THF139-0607-1.pdf

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

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INTENTIONALLY LEFT BLANK


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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 WRITING BY AGUSTAWESTLAND AGUSTAWESTLAND COMPANIES. COMPANIES.


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TABLE OF CONTENTS 1

INTRODUCTION ........................................................................................................... 9 1.1 THE NEW STANDARD FOR INTERMEDIATE CATEGORY HELICOPTERS .................................9 1.2 DESIGN TO SAFETY...................................................................................................10 1.2.1 Compliance with the Latest Regulations..........................................................10 1.2.2 Most Relevant Regulation Changes ................................................................10

2

LEADING FEATURES ................................................................................................ 12 2.1 CERTIFICATION (TYPE AND OPERATIONAL APPROVAL) .................................................. 12 2.1.1 ENAC/EASA (Primary Certification Authority) ................................................. 12 2.1.2 FAA Certification (USA) ................................................................................... 12 2.1.3 Other Certification Authorities..........................................................................13 2.2 APPLICATIONS ......................................................................................................... 13 2.3 EXTERNAL DIMENSIONS ............................................................................................14 2.4 INTERNAL DIMENSIONS AND VOLUMES ........................................................................ 16 2.4.1 Seating Arrangement .......................................................................................18 2.5 WEIGHTS .................................................................................................................19 2.6 FUEL CAPACITY ........................................................................................................ 19 2.7 CG ENVELOPE ........................................................................................................ 20 2.9 ENGINE RATINGS (SL, ISA)....................................................................................... 22 2.10 TRANSMISSION RATINGS ........................................................................................22 2.11 PERFORMANCE SUMMARY TABLES..........................................................................23 2.11.1 All Engine Operative (AEO) Operations................. .......................................... 23 2.11.2 One Engine Inoperative (OEI) Operations ....................................................... 24 2.12 OPERATIONAL ENVELOPE .......................................................................................25 2.12.1 Wind ................................................................................................................25 2.12.2 Velocity Never Exceed V NE ..............................................................................26 2.12.3 Temperature and Altitude ................................................................................ 26 2.12.4 Maximum Take Off and Landing Altitude.........................................................26 2.12.5 Maximum Altitude for Engine Start or Relight .................................................. 26 2.12.6 Wind Speed Limitation for Rotor Engagement.................................................26 2.12.7 Ditching Capability...........................................................................................26 2.13 AW139 STATIC LANDING GEAR LOADING.................................................................27 2.14 SLOPE LANDING ....................................................................................................27 2.15 ENVIRONMENTAL IMPACT ........................................................................................27 2.15.1 External Noise Level........................................................................................27 2.15.2 Engine Characteristics.....................................................................................27 2.15.3 Smoke and Emissions ..................................................................................... 28 2.16 INTERNAL NOISE LEVEL .........................................................................................28


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STANDARD CONFIGURATION AND OPTIONAL EQUIPMENT LIST ...................... 29 3.1 STANDARD CONFIGURATION (EASA / ENAC / FAA IFR CONFIGURATION) .. 29 3.1.1 Basic Configuration..........................................................................................29 3.1.2 Standard 12 – Passenger Configuration Equipment ..........................................32 3.1.3 Miscellaneous ..................................................................................................32 3.2 EQUIPMENT LIST AND WEIGHTS .................................................................................. 33 3.2.1 Standard 12–Seat Interior Weight....................................................................33 3.2.2 Optional Equipment List...................................................................................34 3.2.3 Further Optional Equipment List ...................................................................... 38

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PERFORMANCE INFORMATION .............................................................................. 39 4.1 HOVER IGE ............................................................................................................. 40 4.1.1 Hover IGE (AEO / TOP – ZERO WIND) .......................................................... 40 4.1.2 Hover IGE (AEO / MCP – ZERO WIND)..........................................................41 4.1.3 Hover IGE (OEI / 2.5 min POWER – ZERO WIND).........................................42 4.1.4 Hover IGE (OEI / MCP – ZERO WIND) ........................................................... 43 4.2 HOVER OGE ........................................................................................................... 44 4.2.1 Hover OGE (AEO / TOP – ZERO WIND) ........................................................ 44 4.2.2 Hover OGE (AEO / MCP – ZERO WIND)........................................................45 4.2.3 Hover OGE (OEI/2.5 min POWER – ZERO WIND)......................................... 46 4.2.4 Hover OGE (OEI/MCP – ZERO WIND) ........................................................... 47 4.3 CATEGORY A PERFORMANCE ..................................................................................... 48 4.3.1 Helipad Procedure (Ground Level and Elevated) ............................................ 48 4.3.2 Short field Procedure.......................................................................................48 4.3.3 Back-up Procedure ..........................................................................................48 4.3.4 Clear Area .......................................................................................................48 4.3.5 W-A-T Limitations (Helipad / Short Field / Back Up)........................................ 49 4.3.6 W-A-T Limitations (Clear Area)........................................................................50 4.4 R ATE OF CLIMB PERFORMANCE .................................................................................51 4.4.1 Rate of Climb in Oblique Flight (TOP/AEO).....................................................51 4.4.2 Rate of Climb in Oblique Flight (MCP/AEO) ....................................................52 4.4.3 Rate of Climb in Oblique Flight (2.5 min POWER OEI) ................................... 53 4.4.4 Rate of Climb in Oblique Flight (MCP/OEI)......................................................54 4.5 FUEL CONSUMPTION DATA AEO AT ISA ..................................................................... 55 4.5.1 Fuel Consumption Data* (SL).......................................................................... 55 4.5.2 Fuel Consumption Data* (2,000 ft) ..................................................................56 4.5.3 Fuel Consumption Data* (6,000 ft) ..................................................................57 4.5.4 Fuel Consumption Data* (10,000 ft) ................................................................58 4.6 FUEL CONSUMPTION DATA AEO AT ISA+20°C ........................................................... 59 4.6.1 Fuel Consumption Data* (SL).......................................................................... 59 4.6.2 Fuel Consumption Data* (2,000 ft) ..................................................................60


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4.6.3 Fuel Consumption Data* (6,000 ft) ..................................................................61 4.6.4 Fuel Consumption Data* (10,000 ft) ................................................................62 4.7 FUEL CONSUMPTION DATA AEO AT ISA+35°C ........................................................... 63 4.7.1 Fuel Consumption Data* (SL).......................................................................... 63 4.7.2 Fuel Consumption Data* (2,000 ft) ..................................................................64 4.7.3 Fuel Consumption Data* (6,000 ft) ..................................................................65 4.7.4 Fuel Consumption Data* (10,000 ft) ................................................................66 4.8 HOVERING FUEL CONSUMPTION DATA ........................................................... 67 4.8.1 HOGE Fuel Consumption Data at ISA.............................................................68 4.8.2 HOGE Fuel Consumption Data at ISA+20°C...................................................69 4.8.3 HOGE Fuel Consumption Data at ISA+35°C...................................................70 4.9 GROUND IDLE/START–UP FUEL FLOW.............................................................71 5

ESTIMATED DIRECT OPERATING COST AND RELATED DATA ........................... 72 5.1 GENERAL INFORMATION ................................................................................... 72 5.2 FUEL AND LUBRICANTS ..................................................................................... 72 5.3 AIRFRAME DIRECT MAINTENANCE................................................................... 72 5.4 POWERPLANT MAINTENANCE ..........................................................................73 5.5 OVERHAUL COMPONENTS ..........................................................................................75 5.6 RETIREMENT LIFE COMPONENTS ................................................................................76

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SERVICE PLANS........................................................................................................ 77 6.1 AIRFRAME MAINTENANCE PROGRAM........................................................................... 77 6.1.1 Global Support Plan (GSP)..............................................................................77 6.1.2 Complete Overhaul and Maintenance Program (COMP).................................78 6.1.3 Component Protection Agreement (CPA)........................................................78 6.2 WARRANTIES....................................................................................................... 79 6.2.1 AIRFRAME WARRANTY................................................................................. 79 6.2.2 ENGINE WARRANTY ..................................................................................... 79

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TRAINING ................................................................................................................... 80 7.1 AGUSTAWESTLAND TRAINING CENTERS........................................................ 80 7.1.1 The School ......................................................................................................80 7.1.2 The Simulator ..................................................................................................80 7.2 TRAINING COURSES........................................................................................... 80

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USEFUL INFORMATION ............................................................................................ 81


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1 INTRODUCTION 1.1

THE NEW STANDARD FOR INTERMEDIATE CATEGORY HELICOPTERS

The AW139 is a new medium twin–engine helicopter designed to provide the marketplace with a highly capable aircraft meeting the most stringent safety standards imposed by the latest civil and government requirements. The AW139 is an AgustaWestland – A Finmeccanica Company – program with a risk sharing participation of, among others, Pratt & Whitney, Honeywell, PZL Swidnik, Liebherr, and Kawasaki. The AW139 is a highly performant helicopter, incorporating state–of–the–art components based on proven technologies; it has been designed around a spacious cabin and baggage compartment for maximum flexibility and passenger comfort, providing high capabilities whilst guaranteeing competitive economics. AW139 main features include:

-

-

Twelve passenger seating capacity in standard configuration (15 seats in high density arrangement) in a large and unobstructed cabin of 8 m 3 (283 ft3) Standard large baggage compartment with up to 3.4 m 3 (120 ft3) Maximum cruise speed of 165 KTAS at SL ISA High MTOW (6,400 kg) for excellent payload/range capability IFR (Instrument Flight Rules) certified Full integrated Honeywell avionic system with four 8” × 10” color Active Matrix Liquid Crystal Displays (AMLCDs) Two powerful engines with FADEC Pratt & Whitney Canada PT6C–67C High comfort associated with low acoustic and vibration levels due to mass layout, aerodynamic design, 5 Main Rotor and 4 Tail Rotor blades and optimized rotor profiles and speed Robust retractable energy absorbing tricycle landing gear for ground operations 3–axis Digital Automatic Flight Control System (DAFCS); 4–axis DAFCS is optional Provision for HUMS Reduced maintenance requirements due to the extensive use of reliable components and computerized monitoring system Low pilots workload in all flight regimes thanks to the design characteristics and cockpit management aids Certification according to the most recent FAR/JAR 29 Amendments, with features related to safety, survivability and crashworthiness that include but are not limited to the following: •

Class 1 Category ”A” Take-off and landing operations in hot environment

•

Crashworthy crew and passenger seats, airframe and fuel system

•

High safety standards with “fail–safe” design and system redundancy

•

Damage tolerance (JAR/FAR 29.571)

•

Engine turbine burst containment system

•

30-minute “dry run” capable transmission, intermediate gearbox and tail rotor gear box

•

High inertia main rotor for improved autorotation

•

Bird strike protection

•

LEMP, EMC and HIRF protection according to AC/AMJ20-136A, JAR/FAR29, RTCADO160D and INT/POL/27&29/1


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1.2

DESIGN TO SAFETY

1.2.1 Compli ance wit h the Latest Regulati ons The AW139, as a brand new design helicopter, is the only aircraft in its class that fully meets the latest FAA and EASA amendments.

1.2.2 Most Relevant Regulati on Changes The continuous effort to improve the safety of rotorcraft led the FAA and EASA/JAA to set new, more demanding certification standards through amendments of existing FAR 29 “Transport Category Rotorcraft” and corresponding JAR 29 “Large Rotorcraft” airworthiness requirements. The most recent FAA amendments were introduced in 1989 and then in 1994, 1996, 1997, and 1998 up to the most recent FAR 29 Amendment 29-45. At the same time EASA/ JAA, evolved the requirements from the basic amendment issued in 1999 to Amendment 3 that was introduced in 2002. Due to the harmonization policy between European and American requirements, the two most recent amendments of both Certification Authorities are aligned to each other, with some changes only in specific areas. The disciplines and paragraphs of the FARs affected by these amendments are summarized below: •

Perfor mance and Control lability (Requirement 29.45, 29.49, 29.51, 29.60, 29.75, 29.141) - Amendment 29-39 issued in 1996 introduced more comprehensive and demanding requirements for takeoff and landing weights at altitude together with low speed controllability versus weight, altitude and drive system ratings. This amendment also dealt with Category A performance requirements

•

Structural Loading Conditions (Requirement 29.351, 29.361, 29.547) - Amendment 2941 issued in 1997 introduced very demanding yawing conditions for the structural verification of the airframe, which had to withstand loads from a 90° yaw at 0.6 Vne, or whatever could be obtained by applying instantly full anti-torque pedal travel. Moreover the engine installation had to be structurally substantiated for a sudden engine stoppage. These requirements led to the introduction of higher/more severe loading conditions in the airframe and tail-boom static tests

•

Crashworthiness (Requirement 29.561, 29.562, 29.783, 29.785, 29.952) - Amendment 29-39 issued in 1994 introduced crashworthiness requirements for airframe, airframe mounted components, and seat installations specifying also a TSO for seats and passenger restrain harnesses to be complied with, in order to make them candidates for aircraft installation. Crashworthiness of the fuel tanks and lines was introduced as well, implementing the fuel venting criteria that required that no fuel leak could be possible in case of aircraft rollover with the fuselage resting on its side. These requirements led to the fuel system crash tests, cabin sub-floor crash tests, seat crash tests and crash analysis across the aircraft systems

•

Damage Tolerance (Requirement 29.571) - Amendment 29-28 issued in 1989 introduced the damage tolerance requirements specifying that fatigue demonstrations had to include tolerance to flaws and damage likely to occur in service, or during manufacturing.


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•

Lightning Protection (Requirement 29.610) - Amendment 29-40 issued in 1996 introduced more comprehensive lightning direct effects protection such as bonding and discharge, and establishing a level of protection of electrical and avionics equipment. This requirement led to the introduction of more comprehensive lightning tests including fatigue tests after lightning strike damage on Main Rotor blades

•

Birdstrike Protection (Requirement 29.631) - Amendment 29-40 introduced the requirement to withstand impact with a 2.2lb bird at Vne. This led to the birdstrike tests on the aircraft cowlings, airframe parts and windscreens

•

Baggage Compartment (Requirement 29.787, 29.855) - Amendment 29-31 issued in 1990 raised the standard for the equipment stowage compartment for aspects like fire protection and crashworthiness prescribing also a baggage restraint system.

•

Cabin Safety (Requirement 29.853) - Amendment 29-40 raised standards for fire protection for interiors

•

Engine Rotor Burst (Requirement 29.903 (c), 29.1309 (b) and (d)) - Amendment 29-45 introduced requirements that led P&WC to certify the PT6C-67C engine for rotor burst containment. The required dedicated tests performed by P&WC showed that containment was assured, and this capability is part of the engine Type Certificate. In the case of the AW139, vulnerability assessment assuming the engine experienced an uncontained failure was performed and specific design changes were introduced in the AW139 design to mitigate those effects.

•

High Intensity Radiated Fields and Lightning Direct Effects (Requirement 29.1309) No requirement has evolved in this case, however, the JAA, now EASA, introduced a special condition for High Intensity Radiated Field (HIRF) in accordance with JAA interim policy and guidance material document INT/POL/27&29/1 “Protection from effects of HIRF”. This led to specific aircraft testing up to a peak of 7,200 v/m. The FAA also issued a Special Condition on this subject and further testing had to be done

All these requirements have been incorporated in the AW139 design and are part of its Type Certificate.


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2 LEADING FEATURES 2.1

CERTIFICATION (TYPE AND OPERATIONAL APPROVAL)

The AW139 basis of certification is: JAR 29 “Large Rotorcraft”, up to Amdt 3 dated April 1 st 2002 • The FAA basis of certification is: FAR part 29 “Transport Category Rotorcraft” Amdt 29.1 through 29.45 • Other special mandatory airworthiness standards are: the newest airworthiness standards for HIRF in accordance with JAA interim policy and • guidance material document number INT/POL/27&29/1 “Protection from effects of HIRF”, and FAA Advisory Circular AC/AMJ 20.1317 the MIL-STD-889 for corrosion protection • The helicopter is type certified by the Italian Civil Aviation Authority (ENAC) to operate under: Category A • Day/Night Visual Flight Rules (VFRs) and Day/Night Instrument Flight Rules (IFR) defined • in Appendix B to JAR 29 equal to FAR 29 The AW139 basis of certification for noise is: ICAO Annex 16, Vol.1, 3 rd Edition • For FAA noise certification: FAR part 36, Appendix H, Amdt 1 through the Amdt 14 •

2.1.1 ENAC/EASA 1 (Primary Certifi cation Autho rity) The AW139 is a re-branding of the AB139 which is type certificated by EASA, as the primary certification authority, under Type Certificate no. R006 The AW139 received type certification by ENAC (Italian Airworthiness Authority) on June 18 th 2003 (Type Certificate Number A 415). The type certificate has been transferred to EASA after establishment of the European Agency on September 28th 2003.

2.1.2 FAA Certif ication (USA) The AW139 received type certification by FAA (Federal Aviation Authority – USA) on December 20th 2004 (Type Certificate Number R00002RD).

1

EASA includes: Austria, Belgium, Cyprus, Czech Republic, Denmark, Estonia, Finland, France, Germany, Greece, Hungary, Ireland, Italy, Latvia, Lithuania, Luxemburg, Malta, Poland, Portugal, Slovak Republic, Slovenia, Spain, Sweden, The Netherlands, United Kingdom. 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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2.1.3 Other Certi fic ation Aut hori ties The AW139 has been type certified in the following countries: • • • • • • • •

2.2

Switzerland Namibia United Arab Emirates South Africa Zambia Turkey Mexico Canada

APPLICATIONS

The great flexibility of the cabin layout and the wide range of optional equipment available make the AW139 suitable for many different applications, both civil and military, such as:

-

Passenger transportation Offshore passenger transportation in support of Oil and Gas Industry Search and Rescue (SAR) operations over water / mountains Emergency Medical Service (EMS) operations VIP and Corporate transportation Aerial work operations Law enforcement operations

AgustaWestland – A Finmeccanica Company – is available to discuss configurations tailored to Customer’s needs.


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2.3

EXTERNAL DIMENSIONS

FUSELAGE Length

13.52 m

44 ft

4 in

Width (horizontal tail plane)

4.22 m

13 ft

10 in

Width (at cabin doors)

2.26 m

7 ft

5 in

Height (vertical fin)

3.72 m

12 ft

3 in

Fuselage ground clearance

0.42 m

1 ft

5 in

13.80 m

45 ft

3 in

2.70 m

8 ft

10 in

Wheel Track

3.04 m

9 ft

12 in

Wheel Base

4.34 m

14 ft

3 in

Length (rotors turning) – (D-value)

16.66 m

54 ft

8 in

Main Rotor Tip Blades Clearance 2

3.02 m

9 ft

11 in

Tail Rotor Tip Blades Clearance

2.34 m

7 ft

8 in

ROTORS Main Rotor Diameter Tail Rotor Diameter

LANDING GEAR

OVERALL DIMENSIONS

2

Controls in neutral position


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1.15 m / 3ft 9 in

AW139 external dimensions


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2.4

INTERNAL DIMENSIONS AND VOLUMES

COCKPIT Max Length

1.62 m

5 ft

4 in

Max Width

2.08 m

6 ft

10 in

Max Height

1.42 m

4 ft

8 in

Volume

2.53 m 3

89 ft3

CABIN Length

2.70 m

8 ft

10 in

Max width3

2.10 m

6 ft

11 in

Height

1.42 m

4 ft

8 in

Volume

8.00 m 3

283 ft3

Floor Area

5.50 m 2

59.2 ft2

BAGGAGE COMPARTMENT Max Length

3.00 m

9 ft

10 in

Max Width

1.60 m

5 ft

3 in

Max Height

1.02 m

3 ft

4 in

Volume Floor Area

3

3.40 m 3

120 ft3

3.6 m2

38.7 ft2

Measured at cushion level


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AW139 internal dimensions


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2.4.1 Seati ng Arrangement The AW139 standard seating arrangement consist of three rows, each made using four independent crashworthy seats. The first row behind the cockpit faces rearward, while the second and third rows face forward. Seats are disposed on six fixed rails integrated in the floor, and can be easily removed without using tools. The distance between seats in the first and second row, the pitch of the second and third row and the width of the seats are shown in drawings below.


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2.5

2.6

WEIGHTS

kg

lb

Maximum Ramp Weight

6,450

14,220

Maximum Take Off Weight (Internal)

6,400

14,110

Maximum Take Off Weight (External)

6,800

14,992

Basic Empty Weight (BEW) 4

3,685

8,124

Maximum Useful Load (Internal)

2,715

5,986

Maximum Useful Load (External)

3,115

6,868

Sling Load Capacity

2,200

4,850

FUEL CAPACITY

The standard fuel system has two interconnected cells: Usable q uantities 5 Configuration 2–Cell Standard Fuel System 6

kg

lb

lt

USG

1,254

2,765

1,568

414

The auxiliary fuel tank (optional) has one cell that is interconnected to the standard tanks and located above them. All fuel in the auxiliary fuel tank is usable fuel. Usable quantit ies Configuration 1–Cell Auxiliary Fuel System

kg

lb

lt

USG

400

882

500

132

4

BEW refers to the basic configuration detailed in Section 3.1.1 (point “a” through “h”) ; the BEW includes also: engine oil, transmission oil, hydraulic system oil & unusable fuel (unusable fuel amounts to16 kg / 35 lb). Weight tolerance±2%. 5 Fuel density: 0.8 kg/lt. 6 Total fuel capacity (usable and unusable): 1270 kg / 2800 lb. 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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2.7

CG ENVELOPE

The AW139 Helicopter is approved for flight within longitudinal and lateral center of gravity range limits according to the following diagrams 7.

LONGITUDINAL ENVELOPE

LONGITUDINAL ENVELOPE FUSELAGE STA - in 195

200

205

210

215

220

6600 MTOW = 6,400 kg

14259

6200 13259 5800 g k T H 5400 G I E W

12259

b l T H G I E W

11259 5000

10259

4600

4200 4950

9259 5050

5150

5250

5350

5450

5550

5650

FUSELAGE STA - mm

7

Minimum flight weight design objective is 4,100 kg/ 9,039 lb


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LATERAL ENVELOPE

LATERAL ENVELOPE LATERAL STA - in -4.7

-3.5

-2.3

-1.1

0.1

1.3

2.5

3.7

4.9

6.1

6600 MTOW = 6,400 kg

14259

6200 13259 5800 g k T H 5400 G I E W

12259

b l T H G I E W

11259 5000

10259

4600

4200 -120

9259 -60

0

60

120

180

LATERAL STA - mm

Note: the cargo hook stations are -

STA 5300 mm (longitudinal); BL 0 mm (lateral).


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2.8

ENGINE RATINGS (SL, ISA)

Rating

2.9

Pratt & Whi tney PT6C– 67C kW

shp

AEO Take Off Power (5 min)

2 × 1252

2 × 1679

AEO Maximum Continuous Power

2 × 1142

2 × 1531

OEI 2.5 min Contingency Power

1396

1872

OEI Maximum Continuous Power

1252

1679

kW

shp

AEO Take Off Power (5 min)

1641

2200

AEO Maximum Continuous Power

1491

2000

OEI 2.5 min Contingency Power

1193

1600

OEI Maximum Continuous Power

1044

1400

TRANSMISSION RATINGS Rating


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2.10 PERFORMANCE SUMMARY TABLES 2.10.1 All Engi ne Operativ e (AEO) Operations SEA LEVEL MTOW:

6,000 kg / 13,227 lb

MAXIMUM CRUISE SPEED (TAS) 8

BEST RANGE CRUISE SPEED (TAS) 9

RECOMMENDED CRUISE SPEED (TAS) RATE OF CLIMB (Take Off Power)

MAX RANGE (no reserve, max std fuel, 1254 kg) MAX ENDURANCE (no reserve, max std fuel, 1254 kg) MAX RANGE (no reserve, max std + aux. fuel, 1654 kg) MAX ENDURANCE (no reserve, max std + aux. fuel, 1654 kg)

kt km/h kt km/h kt km/h ft/min m/s nm km

6,400 kg / 14,110 lb

ISA ISA+20°C ISA+35°C 167 169 153 309 313 283 140 140 140 259 259 259 151 150 150 280 278 278 2,390 2,390 2,390 12.14 12.14 12.14 437 441 443 809 817 820

ISA ISA+20°C ISA+35°C 165 166 150 306 307 278 140 140 140 259 259 259 150 150 150 278 278 278 2,140 2,140 2,140 10.87 10.87 10.87 431 435 436 798 806 807

h:min

4:02

3:57

3:55

3:53

3:49

3:47

nm km

581 1076

586 1085

589 1091

573 1061

578 1070

580 1074

h:min

5:25

5:19

5:15

5:13

5:07

5:04

6,000 ft MTOW: MAXIMUM CRUISE SPEED (TAS) BEST RANGE CRUISE SPEED (TAS) RECOMMENDED CRUISE SPEED (TAS) RATE OF CLIMB (Take Off Power) MAX RANGE (no reserve, max std fuel, 1254 kg) MAX ENDURANCE (no reserve, max std fuel, 1254 kg) MAX RANGE (no reserve, max std + aux. fuel, 1654 kg) MAX ENDURANCE (no reserve, max std + aux. fuel, 1654 kg)

6,000 kg / 13,227 lb kt km/h kt km/h kt km/h ft/min m/s nm km

6,400 kg / 14,110 lb

ISA ISA+20°C ISA+35°C 171 171 155 317 317 287 140 140 140 259 259 259 149 150 151 276 278 280 2,400 2,400 2,100 12.19 12.19 10.67 517 516 514 957 956 952

ISA ISA+20°C ISA+35°C 168 167 150 311 309 278 140 140 140 259 259 259 148 149 149 274 276 276 2,150 2,110 1,820 10.92 10.72 9.25 504 500 496 933 926 919

h:min

4:35

4:30

4:27

4:25

4:21

4:17

nm km

690 1278

692 1282

689 1276

675 1250

670 1241

666 1233

h:min

6:08

6:03

5:58

5:56

5:50

5:47

8

The best range cruise speed represents, at given environmental condition and weight, the speed corresponding to the lowest fuel consumption 9 The recommended cruise speed represents, at given environmental condition and weight, the speed corresponding to 99% of the best specific range (nm/kg of fuel) 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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THF139–0607–1

AL TITUDE PERFORMANCE

MTOW: HIGE (Take Off Power) HOGE (Take Off Power) SERVICE CEILING (Take Off Power)

6,000 kg / 13,227 lb ft m ft m ft m

6,400 kg / 14,110 lb

ISA ISA+20°C ISA+35°C 17,310 14,310 11,390 5,276 4,362 3,472 13,085 10,020 6,020 3,988 3,054 1,835 20,000 20,000 18,000 6,096 6,096 5,486

ISA ISA+20°C ISA+35°C 15,360 12,310 9,250 4,682 3,752 2,819 8,130 6,000 3,000 2,478 1,829 914 20,000 18,000 16,000 6,096 5,486 4,877

Residual ROC SERVICE CEILING (Maximum Continuous Power)

ft/min

800

150

130

350

250

210

ft m

20,000 6,096

19,000 5,410

16,250 4,953

20,000 6,096

17,500 5,334

14,750 4,496

Residual ROC

ft/min

600

140

160

170

100

100

2.10.2 One Engin e Inoperati ve (OEI) Operati ons CONTINGENCY POWER – OEI (2.5 min)

MTOW:

6,000 kg / 13,227 lb

HIGE (OEI) (2.5 min Contingency Power)

ft m kg lb HOGE (OEI) kg (2.5 min Contingency Power - SL) lb RATE of CLIMB (OEI) ft/min (2.5 min Contingency Power - SL) m/s SERVICE CEILING (OEI) ft (2.5 min Contingency Power) m Residual ROC

6,400 kg / 14,110 lb

ISA ISA+20°C ISA+35°C 4,250 1,035 0 1,295 315 0 6,000 6,000 5,630 13,227 13,227 12,412 5,455 5,320 4,865 12,026 11,729 10,726 1,300 1,275 975 6.60 6.48 4.95 15,500 13,250 11,000 4,724 4,039 3,353

ft/min

100

100

100

ISA ISA+20°C ISA+35°C 0 0 0 0 0 0 6,310 6,175 5,630 13,911 13,614 12,412 5,455 5,320 4,865 12,026 11,729 10,726 1,200 1,100 820 6.10 5.59 4.17 13,500 11,200 9,050 4,115 3,414 2,758 100

100

100

MAXIMUM CONTINUOUS POWER – OEI

MTOW: SERVICE CEILING (OEI) (Maximum Continuous Power)

6,000 kg / 13,227 lb ft m

6,400 kg / 14,110 lb

ISA ISA+20°C ISA+35°C 13,750 10,600 6,750 4,191 3,231 2,057

ISA ISA+20°C ISA+35°C 11,600 8,700 3,550 3,536 2,652 1,082

Residual ROC

ft/min

100

100

100

100

100

100

CRUISE SPEED at SL (TAS)

kt km/h

CRUISE SPEED at 6,000 ft (TAS)

kt km/h

140 259 142 263

136 252 130 241

122 226 110 204

142 263 138 256

135 250 127 235

110 204 -----


24

THF139–0607–1

2.11 OPERATIONAL ENVELOPE 2.11.1 Wind The wind envelope shown below is applicable up to 9,500 ft Density Altitude, at 6,400 kg (14,110 lb), for take-off, landing and IGE maneuvers.


25

THF139–0607–1

2.11.2 Veloci ty Never Exceed VNE The helicopter has a design Velocity Never Exceed V NE of 167 kt IAS up to 6,000 ft density altitude, thereafter reducing at a rate of 3 kt IAS per 1,000 ft up to the maximum ceiling (20,000 ft).

2.11.3 Temperature and Altitude The helicopter and its components are designed and certified by EASA and FAA for operations at ambient temperatures ranging from –40°C to +50°C: TEMPERATURE AND ALTITUDE 20000 t f E D U T I T L A E R U S S E R P

I S A

I S A + 2 0

16000

I S A + 3 5

12000 8000 4000 0 -50

-40

-30

-20

-10

0 10 OAT - °C

20

30

40

50

60

2.11.4 Maxim um Take Off and Landing Alt itu de Take off and landings are currently permitted up to 14,000 ft (design objective is 18,000 ft).

2.11.5 Maxim um Al tit ude for Engine Start or Relig ht Engine starts and relights are permitted up to 20,000 ft.

2.11.6 Wind Speed Limi tation for Rotor Engagement Maximum wind speed for rotor engagement is 45 kts.

2.11.7 Ditc hing Capabili ty The optional Automatic Float Deployment System (AFDS), designed in accordance with JAR/FAR 29.801, is activated by water electronic sensor switches on ditching via squib valves, and provides floatation capability for the helicopter up to sea state 4.


26

THF139–0607–1

2.12 AW139 STATIC LANDING GEAR LOADING The loads reported below refer to the helicopter at the take off weight of 6,400 kg in the AW139 medium CG configuration. MTOW:

6,000 kg / 13,227 lb

6,400 kg / 14,110 lb

Loading

Contact Area

Contact Press.

Loading

Contact Area

Contact Press.

Nose Landing Gear

2 × 652 kg

21.0 in

2

137 psi

2 × 695 kg

22.4 in

2

137 psi

Main Landing Gear

2 × 2348 kg

43.4 in

2

239 psi

2×2505 kg

46.2 in

2

239 psi

2.13 SLOPE LANDING Take off and landing on terrain with slopes are allowed for the entire weight envelope, up to the following limits: Longitudinal 10° Lateral 10°

2.14 ENVIRONMENTAL IMPACT 2.14.1 Extern al Nois e Level The external noise is presented in the table below: MTOW:

6,400 kg / 14,110 lb AW139 (EPNdB)

FARLimits (EPNdB)

ICAOLimits (EPNdB)

Take off

90.4

98.2

98.1

Flyover

89.6

97.0

97.1

Approach

92.7

99.0

99.1

10

2.14.2 Engi ne Characteris tic s The Pratt & Whitney Canada PT6C–67C engine integrates all the initiatives to meet and exceed environmental international standards: - No asbestos is present; - Environmental friendly protective coatings are used wherever possible; 10

The AW139 also exceeds compliance with the new limits issued by ICAO on Jan. 2001 reported in ICAO Annex 16, Chapter 8, which reduce by 3EPNdB the limit for takeoff, by 4EPNdB the limit for flyover and by 1EPNdB the limit for approach. 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.

27

THF139–0607–1

- Environmental friendly lubricants and cleaning fluids are recommended wherever possible; - A new Low Smoke Combustion Technology is applied.

2.14.3 Smoke and Emissi ons Pollution emission rates have been measured during the engine development phase: - Combustion efficiency (% burnt fuel) greater than 99.9% in flight - Combustion efficiency greater than 99.0% at idle - No visible smoke, with a smoke number less than 12 under all conditions as defined by ICAO Annex 16

2.15 INTERNAL NOISE LEVEL Improved utility/pax transportation and corporate/VIP soundproofing treatments are available in addition to the standard soundproofing to further improve the acoustic comfort in the helicopter. The noise levels in the table below are indicative and refer to measured levels in typical VIP/Corporate configurations. Actual noise level will also depend, in addition to soundproofing choice, upon the specific layouts selected by the Customer. Conditions: The measured cabin internal noise levels, reported in the table below, refer to the following conditions: speed of 140 kt TAS MTOW of 6,400 kg / 14,110 lb

MTOW: 6,400 kg / 14,110 lb Basic/Std soundproofing

Improved soundproofing

Corp./VIP soundproofi ng

(dB-SIL)

(dB-SIL)

(dB-SIL)

87.1

80.9

75.7


28

THF139–0607–1

3 STANDARD CONFIGURATION AND OPTIONAL EQUIPMENT LIST Within this chapter, Section 3.1 details the AW139 standard contractual configuration as follows: 3.1.1 Basic configuration 3.1.2 Miscellaneous Optional equipments are listed in section 3.2

3.1

STANDARD CONFIGURATION (EASA / ENAC / FAA IFR CONFIGURATION)

3.1.1 Basic Config uratio n a) AIRFRAME: Aluminum alloy fuselage Polycarbonate Windshields Overhead cockpit windows Lower cockpit windows Cockpit ram air adjustable outlets Forced fan ventilation Bleed air heater and defroster with air noise suppressions Heated Pitot tubes (2) with Pitot heat failure warning (2) Heated static intakes (2) One cockpit and one pilot cabin fire extinguisher Pilot doors (2) with push–out emergency exit window (with “storm window” on pilot side) Plug in sliding doors (2) for passengers cabin access with four locking latches Six cabin push–out emergency exit windows (two on each passenger cabin door) Baggage compartment with 2 lockable baggage compartment doors, LH & RH side. Baggage compartment cargo tie–down fittings Wheeled retractable tricycle landing gear (two wheels on nose gear and brakes on main landing gear) Structural provisions for nose landing gear doors Landing gear mooring Upper deck mooring provisions Hoisting and jacking fittings Tail boom and vertical fin Stabilizers with composite “winglets” Pilot and copilot windshield wipers Maintenance steps for access to upper deck on both sides Upper deck cowlings (one front forward sliding, two side opening for engine access) Steps for cockpit access Anti-vibration masses (2) under cabin floor b) ROTORS AND CONTROLS: Fully articulated Main Rotor (M/R) with five composite blades, five elastomeric bearings and five hydraulic dampers Rotating M/R flight controls Main rotor hub beanie Three main dual servo actuators Fully articulated Tail Rotor (T/R) with four composite blades, four elastomeric bearings and four elastomeric dampers Rotating T/R flight controls One T/R dual servo actuator 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.

29

THF139–0607–1

-

Force trim system Pilot fixed flight controls (cyclic, collective, anti–torque pedals) Copilot fixed flight controls (cyclic, collective, anti–torque pedals) Dual digital 3–axis linear actuators Rotor brake Provision for main rotor tracking (magnetic pick – up)

c) EL ECTRICAL SYSTEMS: DC primary power generation: 28 V DC regulated voltage provided by two independent 300 A starter generators DC External Power Receptacle Two Nickel–Cadmium Batteries: one 40 Ah main battery plus one 13 Ah auxiliary battery DC Starter Generator Control Units (2) Navigation lights (3) Anticollision light External emergency landing lights on the sponsons (2) Fixed landing/taxi lights on the sponsons (2) Rotating/ retracting landing light Baggage compartment lighting (3) and smoke sensor d) TRANSMISSION / DRIVE SYSTEM AND HYDRAULIC SYSTEM: Main transmission with two direct drive engine inputs Three main transmission chip detectors/debris collectors with burning capability Two freewheel units Four strut rods for upper deck attachment and one anti–torque plate Intermediate gearbox with sight gauge and magnetic drain plug/chip detector Tail gearbox with sight gage and magnetic drain plug/chip detector Dual independent, redundant hydraulic systems Two hydraulic Power Control Modules (PCMs) Three main transmission driven hydraulic mechanical pumps for controls, landing gear and wheel brake actuation One electrical pump for control checks on ground (engines off) Air conditioning compressor quill e) POWER PLANT & FUEL SYSTEM: Two Pratt & Whitney Canada PT6C–67C engines Two independent FADEC systems (one on each engine) with autostart and engine control functions for normal, emergency and training operations Two magnetic chip detectors Two integrated and independent engine oil coolers Separate firewall protection for each engine Fire detection system Fire extinguisher system (2 bottles) Engine exhausts and ejectors Two independent crashworthy fuel cells Two supply pumps on engines Two booster pumps submerged in fuel tanks Two fuel filter assemblies Two engine back–up controls, mechanical and electrical Two manual engine start and ignition systems


30

THF139–0607–1

f) STANDARD AVIONICS PACKA GE: st 1 PFD (Pilot Primary Flight Display 8" × 10" color Active Matrix Liquid Crystal Display) as part of Honeywell Primus Epic System for visualization of flight and navigation data nd 2 PFD (Copilot Primary Flight Display 8" × 10" color Active Matrix Liquid Crystal Display) as part of Honeywell Primus Epic System for visualization of flight and navigation data st 1 MFD (Pilot Multifunction Display 8" × 10" color Active Matrix Liquid Crystal Display) as part of Honeywell Primus Epic System for visualization of flight and navigation data nd 2 MFD (Copilot Multifunction Display 8" × 10" color Active Matrix Liquid Crystal Display) as part of Honeywell Primus Epic System for visualization of flight and navigation data One Electronic Standby Instrument System (ESIS) (attitude, airspeed, altitude, vertical speed, compass, and ILS data) Two Attitude and Heading Reference Systems (AHRSs) Two Air Data Modules (ADMs) Two flux valves Two Display Controllers (DCs) Two Cursor Control Devices (CCDs) One Reversion Control Panel (RCP) One Display Dimming Control Panel (DCP) One Stability Augmentation System (SAS) control panel Two Remote Instrument Controllers (RICs) Two Modular Avionic Units (MAUs) incorporating the following major subsystems and/or functions: Vehicle Monitoring System – VMS (dual) • Monitor Warning System – MWS (dual) • Aural Warning Generator – AWG (single) • Central Maintenance Computer – CMC (single) • 3–Axis Digital Automatic Flight Control System – DAFCS (dual) with autotrim function • Provision for CVR/FDR data interface (single) • Flight Director System (dual) • Pilot and copilot microphone and headset Pilot and Copilot interphone control (cyclic grip and floor switches) Left Modular Radio Cabinet (MRC) with the following modules: • One VHF Comm. • One VOR/LOC/GS/MB Right Modular Radio Cabinet (MRC) with the following modules: • One VHF Comm. • One Mode–S diversity transponder • One VOR/LOC/GS/MB • One ADF • One DME Two pedestal mounted MCDUs (Multi Control Function Display Units) st 1 Radar Altimeter (RT – 300) nd 2 Radar Altimeter System (RT – 300) Emergency Locator Transmitter (ELT – 121.5/243/406 MHz) One Flight Guidance Controller Honeywell GPS module with Flight Plan Management System (FPMS) Pilot and copilot digital audio panels with remote ICS audio port for ground operation Pilot clock (digital) Copilot clock (digital) One magnetic compass -One Outside Air Temperature indicator Two Master Warning Lights (MWLs) 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.

31

THF139–0607–1

-

Two Master Caution Lights (MCLs) Engine 1 Fire Light Engine 2 Fire Light Baggage compartment smoke detector light Dual electrical power connection for CVR/FDR (FAA requirement compliant) Cockpit Voice Recorder & Flight Data Recorder (CVR/FDR) with Underwater Locator Beacon (ULB)

g) INTERIOR TRIM: Cabin, cockpit and baggage compartment utility finishing interior Pilot/ Copilot crashworthy seats (with inertial reels and safety belts) Cockpit dome/storm light Cockpit utility lights (2) 28V DC cockpit/cabin power outlet Cockpit panel sun-glare shields Overhead cockpit windows sun shades Floor provisions for 15-seat configuration Fluorescent lighted emergency exit signs h) EXTERIOR PAINTING: Two color polyurethane painting in accordance with AgustaWestland standard painting scheme

Weight of the AW139 in stand ard con fig urati on: as detailed in section 3.1.1 (part “a” through “h”)

3,685 kg / 8,124 lb

3.1.2 Miscellaneous -

Covers and flags: engine exhaust pipes (2), engine air inlets (2) and Pitot tubes (2), battery connector warning flag (1) Manuals: aircraft log, engines operations, flight and maintenance and overhaul, illustrated parts catalogue Tie down–assemblies for main rotor blades (5) Tail rotor blades flapping block (1) Main rotor blade sock pole (1) Main landing gear wheel chocks (2) Main rotor balance and tracking chart, tail rotor balance chart Nose landing gear center pin (1) and landing gear handle locking pin (1) Jacking dome assy (1) Tow bar (1) Loose equipment bag (1)


32

THF139–0607–1

3.2

EQUIPMENT LIST AND WEIGHTS

3.2.1 Standard 12–Seat Interi or Weight Weight 11 kg lb

Item

Code

1st row

49.2

108.4

TBD

2nd row

47.6

104.9

TBD

3rd row

47.6

104.9

TBD

25.0

55.1

TBD

17.6

38.8

TBD

Cockpit map and data case in central console

1.5

3.3

TBD

Two flash lights for pilot and copilot

0.3

0.7

TBD

First aid kit

0.7

1.4

TBD

Map and data cases in pilot and copilot doors

2.0

4.4

TBD

1 passenger audio panel with plug for one headset

1.4

3.1

TBD

20.0

44.1

TBD

6.0

13.2

TBD

12 – padded crashworthy utility pax seats (with inertia reels and safety belts)

Composite “deluxe” liners installed in the cockpit, cabin and baggage compartment12 and: Passenger cabin ceiling liners integrating: - 12 directional lights and two ambient lights in cabin - PA briefing system: 6 loudspeaker announcement systems plus safety belt lights - Two emergency exit lights

Standard soundproofing12 Steps for passenger cabin access Total

218.9 482.3

11

Weight tolerance for all of the weights reported in this and other sections of this document is ±2% In addition to the basic A/C interior trim configuration outlined in Sec. 3.1.1, point “f”; al so see Sec. 2.15 for further details regarding soundproofing. 12


33

THF139–0607–1

3.2.2 Option al Equipment Lis t This section details those kits that are related to the airframe mechanical and electro–avionic systems. The weight of each kit has to be added to the helicopter basic empty weight. AgustaWestland should be contacted to check for compatibility and for weights not reported in the tables. Weight kg

Ai rf ram e and Sys tem s Air Conditioning System

lb

Code

89.1

196.4

TBD

6.3

13.9

TBD

23.1

50.9

TBD

Windshield Washing System

3.4

7.5

TBD

Cargo Hook External Cameras

2.0

4.4

TBD

2.3

5.1

TBD

22.4

49.4

TBD

7.8

17.2

TBD

Installation

72.3

159.3

TBD

Provision Twin External Life Raft Installation - 2x17 Installation

2.8

5.9

TBD

90.4

199.2

TBD

12.1

26.7

TBD

61.5

135.5

TBD

3.5

7.7

TBD

2.1

4.6

TBD

10.3

22.7

TBD

13.0

28.7

TBD

3.0

6.6

TBD

31.1

68.5

TBD

18.7

41.2

TBD

1.4

3.1

TBD

2,3

5.1

TBD

23.9

52.7

TBD

Engine Air Particle Separator

Cargo Hook (2200 kg / 4850) Emergency Floats

Provision Installation

Provision Installation Provision

Rescue Hoist - 272 kg Provision (600 lbs) Breeze Installation Polycon ICS System External Loudspeaker


Wire Strike Protection System Night Sun Search Light SX–16


RH and LH Electrically Operated Passenger Steps with lights Closed Circuit Refueling System Auxiliary Fuel Tank – 500 lt / 132 USCG



34

THF139–0607–1

Weight

Ai rf ram e and Sys tem s (c on t’ d)

Kg

Provision for snow skis and slump pads kit

Code

Lb 1.3

2.9

TBD

Snow Skis Kit

55.4

122.1

TBD

Slump Pads Kit

30.2

66.6

TBD

0.4

0.9

TBD

25.0

55.1

7.9

17.4

TBD

20.0

44.1

TBD

11.6

25.6

TBD

15.2

33.5

TBD

5.0

11.0

TBD

Storm window for the copilot Heated Windshield

14

13

Nose Landing Gear Doors Cockpit / Cabin Separation Panel

15

Pilot / Copilot Alternative Adjustable Seats Double Layer Cabin Windows

13

13

Bubble Cabin Windows

13

Fast Rope and Rappelling Kit – right and left side*

Provision

TBD

TBD

TBD

Installation

TBD

TBD

TBD

7.6

16.7

TBD

/

/

TBD

Glass windshield

14.4

31.7

TBD

Self contained Lifeport Provision EMS equipment Installation 14

TBD

TBD

TBD

84.1

185.4

TBD

Central Approach Chart Holder with Light

TBD

TBD

TBD

/

/

TBD

TBD

TBD

TBD

/

/

TBD

0.7

1.5

TBD

Rappelling kit All weather covers

Cabin tinted windows Air conditioning control in passenger cabin High visibility main rotor blades Lights for passenger steps

NOTE (*) Equipment not Civil Certified. Installation will be approved by Company Qualification

14 15

Delta Weight Average weight. Weight is different according to the level of customization and finishing of the item


35

THF139–0607–1

Electro/Avionics and Instruments Weather radar Primus 660

lb

2.2

4.8

TBD

Installation

9.0

19.8

TBD

0.2

0.4

15.0

33.1

TBD

Provision

9.0

19.8

TBD

Installation

5.3

11.7

TBD

3.5

7.7

TBD

0.4

0.9

TBD

3.2

7.1

TBD

11.1

24.5

TBD

HUMS

Honeywell EGPWS Mark 22 ELT Deployable

Code

Provision

Autopilot 4–axis (additional to standard 3–axis AFCS)

TCAS I Honeywell

Weight kg

16

TBD

Radio Wulfsberg Flexcom II (provision)

Provision

Moving Map Skyforce Observer Mk II

Provision

7.1

15.6

TBD

Installation

7.7

17.0

TBD

5.5

12.1

TBD

4.6

10.1

TBD

17.1

37.7

TBD

2nd Transponder Mode S

3.7

8.2

TBD

2nd ADF

4.2

9.3

TBD

2nd DME

2.5

5.5

TBD

5th Display

7.0

15.4

TBD

Provision

3.0

6.6

TBD

Installation

4.0

8.8

TBD

Additional anti-collision light

1.3

2.9

TBD

Strobe lights

2.6

5.7

TBD

3.7

8.2

TBD

10.8

23.8

TBD

2.2

4.8

TBD

18.8

34.8

TBD

Installation

HEELS Radio HF Honeywell 1050

Moving map Euronav


Radio Collins – V/UHF AM/FM

Provision

Search/weather radar Primus 701

Provision

16

Installation

Installation

Delta weight.


36

THF139–0607–1

Electro/Avionics and Instruments Radio NAT NTX 138 Maritime band

Weight kg

Code lb

Provision

1.7

3.7

TBD

Installation

3.7

8.2

TBD

0.3

0.7

TBD

TBD

TBD

TBD

2nd utility socket - 28VDC NVG compatibility - internal and external


37

THF139–0607–1

3.2.3 Further Option al Equipm ent List The kits reported in this section are under development, planned to be developed at a further stage or customizations (i.e. FLIR System). AgustaWestland should be contacted for further details on availability, weight and compatibility.

Kit

Weight kg lb

Code

TBD

TBD

TBD

TBD

TBD

TBD

SAR Modes and SAR Patterns (additional to 4-axis AFCS)

TBD

TBD

TBD

Direction Finder DF-935

TBD

TBD

TBD

Close Circuit Refuelling plus Pressure Adapter ISO 45

TBD

TBD

TBD

Lightning Detector System (LSZ-860)

TBD

TBD

TBD

Fire fighting belly tank

TBD

TBD

TBD

Cockpit tinted upper windows

TBD

TBD

TBD

Search Light NightSun XP II

TBD

TBD

TBD

Search Light SX-5

TBD

TBD

TBD

FLIR Console in passenger cabin*

TBD

TBD

TBD

FLIR Sea Flir II *

TBD

TBD

TBD

FLIR Star Safire III *

TBD

TBD

TBD

FLIR Wescam MX15I *

TBD

TBD

TBD

Search radar RDR1500B+

TBD

TBD

TBD

Four Litters MEDEVAC Kit

TBD

TBD

TBD

Hoist Goodrich (single/dual kit)

TBD

TBD

TBD

Limited Ice Protection System

Anti / de-icing system

NOTE (*) Equipment not Civil Certified. Installation will be approved by Company Qualification


38

THF139–0607–1

4 PERFORMANCE INFORMATION This section contains the AW139 flight performance charts illustrating: 4.1 Hovering data IGE AEO TOP • AEO MCP • OEI 2.5 minutes power • OEI MCP • 4.2 Hovering data OGE AEO TOP • AEO MCP • OEI 2.5 minutes power • OEI MCP • 4.3 Category A Performance 4.4 Rate of Climb Take Off Power All Engine Operatives (TOP AEO) • Maximum Continuous Power All Engine Operative (MCP AEO) • 2.5 minutes power One Engine Inoperative (OEI) • Maximum Continuous Power One Engine Inoperative (MCP OEI) • 4.5 Cruise fuel consumption data 17 AEO at ISA At pressure altitudes of 0, 2000, 6000 and 10,000 ft • 4.6 Cruise fuel consumption data 16 AEO at ISA+20°C At pressure altitudes of 0, 2000, 6000 and 10,000 ft • 4.7 Cruise fuel consumption data 16 AEO at ISA+35°C At pressure altitudes of 0, 2000, 6000 and 10,000 ft • 4.8 Fuel flow data for hovering OGE, at ISA, ISA+20°C, ISA+35°C 4.9 Ground idle/start–up fuel flow

17

Note: 1. all fuel consumption data included herein refer to average engine performance and to clean aircraft configuration, with ECS / bleed air heater off; an increase of up to 3% of fuel burn can be expected prior to engine overhaul. 2. cruise fuel consumption charts are established for the following weights: 4,500 kg – 9,921 lb; 5,000 kg – 11,023 lb; 5,500 kg – 12,125 lb; 6,000 kg – 13,227 lb 6,400 kg – 14,110 lb


39

THF139–0607–1

4.1

HOVER IGE

4.1.1 Hover IGE (AEO / TOP – ZERO WIND) HOVER IGE (AEO/TOP) GROSS WEIGHT - lb X 100 88

98

108

118

128

138

20

60

18

55

I S A

50

16 I S A + 2 0

0 0 14 0 1 X t f E 12 D U T I T L A 10 E R U S S E 8 R P

45

40 I S A + 3 5

35

30

25

0 0 1 X m E D U T I T L A E R U S S E R P

20 6 15 4 10 2

5

0

0 40

44

48

52

56

60

64

GROSS WEIGHT - kg X 100


40

THF139–0607–1

4.1.2 Hov er IGE (AEO / MCP – ZERO WIND) HOVER IGE (AEO/MCP) GROSS WEIGHT - lb X 100 88

98

108

118

128

138

20

60

55

18

I S A

16

50


40

I S A + 2 0

35

30

25

I S A + 3 5

6


20

15 4 10 2

5

0

0 40

44

48

52

56

60

64



41

THF139–0607–1

4.1.3 Hover IGE (OEI / 2.5 min POWER – ZERO WIND) HOVER IGE (OEI / 2.5 min) GROSS WEIGHT - lb X 100 88

98

108

118

128

138

20

60

55

18

50

16


40

35 I S A

30

25

I S A + 2 0


20 6 I S A + 3 5

4

15

10 2

5

0

0 40

44

48

52

56

60

64



42

THF139–0607–1

4.1.4 Hov er IGE (OEI / MCP – ZERO WIND) HOVER IGE (OEI / MCP) GROSS WEIGHT - lb X 100 88

98

108

118

128

138

20

60

55

18

50

16


40 I S A

35

30 I S A + 2 0

25


20 6 15 4 10 I S A + 3 5

2

5

0

0 40

44

48

52

56

60

64



43

THF139–0607–1

4.2

HOVER OGE

4.2.1 Hov er OGE (AEO / TOP – ZERO WIND) HOVER OGE (AEO/TOP) GROSS WEIGHT - lb X 100 88

98

108

118

128

138

20

60

55

18

50

16

45

I S A

014 0 0 1 X t f E12 D U T I T L A10 E R U S S E 8 R P

40 I S A + 2 0

35

30

25

I S A + 3 5


20 6 15 4 10 2

5

0

0 40

44

48 52 56 GROSS WEIGHT - kg X 100

60

64


44

THF139–0607–1

4.2.2 Hov er OGE (AEO / MCP – ZERO WIND) HOVER OGE (AEO/MCP) GROSS WEIGHT - lb X 100 88

98

108

118

128

138

20

60

18

55

I S A

50

16

45 I S A + 2 0

0 14 0 1 X t f E 12 D U T I T L A 10 E R U S S E 8 R P

40

35

30 I S A + 3 5

25


20 6 15 4 10 2

5

0

0 40

44

48

52

56

60

64



45

THF139–0607–1

4.2.3 Hover OGE (OEI / 2.5 min POWER – ZERO WIND) HOVER OGE (OEI / 2.5 min) GROSS WEIGHT - lb X 100 88

98

108

118

128

138

20

60

55

18

50

16


40

35

30 I S A

25


20 6

I S A + 2 0

15

4 10 I S A + 3 5

2

5

0

0 40

44

48

52

56

60

64



46

THF139–0607–1

4.2.4 Hov er OGE (OEI/MCP – ZERO WIND) HOVER OGE (OEI / MCP) GROSS WEIGHT - lb X 100 88

98

108

118

128

138

20

60

55

18

50

16


40

35

30 I S A

25


20 6 I S A + 2 0

4

15

10 2

5

0

0 40

44

48

52

56

60

64



47

THF139–0607–1

4.3

CATEGORY A PERFORMANCE

The AW139 is certified to perform the following Cat. A t ake off procedures: - helipad procedure (ground level and elevated) - short field procedure - back-up procedure - clear area procedure Minimum demonstrated helipad size for helipad, short field and back-up procedures is 15×15 m (50×50 ft).

4.3.1 Helipad Procedure (Groun d Level and Elevated) For a ground level or elevated helipad without obstacles in the take off flight path, the vertical take off procedure with TDP fixed at 35 ft can be used. If TDP at 35 ft does not allow to obtain the required clearance from obstacles in the take off flight path, the vertical take off procedure with an Extended TDP (TDP E) up to 70 ft can be used.

4.3.2 Short field Procedure A short field take off procedure consisting in a vertical climb to a TDP that varies between 85 ft and 400 ft is available if there is sufficient space to carry out a rejected take off.

4.3.3 Back-up Procedure A back-up take off procedure consisting in a back-up climb to a TDP that varies between 85 ft and 400 ft is available to clear obstacles.

4.3.4 Clear Ar ea The clear area take off procedure can be used on runaways.

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. TH IS SPECIFICATION IS SUBJECT TO CHANGE WITHOUT NOTICE.

48

THF139–0607–1

4.3.5 W-A-T Lim itati ons (Helip ad / Short Field / Back Up)

WEIGHT-ALTITUDE-TEMPERATURE SHORTFIELD and HELIPORT Gross Weight - lb x 1000 9.5 14

10

10.5

11

11.5

12

12.5

13

13.5

I T MI

13

4

L

d H

12 3.5 11 - 4 0

10 I S A + 2 0 ° C

9 0 0 0 1 x t f e d u t i t l e r u s s e r P

8 7

I S A

- 3 0

0

2.5 0 0

- 2 0

1

- 1 0

I S A + 3 5 ° C

6

3

1.5

e r u s s e r P

0 1 0

5

2

m e d u t i t l

2 0

4

1

3 4 0

2

3 0

0.5 1 5 0

0

0

-1 4.2

4.4

4.6

4.8

5 5.2 5.4 5.6 5.8 Gross Weight - kg x 1000

6

6.2

6.4

6.6


49

THF139–0607–1

4.3.6 W-A-T Limitati ons (Clear Area)

WEIGHT-ALTITUDE-TEMPERATURE CLEAR AREA Gross Weight - lb x 1000 9.5

10

10.5

11

11.5

12

12.5

13

13.5

14

- 4 0

T I M I L d H

13

- 2 0

12

I S A

10

2 0

9

e r u s s e r P

3.5

- 1 0

11

0 0 0 1 x t f e d u t i t l

4

- 3 0

8

0

0

2.5 0 0 1

I S A + 3 5 ° C

7

3

I S A 1 + 0 2 0 ° C

3 0

2

m e d u t i t l

1.5

e r u s s e r P

6 5

4 0

4 1

3 2

0.5 1 0

0

-1 4.2

4.4

4.6

4.8

5 5.2 5.4 5.6 5.8 Gross Weight - kg x 1000

6

6.2

6.4

6.6


50

THF139–0607–1

4.4

RATE OF CLIMB PERFORMANCE

4.4.1 Rate of Climb in Oblique Flig ht (TOP/AEO) RATE OF CLIMB - TOP AEO - V y = 80 kt IAS MTOW = 6,400 kg

RATE OF CLIMB - m/s 0

1

2

3

4

5

6

MTOW = 6,000 kg

7

8

9

10

11

12

20

60

55

18

16

50

I S A

45

I S A


I S A + 2 0

I S A + 3 5

40

35

I S A + 2 0

30

25


20 6

I S A + 3 5

15

4 10 2

5

0

0 0

4

8

12

16

20

24

RATE OF CLIMB - ft/min X 100


51

THF139–0607–1

4.4.2 Rate of Climb in Oblique Flight (MCP/AEO) RATE OF CLIMB - MCP AEO - V y = 80 kt IAS MTOW = 6,400 kg


1

2

3

4

5

6

MTOW = 6,000 kg

7

8

9

10

11

12

20

60

18

16


I S A

55

I S A

50

I S A + 2 0

45

I S A + 2 0

40

I S A + 3 5

35

I S A + 3 5

25

30

20


6 15 4 10 2

5

0

0 0

4

8

12

16

20

24



52

THF139–0607–1

4.4.3 Rate of Climb in Obli que Fligh t (2.5 min POWER OEI) RATE OF CLIMB - 2.5 min OEI - V y = 80 kt IAS MTOW = 6,400 kg


1

2

3

MTOW = 6,000 kg

4

5

6

7

20

60

55

18

50

16


40

35

30 I S A

25


20 6

I S A + 2 0

I S A

15

4 10 I S A + 3 5

2

I S A + 3 5

I S A + 2 0

5

0

0 0

2

4

6

8

10

12

14



53

THF139–0607–1

4.4.4 Rate of Climb in Obli que Fli ght (MCP/OEI) RATE OF CLIMB - MCP OEI - V y = 80 kt IAS MTOW = 6,400 kg


1

2

MTOW = 6,000 kg

3

4

5

6

7

20

60

55

18

50

16


40

35 I S A

30

25

I S A

6

I S A + 3 5

4

IS A + 3 5


20

I S A + 2 0 I S A + 2 0

15

10

2

5

0

0 0

2

4

6

8

10

12

14



54

THF139–0607–1

4.5

FUEL CONSUMPTION DATA AEO AT ISA

4.5.1 Fuel Consump ti on Data* (SL)

FUEL FLOW - AEO SL ISA INDICATED AIR SPEED - kt 35

55

75

95

115

135

155

175

550 TRANSMISSION LIMIT

1151

500 1051

RECOMMENDED CRUISE SPEED

450 h / g k W O 400 L F L E U F

951 h / b l W O L F 851 L E U F 6 ,4 0 0 6 , 0 0 0 5 , 5 0 0 5 , 0 0 0 4 , 5 0 0

350

300

BEST ENDURANCE SPEED

751 I M I L E N V

651

250

551 40

60

80

100

120

140

160

180

TRUE AIR SPEED - kt * Weights equivalences: 4,500 kg – 9,921 lb; 6,400 kg – 14,110 lb

5,000 kg – 11,023 lb;

5,500 kg – 12,125 lb;

6,000 kg – 13,227 lb


55

THF139–0607–1

4.5.2 Fuel Consump ti on Data* (2,000 ft)

FUEL FLOW - AEO 2,000 ft PA ISA INDICATED AIR SPEED - kt 34

54

74

94

114

134

154

174

550

TRANSMISSION LIMIT

1151

500 1051

450 RECOMMENDED CRUISE SPEED

h / g k W O 400 L F L E U F 6 ,4 0 0

350

6 , 0 0 0 5 , 5 0 0 5 , 0 0 0 4 , 5 0 0

300

951 h / b l W O L F 851 L E U F


751 I M I L E N V

651

250

551 40

60

80

100

120

140

160

180

TRUE AIR SPEED - kt

* Weights equivalences: 4,500 kg – 9,921 lb; 6,400 kg – 14,110 lb

5,000 kg – 11,023 lb;

5,500 kg – 12,125 lb;

6,000 kg – 13,227 lb


56

THF139–0607–1



51

71

500

91

111

131

151

171

TRANSMISSION LIMIT

1041 450 941


400 h / g k W O350 L F L E U F

841 h / b l W O L F 741 L E U F

6 ,4 0 0 6 , 0 0 0

300


5 , 5 0 0 5 , 0 0 0 4 , 5 0 0

641 I M I L E N V

250

541

200

441 40

60

80

100

120

140

160

180

TRUE AIR SPEED - kt


5,000 kg – 11,023 lb;

5,500 kg – 12,125 lb;

6,000 kg – 13,227 lb


57

THF139–0607–1

4.5.4 Fuel Consu mpt ion Data* (10,000 ft )


49

69

89

109

129

149

500


450

941

400 RECOMMENDED CRUISE SPEED

h / g k W O 350 L F L E U F

841

6 , 4 0 0

6 , 0 0 0

741 BEST ENDURANCE SPEED

h / b l W O L F L E U F

300 641

5 , 5 0 0

I M I L E N V

5 , 0 0 0

250

4 , 5 0 0

541

200

441 40

60

80

100

120

140

160

180

TRUE AIR SPEED - kt


5,000 kg – 11,023 lb;

5,500 kg – 12,125 lb;

6,000 kg – 13,227 lb


58

THF139–0607–1

4.6

FUEL CONSUMPTION DATA AEO AT ISA+20°C


FUEL FLOW - AEO SL ISA+20°C INDICATED AIR SPEED - kt 34

54

74

94

114

134

154

174


1151 500 1051 RECOMMENDED CRUISE SPEED

450 h / g k W O 400 L F L E U F

6 , 4 0 0

951 h / b l W O L F 851 L E U F


6 , 0 0 0 5 , 5 0 0 5 , 0 0 0 4 , 5 0 0

350

300

751

I M I L E N V

651

250

551 40

60

80

100

120

140

160

180


5,000 kg – 11,023 lb;

5,500 kg – 12,125 lb;

6,000 kg – 13,227 lb


59

THF139–0607–1


FUEL FLOW - AEO 2,000 ft PA ISA+20°C INDICATED AIR SPEED - kt 32

52

72

92

112

132

152

172

550

1151

TRANSMISSION LIMIT

500 1051

450



6 , 4 0 0

350

6 , 0 0 0

951 h / b l W O L F 851 L E U F


751 I M I L E N V

5 , 5 0 0 5 , 0 0 0 4 , 5 0 0

300

651

250

551 40

60

80

100

120

140

160

180

TRUE AIR SPEED - kt


5,000 kg – 11,023 lb;

5,500 kg – 12,125 lb;

6,000 kg – 13,227 lb


60

THF139–0607–1



50

70

90

110

130

150

500 MCP

1041 450 941 RECOMMENDED CRUISE SPEED

400 h / g k W O 350 L F L E U F

841 h / b l W O L F 741 L E U F

6 , 4 0 0 6 , 0 0 0


5 , 5 0 0

300

641

5 , 0 0 0 4 , 5 0 0

I M I L E N V

250

200

541

441 40

60

80

100

120

140

160

180

TRUE AIR SPEED - kt


5,000 kg – 11,023 lb;

5,500 kg – 12,125 lb;

6,000 kg – 13,227 lb


61

THF139–0607–1



48

68

88

108

128

148

450 MCP

941

400 841 RECOMMENDED CRUISE SPEED 6 , 4 0 0

h / 350 g k W O L F L E U F 300

h / b l 741 W O L F L E U F

6 , 0 0 0

5 , 5 0 0


641 I M I L E N V

5 , 0 0 0 4 , 5 0 0

250

541

200

441 40

60

80

100

120

140

160

180

TRUE AIR SPEED - kt


5,000 kg – 11,023 lb;

5,500 kg – 12,125 lb;

6,000 kg – 13,227 lb


62

THF139–0607–1

4.7

FUEL CONSUMPTION DATA AEO AT ISA+35°C


FUEL FLOW - AEO SL ISA+35°C INDICATED AIR SPEED - kt 33

53

73

93

113

133

153

173

500

1051 MCP

450


951

h / 400 g k W O L F L E U F 350

6 , 4 0 0

6 , 0 0 0

h / b l 851 W O L F L E U F


5 , 5 0 0

751

5 , 0 0 0 4 , 5 0 0

I M I L E N V

300

651

250

551 40

60

80

100

120

140

160

180


5,000 kg – 11,023 lb;

5,500 kg – 12,125 lb;

6,000 kg – 13,227 lb


63

THF139–0607–1



51

71

91

111

131

151

171

450 MCP

951


400 851 6 , 4 0 0


6 , 0 0 0

h / b l W O L F 751 L E U F


5 , 5 0 0

I M I L E N V

5 , 0 0 0

300

4 , 5 0 0

651

250

551 40

60

80

100

120

140

160

180

TRUE AIR SPEED - kt


5,000 kg – 11,023 lb;

5,500 kg – 12,125 lb;

6,000 kg – 13,227 lb


64

THF139–0607–1



49

69

89

109

129

149

450

951 MCP RECOMMENDED CRUISE SPEED

400

851 h / g k W O 350 L F L E U F

h / b l W O L F 751 L E U F

6 , 4 0 0

6 , 0 0 0


5 , 5 0 0

300

I M I L E N V

5 , 0 0 0 4 , 5 0 0

250

651

551 40

60

80

100

120

140

160

180

TRUE AIR SPEED - kt


5,000 kg – 11,023 lb;

5,500 kg – 12,125 lb;

6,000 kg – 13,227 lb


65

THF139–0607–1



47

67

87

107

127

147

400

841

MCP


6 , 4 0 0

350 6 , 0 0 0


5 , 5 0 0

741 h / b l W O L F 641 L E U F


5 , 0 0 0

4 , 5 0 0

250

I M I L E N V

200

541

441 40

60

80

100

120

140

160

180

TRUE AIR SPEED - kt


5,000 kg – 11,023 lb;

5,500 kg – 12,125 lb;

6,000 kg – 13,227 lb


66

THF139–0607–1

4.8

HOVERING FUEL CONSUMPTION DATA

In this section fuel flow data versus pressure altitude for hovering OGE, zero airspeed, zero wind, are presented for gross weights of: -

4,500 kg / 5,000 kg / 5,500 kg / 6,000 kg / 6,400 kg /

9,921 lb 11,023 lb 12,125 lb 13,227 lb 14,110 lb

For hovering OGE limits in terms of weight versus altitude and temperature, reference should be made to Sec. 4.2.


67

THF139–0607–1

4.8.1 HOGE Fuel Consu mpt ion Data at ISA

HOGE FUEL FLOW - AEO ISA

FUEL FLOW - lb/h 717

817

917

1017

1117

1217

1317

10

30

25

8

0 0 0 1 x t f 6 E D U T I T L A E R U 4 S S E R P

2

20

15

G G G W W W = = = 4 5 5 , 5 , 0 , 5 0 0 0 0 0 0 k k k g g g / / / 9 1 1 , 9 1 2 , 0 2 , 1 1 2 2 3 l b 5 l b l b

G W = 6 , 0 0 0 k g / 1 3 , 2 2 7 l b

G W = 6 , 4 0 0 k g / 1 4 , 1 1 0 lb

10

5

0 325

0 0 1 x m E D U T I T L A E R U S S E R P

0 375

425

475

525

575

625

FUEL FLOW - kg/h


68

THF139–0607–1

4.8.2 HOGE Fuel Cons ump tion Data at ISA+20°C HOGE FUEL FLOW - AEO ISA+20°C


870

970

1070

1170

1270

1370

10

30

25

8


2

20

15

G G G W W W = = = 5 4 5 , 0 , 5 , 5 0 0 0 0 0 0 k k k g g g / / / 1 9 1 1 , 9 2 , 0 , 1 2 2 1 2 3 5 lb l b l b

G W = 6 , 0 0 0 k g / 1 3 , 2 2 7 l b

G W = 6 , 4 0 0 k g / 1 4 , 1 1 0 l b

10

5

0 350


0 400

450

500

550

600

650

FUEL FLOW - kg/h


69

THF139–0607–1

4.8.3 HOGE Fuel Cons ump tion Data at ISA+35°C HOGE FUEL FLOW - AEO ISA+35°C


870

970

1070

1170

1270

1370

1470

10

30

25

8


2

20

15

G G G W W W = = = 4 5 5 , 5 , 0 , 5 0 0 0 0 0 0 k k k g g g / / / 9 1 1 , 9 1 2 , 0 , 1 2 1 2 2 3 5 l b l b lb

G W = 6 , 0 0 0 k g / 1 3 , 2 2 7 l b

G W = 6 , 4 0 0 k g / 1 4 , 1 1 0 l b

10

5

0 350


0 400

450

500

550

600

650

700

FUEL FLOW - kg/h


70

THF139–0607–1

4.9

GROUND IDLE/START–UP FUEL FLOW

The ground idle fuel consumption (with engine running at 60 per cent of the nominal maximum continuous power) has been estimated in 2 kg/min ( ≅ 4.4 lb/min) per engine.

Idle Fuel / Start Up Fuel Flow

kg/min

lb/min

2.0

4.4


71

THF139–0607–1

5 ESTIMATED DIRECT OPERATING COST AND RELATED RELATED DATA DATA 5.1

GENERAL GENERAL INFORMATION INFORMATION

This chapter provides information on the Direct Operating Costs (DOCs) associated with the typical operation of the AW139 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. 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 multipurpose configuration has been analyzed with the following assumptions: - 300 FH per year; - 20,000 FH as reference period; - 1 Landing per FH; - 1 Engine cycle per FH Direct Operating Costs are, by definition, those related directly to each hour flown and cover: - Fuel & Lubricants Maintenance - Airframe Direct Maintenance - Powerplant Maintenance The following sections provide additional rationale for the data reported in this chapter. 5.2

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 f uel. 5.3 AIRFRA ME DIRECT MAINTENANCE MAINTENA NCE The airframe direct maintenance cost estimates are provided in the categories of line maintenance labor, and parts. Labor The estimated labor 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.


72

THF139–0607–1

Parts

-

5.4

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 labor) and replacement of non-repairable parts for unscheduled unscheduled maintenance; Overhaul: the data shown refers to the average overhaul (including parts and labor) 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.

POWERPLA POWERPLANT NT MAINTENANCE

The powerplant direct operating cost estimate includes costs for periodic inspections and overhauls as per P&WC Engine Maintenance Cost for PT6C-67C 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.


73

THF139–0607–1

The table below reports detailed information about estimated DOCs. Further information is available through AgustaWestland Company Customer Support and Marketing Organizations. Organizations.

Economic Conditions 2005

Operator

Hourly Op.

MMH/FH

Cost (USD) (USD)

FUEL AND LUB RICANTS Fuel18

129 USG/h at 134 kts

Lubricants

3% of fuel cost

290.3 8.7

AIRFRAME AIRFRA ME DIRECT MAINTENANCE Airframe Line Maintenance Maintenance Labor Labor 19: - Scheduled Maintenance

0.83

53.6

- Unscheduled Maintenance Maintenanc e

0.47

30.7

Airframe Parts: - Inspections Consumables - Unscheduled Unscheduled

2.0 234.1

- Overhaul Components

89.6

- Life-Limited Parts

21.7

POWERPLANT DIRECT MAINTENANCE - Line Maintenance & Overhaul Incl. Accessories20

144.1

TOTAL ESTIMATED DOC PER FH

874.8

18

Fuel at USD 2.25 per USG Labor at USD 65 per hour 20 Pratt & Whitney Engine Maintenance Cost (DMC) for PT6C-67C, 1 cycle per hour 19


74

THF139–0607–1

5.5

OVERHAUL COMPONENTS

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

Description

Quantity

TBO

per A/C

(Flight (Flight Hours)

Dc Starter Generator (300A)

2

1,000

Fire Extinguisher Extinguishe r Bottle

2

5 years

Main Rotor Damper

5

2,400

Main Gearbox Assy

1

5,000

Torque Tube Assy

2

5,000

Crosshead, Left

1

5,000

Crosshead, Right

1

5,000

Input Shaft (LH & RH)

2

5,000

Pump, Lubrication Assy

2

5,000

MGB Oil Cooling Fan

1

5,000

Duplex Bearing

1

3 years

Bearing Support

1

5,000

Intermediate Gearbox Assy

1

5,000

Tail Gearbox Assy

1

5,000

Main Rotor Actuator

3

3,000

Tail Rotor Actuator

1

3,000

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


75

THF139–0607–1

5.6

RETIREMENT LIFE COMPONENTS

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

Description

Quantity

RETIREMENT LIFE

per A/C

(Flight Hours)

TGB Fitting

1

7,200

Main Rotor Rotating Swashplate

1

10,000

MGB Shaft, Main Rotor

1

54,000 LDN or 10,000

MGB Front Bracket

2

7,000

MGB Rear Bracket

2

8,000

Tail Rotor Hub Assy

1

10,100

Tail Rotor elastomeric Bearing

4

5,000


76

THF139–0607–1

6 SERVICE PLANS Several service plans are available both for the airframe and the power plant of the AW139, at fixed hourly rates.

6.1

AIRFRAME MAINTENANCE PROGRAM

AgustaWestland airframe maintenance programs are: -

GSP

(Global Support Plan)

-

COMP

(Complete Overhaul and Maintenance Program)

-

CPA

(Components Protection Agreement)

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

6.1.1 Global Suppo rt Plan (GSP) For Civil Operators desiring complete coverage, including maintenance labor to ensure the highest level of operating cost assurance, AgustaWestland has assembled a comprehensive support plan which covers the basic helicopter and the required maintenance manpower. The Global Support Plan (GSP) provides labor 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 (the coverage of the Honeywell avionic systems is guaranteed under the signature of the Honeywell Avionic Protection Plan)

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: −

Labor for scheduled and unscheduled inspections as per Chapter 5 of the Maintenance Manual (labor 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)

−

Labor and Parts support for the application of Agusta mandatory technical bulletins


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Plan exclusions: -

Any costs attributable to abuse or misuse of the aircraft.

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

Airframe components

−

Avionics components (the coverage of the Honeywell avionic systems is guaranteed under the signature of the Honeywell Avionic Protection Plan)

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: − − −

Labor for scheduled and unscheduled/on-condition maintenance Any costs attributable to abuse or misuse of the aircraft Transportation charges

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


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Main covered components: -

Main Gearbox

-

Intermediate Gearbox

-

Tail Rotor Gearbox

-

Main & Tail Rotor Servos

-

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 -

Labor for scheduled and unscheduled/on-condition maintenance

-

Any costs attributable to abuse or misuse of the aircraft

-

Transportation charges

-

Fuel, lubricants and consumables material

6.2

WARRANTIES

6.2.1 AIRFRAME WARRANTY The AW139 is covered by AgustaWestland with the “Triple 3” warranty. Detailed information about "Triple 3" warranty are available through the AgustaWestland “Warranty Policy” publication.

6.2.2 ENGINE WARRANTY The PT6C-67C engine is covered by Pratt & Whitney warranty. For an outline of Pratt & Whitney warranty see the “PT6C-67C Customer Support Handbook” publication.


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7 TRAINING 7.1

AGUSTAWESTLAND TRAINING CENTERS

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

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

7.1.2 The Simu lator 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 AW139 “full flight simulator” (STD-1H Level D), available from the 2 nd quarter of 2007, 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 AW139 operators worldwide.

7.2

TRAINING COURSES

Training courses available include: - Pilot ground course - Pilot transition course - Airframe maintenance course - Engine line maintenance course Specific and tailored training solutions are available to the Customer.


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THF139-0607-1.pdf

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