MANUAL (ASMTTC) AGUSTAWESTLAND PROPRIETARY / FOR TRAINING PURPOSE ONLY
All information and training material obtained from AgustaWestland Training Academy “A.Marchetti” shall be treated as confidential and proprietary of AWTA. Clients shall protect and keep such Confidential Information in confidence and not make available or otherwise disclose such Confidential Information to any third party without the prior written consent of AWTA.
39-A-00-00-03-00A-001A-T Issue No. 001 Issue Date 2010-01-01
PMC-39-A0126-AV001-00
PMC-39-A0126-AV001-00
LIST OF EFFECTIVE DATA MODULES AND RELEVANT PAGES
The listed Data Modules are included in issue 001, dated 2010-01-01, of this Training Information Set. C = Changed DM; N = New DM. Revised text is highlighted by a yellow colour background.
DATA MODULE TITLE DATA MODULE CODE DM STATUS ISSUE DATE NO. OF PAGES
Title Page 39-A-00-00-03-00A-001A-T N 2010-05-31 1
List of effective data modules 39-A-00-00-03-00A-002A-T N 2010-05-31 6
Highlights 39-A-00-00-03-00A-003A-T N 2010-05-31 1
List of abbreviations 39-A-00-00-03-00A-005A-T N 2010-05-31 13
Table of contents 39-A-00-00-03-00A-009A-T N 2010-05-31 8
AW Training Academy Italy “A. Marchetti” 3E-A-00-00-00-00A-018A-T C 2010-07-13 26
Helicopter - General 39-A-00-00-00-00A-047A-T N 2009-07-19 32
Cockpit layout 39-A-00-03-00-00A-047A-T N 2009-07-19 11
Conversion tables 39-A-00-12-00-00A-047A-T N 2009-07-19 7
Helicopter safety for maintenance 39-A-00-20-00-00A-047A-T N 2009-07-19 3
Technical publications 39-A-00-40-00-00A-047A-T N 2009-07-19 7
Maintenance publication 39-A-00-41-00-00A-047A-T N 2009-07-19 9
Worthiness (fit for purpose) limitations 39-A-04-00-00-00A-047A-T N 2009-07-19 7
Scheduled/unscheduled maintenance 39-A-05-00-00-00A-047A-T N 2009-07-19 18
39-A-00-00-03-00A-002A-T 2010-01-01 Page: 1
PMC-39-A0126-AV001-00
DATA MODULE TITLE DATA MODULE CODE DM STATUS ISSUE DATE NO. OF PAGES
Principal dimensions 39-A-06-10-00-00A-047A-T N 2009-07-19 3
Reference lines 39-A-06-20-00-00A-047A-T N 2009-07-19 5
Access provisions 39-A-06-40-00-00A-047A-T N 2009-07-19 5
Jacking 39-A-07-10-00-00A-047A-T N 2009-07-19 4
Slinging 39-A-07-30-00-00A-047A-T N 2009-07-19 3
Leveling 39-A-08-20-00-00A-047A-T N 2009-07-19 2
Weighing 39-A-08-30-00-00A-047A-T N 2009-07-19 6
Mass and c.g. data 39-A-08-40-00-00A-047A-T N 2009-07-19 11
Handling 39-A-09-10-00-00A-047A-T N 2009-07-19 2
Parking 39-A-10-10-00-00A-047A-T N 2009-07-19 4
Servicing 39-A-12-00-00-00A-047A-T N 2009-07-19 1
Replenishing and depleting 39-A-12-10-00-00A-047A-T N 2009-07-19 5
Support equipment connect / disconnect 39-A-12-40-00-00A-047A-T N 2009-07-19 4
Vibration analysis 39-A-18-10-00-00A-047A-T N 2009-07-19 19
Environmental control 39-A-21-00-00-00A-047A-T N 2009-07-19 17
Distribution 39-A-21-20-00-00A-047A-T N 2009-07-19 18
Heating 39-A-21-40-00-00A-047A-T N 2009-07-19 22
Integrated environmental control system (ECS) 39-A-21-90-00-00A-047A-T N 2009-07-19 20
Auto flight 39-A-22-00-00-00A-047A-T N 2009-07-19 122
39-A-00-00-03-00A-002A-T 2010-01-01 Page: 2
PMC-39-A0126-AV001-00
DATA MODULE TITLE DATA MODULE CODE DM STATUS ISSUE DATE NO. OF PAGES
Communications 39-A-23-00-00-00A-047A-T N 2009-07-19 56
Speech communication 39-A-23-10-00-00A-047A-T N 2009-07-19 8
Audio integrating and voice command systems 39-A-23-50-00-00A-047A-T N 2009-07-19 10
Integrated automatic tuning 39-A-23-80-00-00A-047A-T N 2009-07-19 15
Electrical power 39-A-24-00-00-00A-047A-T N 2009-07-19 46
DC main generation 39-A-24-30-00-00A-047A-T N 2009-07-19 57
External power 39-A-24-40-00-00A-047A-T N 2009-07-19 28
DC electrical load distribution 39-A-24-60-00-00A-047A-T N 2009-07-19 13
Equipment/furnishings 39-A-25-00-00-00A-047A-T N 2009-09-30 26
Passenger/operating crew compartment 39-A-25-20-00-00A-047A-T N 2009-09-30 4
Emergency 39-A-25-60-00-00A-047A-T N 2009-07-19 12
Rescue hoist 39-A-25-91-00-00A-047A-T N 2009-07-19 25
Cargo hook 39-A-25-92-00-00A-047A-T N 2009-07-19 18
Fire protection 39-A-26-00-00-00A-047A-T N 2010-06-01 22
Storage 39-A-28-10-00-00A-047A-T N 2009-07-19 15
Distribution 39-A-28-20-00-00A-047A-T N 2009-07-19 26
Indicating 39-A-28-40-00-00A-047A-T N 2009-07-19 18
Main 39-A-29-10-00-00A-047A-T N 2009-07-19 16
Power control module 39-A-29-11-00-00A-047A-T N 2009-07-19 44
39-A-00-00-03-00A-002A-T 2010-01-01 Page: 3
PMC-39-A0126-AV001-00
DATA MODULE TITLE DATA MODULE CODE DM STATUS ISSUE DATE NO. OF PAGES
Hydraulic power supply 39-A-29-12-00-00A-047A-T N 2009-07-19 4
Tail rotor shut-off valve 39-A-29-13-00-00A-047A-T N 2009-07-19 2
Auxiliary 39-A-29-20-00-00A-047A-T N 2009-07-19 5
Pitot and static 39-A-30-30-00-00A-047A-T N 2009-07-19 10
Windows, windshields, canopies and doors 39-A-30-40-00-00A-047A-T N 2009-07-19 12
Indicating/recording systems 39-A-31-00-00-00A-047A-T N 2009-07-19 13
Instrument and control panels 39-A-31-10-00-00A-047A-T N 2009-07-19 2
Independent instruments 39-A-31-20-00-00A-047A-T N 2009-07-19 13
Recorders 39-A-31-30-00-00A-047A-T N 2009-07-19 27
General computers 39-A-31-40-00-00A-047A-T N 2009-07-19 35
Central warning system 39-A-31-50-00-00A-047A-T N 2009-07-19 20
Central display systems 39-A-31-60-00-00A-047A-T N 2009-07-19 103
Landing gear 39-A-32-00-00-00A-047A-T N 2010-06-07 2
Main gear and doors 39-A-32-10-00-00A-047A-T N 2009-07-19 4
Nose gear and doors 39-A-32-20-00-00A-047A-T N 2009-07-19 3
Extension and retraction 39-A-32-30-00-00A-047A-T N 2009-07-19 32
Wheels and brakes 39-A-32-40-00-00A-047A-T N 2009-07-19 16
Steering 39-A-32-50-00-00A-047A-T N 2009-07-19 9
Flight compartment 39-A-33-10-00-00A-047A-T N 2009-07-19 18
39-A-00-00-03-00A-002A-T 2010-01-01 Page: 4
PMC-39-A0126-AV001-00
DATA MODULE TITLE DATA MODULE CODE DM STATUS ISSUE DATE NO. OF PAGES
Passenger compartment 39-A-33-20-00-00A-047A-T N 2009-07-19 12
Cargo and service compartments 39-A-33-30-00-00A-047A-T N 2009-07-19 7
Exterior 39-A-33-40-00-00A-047A-T N 2009-07-19 12
Emergency lighting 39-A-33-50-00-00A-047A-T N 2009-07-19 6
Navigation 39-A-34-00-00-00A-047A-T N 2009-07-19 3
Flight environment data 39-A-34-10-00-00A-047A-T N 2009-07-19 27
Attitude and direction 39-A-34-20-00-00A-047A-T N 2009-07-19 35
Landing and taxiing aids 39-A-34-30-00-00A-047A-T N 2009-07-19 30
Independent position determining 39-A-34-40-00-00A-047A-T N 2009-07-19 17
Weather radar system 39-A-34-41-00-00A-047A-T N 2009-07-19 8
Global position system 39-A-34-51-00-00A-047A-T N 2009-07-19 4
DME system 39-A-34-52-00-00A-047A-T N 2009-07-19 5
Automatic Direction Finder (ADF) system 39-A-34-53-00-00A-047A-T N 2009-07-19 15
ATC transponder system 39-A-34-54-00-00A-047A-T N 2009-07-19 8
Flight management system 39-A-34-60-00-00A-047A-T N 2009-07-19 12
Central maintenance system (CMS) 39-A-45-45-00-00A-047A-T N 2009-07-19 79
Systems integration and display 39-A-46-00-00-00A-047A-T N 2009-07-19 22
Doors 39-A-52-00-00-00A-047A-T N 2009-07-19 8
Door warning 39-A-52-70-00-00A-047A-T N 2009-07-19 13
39-A-00-00-03-00A-002A-T 2010-01-01 Page: 5
PMC-39-A0126-AV001-00
DATA MODULE TITLE DATA MODULE CODE DM STATUS ISSUE DATE NO. OF PAGES
Forward sections 39-A-53-10-00-00A-047A-T N 2009-07-19 6
Tail section 39-A-53-40-00-00A-047A-T N 2009-07-19 6
Windows 39-A-56-00-00-00A-047A-T N 2009-07-19 10
Main rotors 39-A-62-00-00-00A-047A-T N 2009-07-19 23
Main rotor drives 39-A-63-00-00-00A-047A-T N 2010-06-09 21
Indicating 39-A-63-40-00-00A-047A-T N 2009-07-19 21
Rotor brake 39-A-63-50-00-00A-047A-T N 2009-07-19 16
Tail rotor 39-A-64-00-00-00A-047A-T N 2009-07-19 10
Tail rotor drive 39-A-65-00-00-00A-047A-T N 2010-06-09 16
Rotors flight control 39-A-67-00-00-00A-047A-T N 2009-07-19 19
Servo-control system 39-A-67-30-00-00A-047A-T N 2009-07-19 8
Power plant 39-A-71-00-00-00A-047A-T N 2009-07-19 83
Electrical power supply 39-A-74-10-00-00A-047A-T N 2009-07-19 6
Cranking 39-A-80-10-00-00A-047A-T N 2009-07-19 8
39-A-00-00-03-00A-002A-T 2010-01-01 Page: 6
Record of Issues: Issue 001: 2010-01-01
The listed changes are included in Issue 001, dated 2010-01-01, of this Training Information Set.
DATA MODULE CODE DATA MODULE
39-A-00-00-03-00A-003A-T 2010-01-01 Page: 1
A/C Aircraft
ACP Audio Control Panel
AGB Accessory Gear Box
AGL Above Ground Level
AHRU Attitude Heading Reference Unit
AIOP Actuator Input/Output Processor (Module)
ALT Altitude; Barometric Altitude
AMM Air Management Module
ASCB-D Avionics Standard Communication Bus ver.D
ASEL Altitude Preselect
AUD Audio
AUTO Automatic
AUX Auxiliary
AW AgustaWestland
BFO Beat Frequency Oscillator
BIT Built In Test
CAPTS Captions
CAT Category
CKPT Cockpit
CMS Central Maintenance System
CSL Console
CVR Cockpit Voice Recorder
DCL Deceleration
DET Detector
DETR Detector
DG Directional Gyro
DGR Degraded
DME Distance Measuring Equipment
DMG Digital Map Generator
39-A-00-00-03-00A-005A-T 2010-05-31 Page: 3
DR Dead Reckoning
ECL Engine Control Lever
ECP Engine Control Panel
ECS Environmental Control System
ECU Engine Control Unit
EDS Electronic Display System
EEC Electronic Engine Control
EICAS Engine Instruments and Crew Alerting System
ELEC Electric / Electrical
ENBL Enable / Enabled
EPGDS Electrical Power Generation And Distribution System
EPU Estimated Position Uncertainty
ESS Essential
ETE Estimated Time En-route
39-A-00-00-03-00A-005A-T 2010-05-31 Page: 4
FCP Fuel Control Panel
FCU Fuel Computer Unit
FDR Flight Data Recorder
FL Flight Level; Fuel
FLT Flight
FMM Fuel Management Module
FMS Flight Management System
FMV Fuel Management Valve
FOD Foreign Object Damage
FOG Fiber Optic Gyro
FOM Figure of Merit
GSE Ground Support Equipment
HF High Frequency
HOV Hover
HPA hecto Pascal (hPa)
HPS Hydraulic Power Supply
HPU Hydraulic Power Unit
HSI Horizontal Situation Indicator
HVR Hover
IFR Instrument Flight Rules
KPH Kilograms per Hour
LH Left Hand
LIM Limiter / Limiting
LLS Lightning Sensor System
MAG Magnetic
MAN Manual
MCL Master Caution Light
MDA Minimum Descent Altitude
MMH Maintenance Man Hour
MR Main Rotor
MSG Message
MTBF Mean Time Between Failures
MTBO Mean Time Between Overhaul
MTBR Mean Time Between Removal
MTTR Maintenance Time to Replace
MWF Monitor Warning Function
MWL Master Warning Light
MWS Monitor Warning System
NAV Navigation
Nf/Npt Engine free turbine speed
Ng Engine gas generator Turbine/Compressor Speed
Ng or NG Engine gas generator speed
NIC Network Interface Controller
NIM Network Interface Module
NLG Nose Landing Gear
N-S Non Essential
OS Over Station
PAX Passengers
P/R Partial Retraction
PWR Power
39-A-00-00-03-00A-005A-T 2010-05-31 Page: 9
RAM Random Access Memory; Reliability; Availablility and Maintainability
RB Rotor Brake
RCB Radio Control Bus
RCP Reversion Control Panel
SEAT BLT Seat Belt
STBY Stand-By
TBD To Be Defined
TBO Time Between Overhaul
TCPS Temperature Compensated Pressure Switch
TCV Temperature Control Valve
TOD Top Of Descent
TOP Take Off Power
TSO Time Since Overhaul
UV Ultra-Violet
VIP Very Important Person
VNE Never Exceed speed
VPATH Vertical Flight Path
V REF Reference Speed
PMC-39-A0126-AV001-00
00 - HELICOPTER - GENERAL 00 List of effective data modules 39-A-00-00-03-00A-002A-T 00 00
Highlights 39-A-00-00-03-00A-003A-T 00 00
AW Training Academy Italy “A. Marchetti” 3E-A-00-00-00-00A-018A-T 00 00
Helicopter - General 39-A-00-00-00-00A-047A-T 00 00
Cockpit layout 39-A-00-03-00-00A-047A-T 00 03
Conversion tables 39-A-00-12-00-00A-047A-T 00 12
Helicopter safety for maintenance 39-A-00-20-00-00A-047A-T 00 20
Technical publications 39-A-00-40-00-00A-047A-T 00 40
Maintenance publication 39-A-00-41-00-00A-047A-T 00 41
04 - WORTHINESS (FIT FOR PURPOSE) LIMITATIONS 04 Worthiness (fit for purpose) limitations 39-A-04-00-00-00A-047A-T 04 00
05 - SCHEDULED/UNSCHEDULED MAINTENANCE 05 Scheduled/unscheduled maintenance 39-A-05-00-00-00A-047A-T 05 00
06 - DIMENSIONS AND AREAS 06 Principal dimensions 39-A-06-10-00-00A-047A-T 06 10
39-A-00-00-03-00A-009A-T 2010-01-01 Page: 1
DATA MODULE TITLE DATA MODULE CODE CHAPTER SECTION Reference lines 39-A-06-20-00-00A-047A-T 06 20
Access provisions 39-A-06-40-00-00A-047A-T 06 40
07 - LIFTING, SHORING, RECOVERING AND TRANSPORTING 07 Jacking 39-A-07-10-00-00A-047A-T 07 10
Slinging 39-A-07-30-00-00A-047A-T 07 30
Weighing 39-A-08-30-00-00A-047A-T 08 30
09 - HANDLING AND TAXIING 09 Handling 39-A-09-10-00-00A-047A-T 09 10
10 - PARKING, MOORING, STORING AND RETURN TO SERVICE 10 Parking 39-A-10-10-00-00A-047A-T 10 10
12 - SERVICING 12 Servicing 39-A-12-00-00-00A-047A-T 12 00
Replenishing and depleting 39-A-12-10-00-00A-047A-T 12 10
Support equipment connect / disconnect 39-A-12-40-00-00A-047A-T 12 40
18 - VIBRATION AND NOISE ANALYSIS AND ATTENUATION 18 Vibration analysis 39-A-18-10-00-00A-047A-T 18 10
39-A-00-00-03-00A-009A-T 2010-01-01 Page: 2
21 - ENVIRONMENT CONTROL 21 Environmental control 39-A-21-00-00-00A-047A-T 21 00
Distribution 39-A-21-20-00-00A-047A-T 21 20
Heating 39-A-21-40-00-00A-047A-T 21 40
22 - AUTO FLIGHT 22 Auto flight 39-A-22-00-00-00A-047A-T 22 00
23 - COMMUNICATIONS 23 Communications 39-A-23-00-00-00A-047A-T 23 00
Speech communication 39-A-23-10-00-00A-047A-T 23 10
Audio integrating and voice command systems 39-A-23-50-00-00A-047A-T 23 50
Integrated automatic tuning 39-A-23-80-00-00A-047A-T 23 80
24 - ELECTRICAL POWER 24 Electrical power 39-A-24-00-00-00A-047A-T 24 00
DC main generation 39-A-24-30-00-00A-047A-T 24 30
External power 39-A-24-40-00-00A-047A-T 24 40
DC electrical load distribution 39-A-24-60-00-00A-047A-T 24 60
25 - EQUIPMENT/FURNISHING 25 Equipment/furnishings 39-A-25-00-00-00A-047A-T 25 00
Passenger/operating crew compartment 39-A-25-20-00-00A-047A-T 25 20
39-A-00-00-03-00A-009A-T 2010-01-01 Page: 3
Rescue hoist 39-A-25-91-00-00A-047A-T 25 91
Cargo hook 39-A-25-92-00-00A-047A-T 25 92
26 - FIRE PROTECTION 26 Fire protection 39-A-26-00-00-00A-047A-T 26 00
28 - FUEL 28 Storage 39-A-28-10-00-00A-047A-T 28 10
Distribution 39-A-28-20-00-00A-047A-T 28 20
Indicating 39-A-28-40-00-00A-047A-T 28 40
Power control module 39-A-29-11-00-00A-047A-T 29 11
Hydraulic power supply 39-A-29-12-00-00A-047A-T 29 12
Tail rotor shut-off valve 39-A-29-13-00-00A-047A-T 29 13
Auxiliary 39-A-29-20-00-00A-047A-T 29 20
30 - ICE AND RAIN PROTECTION 30 Pitot and static 39-A-30-30-00-00A-047A-T 30 30
Windows, windshields, canopies and doors 39-A-30-40-00-00A-047A-T 30 40
31 - INDICATING/RECORDING SYSTEMS 31 Indicating/recording systems 39-A-31-00-00-00A-047A-T 31 00
39-A-00-00-03-00A-009A-T 2010-01-01 Page: 4
PMC-39-A0126-AV001-00
DATA MODULE TITLE DATA MODULE CODE CHAPTER SECTION Instrument and control panels 39-A-31-10-00-00A-047A-T 31 10
Independent instruments 39-A-31-20-00-00A-047A-T 31 20
Recorders 39-A-31-30-00-00A-047A-T 31 30
Central warning system 39-A-31-50-00-00A-047A-T 31 50
Central display systems 39-A-31-60-00-00A-047A-T 31 60
32 - LANDING GEAR 32 Landing gear 39-A-32-00-00-00A-047A-T 32 00
Main gear and doors 39-A-32-10-00-00A-047A-T 32 10
Nose gear and doors 39-A-32-20-00-00A-047A-T 32 20
Extension and retraction 39-A-32-30-00-00A-047A-T 32 30
Wheels and brakes 39-A-32-40-00-00A-047A-T 32 40
Steering 39-A-32-50-00-00A-047A-T 32 50
Passenger compartment 39-A-33-20-00-00A-047A-T 33 20
Cargo and service compartments 39-A-33-30-00-00A-047A-T 33 30
Exterior 39-A-33-40-00-00A-047A-T 33 40
34 - NAVIGATION 34 Navigation 39-A-34-00-00-00A-047A-T 34 00
39-A-00-00-03-00A-009A-T 2010-01-01 Page: 5
PMC-39-A0126-AV001-00
DATA MODULE TITLE DATA MODULE CODE CHAPTER SECTION Flight environment data 39-A-34-10-00-00A-047A-T 34 10
Attitude and direction 39-A-34-20-00-00A-047A-T 34 20
Landing and taxiing aids 39-A-34-30-00-00A-047A-T 34 30
Independent position determining 39-A-34-40-00-00A-047A-T 34 40
Weather radar system 39-A-34-41-00-00A-047A-T 34 41
Global position system 39-A-34-51-00-00A-047A-T 34 51
DME system 39-A-34-52-00-00A-047A-T 34 52
Automatic Direction Finder (ADF) system 39-A-34-53-00-00A-047A-T 34 53
ATC transponder system 39-A-34-54-00-00A-047A-T 34 54
Flight management system 39-A-34-60-00-00A-047A-T 34 60
45 - CENTRAL MAINTENANCE SYSTEM (CMS) 45 Central maintenance system (CMS) 39-A-45-45-00-00A-047A-T 45 45
46 - SYSTEM INTEGRATION AND DISPLAY 46 Systems integration and display 39-A-46-00-00-00A-047A-T 46 00
52 - DOORS 52 Doors 39-A-52-00-00-00A-047A-T 52 00
Door warning 39-A-52-70-00-00A-047A-T 52 70
53 - FUSELAGE 53 Forward sections 39-A-53-10-00-00A-047A-T 53 10
Tail section 39-A-53-40-00-00A-047A-T 53 40
39-A-00-00-03-00A-009A-T 2010-01-01 Page: 6
56 - WINDOWS 56 Windows 39-A-56-00-00-00A-047A-T 56 00
62 - MAIN ROTORS 62 Main rotors 39-A-62-00-00-00A-047A-T 62 00
63 - MAIN ROTOR DRIVES 63 Main rotor drives 39-A-63-00-00-00A-047A-T 63 00
Indicating 39-A-63-40-00-00A-047A-T 63 40
64 - TAIL ROTOR 64 Tail rotor 39-A-64-00-00-00A-047A-T 64 00
65 - TAIL ROTOR DRIVE 65 Tail rotor drive 39-A-65-00-00-00A-047A-T 65 00
67 - ROTORS FLIGHT CONTROL 67 Rotors flight control 39-A-67-00-00-00A-047A-T 67 00
Servo-control system 39-A-67-30-00-00A-047A-T 67 30
71 - POWER PLANT 71 Power plant 39-A-71-00-00-00A-047A-T 71 00
74 - IGNITION 74
PMC-39-A0126-AV001-00
DATA MODULE TITLE DATA MODULE CODE CHAPTER SECTION Electrical power supply 39-A-74-10-00-00A-047A-T 74 10
80 - STARTING 80 Cranking 39-A-80-10-00-00A-047A-T 80 10
39-A-00-00-03-00A-009A-T 2010-01-01 Page: 8
3E-A-00-00-00-00A-018A-T 2010-01-01 Page: 1
3E-A-00-00-00-00A-018A-T 2010-01-01 Page: 15
3E-A-00-00-00-00A-018A-T 2010-01-01 Page: 23
3E-A-00-00-00-00A-018A-T 2010-01-01 Page: 25
End of data module 3E-A-00-00-00-00A-018A-T 2010-01-01 Page: 26
PMC-39-A0126-AV001-00
SECTION 00 - HELICOPTER - GENERAL
GENERAL DESCRIPTION The AW139 is a large twin turbo-shaft engines multi-purpose helicopter designed for the following:
PRIMARY ROLES
SECONDARY ROLES
• air taxi
• off-shore
• fire-fighting
• paramilitary
NOTE A AW139 abd AB139 are two names for the same product. They identify two batches of aircraft manufactured in conformity with a unique Type Certificate Data Sheet. AB139: up to s/n 31054 AW139: from s/n 31055 onward
JAR CERTIFICATION The AW139 is certificated by European Aviation Safety Agency (EASA) in accordance with JAR 29 for Large Rotorcraft Categor A (Appendix B - IFR, and Appendix C - Icing conditions) and Category B Certification includes:
• Taxiing from prepared surfaces
• Overwater operations (no amphibian operations)
• Carriage of external loads
• Hot and high operations.
• IFR single pilot operations
• VFR night single pilot operations Installation of dedicate optional kits may be necessary to perform some of the certified operations.
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PMC-39-A0126-AV001-00
STRUCTURE The cockpit, the front part of the fuselage, include the pilot (RH) and co-pilot or passenger (LH) side-by-side seating positions, adjustable crashworthy seats, the instrument panel and a forward opening hinged door on each side with emergency release. The middle part of the fuselage is composed by cabin and rear fuselage. The cabin include the passenger seating area, a sliding door on each side, the fuel tanks housing, the main gearbox and engine attachments, main landing gear attachments and housing. The rear part of the fuselage includes the baggage bay. Cabin size is adequate for the following internal arrangements:
• Normal density civil transport 2 +11 passengers (all looking forward) in crashworthy seats.
• Normal density civil transport 2 + 12 passengers
• High density civil transport 2 +15 passengers.
• Civil EMS 6 litter patients, 2 non-litter patients and 2 medical attendants. The tail boom, the final part of the fuselage, shall include the stabilizer, the fin, the intermediate and tail gearbox attachments. The parts mentioned above are considered primary structure. The remaining parts of the fuselage, are considered secondary structure and include:
• pilot doors
• passenger doors
• inspection doors
• Service Ceiling (Hp or Hd) .................................................. 20000 ft
• Hovering Ceiling (IGE & OGE, @ MCP, AEO).......... Up to 18000 ft
• Takeoff & Landing Ceiling (Hp or Hd)........................ Up to 14000 ft
• Operating Temperature.................................... -40°C to ISA + 35°C
WEIGHT LIMITS
• Increased Gross Weight (Kit P/N 4G0000F00111 – see RFM Suppl-50).................................................................... 6800 Kg
• Minimum flight/rotor-turning gross weight........................... 4400 Kg
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EMERGENCY EXITS Four emergency exits per side are provided by jettison on the following windows:
- Cockpit Door Window (1 per side) - Cabin Window (1 per side, on the fixed frame) - Cabin Door Windows (2 per side)
A red strap in the internal bottom side of each emergency exit window permits removal of the rubber cord that holds the window transparent panel in place. The emergency exit is made free by pushing the transparent panel out acting on its bottom left corners.
OPTIONAL EQUIPMENT A wide selection of optional kits can be installed on the AW139 helicopter. Some of the available optional kits are listed below:
• Rotor Brake
• Engine Air Particle Separator (EAPS)
• HF Radio
• V/UHF Radio
• Enhanced Ground Proximity Warning System (EGPWS)
• Emergency Floats and Liferafts (Ditching configuration)
• Deployable ELT
• Second Radar Altimeter
• Hinged passenger doors
• Digital Map System (Sky Force Observer Mark II, EURONAV IV, EURONAV V)
• Nightsun Searchlight (SX-16, SX-5, II XP)
• FLIR (SEA FLIR II, Star Safire III, Ultraforce 350, TALON)
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POWERPLANT The power plant shall comprise: engines and related installation, fire detection and extinguishing system.
Engines The helicopter is powered by two PT6C-67C turboshaft engines. Each engine is installed in a separated fireproof area above the cabin roof and supplies power to the drive system by means of a rotating shaft. The engines are connected to the airframe by means of two attachment points on the engine body and to the main gearbox by means of a tube and a gimbal joint. Air is supplied to the engine via individual, side facing air inlets. The engines are started by a DC starter-generator. Engine control is achieved via a control panel located in the cockpit and manual back-up of the engine control via pushpull cables. The engines are provided with torque sensing and matching.
Fire Detection / Extinguishing The fire detection system consists of a continuous wire detector installed in the powerplant fire zones, routed in a way that allows coverage of all critical areas. The fire extinguishing system consists of directional flow valves which allow discharging the contents of one bottle while sealing the connection to the other bottle and the subsequent discharge of the second bottle in the same bay if required.
DRIVE SYSTEM The drive system consists of the Main Rotor Drive System and the Tail Rotor Drive System.
Main Rotor Drive System The Main Rotor Drive System mainly consists of the Main Gearbox (MGB) that is mounted on the roof of the cabin by means of four struts and an anti-torque device. The MGB has three stages of reduction and includes a duplicated oil lubrication system. It provides the attachment points for the rotor brake coaxial with the tail rotor drive output. The MGB drives three hydraulic pumps and other accessories.
Tail Rotor Drive System The tail rotor drive system consists of three drive shafts driven by the MGB, the Intermediate Gearbox IGB and the Tail Gearbox TGB oil splash lubricated. The main rotor is a five blades, fully articulated rotor. The tail rotor is a four blades, fully articulated rotor.
ROTORS The rotor system consists a main rotor (MR) and tail rotor (TR). The main rotor is a five blades, fully articulated rotor. The tail rotor is a four blades, fully articulated rotor.
HYDRAULIC POWER The hydraulic power system consists of two independent circuits that supply hydraulic fluid at a nominal working pressure of 3000 psi (207 bar). Both hydraulic power system circuits supply the hydraulic power necessary to operate the flight control servo-actuators and the landing gear.
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For ground test and malfunction condition, a shut-off valve allows to shut-off the flight controls circuits. For safety reason, another shut-off valve allows to shut the landing gear circuits off, increasing the survivability of the flight control functions. Hydraulic power to the landing gear actuators is used to extend and retract the main and the nose landing gears. The main and nose landing gear are maintained in UP position by the hydraulic pressure (no mechanical uplocks are provided). The extended DOWN position is maintained with a mechanical locks in the main and nose gear actuators.
LANDING…