 landings

Strap pin 2 20000 landings

Sleeve 1 3300

Tail rotor shaft assembly 1 3600

Main rotor servo actuator 3 8000

Main rotor servo actuator attachment 3 1000




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6 DIRECT OPERATING COST (DOC)

6.1 GENERAL INFORMATION

This section provides information on the Direct Operating Costs (DOC) connected with the typicaloperation of the Grand. It is assumed that the helicopter is civil certified and operates in atemperate climate in a non-corrosive environment (recommended anti-corrosive measures must beobserved for off-shore operations and adequate protection from weather provided when not flying,etc.). The DOC reflects the aircraft operated, maintained and supported using the recommendedtooling and facilities by experienced personnel in defined working conditions. It is assumed that thehelicopter is in basic configuration without any optional equipment.DOC information has been estimated in accordance with the Helicopter Association International(HAI) methodology.

Since the DOC may vary depending upon parameters such as FH per Year, Operational Life,Engine Cycle etc., a typical usage spectrum for a Corporate configuration has been analysed:

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

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

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

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

6.1.1 Fuel and lubricants

The data shown reflects the average fuel consumption assuming operation at the optimum rangespeed, at 1000 ft altitude, and ISA conditions. Customers' actual fuel consumption may varydepending on many factors, including: speed, temperature, weight, altitude, helicopterconfiguration, and mission. Depending on these factors, the average fuel consumption couldincrease 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 maintenancelabour, and parts.

a. Labour

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



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b. Parts

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

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

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

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

6.1.3 Powerplant maintenance

The powerplant direct operating cost estimate includes costs for periodic inspections andoverhauls as per P&WC Engine Maintenance Cost for PW207C. Since the engine overhaul interval

is bound by both operating hours, and engine cycles, the engine cycles assumed in each EngineMaintenance Cost estimation are detailed in the main assumptions table to respect the differentmission profiles. It is assumed that the aircraft powerplant overhaul is performed by the enginemanufacturer.

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

Economic Condit ions: January 2006OperatorMMH/FH

Hourly Op.Cost (USD)

Fuel and lubricantsFuel8 66 USG/h at 138 kts 148.5

Lubricants 3% of fuel cost 4.46

Direct Maintenance

Airframe Line Maintenance Labour9:

- Scheduled Maintenance 0.90 58.36

- Unscheduled Maintenance 0.44 28.89

Airframe Parts:

- Inspections Consumables 3.94

- Unscheduled 138.23

- Overhaul Components 15.23 - Life-Limited Parts 22.14

Powerplant Direct Maintenance:

- Line Maintenance and Overhaul Incl. Accessories10 130.12

TOTAL DOC PER FH 549.87

8Fuel at USD 2.25 per USG

9Labour at USD 65.00 per hour

10Pratt & Whitney Engine Maintenance Cost (DMC) for PW207C, 1 cycle per hour




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7 SERVICE PLANS

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

7.1 AIRFRAME MAINTENANCE PROGRAMME

AgustaWestland airframe maintenance programmes are:

GSP (Global Support Plan)

COMP (Complete Overhaul and Maintenance Programme)

CPA (Components Protection Agreement)

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

7.1.1 Global support plan (GSP)

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

Covered components:

Airframe components

Avionics components

Components and items excluded:

Engines and engine accessories

Items with a unit price less than 200 USD

Aircraft paint, upholstery, carpets, interior panels Fuel, and consumable materials

Optional kits (can be included upon Customer request)

Plan provisions:

Labour for scheduled and unscheduled inspections as per Chapter 5 of the MaintenanceManual (labour will be performed by the AgustaWestland authorized service centre nearestto the Customer)

Spare parts for scheduled and unscheduled/on-condition maintenance

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



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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 misuse of the aircraft.

7.1.2 Complete overhaul and maintenance programme (COMP)

For Civil Operators desiring comprehensive coverage with an added level of operating costassurance, AgustaWestland has assembled a special support plan which covers the basichelicopter configuration.The Complete Overhaul and Material Program (COMP) provides repair, overhaul and replacementand/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

Documents

THF-AG-0607-1.pdf