Aw109sp Rfm

ROTORCRAFT FLIGHT MANUAL

Agusta Publication Code 502700600

AW109SP

AW109SP RFMDocument N 109G0040A018

ROTORCRAFTFLIGHT MANUAL

AW109SP

Document N109G0040A018

Approved by EASA

Copy assigned to rotorcraft: S/N . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Registration Marks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ISSUE B: 11 DECEMBER 2009REVISION 4: 11 FEBRUARY 2011

THIS DOCUMENT MUST BE CARRIED IN AIRCRAFT AT ALL TIMES

Issued by Agusta S.p.A.

This publication contains information proprietary to Agusta S.p.A.Reproduction and/or resale of the information or illustrations containedherein is not permitted without the written approval of CUSTOMERSUPPORT & SERVICES - ITALY - Product Support Engineering Dept.Additional copies of this publication and/or change service may beobtained from:

AGUSTA S.p.A.CUSTOMER SUPPORT & SERVICES - ITALY

Product Support Engineering DepartmentVia Del Gregge, 100

21015 Lonate Pozzolo (VA) - ItaliaTel.: 0039-0331664845 - Fax.: 0039-0331664684

e-mail: [email protected]

AW109SP RFM List of Document N109G0040A018 Revisions

EASA Approved 11-12-09 A-1

LIST OF REVISIONS

REVISIONNo. SUBJECT APPROVAL

Issue A EASA Approval withType Certificate DataSheet (TCDS) R.005dated 25 May 2009

Issue B EASA Approvals N10028242, 10028244,10028246, 10028248dated 11 December 2009

1 Revised Title page, A-1, B-1 and 3-147.

EASA ApprovalN 10031062dated 26 July 2010

2 Revised Title page, A-1, B-1, B-2,1-25, 2-iv, 2-64, 2-66, 2-67 thru2-70, 3-iv thru 3-viii, 3-74 thru 3-76,3-103 thru 3-108 and 3-169 thru 3-171.Added pages 2-71 and 2-72.

EASA ApprovalsN10030940,10031063dated 26 July 2010

3 Revised Title page, A-1, B-1, B-2,1-iii, 1-25, 1-26, 2-20 thru 2-25 and2-30.

EASA ApprovalN 10032356dated 8 November 2010

4 Revised Title page, A-1, B-1, B-2,1-25, 1-30, 2-20, 2-30, 3-167, 3-168.Added pages B-3 and B-4.

EASA ApprovalN 10033829dated 11 February 2011

Revised pages 1-31, 1-37, 1-39, 1-41,4-24 and 4-25.

Approved under theAuthority of DOAN EASA 21J.005

List of AW109SP RFMRevisions Document N109G0040A018

A-2 11-12-09 EASA Approved

This Page Is Intentionally Left Blank

AW109SP RFM List of Document N109G0040A018 Effective Pages

11-12-09 B-1

LIST OF EFFECTIVE PAGES

NOTE: Revised text is indicated by a black vertical line in the outermargin of the page and the approval revision number is printedin the lower margin. Page Revision N

Title page 4A-1 4A-2 0B-1 thru B-4 4i thru xiv 0Part I - EASA APPROVED1-i and 1-ii 01-iii 31-iv thru 1-viii 01-1 thru 1-24 01-25 41-26 31-27 thru 1-29 01-30 and 1-31 41-32 thru 1-36 01-37 41-38 01-39 41-40 01-41 41-42 thru 1-54 02-i thru 2-iii 02-iv 22-1 thru 2-19 02-20 42-21 thru 2-25 32-26 thru 2-29 02-30 4

2-31 thru 2-63 02-64 22-65 02-66 thru 2-72 23-i thru 3-iii 03-iv thru 3-viii 23-ix and 3-x 03-1 thru 3-73 03-74 thru 3-76 23-77 thru 3-102 03-103 thru 3-108 23-109 thru 3-146 03-147 13-148 thru 3-166 03-167 and 3-168 43-169 thru 3-171 23-172 thru 3-186 04-i thru 4-iv 04-1 thru 4-23 04-24 and 4-25 44-26 thru 4-56 05-i and 5-ii 05-1 and 5-2 0

Page Revision N

List of AW109SP RFMEffective Pages Document N109G0040A018

B-2 11-12-09

List of Effective Pages (Cont.d)

Part II - MANUFACTURERS DATAC-1 4C-2 06-i and 6-ii 06-1 thru 6-32 07-i thru 7-xviii 47-1 thru 7-30 07-31 47-32 07-33 thru 7-38 47-39 thru 7-54 07-55 47-56 thru 7-78 07-78A thru 7-78G 37-78H thru 7-78P 47-79 thru 7-92 07-93 47-94 thru 7-124 07-124A thru 7-124D 47-125 thru 7-158 07-159 27-160 thru 7-162 07-163, 7-164, 7-164Aand 7-164B 27-165 thru 7-173 07-174 27-175 thru 7-190 07-190A and 7-190B 27-191 thru 7-202 07-202A thru 7-202D 27-203 37-204 thru 7-218 0

Page Revision N7-219 thru 7-221 37-222 thru 7-227 07-228 thru 7-234 and7-234A thru 7-234C 27-234D thru 7-234H 47-235 thru 7-238 07-239 37-240 thru 7-244 27-245 thru 7-254 07-255 27-256 and 7-257 07-258 27-259 thru 7-283 07-283A thru 7-283J 27-284 47-285 and 7-286 07-287 47-288 thru 7-293 07-294 and 7-295 47-296 07-297 47-298 thru 7-300 07-301 47-302 thru 7-307 07-308 and 7-309 47-310 thru 7-313 07-314 47-315 07-316 47-317 thru 7-319 07-320 27-321 and 7-322 0

Page Revision N

AW109SP RFM List of Document N109G0040A018 Effective Pages

11-12-09 B-3

List of Effective Pages (Cont.d)

7-323 thru 7-331 07-332 thru 7-334 27-335 thru 7-337 07-338 thru 7-340 37-340A and 7-340B 27-341 thru 7-352 07-353 27-354 thru 7-361 07-362 27-363 and 7-364 07-364A and 7-364B 27-365 thru 7-400 07-400A thru 7-400F 47-401 thru 7-420 07-421 27-422 and 7-423 07-424 thru 7-428 28-i and 8-ii 08-1 thru 8-14 09-i thru 9-iv 09-1 thru 9-70 0

Page Revision N Page Revision N

List of AW109SP RFMEffective Pages Document N109G0040A018

B-4 11-12-09

This Page Intentionally Left Blank

AW109SP RFM Table of ContentsDocument N109G0040A018

11-12-09 Page i

TABLE OF CONTENTS

Page

LIST OF REVISIONS...................................................................... A-1

LIST OF EFFECTIVE PAGES ........................................................ B-1

TABLE OF CONTENTS ....................................................................... I

INTRODUCTION ................................................................................ II

PART I

Section

LIMITATIONS...................................................................................... 1

NORMAL PROCEDURES .................................................................. 2

EMERGENCY AND MALFUNCTION PROCEDURES....................... 3

PERFORMANCE DATA..................................................................... 4

OPTIONAL EQUIPMENT SUPPLEMENTS....................................... 5

PART II - MANUFACTURERS DATA

Page

LIST OF REVISIONS...................................................................... C-1

Section

WEIGHT AND BALANCE ................................................................... 6

SYSTEMS DESCRIPTION ................................................................ 7

HANDLING, SERVICING AND MAINTENANCE ................................ 8

SUPPLEMENTAL PERFORMANCE INFORMATION......................... 9

Table of Contents AW109SP RFMDocument N109G0040A018

Page ii 11-12-09


AW109SP RFM IntroductionDocument N109G0040A018

11-12-09 Page iii

INTRODUCTION

GENERALIt is responsibility of the flight crew to be familiar with the contents ofthis manual.

REVISIONS (REISSUES)This manual is subject to revisions (reissues) which will be automati-cally distributed to all holders of the manual. It is the responsibility ofthe operator to assure that the revisions (reissues) are incorporatedinto the manual upon receipt.At the beginning of the manual there is the List of Revisions tablethat shows all pages of the manual which have been revised as wellas number and approval reference of each revision.

REVISION SYMBOLRevised text is indicated by a black vertical line on the outer margin ofthe page, adjacent to the affected text and the revision is printed in thelower inner margin. The revision symbol identifies the addition of newinformation, a change of procedure, the correction of an error, or arewording of the previous information.

TEMPORARY REVISIONSTemporary Revisions are issued when immediate data is to beincluded in the manual. The Temporary Revision data can add to orcancel the initial data in the manual. They are numbered progressivelyfor each section of the manual. Temporary Revision pages are notwritten in the List of Effective Pages. A complete list of active andinactive Temporary Revision are written in the List of TemporaryRevisions page.

Introduction AW109SP RFMDocument N109G0040A018

Page iv 11-12-09

TERMINOLOGY

WARNINGS, CAUTIONS AND NOTES

WARNING

An operating procedure, practice, etc.,which, if not correctly followed, could resultin personal injury or loss of life.

CAUTION

An operating procedure, practice, etc.,which, if not strictly observed, could result indamage to, or destruction of, equipment.

NoteAn operating procedure, condition, etc.,which is essential to highlight.

USE OF PROCEDURAL WORDSThe concept of procedural word usage and intended meaning whichhas been adhered to in preparing this RFM is as follows:Shall or Must have been used only when application of a proce-dure is mandatory.Should has been used only when application of a procedure is rec-ommended.May has been used only when application of a procedure is optional.Will has been used only to indicate futurity, never to indicate a man-datory procedure.Condition has been used to determine if the item under examinationpresents external damage which could jeopardize its safe operation.Secured has been used to determine if the item under examinationis correctly locked; mainly referred to doors and disconnectable items.


11-12-09 Page v

Security has been used to determine if the item under examinationis correctly positioned and installed.Fly Attentive has been used when the pilot needs to maintain closecontrol of the flight path using hands-on when required.Fly Manually has been used when the pilot needs to directly controlthe flight path using hands-on.

ABBREVIATIONThe use of capitol letters in the text, apart from normal grammaticalusage indicates the actual wording or marking of indicators, controlsor control positions on the helicopters.Abbreviations and acronyms used throughout this RFM are defined asfollows:

a.c : Alternating current

ADC : Air Data Computer

ADU : Air Data Unit

ADF : Automatic Direction Finder

ADI : Attitude Data Indicator

ADL : Airborne Data Loader

ADLCP : Airborne Data Loader Control Panel

ADS : Air Data System

AEO : All Engines Operating

A/F : Airframe

AFCS : Automatic Flight Control System

AFDS : Automatic Flight Director System

AGL : Above Ground Level

AHRS : Attitude and Heading Reference System

ALS : Above Landing Surface

ALT : Baro - ALTitude mode


Page vi 11-12-09

AM : Amplitude Modulation

ANP : Actual Navigation Performance

AP : Automatic Pilot

APCP : AutoPilot Control Panel

API : Actuator Position Indicator

APD : Actuator Position Display

ATH : Approach To Hover

ATTD : ATTituDe

AWG : Aural Warning Generator

BC : Back Course mode

BCD : Binary Coded Data

BIT : Built In Test

BRG : BeaRinG

BRT : BRighTness

CAS : Calibrated AirSpeed

CCW : CounterClockWise

CDS : Cockpit Display System

CG : Center of Gravity

CHS : Core Helivionics System

CLB : CLimB mode

CLR : CLeaR

CMS : CoMmunication System

CMU : Communication Management Unit

COLL : COLLective mode

COM : COMmunication

CPL : CouPLing

CRS : CouRSe


11-12-09 Page vii

CS : Certification Specifications

CST : ContraST

CVDR : Cockpit Voice Data Recorder

CVR : Cockpit Voice Recorder

CW : ClockWise

d.c : Direct current

DF : Direction Finder

DH : Decision Height

DIS : DIStance

DME : Distance Measuring Equipment

DMG : Digital Map Generator

DP IFR : Dual Pilot IFR

DR : Dead Reckoning mode

DTK : Desired TracK

DTM : Data Transfer Module

DTO : Direct TO

DU : Display Unit

DVS : Doppler Velocity System

EADI : Electronic Attitude Direction Indicator

ECU : Engine Control Unit

EDU : Electronic Display Unit

EECU : Engine Electronic Control Unit

EEPROM : Electrically Erasable Programmable Read Only Memory

ELEC : ELECtrical

ELT : Electronic Locator Transmitter


Page viii 11-12-09

EMM : Engine Maintenance Manual

ENT : ENTer

EOP : Engine Oil Pressure

EOT : Engine Oil Temperature

ESIS : Electronic Standby Instrument System

ETA : Estimated Time of Arrival

F() : Function of

F-1() : Inverse Function of

FADEC : Full Authority Digital Engine Control

FAF : Final Approach Fix

FAR : Federal Airworthiness Regulation

FCC : Flight Control Computer

FCU : Fuel Computer Unit

FD : Flight Director

FDCP : Flight Director and Control Panel

FDE : Flight Deck Effect

FDR : Flight Data Recorder

FLI : First Limit Indicator

FLIR : Forward Looking Infra-Red

FM : Frequency Modulation

FMEA : Failure Modes and Effects Analysis

FMS : Flight Management System

FP : Fuel Pressure

FPLN : Flight PLaN

FPS : Flight Planning System

FTR : Force Trim Release


11-12-09 Page ix

G/S : Glide Slope

Hd : Density altitude

HDG : HeaDinG

HDG SEL : HeaDinG SELect

HF : High Frequency

HOV : HOVer

Hp : Pressure Altitude

HTAWS : Helicopter Terrain Awareness and Warning System

HUMS : Health and Usage Monitoring System

HYD : HYDraulic

IAS : Indicated AirSpeed

ICS : InterCommunication System

IGE : In Ground Effect

IFR : Instrument Flight Rules

IGRF : International Geomagnetic Reference Field

ILS : Instrument Landing System

IMC : Instrument Meteorological Condition

INS : Inertial Navigation System

ISA : International Standard Atmosphere

ITT : Inter-Turbine Temperature

IVSI : Instantaneous Vertical Speed Indicator

JAR : Joint Aviation Regulations

KCAS : Knots Calibrated AirSpeed


Page x 11-12-09

LCD : Liquid Crystal Display

LCF : Low Cycle Fatigue

LH : Left Hand

LNAV : Lateral NAVigation

LOC : LOCalizer

LX : Stormscope / Lightning detector

MAINT : MAINTenance

MCDU : Multifunction Control and Display Unit

MAP : Missing Approach Point

MCL : Master Caution Light

MCP : Maximum Continuous Power

MDA : Minimum Descent Altitude

MER : Modular Electronic Rack

MFD : Multi Function Display

MFR : ManuFactureR

MGB : Main Gear Box

MISS : MISSion

MON : MONitoring

MSG : MeSsaGe

MSM : Mission System Management module

MTR : MoniToR

MWL : Master Warning Light

NAVM : NAVigation Module

ND : Navigation Display

NF : Free turbine speed (= N2)


11-12-09 Page xi

NG : Gas generator speed (= N1)

NM : Nautical Miles

NR : Rotor speed

NVM : Non Volatile Memory

NVG : Night Vision Goggles

OAT : Outside Air Temperature

OEI : One Engine Inoperative

OGE : Out of Ground Effect

OTS : Observation Targeting System

PAM : Power Assurance Margin

PAX : Passenger(s)

PCP : PFD Control Panel

PERF : PERFormance

PFD : Primary Flight Display

PFT : Pre Flight Test

PLA : Power Lever Angle (alias engine power lever)

PMS : Power Management Switch (alias engine mode switch)

PROG : PROGress

PSSA : Preliminary System Safety Analysis

QTY : QuantiTY

R ALT : Radar Altimeter mode

R.A : Radar Altimeter

RAM : Random Access Memory

RCP : Reconfiguration Control Panel

REC : RECording


Page xii 11-12-09

RF : Radio Frequency

RFI : Radio Frequency Indicator

RFM : Rotorcraft Flight Manual

RH : Right Hand

RNAV : Radio NAVigation

RNG : RaNGe

RNP : Required Navigation Performance

ROC : Rate Of Climb

RPM : Revolutions Per Minute

SAS : Stabilization Augmentation System

SCP : System Control Panel

SCRL : SCRolL

SID : Standard International Departure

SOE : Set Of Sensors

SPIFR : Single Pilot IFR

STAR : STandard ARrival

STD : STandarD

SYS : SYStem

TAS : True AirSpeed

TAWS : Terrain Awareness and Warning System

TCA : Track Change Alert

TKE : TracK angle Error

TOC : Top Of Climb

TOP : Take Off Power

TQ : TorQue

TRQ : ToRQue


11-12-09 Page xiii

TNG : TraiNinG

TST : TeST

TTD : Time To the end of Destination

TTG : Time To Go to the way point

UHF : Ultra High Frequency

UTC : Coordinated Universal Time

UTM : Universal Transverse Mercator

VFR : Visual Flight Rules

VHF : Very High Frequency

VID : Video

VLE : Maximum landing gear extended speed

VLO : Maximum landing gear operating speed

VMM : Vehicle Monitoring Module

VMS : Vehicle Monitoring Systems

VNE : Velocity Never Exceed

VNEI : VNE for IFR operations

VMINI : Minimum airspeed for flight under Instrument Flight Rules

VOR : VHF Omni-directional Relative bearing

VS : Vertical Speed Vy : Best Rates of Climb Speed WCA : Warning Caution Advisory WOW : Weight On Wheels WX : Weather Radar WxR : Weather Radar XTK : Cross TracK Distance


Page xiv 11-12-09


AW109SP RFM Part IDocument N109G0040A018

PART I - EASA APPROVED

AW109SP RFM Section 1Document N109G0040A018 Table of Contents

EASA Approved 11-12-09 Page 1-i

SECTION 1

LIMITATIONS

TABLE OF CONTENTSPage

GENERAL ....................................................................................... 1-1

BASIS OF CERTIFICATION ........................................................... 1-1

TYPE OF OPERATIONS ................................................................. 1-1

MINIMUM FLIGHT CREW............................................................... 1-1

NUMBER OF SEATS ...................................................................... 1-1

WEIGHT AND CENTER OF GRAVITY LIMITATIONS ................... 1-2WEIGHT...................................................................................... 1-2CENTER OF GRAVITY .............................................................. 1-2

AIRSPEED LIMITATIONS............................................................... 1-5

GROUND SPEED LIMITATIONS.................................................... 1-5ON CONCRETE, EVEN SURFACES......................................... 1-5ON UNPREPARED OR UNEVEN SURFACES.......................... 1-5

WIND SPEED LIMITATIONS FOR ROTOR STARTINGAND STOPPING ............................................................................. 1-6

ALTITUDE LIMITATIONS ............................................................... 1-6

AMBIENT AIR TEMPERATURE LIMITATIONS ............................. 1-6

Section 1 AW109SP RFMTable of Contents Document N109G0040A018

Page 1-ii 11-12-09 EASA Approved

Page

SLOPE LIMITATIONS .................................................................... 1-6

DOORS OPENED OR REMOVED................................................ 1-10

POWER PLANT AND TRANSMISSION LIMITATIONS................1-11GENERAL ................................................................................ 1-11

POWER PLANT LIMITATIONS .....................................................1-11GAS GENERATOR SPEED (N1) ............................................. 1-11POWER TURBINE SPEED (N2) .............................................. 1-12TURBINE OUTLET TEMPERATURE (TOT)............................ 1-13ENGINE OIL PRESSURE ........................................................ 1-14ENGINE OIL TEMPERATURE................................................. 1-14ENGINE STARTER LIMITATIONS .......................................... 1-14

TRANSMISSION LIMITATIONS ................................................... 1-15TORQUE (TRQ) ....................................................................... 1-15TRANSMISSION OIL PRESSURE .......................................... 1-15TRANSMISSION OIL TEMPERATURE ................................... 1-15

ROTOR LIMITATIONS (NR) ......................................................... 1-16POWER-ON (AEO) .................................................................. 1-16POWER-ON (OEI).................................................................... 1-16POWER-OFF ........................................................................... 1-16

FUEL SYSTEM LIMITATIONS ..................................................... 1-17FUEL PRESSURE ................................................................... 1-17FUEL QUANTITY ..................................................................... 1-17TOTAL UNUSABLE FUEL ....................................................... 1-17FUEL TYPES ........................................................................... 1-18EMERGENCY FUELS.............................................................. 1-19

LUBRICANTS ............................................................................... 1-20AUTHORIZED ENGINE OILS .................................................. 1-20AUTHORIZED TRANSMISSION OIL....................................... 1-21


EASA Approved 11-12-09 Page 1-iiiRev. 3

Page

HYDRAULIC SYSTEM LIMITATIONS .......................................... 1-22MAIN SYSTEM FLUID PRESSURE......................................... 1-22NORMAL UTILITY SYSTEM - FLUID PRESSURE.................. 1-22EMERGENCY UTILITY SYSTEM - FLUID PRESSURE .......... 1-22APPROVED FLUIDS ................................................................ 1-22

GENERATOR LOAD LIMITATIONS............................................. 1-23

NAVIGATION LIMITATIONS......................................................... 1-23MAGNETIC COMPASS............................................................ 1-23

FLIGHT MANAGEMENT SYSTEM LIMITATIONS ....................... 1-24EN ROUTE AND TERMINAL.................................................... 1-24PRECISION APPROACH......................................................... 1-24NON PRECISION APPROACH (NPA) ..................................... 1-25

EFIS LIMITATIONS........................................................................ 1-25

HTAWS LIMITATIONS................................................................... 1-25

AUTOMATIC FLIGHT CONTROL SYSTEM LIMITATIONS......... 1-26DUAL AP OPERATION ............................................................ 1-26SINGLE AP OPERATION......................................................... 1-26

FLIGHT DIRECTOR LIMITATIONS .............................................. 1-27UPPER AND FLIGHT DIRECTOR MODES ENGAGEMENT LIMITS AND MINIMUM USE HEIGHT (MUH) .......................... 1-27GENERAL LIMITATIONS ......................................................... 1-29ILS APPROACH ....................................................................... 1-29GPS APPROACH ..................................................................... 1-29UPPER MODES ....................................................................... 1-30

ROTOR BRAKE LIMITATION....................................................... 1-31


Page 1-iv 11-12-09 EASA Approved

Page

MISCELLANEOUS LIMITATIONS................................................ 1-31FUEL MANAGEMENT SYSTEM.............................................. 1-31PASSENGERS CABIN LIMITATIONS ..................................... 1-31BAGGAGE COMPARTMENT LIMITATIONS........................... 1-31

PLACARDS ................................................................................. 1-32

INSTRUMENT MARKINGS .......................................................... 1-35


EASA Approved 11-12-09 Page 1-v

LIST OF FIGURES

Page

Figure 1-1 Weight, Longitudinal and Lateral CG Envelope (metric units)............................................................ 1-3

Figure 1-2 Weight, Longitudinal and Lateral CG Envelope(imperial units) ......................................................... 1-4

Figure 1-3 Airspeed Limitation VNE (Power-ON) ...................... 1-7

Figure 1-4 Pressure altitude / OAT Envelope ........................... 1-9

Figure 1-5 Airspeed (Vne) Placard ......................................... 1-32

Figure 1-6 Cockpit Placards.................................................... 1-33

Figure 1-7 Placards in Baggage Compartment....................... 1-34

Figure 1-8 EFIS - Indicated Airspeed (IAS) ............................ 1-35

Figure 1-9 EDU1 - Gas Generator Speed (AEO).................... 1-36

Figure 1-10 EDU1 - Gas Generator Speed (OEI) ..................... 1-37

Figure 1-11 EDU1 - Turbine Outlet Temperature (AEO) .......... 1-38

Figure 1-12 EDU 1 - Turbine Outlet Temperature (OEI)........... 1-39

Figure 1-13 EDU1 - Torque (AEO) ........................................... 1-40

Figure 1-14 EDU 1 - Torque (OEI)............................................ 1-41

Figure 1-15 EDU1 - Rotor / Power Turbine Speed (AEO) ........ 1-42

Figure 1-16 EDU1 - Rotor / Power Turbine Speed (OEI).......... 1-43

Figure 1-17 EDU1 - Rotor Speed (Power-OFF)........................ 1-44

Figure 1-18 EDU2 (MAIN) - Engine Oil Pressure ..................... 1-45

Figure 1-19 EDU2 (MAIN) - Engine Oil Temperature ............... 1-46

Figure 1-20 EDU2 (MAIN) - Transmission Oil Pressure ........... 1-47

Figure 1-21 EDU2 (MAIN) - Transmission Oil Temperature ..... 1-48

Figure 1-22 EDU2 (MAIN / AUXILIARY) - Main Hydraulic System Pressure ................................................... 1-49


Page 1-vi 11-12-09 EASA Approved

Page

Figure 1-23 EDU2 (MAIN) - Fuel Pressure............................... 1-50

Figure 1-24 EDU2 (AUXILIARY) - Generator Load.................. 1-51

Figure 1-25 EDU2 (AUXILIARY) - Utility Hydraulic System Pressure (Normal)................................................. 1-52

Figure 1-26 EDU2 (AUXILIARY) - Utility Hydraulic System Pressure (Emergency) .......................................... 1-53


EASA Approved 11-12-09 Page 1-vii

LIST OF TABLES

Page

Table 1-1 Authorized Fuels....................................................... 1-18

Table 1-2 Emergency Fuels...................................................... 1-19

Table 1-3 Authorized Lubricating Oils, Type II (5 Centistokes) ......................................................... 1-20

Table 1-4 Authorized Lubricating Oils....................................... 1-21


Page 1-viii 11-12-09 EASA Approved


AW109SP RFM Section 1Document N109G0040A018 Limitations

EASA Approved 11-12-09 Page 1-1

SECTION 1LIMITATIONS

GENERALCompliance with Section 1 of this manual is mandatory.

The helicopter must also be operated in accordance with theappropriate operating rules.

BASIS OF CERTIFICATIONThe helicopter is certified by the European Aviation Safety Agency(EASA ) in accordance with CS / JAR / FAR 27 for Small Rotorcraftas detailed in the Type Certificate Data Sheet EASA R.005.

TYPE OF OPERATIONSThe AW109SP helicopter, in its basic configuration, is approved forDay and Night VFR and IFR operations in non-icing conditions.

Aerobatic manoeuvres are prohibited.

MINIMUM FLIGHT CREWThe minimum flight crew consists of one pilot who shall operate thehelicopter from the right crew seat.

The left crew seat may be used for an additional pilot when theapproved dual controls are installed.

NUMBER OF SEATSEight, including the pilots seat.

Section 1 AW109SP RFMLimitations Document N109G0040A018

Page 1-2 11-12-09 EASA Approved

WEIGHT AND CENTER OF GRAVITY LIMITATIONS

WEIGHT

Maximum gross weight forground taxing and towing .......................................... 3175 kg (7000 lb)

Maximum gross weight for take-off and landing........ 3175 kg (7000 lb)

Minimum gross weight for flight................................. 2050 kg (4519 lb)

CENTER OF GRAVITY

Longitudinal limits............................................ See Figures 1-1and 1-2

Lateral limits .................................................... See Figures 1-1and 1-2



Figure 1-1 Weight , Longitudinal and Lateral CG Envelope (metric units)

WEIGHT and CG Envelopemetric units

109G1560A009 Rev.A ICN-0B-C-151000-G-A0126-00032-A-01-1

3200 3250 3300 3350 3400 3450 3500 35501800

2000

2200

2400

2600

2800

3000

3200

3400

Longitudinal Station - [mm]

Gro

ss W

eig

ht

- [k

g]

3444

2370

3225

2910

3249

3175

3330

3175

3430

2970

3520

2050

3520

-100 -80 -60 -40 -20 0 20 40 60 80 1001800

2000

2200

2400

2600

2800

3000

3200

3400

Lateral Station - [mm]

Gro

ss W

eig

ht

- [k

g]

2450

3175

-40

3175

40

2450

2050

80

2050

-80



Figure 1-2 Weight, Longitudinal and Lateral CG Envelope(imperial units)

WEIGHT and CG Envelopeimperial units

109G1560A009 Rev.B ICN-0B-C-151000-G-A0126-00033-A-02-1

126 128 130 132 134 136 138 1404000

4500

5000

5500

6000

6500

7000

7500

Longitudinal Station - [in]

Gro

ss W

eig

ht

- [l

b]

4519

135.6

5225

127

6415

127.9

7000131.1

7000135

6548

138.6

138.6

-4 -3 -2 -1 0 1 2 3 44000

4500

5000

5500

6000

6500

7000

7500

Lateral Station - [in]

Gro

ss W

eig

ht

- [l

b]

5401

7000

-1.6

7000

1.6

5401

4519

3.1

4519

-3.1



AIRSPEED LIMITATIONSVNE (Power-ON) ........................................................... See Figure 1-3

VNE (OEI/Power-OFF): .............................. VNE (Power-ON) - 40 KIAS

VNEI (maximum IFR airspeed) ................... VNE (Power-ON) - 20 KIAS

Vmini (minimum IFR airspeed) ................................................ 55 KIASMaximum airspeed during IFR/VFR approaches................... 140 KIASMaximum landing gear operating airspeed (VLO) .................. 140 KIAS

Maximum landing gear extended airspeed (VLE)................... 140 KIAS

Minimum airspeed in autorotation (withoutclose external references)........................................................ 60 KIAS

Maximum airspeed with single AP operational: normal flight ......................................... VNE (Power-ON) - 40 KIAS in IFR/VFR approaches ................................................... 115 KIAS in moderate to high turbulence ........................................ 115 KIAS

Maximum airspeed for searchlight extension, orientation and retraction ........................................................................ 135 KIAS

GROUND SPEED LIMITATIONS

ON CONCRETE OR EVEN SURFACESMaximum speed for running take-off and landing ....................40 knotsMaximum taxiing speed (nose wheel unlocked): straight ...............................................................................20 knots turning................................................................................10 knots

ON UNPREPARED OR UNEVEN SURFACESMaximum speed for running take-off and landing ....................20 knotsMaximum taxiing speed (nose wheel unlocked): straight ...............................................................................20 knots turning................................................................................10 knots



WIND SPEED LIMITATIONS FOR ROTOR STARTINGAND STOPPINGThe maximum wind speed for rotor starting and stopping is 40 knotsfrom any direction.

ALTITUDE LIMITATIONSMaximum altitude for take-off and landing .....................see Figure 1-4

Minimum and maximum operating altitudes...................see Figure 1-4

NoteFor low speed controllability, IGE and OGEhover performance and H-V refer to Section 4.

AMBIENT AIR TEMPERATURE LIMITATIONSMinimum ambient air temperature .................................-25 C (-13 F)

Maximum sea level ambient air temperature .................50 C (122 F)

The maximum ambient air temperature for operation decreases withpressure altitude at the standard lapse rate of 2 C (3.6 F) every1000 ft (305 m) up to 20000 ft (6096 m).

SLOPE LIMITATIONSSlope operations are prohibited on surfaces with a slope anglesteeper than the following:

From 90 to the left of nose up to 90 to the right of nose up..... 10 deg

Nose down ................................................................................... 2 deg



AIRSPEED LIMITATION

ICN-0B-C-151500-G-A0126-00036-A-02-1

-30 -20 -10 0 10 20 30 40 50-8

-6

-4

-2

0

2

4

6

8

10

12

14

16

18

20

OAT [C]

D

E

N

S

I

T

Y

A

L

T

I

T

U

D

E

[

f

t

X

1

0

0

0

]

Hp 0 f

t

Hp 50

00 ft

Hp 10

000 ft

Hp 15

000 ft

ISA

ISA

+35C

100 110 120 130 140 150 160 170

VNE

[kIAS]

VNE

POW

ER

ON

Figure 1-3 Airspeed Limitation VNE (Power-ON)



This Page Intentionally Left Blank



Figure 1-4 Pressure altitude / OAT Envelope

FLIGHT and T.O/LANDING

ENVELOPE

109G1560A009 Rev.A ICN-0B-A-151000-G-A0126-00037-A-04-1

-200

0

200

400

600

800

1000

1200

1400

1600

1800

2000

2200

2400

2600

2800

3000

3200

3400

3600

3800

4000

4200

4400

4600

4800

5000

5200

5400

5600

5800

6000

Pre

ss

ure

Alt

itu

de

- [

m]

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

0

1000

2000

3000

4000

5000

6000

7000

8000

9000

10000

11000

12000

13000

14000

15000

16000

17000

18000

19000

20000

OAT - [C]

Pre

ss

ure

Alt

itu

de

- [

ft]

MIN

OA

T L

IMIT

MA

XO

AT

LIM

IT IS

A+35C

Hd LIMIT 20000 ft

Hd LIMIT 16000 ft

TAKE OFF and

LANDING

ENVELOPE



DOORS OPENED OR REMOVEDFlight with either one or both passengers cabin sliding doors open isprohibited if passenger door modification P/N 109-0814-35 is notinstalled.

It is possible to fly with pilot / copilot doors removed and/or passen-gers cabin sliding doors opened to lock position or removed in which-ever combination.

VNE with any door removed or open to lock position................75 KIAS

Maximum airspeed for passengers cabin sliding doors opening or closing ....................................................................50 KIAS



POWER PLANT AND TRANSMISSION LIMITATIONS

GENERAL

NoteThe one engine inoperative (OEI) ratings areintended for emergency use only, when oneengine becomes inoperative due to an actualmalfunction. OEI operations for maintenance or trainingpurposes shall be limited to the OEIContinuous Operation power range.

NoteTransient range must not be used intentionally.

POWER PLANT LIMITATIONSThe helicopter is powered by Pratt and Whitney PW207C turboshaftengines.

GAS GENERATOR SPEED (N1)

All Engines Operating (AEO)

Continuous Operation ........................................................ 50 to 97.1%

Take-Off Range (5 minutes) ............................................ 97.2 to 99.7%

Maximum .................................................................................... 99.7%

Transient (20 seconds) ............................................................. 104.1%

One Engine Inoperative (OEI)

Continuous Operation ........................................................ 50 to 99.7%

2.5 minutes Range........................................................ 99.8 to 102.9%

Maximum .................................................................................. 102.9%

Transient (20 seconds) ............................................................. 104.1%



POWER TURBINE SPEED (N2)


Transient ........................................................................................95%

Minimum.........................................................................................99%

Continuous Operation (except for Take-Off and Landing)...99 to 101%

Take-Off, Landing and below Vy .......................................101 to 102%

Maximum......................................................................................102%

Transient (20 seconds)................................................................. 112%


Transient ........................................................................................85%

Minimum.........................................................................................90%

Cautionary Range .................................................................90 to 98%

Continuous Operation (except for Take-Off and Landing).. 99 to 101%


Maximum......................................................................................102%

Transient (20 seconds)................................................................. 112%



TURBINE OUTLET TEMPERATURE (TOT)

Engine Starting

Maximum (unlimited).................................................................. 650 C

Maximum transient (2 seconds)................................................. 875 C

NoteA linear variation applies between 20 sec-onds at 650 C and 2 seconds at 760 C.A transient of 2 seconds applies above760 C.


Maximum Continuous ................................................................ 840 C

Take-Off Range (5 minutes) ............................................ 841 to 900 C

Transient (20 seconds) ............................................................ 1000 C


Maximum Continuous ................................................................ 900 C

2.5 minutes Range.......................................................... 901 to 970 C

Transient (20 seconds) ............................................................ 1000 C



ENGINE OIL PRESSURE

NoteThe oil pressure limits vary as a function of thegas generator speed.

Minimum for ground idle....................................... Above lower red line

Continuous Operation .......................................... ..............Green band(variable as a function of N1)

Cautionary Range .............................................. ..............Yellow bands(variable as a function of N1)

Maximum during engine starting ............................................... 200 psi

NoteThe engine can operate with oil pressure upto 200 psi during or after start or if the oiltemperature drops significantly below 71 C.Oil pressure will decrease as oil temperatureincreases and is not expected to endure formore than 5 sec. The operation at an oilpressure up to 200 psi is permitted for aperiod of 10 minutes.

ENGINE OIL TEMPERATURE

Continuous Operation ....................................................... 10 to 125 C

Maximum....................................................................................125 C

ENGINE STARTER LIMITATIONS

The engine starter duty cycle is the following:

45 seconds on, 1 minute off;

45 seconds on, 1 minute off;

45 seconds on, 30 minutes off.



TRANSMISSION LIMITATIONS

TORQUE (TRQ)


Maximum Continuous .................................................................. 100%

Take-Off Range (5 minutes) .............................................. 101 to 107%

Maximum ..................................................................................... 107%

Transient (6 seconds) .................................................................. 110%


Maximum Continuous .................................................................. 133%

2.5 minutes Range............................................................ 134 to 162%

Maximum ..................................................................................... 162%

Transient (6 seconds) .................................................................. 173%

TRANSMISSION OIL PRESSURE

Minimum ......................................................................................30 psi

Continuous Operation .........................................................30 to 50 psi

Cautionary Range ...............................................................51 to 70 psi

Maximum .....................................................................................70 psi

NoteDuring cold starting conditions, thetransmission oil pressure may temporarily riseup to 100 psi.

TRANSMISSION OIL TEMPERATURE

Continuous Operation ......................................................... 0 to 120 C

Maximum ................................................................................... 120 C



ROTOR LIMITATIONS (NR)

POWER-ON (AEO)

Transient ........................................................................................95%

Minimum.........................................................................................99%



Maximum......................................................................................102%

POWER-ON (OEI)

Transient ........................................................................................85%

Minimum ........................................................................................90%

Cautionary Range .................................................................90 to 98%



Maximum......................................................................................102%

POWER-OFF

Transient ........................................................................................90%

Minimum.........................................................................................95%

Continuous Operation ......................................................... 95 to 110%

Maximum...................................................................................... 110%

NoteTransient range must not be used intentionally.



FUEL SYSTEM LIMITATIONS

FUEL PRESSURE

Cautionary Range ...................................................................0 to 7 psi

Continuous Operation ...........................................................8 to 25 psi

Maximum .....................................................................................25 psi

FUEL QUANTITY

Total ........................................................................................... 460 kg

(575 liters at 0.8 kg/liter)

TOTAL UNUSABLE FUEL

In coordinated flight...................................................................... 10 kg

(12 liters at 0.8 kg/liter)



FUEL TYPESThe fuels shown in Table 1-1 have been authorized for use with thePratt & Whitney PW207C engines.

NoteAn approved fuel or any mixture of accept-able fuels may be used. However, changingto a fuel with a substantially different heatingvalue or specific gravity may require mainte-nance in the form of engine fuel control(trimmer) adjustment. Refer to the Pratt &Whitney PW207C engine manual.

NoteFuel grades marked with an asterisk (*) con-tain a fuel system icing inhibitor (FSII). ForJP-8, MIL-T-83133C allows two grades. Thegrade meeting NATO code F-34 has FSIIwhile the grade meeting code F-35 has noFSII unless specifically requested.

Table 1-1 Authorized Fuels

Kerosene Type Applicable Specification

JET AJET A-1

JP-5 *JP-8 *

R.T.R.T.

TS-1**TS-1**

ASTM D1655ASTM D1655

MIL-T-5624MIL-T-83133

GOST 10227-86GSTU 320.00149943.007-97

GOST 10227-86GSTU 320.00149943.011-99



NoteFuel grades marked with double asterisk (**)are for occasional use only. Refer to Pratt &Whitney PW207C Maintenence Manual forfull details and restrictions.

NoteFor operations below +4C, the use of anti-ice additive is authorized but not mandatorysince the helicopter is equipped with an air-frame anti-ice fuel filter. For additive require-ments and blending procedures refer to thePratt & Whitney PW207C engine manual.

EMERGENCY FUELS

Table 1-2 presents a list of fuels approved for emergency use.Emergency fuels should only be used whenever any of the authorizedfuels are not available.

Refer to the Pratt & Whitney PW207C Manual for full details. Table 1-2 Emergency Fuels

Fuel Type Applicable Specification

Restrictions

Automotive Diesel

CPW 46

Aviation Gasoline

Grades: 80, 100 and 100 LL

Arctic Grade

Winter Grade

Regular Grade

MIL-G-5572

Do not use below -15 C (5 F) OAT

Do not use below -7 C (20 F) OAT

Do not use below 5 C (40 F) OAT

Do not use for longer than 150 hours during any period between engine overhauls.

Engine operation in suction mode is prohibited.



LUBRICANTS

AUTHORIZED ENGINE OILS

The oils shown in Table 1-3 have been authorized for use with thePW207C engines.

NoteEngine oil tank capacity is 5.12 liters (1.35 USGallon).

NoteMixing of the different brands and types isprohibited.

Table 1-3 Authorized Lubricating Oils, Type II (5 Centistokes)

ApplicableSpecification

Brand Names(For reference only)

MIL-PRF-23699 Aero-Shell Turbine Oil 500

Aero-Shell Turbine Oil 560

BP Turbo Oil 2380 (formerly Exxon Turbo Oil 2380)

BP Turbo Oil 25 (formerly Exxon Turbo Oil 25)

Castrol 5000

Mobil Jet Oil II

Royco Turbine Oil 500

Royco Turbine Oil 560

Turbonycoil 525-2A



AUTHORIZED TRANSMISSION OILS

The oils shown in Table 1-4 have been authorized for use with themain transmission and the tail rotor gearbox lubrication systems.

Oils are limited to ambient temperatures above -40 C (-40 F).

NoteMixing of oils of different brands and types isprohibited.

Table 1-4 Authorized Lubricating Oils

Designation Specification

BP Turbo oil 2380 (formerly EXXON Turbo oil 2380)

MIL-PRF-23699

Mobil Jet Oil II MIL-PRF-23699

Mobil Jet Oil 254 MIL-PRF-23699

Aeroshell Turbine oil 500 MIL-PRF-23699

Aeroshell Turbine oil 555 DOD-PRF-85734

Aeroshell Turbine oil 560 MIL-PRF-23699

Castrol Aero 5000 MIL-PRF-23699

BP Turbo oil 2197 MIL-PRF-23699



HYDRAULIC SYSTEM LIMITATIONS

MAIN SYSTEM FLUID PRESSURE

Minimum.................................................................................. 1200 psi

Cautionary Range ...................................................... 1200 to 1400 psi

Continuous Operation ................................................ 1401 to 1600 psi

Maximum................................................................................. 1600 psi

NORMAL UTILITY SYSTEM - FLUID PRESSURE

Minimum.................................................................................... 500 psi

Cautionary Range .........................................................500 to 1140 psi

Continuous Operation .................................................1141 to 1600 psi

Maximum................................................................................. 1600 psi

EMERGENCY UTILITY SYSTEM - FLUID PRESSURE

Minimum...................................................................................1140 psi

Maximum................................................................................. 1600 psi

APPROVED FLUIDS

The following hydraulic fluids are approved:

MIL-PRF-5606MIL-PRF-83282.

NoteMixing of fluids of different brands and types isprohibited.



GENERATOR LOAD LIMITATIONS

For each generator

Up to 15000 ft Hp

Continuous Operation: ..............................................0 to 200 A

Maximum load at MPOG (no time limitiation):..................160 A

Maximum load at MPOG (10 minutes): .................160 to 200 A

Above 15000 ft Hp

Continuous Operation: ..............................................0 to 130 A

Maximum load at MPOG (no time limitiation):..................130 A

Transient at starting (45 seconds):...............................................300 A

NAVIGATION LIMITATIONS

MAGNETIC COMPASS

When operating the SRCH LT, the magnetic compass is unreliable.



FLIGHT MANAGEMENT SYSTEM LIMITATIONSOperations in European B-RNAV airspace are demonstrated in accor-dance to EASA AMC 20-4, where GPS stand-alone equipment is usedas the only means for B-RNAV operations. This does not constitute anoperational approval.

It is prohibited to navigate using the Flight Management System inDead Reckoning mode.

NoteThe Dead Reckoning mode will be automati-cally activated as the navigation mode onlyif the GPS systems have failed. The accu-racy of the Dead Reckoning mode cannotbe guaranteed.

IFR en route and terminal navigations are prohibited unless the pilotverifies the currency of the navigation database or verifies eachselected waypoint for accuracy by referring to current approved data.

IFR approaches and departures must be carried out in accordancewith approved instrumental procedures that are retrieved from theFMS approved database. The FMS database must incorporate thecurrent update cycle.

EN ROUTE AND TERMINAL

It is prohibited to use VNAV mode data for navigation.

Traditional IFR approved navigation equipment shall be available tocontinue the flight including the alternate when GPS integrity is lost(GPS LOI and/or GPS LON displayed on IDU caution list). The ground based aids on the route to be flown or ground based aidsfor RNAV routes must be operational and aircraft equipment otherthan GPS suitable for the route to be flown must be serviceable.

PRECISION APPROACH

It is prohibited to use FMS-GPS for IFR precision approaches.


EASA Approved 11-12-09 Page 1-25Rev. 4

NON PRECISION APPROACH (NPA)

It is prohibited to perform an IFR approach after the Final ApproachFix if GPS LOI caution is displayed on IDU caution list. If GPS LOIcaution is due to a GPS failure, carry out the GPS FAILUREmalfunction procedure, or initiate a missed approach.

For EFIS with software version A109 7.0D

It is prohibited to continue a Non Precision Approach proceduresfollowing a PFD failure.

EFIS LIMITATIONSSkyway simbology does not provide precision approach guidance norit does guarantee terrain separation.It remains the pilot's responsibility to provide self separation fromterrain.

HTAWS LIMITATIONSThe TAWS installed is a class B HTAWS and it provides the followingfunctions:

Terrain and Obstruction display;

Forward Looking Terrain Awareness (FLTA);

Sink Rate after Takeoff or Missed Approach (GPWS Mode 3).

HTAWS must not be used for navigation.Do not attempt to navigate using the terrain depiction.

HTAWS must not be used for terrain following flight.Do not use hue nor grid as cues for altitude or direction.

The HTAWS database installed shall be the last update for the regionbeing flown.


Page 1-26 11-12-09 EASA ApprovedRev. 3

CAUTION

The terrain and obstacle display is intendedto serve as a terrain and obstacle aware-ness tool only. The display and databasemay not provide the accuracy and fidelity onwhich to base routine navigation decisionsand plan routes to avoid terrain or obstacles.

CAUTION

There are many towers , antennas, powerlines, and obstructions that are not in thedatabase.

AUTOMATIC FLIGHT CONTROL SYSTEM LIMITATIONSMinimum AFCS configuration for IFR / VFR flight...2 AP in ATT mode

DUAL AP OPERATION

Flight at altitude below 1000 ft AGL ...................................Fly attentive

Flight at airspeed above VNE (Power-ON) - 20 KIAS........Fly manually

SINGLE AP OPERATION

Flight at altitude above 500 ft AGL.....................................Fly attentive

Flight at altitude at or below 500 ft AGL ............................Fly manually

Flight in moderate to high turbulence................................Fly manually

In single AP operation, the AFCS Upper Modes and Flight DirectorModes must not be used unless conducting an approach, missedapproach, transition to/from the hover or hover.



FLIGHT DIRECTOR LIMITATIONS

UPPER AND FLIGHT DIRECTOR MODES ENGAGEMENT LIMITSAND MINIMUM USE HEIGHT (MUH)

Hold Mode

Applicable Range MUH Notes

ALT 0 KIAS to VneAltitude -1000 ft to 20000 ft

300ft AGL in cruise or50 ft AGL in hover

RHT0 KIAS to Vne 15 ft to 2500 ft AGL

200 ft AGL in cruise (overflat surfaces only) or50 ft AGL in hover and transition to/from hover

HDG

0 KIAS to Vne

200 ft AGL in cruise or 50 ft AGL during approachin hover and transition to/from hover

ALTA* 40 KIAS to VneAltitude -1000 ft to 20000 ft

300 ft AGL

VS* 40 KIAS to Vne within -1500 fpm and 2000 fpm 200 ft AGL 3

IAS*

40 KIAS to Vne


HOV Airspeed less than 80 KIAS andGroundspeed Longitudinal -20 to +60 kts Lateral -20 to +20 kts


GA 40 KIAS to Vne N/A 1



Notes

1 GA mode engagement is inhibited (regardless of airspeed value) ifHOV mode engaged.

2 TU mode engages also for airspeed less than 40 kts if HOV modeengaged.

3 VS Mode engagement above 2000 fpm or below -1500 fpm willresults in the mode returning the aircraft to the maximum ratesquoted (2000 fpm or -1500 fpm).

TU Airspeed less than 40 KIAS10 ft to 2500 ft AGL


2

NAV

40 KIAS to Vne


VOR

40 KIAS to Vne


VAPP40 KIAS to Vne


LOC/NLOC 40 KIAS to Vne


GS/NGS 40 KIAS to Vne


UPPER AND FLIGHT DIRECTOR MODES ENGAGEMENT LIMITSAND MINIMUM USE HEIGHT (MUH) (CONT.D)

Hold Mode

Applicable Range MUH Notes



GENERAL LIMITATIONS

With AFCS Upper Modes and Flight Director Modes engaged the torquelimiter must be active (LIMITER ON advisory message displayed).

ILS APPROACH

Steepest ILS approach gradient................................................ 7,5 degMaximum Airspeed according to the following table:

GPS APPROACH

Steepest GPS approach gradient ............................................. 9,0 degMaximun Airspeed according to the following table

GLIDE PATH ANGLE (deg) AIRSPEED (KIAS)3 1404 1205 1106 100

7,5 90

GLIDE PATH ANGLE (deg) AIRSPEED (KIAS)3 1404 1205 1106 100

7,5 908 809 70


Page 1-30 11-12-09 EASA ApprovedRev. 4

UPPER MODES

HOV Mode

HDG datum shall not be changed with variation greater than 10when HOV mode is engaged with relative wind speed and/or non-zeroground-speed reference.

For EFIS with software version A109 7.0DHOV mode is prohibited if the Magnetic Variation is in excess of 5[5W, 5E].

RHT Mode

The use of Radar Height (RHT) mode is prohibited in cruise over non-flat surfaces.

When in RHT mode the RadAlt must be continuously cross-checkedwith BarAlt set to QFE.

TU Mode

Safe operation of TU mode has been demonstrated up to 25 kts windspeed coming from 90 deg with respect to rotorcraft heading.


TU mode is prohibited if the Magnetic Variation is in excess of 5 [5W,5E].

NLOC and NGS Modes


NLOC and NGS modes are prohibited, either coupled or uncoupled, ifthe Magnetic Variation is in excess of 2 [2W, 2E].

LOC and GS Modes


LOC and GS modes are prohibited, either coupled or uncoupled, if theMagnetic Variation is in excess of 2 [2W, 2E].



ROTOR BRAKE LIMITATIONSelection of the rotor brake to the ON position is limited as follows:

Rotor Speed (NR) ................................................................below 40%

MISCELLANEOUS LIMITATIONS

Pilot(s) must not use polarized type sun glasses.

FUEL MANAGEMENT SYSTEM

It is prohibited to rely upon Fuel Flow data for flight planning andnavigation.

PASSENGERS CABIN LIMITATIONS

Baggage storage under the seat is prohibited.

BAGGAGE COMPARTMENT LIMITATIONS

Maximum load............................................................... 120 kg (264 lb)

Maximum Unit Load .......................................... 500 kg/m2 (102 lbs/ft2)

NoteRefer to Section 6, Weight and Balance,for load distribution.



PLACARDS

Figure 1-5 Airspeed (Vne) Placard

A

OATC

-

-10000

2000400060008000100001200014000160001800020000

-25 50

168168

----------

---

----

----

-

---

--

-20 -10 0 10 20 30 40

----

Hp-ft

ICN-0B-C-151000-G-A0126-01022-A-01-1

168168

168161

168168168166156146

168168168168160

141131115

168168168168165155145135122

168168168168168160150140129113

168168168168168164154145135121

168168168168168168159149140128112

168168168168168168162152142132116100

105107

151137

AIRSPEED LIMITATIONS V - KIAS

C

BD

EA

ne

nei

AUTOROTATION OR OEI: REDUCE V BY 40 KIAS ne

V : REDUCE V BY 20 KIAS ne

140 KIASMAX FWD TOUCHDOWN SPEED: 40 Kts V AND V :LO LE



Figure 1-6 Cockpit Placards

IN ALTN POSITIONOPEN VENTS AND

TURN HEATER/ECS OFF

DO NOT APPLY ROTORBRAKE ABOVE 40%

ROTOR RPM

APPROVED TYPES OF OPERATION DAY/NIGHT VFRDAY/NIGHT IFR

ICING PROHIBITED

C

B

D

E

ALT. STATICDECREASE ALTIMETER READING BY 120 ft

ICN-0B-C-151000-G-A0126-01023-A-01-1



Figure 1-7 Placards in Baggage Compartment

A

ICN-0B-C-151000-G-A0126-01002-A-01-1

BAGGAGE COMPARTMENT

MAXIMUM ALLOWABLE BAGGAGE LOAD

ZONEKG (LB)

1 2 3 4 5120 ( 264 ) 110 ( 242 ) 102 ( 224 ) 93 ( 205 ) 84 ( 185 )

MAXIMUM TOTAL LOAD 120 KG ( 264 LB )MAX UNIT FLOOR LOADING 500 KG/M2( 102 LB/SQ.FT. ) ALL CARGO MUST BE SECURED MAX LOAD PER TIE DOWN RING 91KG ( 200LB )

A



INSTRUMENT MARKINGS

Figure 1-8 EFIS - Indicated Airspeed (IAS)



Figure 1-9 EDU1 - Gas Generator Speed (AEO)

ICN-0B-C-151000-G-A0126-01004-A-01-1

N1 N1

50 %

MAX CONTINUOUS 97.1 %

50 %

START format CRUISE formatAUTOROTATION format REVERSIONARY format

0 % 0 %

TRANSIENT 104.1 %MAX TAKE-OFF 99.7 %

TRANSIENT 104.1 %

MAX CONTINUOUS 97.1 %MAX TAKE - OFF 99.7 %

TOTN1100959577077095.595.5

SERVO 1 PARK BRK ON

CLR

ON

OFF

ENT

BRT

DIM

M

TRQ NR

#1 OIL PRES #2 OIL PRES#2 DC GENSERVO 2

#1 DC GENBATT HOTXMSN OIL PRES

100

ENG 1(2) OUT+ Audio tone

When N1 is 35% and below:

+ Voice message ENGINE 1(2) OUT



Figure 1-10 EDU1 - Gas Generator Speed (OEI)

ICN-0B-C-151000-G-A0126-01005-A-01-1

CLR

ON

OFF

ENT

BRT

DIM

M

TRQ NR

ENG 2 OUT

95

OEI

OEI

OEI

100

TRANSIENT 104.1 %MAX 2.5 MIN 102.9 %

MAX CONTINUOUS 99.7 %

50 %

N1

OEI formatREVERSIONARY OEI format

0 %

0 100770 095.5 0

ENG 1(2) OUT+ Audio tone

When N1 is 35% and below:

+ Voice message ENGINE 1(2) OUT

NOTEThe OEI legend colour changesfrom white to yellow whenpassing from continuous to timelimited range.When the OEI 2.5 minutes ratingis used, 10 seconds before the2.5 minutes time expires theyellow OEI legend becomes redand starts flashing. Upon expiry,the OEI legend becomes fixedred.



Figure 1-11 EDU1 - Turbine Outlet Temperature (AEO)

TOT

CLR

ON

OFF

ENT

BRT

DIM

M

TRQ NR



100

START format (AEO)

50 C

1009577077095.595.5

SERVO 1 PARK BRK ON

95N1

TRANSIENT 1000 C

MAX TAKE-OFF 900 C

START LIMIT 875 C

MAX CONTINUOUS 840 C

ICN-0B-C-151000-G-A0126-01006-A-01-1

TOT

MAX TAKE-OFF 900 C


TRANSIENT 1000 C

50 C

CRUISE format (AEO)

AUTOROTATION formatREVERSIONARY format

#1(2) HOT START

When a TOT limit is exceededduring starting:



Figure 1-12 EDU1 - Turbine Outlet Temperature (OEI)

ICN-0B-C-151000-G-A0126-01007-A-01-1

CLR

ON

OFF

ENT

BRT

DIM

M

TRQ NR

ENG 2 OUT

95

OEI

OEI

OEI

100

TRANSIENT 1000 C


TOT

OEI format REVERSIONARY OEI format

TRANSIENT 875 C

50 C

0TOTN1

100770 095.5 0

MAX 2.5 MIN 970 C

#1(2) HOT START

When a TOT limit is exceededduring starting:

NOTEThe transient value at starting (halfred dot at 875C) is displayed onthe scale of the engine beingstarted, during the restart phaseonly.

NOTEThe OEI legend colour changesfrom white to yellow when passingfrom continuous to time limitedrange.When the OEI 2.5 minutes rating isused, 10 seconds before the 2.5minutes time expires the yellow OEIlegend becomes red and startsflashing. Upon expiry, the OEIlegend becomes fixed red.



Figure 1-13 EDU1 - Torque (AEO)

ICN-0B-C-151000-G-A0126-01008-A-01-1

TRANSIENT 110 %

MAX TAKE-OFF 107 %

0 % 0 %

START format (AEO)

MAX. CONTINUOUS 100 % MAX. CONTINUOUS 100 %

TRANSIENT 110 %

MAX TAKE-OFF 107 %

CRUISE format (AEO)AUTOROTATION format REVERSIONARY format

CLR

ON

OFF

ENT

BRT

DIM

M

TRQ NR



100

SERVO 1 PARK BRK ON

100N2 N2

TOTN19595.5 9595.5 770 770

TRQ TRQ

XMSN OVTRQ

When TRQ1 + TRQ2 is above 214% (AEO):

+ Voice message OVERTORQUE

+ Audio tone



Figure 1-14 EDU 1 - Torque (OEI)

CLR

ON

OFF

ENT

BRT

DIM

M

TRQ NR

ENG 2 OUT

95

OEI

OEI

OEI

100N2 N2

0 100770 095.5 0

ICN-0B-C-151000-G-A0126-01009-A-01-1

MAX CONTINUOUS 133 %

0 %

TRQ


TRANSIENT 173 %

MAX 2.5 MIN 162 %

XMSN OVTRQ

When TRQ1 or TRQ2 is above 162% (OEI):

+ Voice message OVERTORQUE

+ Audio tone

NOTEThe OEI legend colour changes fromwhite to yellow when passing fromcontinuous to time limited range.When the OEI 2.5 minutes rating isused, 10 seconds before the 2.5minutes time expires the yellow OEIlegend becomes red and startsflashing. Upon expiry, the OEI legendbecomes fixed red.



Figure 1-15 EDU1 - Rotor / Power Turbine Speed (AEO)

ICN-0B-C-151000-G-A0126-01010-A-01-1

TRANSIENT 112 % N2 NR

MAXIMUM 102 %

MINIMUM 99 %

20 %

TRANSIENT 95 %

MAX CONTINUOUS 101 % CONTINUOUSOPERATION

CLR

ON

OFF

ENT

BRT

DIM

M

TRQ NR



100

TOTN1

SERVO 1 PARK BRK ON

100959577077095.595.5

START and CRUISE formats (AEO)REVERSIONARY format

ROTOR LOW

ROTOR HIGH

#1(2) OVSPD

When N2 is at or above 111%:

When NR is above 105%:+ Audio tone + Voice message ROTOR HIGH

When NR is below 96%:+ Audio tone

+ Voice message ROTOR LOW+ Horn



Figure 1-16 EDU1 - Rotor / Power Turbine Speed (OEI)

ICN-0B-C-151000-G-A0126-01011-A-01-1

CLR

ON

OFF

ENT

BRT

DIM

M

TRQ NR

ENG 2 OUT

95

OEI

OEI

OEI

100

N1 TOT0 100770 095.5 0

TRANSIENT 112 % N2 NR

MINIMUM 90 %

20 %

TRANSIENT 85 %

99% to 101% CONTINUOUS OPERATION

MAXIMUM 102 %


ROTOR LOW

ROTOR HIGH

#1(2) OVSPD

When N2 is at or above 111%:






Figure 1-17 EDU1 - Rotor Speed (Power-OFF)

ICN-0B-C-151000-G-A0126-01012-A-01-1

NR

MAXIMUM 110 %

MINIMUM 95 %

20 % AUTOROTATION format

TRANSIENT 90 %

REVERSIONARY AUTOROTATION format

CONTINUOUSOPERATION

CLR

ON

OFF

ENT

BRT

DIM

M

TRQ NR


#1 DC GEN XMSN OIL PRESROTOR LOW

100

TOTN1100004304306767

SERVO 1 PARK BRK ON

ROTOR LOW

ROTOR HIGH






Figure 1-18 EDU2 (MAIN) - Engine Oil Pressure

ICN-0B-C-151000-G-A0126-01013-A-01-1

MAXIMUM

MINIMUM

CLR

ON

OFF

ENT

BRT

DIM

M

TESTPOWERCHECK

MENU 1/3

MAIN

PSI

1450PSI

HYD 1

22 23 1450PSI

HYD 2225 FUEL

COAT

PSI COILENG 1 OILXMSN

COILENG 2

225

ENG 1 (2) OIL - PSI

CAUTIONARY

PSI C

PSI PSI

KGKG

55 65 45 68 55 65+15

AUXEXIT

CAUTIONARY

CONTINUOUSOPERATION

#1(2) OIL PRES

When engine oil pressure is

+ Audio tone

above the maximum orbelow the minimum:

Voice message WARNING

NOTEEngine oil pressurelimits vary as afunction of N1.



Figure 1-19 EDU2 (MAIN) - Engine Oil Temperature

ICN-0B-C-151000-G-A0126-01014-A-01-1

CLR

ON

OFF

ENT

BRT

DIM

TESTPOWERCHECK

MENU 1/3

MAIN

PSI

1450PSI

HYD 1

22 23 1450PSI

HYD 2225 FUEL

COAT


COILENG 2

225

PSI C

PSI PSI

55 65 55 6545 68 +15

AUXEXIT

M

0 C

MAXIMUM 125 C

10 C

130 CENG 1(2) OIL - C

CONTINUOUSOPERATION

#1(2) OIL HOT

When engine oil temperatureis above 125C:



Figure 1-20 EDU2 (MAIN) - Transmission Oil Pressure

ICN-0B-C-151000-G-A0126-01015-A-01-1

0 PSI

CAUTIONARY

XMSN OIL - PSI100 PSI

MAXIMUM 70 PSI

MINIMUM 30 PSI

50 PSI

CLR

ON

OFF

ENT

BRT

DIM

M

TESTPOWERCHECK

MENU 1/3

MAIN

PSI

1450PSI

HYD 1

22 23 1450PSI

HYD 2225 FUEL

COAT


COILENG 2

225

PSI C

AUXEXIT

PSI PSI

55 65 45 68 55 65+15

CONTINUOUSOPERATION

XMSN OIL PRES

When transmission oil pressure is

+ Audio tone Voice message WARNING



Figure 1-21 EDU2 (MAIN) - Transmission Oil Temperature

ICN-0B-C-151000-G-A0126-01016-A-01-10 C

XMSN OIL - C

CLR

ON

OFF

ENT

BRT

DIM

M

TESTPOWERCHECK

MENU 1/3

MAIN

PSI

1450PSI

HYD 1

22 23 1450PSI

HYD 2225 FUEL

COAT


COILENG 2

225

PSI C

AUXEXIT

PSI PSI

55 65 55 6545 68 +15

KG KG

MAXIMUM 120 C

130 C

CONTINUOUSOPERATION

XMSN OIL HOT

When transmission oil temperature is

+ Audio tone above 120C:

+ Voice message WARNING



Figure 1-22 EDU2 (MAIN / AUXILIARY) - Main Hydraulic System Pressure

CONTINUOUSOPERATION

ICN-0B-C-151000-G-A0126-01017-A-01-1

MINIMUMCONTINUOUS

1400 PSI

800 PSI

CAUTIONARY

2000 PSI

HYD 1(2)

CLR

ON

OFF

ENT

BRT

DIM

M

TESTPOWERCHECKEXIT AUX

MENU 1/3

MAIN

55 65 45 68 +15PSI

1450PSI

HYD 1

22 23PSI PSI

1450PSI

HYD 2225 FUEL

COAT

55 65PSI C

KG KG

OILENG 1 OILXMSNCPSI C

OILENG 2

CLR

ON

OFF

ENT

BRT

DIM

M


MENU 1/3

MAIN

HYD 1PSI

HYD 2

XFEEDKG

KG/HR

FUEL

VDC

VAC 116

MAINHYDRAULICS

PSI

UTILNORM EMER

118 AMP 123 100 99

1450 1450

27.3 27.5

115 225 227

14501450

EDU2 - AUXILIARY EDU2 - MAIN

ELECTRICS

MAXIMUM1600 PSI

225

MINIMUM1200 PSI



Figure 1-23 EDU2 (MAIN) - Fuel Pressure

FUEL

CLR

ON

OFF

ENT

BRT

DIM

M

TESTPOWERCHECK

MENU 1/3

MAIN

PSI

1450PSI

HYD 1

22 23 1450PSI

HYD 2225 FUEL

COAT

PSI COIL XMSN

COILENG 2

225

PSI PSI

KGKG

PSI CENG 1

55 65 55 6545 68 +15

OIL

ICN-0B-C-151000-G-A0126-01018-A-01-1

CAUTIONARY

MAXIMUM25 PSI

MINIMUM0 PSI

MINIMUMCONTINUOUS

7 PSI

30 PSICONTINUOUSOPERATION

FUEL PUMP 1(2)

When fuel system pressuredrops to zero psi:



Figure 1-24 EDU2 (AUXILIARY) - Generator Load

ICN-0B-C-151000-G-A0126-01019-A-01-1

CLR

ON

OFF

ENT

BRT

DIM

M


MENU 1/3

MAIN

HYD 1PSI

HYD 2

KG

KG/HR

FUEL

VDC

VAC 116

MAINHYDRAULICS

PSI

UTILNORM EMER

118 AMP 123 100 99

1450 1450

27.3 27.5

115 225

14501450

ELECTRICS

225

ELECTRICS - AMP

0 AMPMAXIMUM

200 AMP

CONTINUOUSOPERATION

TRANSIENT300 AMP

TRANSIENT

0 AMP

300 AMP

( Up to 15000 ft Hp )

( Above 15000 ft Hp )

MAXIMUM130 AMP

CONTINUOUSOPERATION



Figure 1-25 EDU2 (AUXILIARY) - Utility Hydraulic System Pressure (Normal)

ICN-0B-C-151000-G-A0126-01020-A-01-1

CLR

ON

OFF

ENT

BRT

DIM

M

TESTPOWERCHECK

MENU 1/3

MAIN

HYD 1PSI

HYD 2

KG

KG/HR

FUEL

VDC

VAC 116

MAINHYDRAULICS

PSI

UTILNORM EMER

118 AMP 123

27.3 27.5

115 225

14501450

ELECTRICS

225

100 99

AUXEXIT

UTIL - NORM

300 PSI

MINIMUM500 PSI 1140 PSI

2000 PSI

CAUTIONARY

MAXIMUM1600 PSI

CONTINUOUSOPERATION



Figure 1-26 EDU2 (AUXILIARY) - Utility Hydraulic System Pressure (Emergency)

ICN-0B-C-151000-G-A0126-01021-A-01-1

CLR

ON

OFF

ENT

BRT

DIM

M

TESTPOWERCHECK

MENU 1/3

MAIN

HYD 1PSI

HYD 2

KG

KG/HR

FUEL

VDC

VAC 116

MAINHYDRAULICS

PSI

UTILNORM EMER

118 123

27.3 27.5

115 225

14501450

ELECTRICSAMP

225

14501450

100 99

1432

EXIT AUX

300 PSI2000 PSI

MINIMUM1140 PSI

UTIL - EMER

MAXIMUM1600 PSI

CONTINUOUSOPERATION

EMER UTIL PRES

When emergency utility

is below 1140 psi:hydraulic system pressure


EASA Approved 11-12-09 Page 2-i

SECTION 2

NORMAL PROCEDURES

TABLE OF CONTENTSPage

GENERAL ....................................................................................... 2-1

FLIGHT PLANNING ........................................................................ 2-2

PRE-FLIGHT CHECKS ................................................................... 2-2GENERAL................................................................................... 2-2PILOTS PRE-FLIGHT CHECK .................................................. 2-3

ENGINE PRE-START CHECK...................................................... 2-19INITIAL CHECKS...................................................................... 2-19ELECTRICAL POWER-UP....................................................... 2-20

ENGINE START ............................................................................ 2-26NORMAL ENGINE START....................................................... 2-26QUICK ENGINE START........................................................... 2-31ABORTED ENGINE START PROCEDURE............................. 2-35DRY MOTORING RUN............................................................. 2-36

SYSTEM CHECKS ...................................................................... 2-38HYDRAULIC SYSTEMS........................................................... 2-38FUEL SYSTEM......................................................................... 2-39ELECTRICAL A.C. SYSTEM.................................................... 2-41RCP .......................................................................................... 2-41AFCS ........................................................................................ 2-42MISCELLANEOUS ................................................................... 2-43

BEFORE TAKE-OFF CHECKS .................................................... 2-45

GROUND TAXIING ....................................................................... 2-46


Page 2-ii 11-12-09 EASA Approved

Page

TAKE-OFF..................................................................................... 2-46HOVER TAKE-OFF ................................................................ 2-46ROLLING TAKE-OFF .............................................................. 2-48

IN FLIGHT ................................................................................... 2-49SEARCHLIGHT OPERATING PROCEDURE.......................... 2-50AUTOMATIC FLIGHT CONTROL SYSTEM ............................ 2-51ILS APPROACHES .................................................................. 2-51EFIS SYSTEM.......................................................................... 2-51FLIGHT MANAGEMENT SYSTEM .......................................... 2-52TAWS ....................................................................................... 2-52

APPROACH AND LANDING ...................................................... 2-53VERTICAL LANDING .............................................................. 2-54RUNNING LANDING .............................................................. 2-55

SHUTDOWN ................................................................................ 2-56

POST FLIGHT CHECK ................................................................. 2-58

FLIGHT HANDLING CHARACTERISTICS .................................. 2-59ENGINE LIMIT GOVERNING .................................................. 2-59CLIMB SPEED ......................................................................... 2-60AUTOROTATIVE DESCENT ................................................... 2-60STEEP APPROACHES AND VERTICAL DESCENT MANOEUVRES........................................................................ 2-60

EDU 1 CAUTIONARY CAPTION DEFINITIONS .......................... 2-61

EDU 1 ADVISORY CAPTION DEFINITIONS ............................... 2-62

EDU 2 ADVISORY CAPTION DEFINITIONS ............................... 2-63

VOICE ONLY ADVISORY............................................................. 2-63

EFIS WARNING/CAUTION/ADVISORY SYSTEM ....................... 2-64


EASA Approved 11-12-09 Page 2-iii

LIST OF FIGURES

Page

Figure 2-1 Pre-flight Check Sequence...................................... 2-3

Figure 2-2 IGN Circuit Breakers Location ............................... 2-37


Page 2-iv 11-12-09 EASA ApprovedRev. 2

LIST OF TABLES

Page

Table 2-1 Warnings Annunciation Captions ......................... 2-64

Table 2-2 Caution Annunciation Captions ............................ 2-65

Table 2-3 Advisory Annunciation Captions .......................... 2-69

Table 2-4 AFCS Alerts Captions .......................................... 2-71

AW109SP RFM Section 2Document N109G0040A018 Normal Procedures


SECTION 2NORMAL PROCEDURES

GENERALThis section contains instructions and procedures for operating thehelicopter from the planning stage, through actual flight conditions, tosecuring the helicopter after landing.

Normal and standard conditions are assumed in these procedures.Pertinent data in other sections is referenced when applicable.

The instructions and procedures contained herein are written for thepurpose of standardization and are not applicable to all situations.

The minimum and maximum limits, and the normal and cautionaryoperating ranges for the helicopter and its subsystems are indicatedby instrument markings and placards. Refer to Section 1 for details ofthe operating limitations.

Each time an operating limitation is exceeded, a malfunction or anemergency occurs, an appropriate entry shall be made in the logbook(airframe, engine, etc.). The entry shall state which limit wasexceeded, the duration of time, the extreme value attained, and anyadditional information essential in determining the maintenance actionrequired. As an aid to this task, the IDS software includes logs of limitexceed data, fault data, and caution and warning signals which arestored in a Non-Volatile Memory for subsequent retrieval.

Section 2 AW109SP RFMNormal Procedures Document N109G0040A018


FLIGHT PLANNINGEach flight must be planned adequately to ensure safe operations andto provide the pilot with the data to be used during the flight.

Essential weight and balance, and performance information should becompiled as follows:- Check type of mission to be performed and destination.- Select appropriate performance charts to be used from Section 4.- Review the appropriate Supplements of this Rotorcraft Flight Manual

for the optional equipment installed.Ascertain proper weight and balance of the helicopter as follows:- Consult Section 6 - Weight and Balance;- Ascertain weight of fuel, oil, payload, etc;- Compute take-off and anticipated landing gross weights;- Check helicopter center of gravity (CG) locations;- Check that the weight and CG limitations in Section 1 are not

exceeded during the flight.

PRE-FLIGHT CHECKS

GENERAL

Preflight checks are to be performed by the pilot in order to confirmthat the helicopter is flightworthy and adequately equipped.

The checks are categorised as follows:- First flight of the day- Every flight

Checks marked with an arrow ( ) are required before the firs

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