unmaintained copy for information only aw139 quick reference handbook

UNMAINTAINED COPYFOR INFORMATION ONLY

AGUSTA PUB. CODE: 502500033 Page i

AW139-QRH

AW139

QUICK REFERENCE HANDBOOKISSUE 1 : 15 09 2006Rev. 21 : 09 08 2010

Source Document :RFM Document No. 139G0290X002ISSUE 1 : 22-08-2006 - Rev. See Record of Revisions

AW139 and AB139 are two names of the same product.

They identify two batches of aircraft manufactured in conformity with a unique Type Certificate Data Sheet

Where not specifically declared, the content of this document is applicable to both AW139 and AB139 helicopters.

Continuing airworthiness criteria for the AW139 is developed and maintained by Agusta, who is the holder of the type certificate in the state of design.

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AW139-QRH

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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]

UNMAINTAINED COPYOR INFORMATION ONLY

Rev. 20 Page ii

AW139-QRH Table of Contents

TABLE OF CONTENTS

PageQRH General Information .......................................................... ivRecord of Revision..................................................................... A-1Record of Effective Pages ......................................................... B-1

PageLimitations ..............................................Lims-Norm-Perf 1 to 24bGW Ext 6800 kg (if applicable) ........ Lims-Norm-Perf GW1 to GW12

Alt Ext 19000 ft (if applicable)........... Lims-Norm-Perf ALT1 to ALT6Normal Procedures .................................. Lims-Norm-Perf 25 to 62Performance Data..................................... Lims-Norm-Perf 63 to 72Emergency and Malfunction Procedures................................................. Emerg-Malfunc 1 to 100


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Rev. 19 Page iv

AW139-QRH

QRH GENERAL INFORMATIONCONTENT. The QRH consists of 4 sections which have been grouped intotwo parts. The first part combines Limitations, Normal Procedures and Per-formance Data. The second part contains Emergency/Malfunction Proce-dures. The two parts are mounted back-to-back to allow quick access toeither.

The various sections/systems are colour tabbed for ease and quickness oflocating the page required.

A Index of Content is included at the start of each of the two parts.

FLIGHT MANUAL. The QRH does not replace the RFM, however, all infor-mation contained in the QRH is based on the RFM. To operate the aircraftsafely and efficiently, the RFM must be read and thoroughly understood.

If any conflict should exist between this QRH and the Approved RFM theRFM shall take precedence.

QRH Limitations: The limitations have been copied from the RFM, how-ever any limitations that are covered by colour markings on the PFD/MFD(e.g engine limits, rotor limits) have not been included.

QRH Normal Procedures: The normal procedures have been copied fromthe RFM, CAT A and CAT B procedures have been included.

QRH Performance: The performance data includes only the Power Assur-ance Charts and, in tabulated data format, Hover Ceiling, Rate Of Climband Fuel Consumption.

QRH Emergency and Malfunction Procedure: The procedures havebeen copied from the RFM and grouped into systems. The systems arethen highlighted with RED tabs for Emergency Procedures, AMBER tabs forMalfunction Procedures, which have been placed in alphabetical order.

Additionally a table of Warning and Caution messages and the appropriatepage number for the procedure is included at the start of each section(Emergency/Malfunction) to aid in rapid location of the correct page.

Optional Equipment: The QRH includes Limitations, Procedures andEmergency Malfunction Procedures on a small number of Optional Equi-pent Suppleents that may be applicable to the aircraft. The RFM must beconsulted for comprehensive information and applicability of the Limitations,Normal Procedures etc. for the Optional Equipment Supplements that areincluded on the aircraft.

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AW139-QRH Record of
Revisions
Record of Revisions

NoteFor revisions of the RFM which do not affectthe QRH no revision of the QRH is carried out.

REVISIONNo. Date Basis of Revision Notes

Issue 1 15-09-2006 AW139-RFM-4D Issue 1 -Rev. 1 14-12-2006 AW139-RFM-4D Issue 1

Rev. 1-

Rev. 2 11-05-2007 AW139-RFM-4D Issue 1Rev. 2

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-


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-

Rev. 6 and 7 06-12-2007 AW139-RFM-4D Issue 1Rev. 6 and 7

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-

Rev. 11, 12 and 13

18-12-2008 AW139-RFM-4D Issue 1Rev. 11, 12 and 13

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AW139-QRH Record ofRevisions

Page A-2TOC, RECof REVS

AW139-QRH Record ofEffective Pages

Record of effective pages

PAGE REVISION N°

i 21ii 20iii and iv 19A-1 21A-2 0B-1 thru B-3 21B-4 20

LIMITATIONS, NORMAL PROCEDURES AND

PERFORMANCE DATA1 192 03 164 thru 6 197 and 8 209 010 blank 011 312 and 13 1614 blank 015 1616 017 418 and 19 019a and 19b 1620 blank 020a 2120b 1921 1922 1323 and 24 2124a 2124b 15GW1 19GW2 20GW3 thru GW12 19ALT1 thru ALT6 19

25 1926 2026a 1626b blank 1627 028 thru 30 231 2132 and 33 1534 2135 and 36 237 838 and 39 240 blank 041 1942 1743 1544 045 and 46 447 1648 2148a 1648b 2148c 1648d blank 1649 and 50 251 1352 1053 and 54 1654a 2054b 1654c 2154d blank 1655 1056 2156a thru 56d 2157 thru 60 361 15

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62 2063 1564 and 65 1966 1567 and 68 2069 and 70 071 2072 19

EMERGENCY AND MALFUNCTION PROCEDURES

1 and 2 03 194 thru 6 157 and 8 169 1910 2111 2012 213 014 315 1516 317 2118 and 19 1520 1621 1522 and 23 2024 1524a thru 24d (*) 1925 2126 2027 and 28 229 030 331 1532 2133 and 34 1535 and 36 21

PAGE REVISION N°

37 and 38 2039 and 40 1540a 1540b thru 40d 2141 1542 2143 2044 and 45 1546 047 2048 2149 750 2151 and 52 1552a 1552b blank 1553 2054 1655 2156 1657 058 and 59 1660 and 61 062 1563 and 64 2064a and 64b 2065 2066 267 068 269 1670 2171 1672 thru 74 275 076 2177 1578 20

PAGE REVISION N°


Page B-2 Rev. 21


(*) Yellow pages, T.C. only

78a 1578b blank 1579 and 80 081 2082 582a and 82b 583 584 385 1986 2086a 2086b and 86c 2186d 1587 2088 1689 thru 91 092 blank 093 thru 96 1696a 1696b 1797 1698 1799 and 100 16

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Page B-2 Rev. 20Page B-4

AW139-QRH

GENWT/CGSPD ALT

ENG FUEL

ABORTDRY MOTENGSTART

TAXI T-O

MISC

PRESTART

IN

FD/FMS

TEMP

LUB HYD

EXTN

CAT A/B

FLIGHT

OPER

POST LDSHT DN

HVR ROCFL CONS

CAPTSMSGS

SYSCHECKS

CHECKS

H-VCAT A/B

LANDAPPR

Hd PAVFLYAWAY

GENERAL, TYPE OF OPER, MIN CREW, WEIGHT, CG LIMITATIONS

SPEED, ALTITUDE, TEMP LIMITATIONS

H-V, CAT B/A LIMITATIONS

ENGINE, FUEL, LUBRICANTS, HYDRAULICS LIMITATIONS

MISCELLANEOUS LIMITATIONS

GENERAL, FLIGHT PLANNING, EXTERNAL CHECKS

PRE-START CHECKS

ABORTED ENGINE START DRY MOTORING PROCEDURE

ENGINE START PROCEDURE

SYSTEM CHECKS

TAXIING, PRE-TAKE OFF, TAKE OFF

IN FLIGHT PROCEDURES

APPROACH, LANDING CAT B/A

POST LANDING & SHUTDOWN

FLIGHT MANAGEMENT SYSTEM OPER-ATIONADVISORY CAPTIONS, PDF MESSAGESDENSITY ALTITUDE, POWER ASSUR,CAT B & A DISTANCE CHARTSHOVER CEILING, ROC, FUEL CONSUMPTION

LI

MITS

GENERAL, TYPE OF OPER, MIN CREW, WEIGHT, CG LIMITATIONS

SPEED, ALTITUDE, TEMP LIMITATIONS

H-V, CAT A/B LIMITATIONS

ENGINE, FUEL, LUBRICANTS, HYDRAULICS LIMITATIONSMISCELLANEOUS LIMITATIONS(GW EXT, ALT EXT if applicable)GENERAL, FLIGHT PLANNING, EXTERNAL CHECKS

PRE-START CHECKS

ABORTED ENGINE START DRY MOTORING PROCEDURE

ENGINE START PROCEDURE

SYSTEM CHECKS

TAXIING, PRE-TAKE OFF, TAKE-OFF CAT A/B

IN FLIGHT PROCEDURES

APPROACH, LANDING CAT A/B

POST LANDING & SHUTDOWN

FLIGHT DIRECTOR AND FLIGHT MANAGEMENT SYSTEM OPERATIONADVISORY CAPTIONS, PDF MESSAGESDENSITY ALTITUDE, POWER ASSURFLYAWAY HEIGHT LOSSHOVER CEILING, ROC, FUEL CONSUMPTION

N

O

R

M

A

L

PROCEDURES

PE

RF

LI

MITS


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AW139-QRH

USE OF WARNINGS, CAUTIONS AND NOTESWarnings, Cautions and Notes are used to emphasize important and criticalinstructions and are used as follows:

WARNINGAn operating procedure, practice, etc., which, ifnot correctly followed, could result in personalinjury or loss of life.

CAUTION

An operating procedure, practice, etc., which, ifnot strictly observed, could result in damage to, ordestruction of, equipment.

NoteAn operating procedure, condition, etc., which is essential tohighlight.

USE OF PROCEDURAL WORDSThe concept of procedural word usage and intended meaning which hasbeen adhered to in preparing this QRH is as follows:

”Shall” or ”Must” have been used only when application of a procedure ismandatory.”Should” has been used only when application of a procedure is re-com-mended.”May” has been used only when application of a procedure is optional.”Will” has been used only to indicate future events, not to indicate a manda-tory procedure.”Condition” has been used to determine if the item under examination pre-sents external damage which could jeopardize its safe operation.”Secure” has been used to determine if the item under examination is cor-rectly locked, referring to doors and disconnectable items, or correctly posi-tioned and installed.


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AW139-QRH

LIMITATIONSGENERAL....................................................................................... 7TYPES OF OPERATION................................................................. 7MINIMUM FLIGHT CREW .............................................................. 7NUMBER OF OCCUPANTS ........................................................... 7WEIGHT AND CENTER OF GRAVITY LIMITATIONS................... 7AIRSPEED LIMITATIONS .............................................................. 11GROUND SPEED LIMITATIONS ................................................... 11WIND SPEED LIMITATIONS FOR ROTOR STARTING & STOPPING ............................................................... 12ALTITUDE LIMITATIONS ............................................................... 12AMBIENT AIR TEMPERATURE LIMITATIONS (OAT) .................. 12MANOEUVRING LIMITATIONS ..................................................... 12ICING LIMITATIONS....................................................................... 12AUTOROTATION LIMITATIONS .................................................... 12SLOPE LIMITATIONS .................................................................... 13ALTITUDE AND TEMPERATURE LIMITATIONS CHART ............ 13HEIGHT- VELOCITY LIMITATIONS ............................................... 15CAT A MISCELLANEOUS LIMITATIONS...................................... 15HEIGHT - VELOCITY DIAGRAM.................................................... 16CATEGORY B OPERATION LIMITATIONS................................... 17CATEGORY A OPERATION LIMITATIONS................................... 18ENGINE AND TRANSMISSION DIGITAL LIMITATIONS ............ 20aENGINE LIMITATIONS................................................................... 21

ENGINE STARTER DUTY CYCLE. . . . . . . . . . . . . . . . . . . . . . 21POWER MARGIN TREND MONITORING . . . . . . . . . . . . . . . . 21ENGINE TRAINING MODE LIMITATIONS. . . . . . . . . . . . . . . . 21

FUEL LIMITATIONS ....................................................................... 21FUEL CAPACITIES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21UNUSABLE FUEL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21AUTHORIZED FUEL TYPES . . . . . . . . . . . . . . . . . . . . . . . . . . 21

LUBRICANT LIMITATIONS............................................................ 22AUTHORIZED ENGINE OILS . . . . . . . . . . . . . . . . . . . . . . . . . . 22AUTHORIZED TRANSMISSION OIL . . . . . . . . . . . . . . . . . . . . 22ELECTRICAL HYDRAULIC PUMP. . . . . . . . . . . . . . . . . . . . . . 22AUTHORIZED HYDRAULIC FLUIDS . . . . . . . . . . . . . . . . . . . . 22


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AW139-QRH

MISCELLANEOUS LIMITATIONS................................................. 23DC GENERATOR LOAD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23WHEEL BRAKE LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . 23PITOT HEATING LIMITATIONS. . . . . . . . . . . . . . . . . . . . . . . . 23AUTOMATIC FLIGHT CONTROL SYSTEM LIMITATIONS. . . 23AVIONIC LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23FLIGHT DIRECTOR LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . 24FMS AND GPS LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . 24bTORQUE LIMITER FUNCTION . . . . . . . . . . . . . . . . . . . . . . . . 24bENGINE EEC LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . 24bSYNOPTIC MFD PAGE LIMITATIONS . . . . . . . . . . . . . . . . . . 24bHEADSET/HELMET LIMITATIONS . . . . . . . . . . . . . . . . . . . . . 24bINCREASED GROSS WEIGHT 6800 KG (IF APPLICABLE). GW1T-O & LANDING ALTITUDE EXTENSION (IF APPLICABLE) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ALT1

NORMAL PROCEDURESGENERAL ...................................................................................... 25FLIGHT PLANNING ....................................................................... 25

CAT B WEIGHT AND H-V DETERMINATION .......................... 25CATEGORY A PROCEDURES................................................. 25CATEGORY A TAKE OFF......................................................... 25VERTICAL PROCEDURE ......................................................... 25SHORT FIELD PROCEDURE................................................... 25BACK UP PROCEDURE........................................................... 25CLEAR AREA PROCEDURE.................................................... 25CONFINED AREA PROCEDURE ............................................. 26OFFSHORE HELIDECK PROCEDURE.................................... 26CATEGORY A LANDING .......................................................... 26HELIPORT/HELIDECK PROCEDURE...................................... 26CLEAR AREA PROCEDURE.................................................... 26CONFINED AREA PROCEDURE ............................................. 26OFFSHORE HELIDECK PROCEDURE................................... 26a

GROSS WEIGHT AND CENTER OF GRAVITY ........................... 26aCOLD WEATHER OPERATION ................................................... 26aEXTERNAL PRE-FLIGHT CHECKS.............................................. 27COCKPIT/ENGINE PRE-START CHECKS ................................... 31ABORTED ENGINE START PROCEDURES ................................ 35DRY MOTORING PROCEDURE.................................................... 36NORMAL ENGINE START............................................................. 37QUICK ENGINE START................................................................. 39SYSTEM CHECKS......................................................................... 41TAXIING.......................................................................................... 43


Lims-Norm-Perf Page 4 Rev. 19

AW139-QRH

PRE TAKE-OFF CHECKS.............................................................. 43TAKE-OFF PROCEDURES ............................................................ 44

TAKE-OFF CATEGORY B PROCEDURE................................. 44CATEGORY A TAKE-OFF GENERAL........................................45CATEGORY A TAKE-OFF VERTICAL, SHORT FIELD AND BACK UP PROCEDURE................................................... 45CATEGORY A TAKE-OFF CLEAR AREA PROCEDURE ......... 46CATEGORY A TAKE-OFF CONFINED AREA PROCEDURE ...47CATEGORY A TAKE-OFF OFFSHORE HELIDECK PROCEDURE ............................................................................48a

SLOPING GROUND OPERATION................................................ 48cTAKE OFF PROCEDURE......................................................... 48c

IN-FLIGHT PROCEDURES ............................................................ 49AFTER TAKE-OFF..................................................................... 49CLIMB CHECKS ........................................................................ 49CRUISE CHECKS...................................................................... 49

APPROACH AND LANDING.......................................................... 51PRE-LANDING CHECKS........................................................... 51

LANDING ........................................................................................ 52CATEGORY B LANDING PROCEDURE................................... 52CATEGORY A LANDING GENERAL..........................................52CATEGORY A HELIPORT LANDING PROCEDURE................ 52CATEGORY A CLEAR AREA LANDING PROCEDURE........... 53CATEGORY A CONFINED AREA LANDING PROCEDURE .... 53CATEGORY A OFFSHORE HELIDECK LANDING PROCEDURE ........................................................................... 54a

SLOPING GROUND OPERATION................................................ 54cLANDING PROCEDURE .......................................................... 54c

POST LANDING AND SHUTDOWN PROCEDURES.................... 55POST LANDING CHECKS......................................................... 55PRE-SHUTDOWN CHECKS...................................................... 55ENGINES AND ROTOR SHUTDOWN ...................................... 55POST SHUTDOWN CHECKS ................................................... 56

FLIGHT DIRECTOR COUPLED AND UNCOUPLED OPERATIONS................................................................................ 56a

COLLECTIVE PI LIMITING FUNCTION . . . . . . . . . . . . . . . . . 56aSAFETY FLY-UP FUNCTIONALITY WHEN FD MODES ENGAGED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56aSPECIFIC MODE INFORMATION . . . . . . . . . . . . . . . . . . . . . . 56b

FMS OPERATION NORMAL PROCEDURES ............................... 57GENERAL .................................................................................. 57BASIC OPERATIONS................................................................ 57AUTOPILOT COUPLED OPERATIONS WITH FLIGHT DIRECTOR (IF FITTED) ............................................................ 59



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AW139-QRH

FMS ADVISORY ANNUNCIATORS.......................................... 59

ADVISORY CAPTIONS DEFINITIONS.......................................... 61PFD MESSAGES ........................................................................... 62

PERFORMANCEDENSITY ALTITUDE CHART........................................................ 63PWC\PT6C-67C HOVER POWER CHART 100%NR .................... 64PWC\PT6C-67C HOVER POWER CHART 102%NR .................... 65HEIGHT LOSS DURING FLYAWAY MONOEUVRE .................... 66HOVER CEILING .......................................................................... 67RATE OF CLIMB AT 6400 kg AEO............................................... 69RATE OF CLIMB AT 6400 kg OEI ................................................ 69FUEL CONSUMPTION AT 6400kg ............................................... 70HOVER CEILING 6800 kg (if applicable) ..................................... 71RATE OF CLIMB AT 6800 kg AEO (if applicable)....................... 71RATE OF CLIMB AT 6800 kg OEI (if applicable) ........................ 71FUEL CONSUMPTION AT 6800 kg (if applicable) ...................... 72



AW139-QRH

GENWT/CG

LIMITATIONSGENERALThis QRH includes:

• Information from RFM Sections 1, 2, 3 and limited data from Section 4.

• Optional Supplements included: Heater, Rotor Brake, Flight Director,CATEGORY A, Increased Gross Weight 6800 kg and Take Off andLanding Altitude Extension.

TYPES OF OPERATIONIn the basic configuration the rotorcraft is approved CAT B and CAT Aoperations for Day/Night VFR and Day/Night IFR operations.

CAT A Take Off and Landing can be carried out from the right or left handseat.

MINIMUM FLIGHT CREWSee Basic Flight Manual

When CAT A Take Off or Landing is carried out from left hand seat or theCAT A Offshore Helideck procedure is required, minimum flight crew is 2pilots

NUMBER OF OCCUPANTSThe total number of occupants, including the crew, shall not exceed:

— low density configuration 14

— high density configuration 17

— Each occupant must have a seat and seat belt.

— The low density or high density configuration may have a reducednumber of passenger seats installed in cabin. A minimum of 3 seats, inat least one row, must be installed.

— After seat removal or installation the new empty weight and C of Gposition must be determined to ensure C of G limits are not exceeded.

WEIGHT AND CENTER OF GRAVITY LIMITATIONSWEIGHT

Minimum flight/rotor running gross weight ...................................... 4400 kg

Maximum towing or taxi gross weight .............................................. 6450 kg

Maximum gross weight for take-off/landing..................................... 6400 kg

CAT B WAT Limitations chart ...................................................... Figure 1-5

CAT A Heliport Vertical, Short Field and Back Up Procedure WAT Limitations chart....................................................................Figure 1-6

CAT A Clear Area WAT Limitations chart ......................................Figure 1-7

CAT A Confined Area WAT Limitations chart ................................Figure 1-8

CAT A Offshore Helideck WAT Limitations chart...........................Figure 1-9



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AW139-QRH

GENWT/CG

CENTER OF GRAVITY

Longitudinal limits ............................................................... See Figure 1-1

Lateral limits ....................................................................... See Figure 1-2

Figure 1-1 Weight and Longitudinal CG Envelope

MA

ST

5.5

04

5.1

80

6400

4400

5.0

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6400

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55.1

5.2

5.3

5.4

5.5

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5.7

ST

A [m

]

Weight [Kg]

ICN

-39

-A-1

51

00

0-A

-A0

12

6-0

00

1-A

-06

-11

39

G1

58

0A

00

6 issu

e A



AW139-QRH

GENWT/CG

Figure 1-2 Weight and Lateral CG Envelope

-0.088

6400

+0.090-0.070

+0.120

4400

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BL [m]

Weig

ht [k

g]

139G0290T044/2 issue A ICN-39-A-151000-A-A0126-0002-A-05-1



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AW139-QRH

SPD ALTTEMP

AIRSPEED LIMITATIONSMaximum airspeed with Take-Off Power .......................................... 90 KIAS

Maximum airspeed with NR at 102% ............................................... 90 KIAS

Maximum airspeed in sideward or rearward flight ........................ Figure 1-5

Maximum allowable tailwind and crosswind ................................. Figure 1-5

Maximum airspeed for landing gear VLO or VLE.........................150 KIAS orVne if less

Minimum airspeed for flight under IFR (Vmini) ................................ 50 KIAS

Maximum airspeed for IFR approach ............................................. 150 KIAS

Maximum airspeed for climb with one AP failed............................. 100 KIAS

Maximum rate of climb with one AP failed...................................... 1000 fpm

Maximum airspeed with one AP failed ........................................... 140 KIAS

Maximum airspeed for operation of windscreen wipers ................. 140 KIAS

Minimum airspeed in autorotation .................................................... 40 KIAS

CAT A Take-Off & Balked Landing Safety Speed (VTOSS/VBLSS):Vertical, Short Field and Back Up Procedures............................. 40 KIAS

Clear Area Procedure .................................................................. 50 KIAS

Best Rate Of Climb speed (VY) ............................Below 10000ft Hp 80 KIASAbove 10000ft Hp 70 KIAS

Maximum airspeed with right cabin door locked open....................100 KIAS

Maximum airspeed with left or both cabin doors locked open.......... 80 KIAS

Maximum airspeed for opening/closing cabin doors ........................ 80 KIAS

GROUND SPEED LIMITATIONSON PAVED SURFACES

Maximum taxi speed ....................................................................... 40 knots(above 20 knots nose wheel must be locked fore and aft)

Maximum for emergency landing speed(nose wheel locked in fore and aft position) ................................... 60 knots

Maximum towing speed .................................................... 37 km/hr(23mph)

Maximum GS with PARK BRAKE ON ................................................... 5 kts

ON GRASS SURFACES

Maximum taxi speed (nose wheel locked fore and aft) .................. 20 knots(above 10 knots nose wheel must be locked fore and aft)

Maximum speed for emergency landing(nose wheel locked fore and aft) .................................................... 40 knots



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AW139-QRH

SPD ALTTEMP

WIND SPEED LIMITATIONS FOR ROTOR STARTING & STOPPINGMaximum wind speed ..................................................................... 50 knots

NoteEach rotor starting and stopping in wind speeds above 27ktsmust be recorded in the helicopter log book.

ALTITUDE LIMITATIONSMaximum operating altitude ...................................................See Figure 1-3

Minimum operating altitude .................................................. See Figure 1-3

Maximum CAT B Take-Off and Landing altitude.................... See Figure 1-3

Maximum altitude for CAT A Heliport Vertical Take-Off Procedure:TDP 35ft ............................................................................ 14000ft Hp of Hd

whichever comes firstTDP 36ft to 70ft .................................................................... 7000ft Hp of Hd

whichever comes firstMaximum altitude for CAT A Short Field, Back Up and Clear Area Take-Off Procedures......................................... 14000ft Hp of Hd

whichever comes first

Maximum altitude for CAT A Heliport, Short Field or Clear Area Landing Procedures ........................................................... 14000ft Hp or Hd


Maximum altitude for CAT A Confined Area Take Offand Landing ....................................................................... 10000ft Hp or Hd


Maximum altitude for CAT A Offshore Helideck Take Offand Landing ......................................................................... 5000ft Hp or Hd


AMBIENT AIR TEMPERATURE LIMITATIONS (OAT)Minimum temperature for ground starting ............................................ -40°C

Maximum and minimum air temperature limitations ...............See Figure 1-3

MANOEUVRING LIMITATIONSAerobatic manoeuvres are prohibited.

ICING LIMITATIONSFlight into known icing conditions or freezing rain is prohibited.

AUTOROTATION LIMITATIONSPractice autorotative landings are prohibited.

During autorotation the ENG MODE select switch must not be retarded fromFLIGHT to IDLE except in an emergency.



AW139-QRH

SPD ALTTEMP

SLOPE LIMITATIONSSloped Take Off and Landing is limited to the following:

Nose up ...................................................................................................... 5°

Nose Down................................................................................................. 5°

Left Wing Low............................................................................................. 5°

Right Wing Low .......................................................................................... 5°

ALTITUDE AND TEMPERATURE LIMITATIONS CHART

Figure 1-3 Altitude - Temperature Limitations

ALTITUDE-OATEnvelope

ICN-39-A-151000-A-A0126-00004-B-01-1

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IT

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LIM

IT 20000 ft

Hd LIMIT

20000 ft

Hd LIMIT 14000 ft

Cat.A

ENVELOPE

Hd LIMIT 10000 ft

Confined Area

ENVELOPE

Hd LIMIT 5000 ft

Off-Shore

ENVELOPE



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AW139-QRH




AW139-QRH

H-VCAT A/B

HEIGHT- VELOCITY LIMITATIONSThe Height-Velocity diagram defines, in the event of a single engine fail-ure during take off, landing or other operation near the surface, a combi-nation of airspeed and height above ground from which a safe singleengine landing on a smooth, level and hard surface cannot be assured.

CAUTION

Prior to the determination of the H-V envelope the CATEGORYB weight should be defined for the ambient conditions. SeeFlight Planning in Section 2 for use of the CAT B W.A.T. and H-Venvelope charts.

Height Velocity Diagram .......................................................See Figure 1-4

CAT A MISCELLANEOUS LIMITATIONSGround and Elevated Heliport / Helideck Size

Minimum demonstrated heliport/helideck size for Vertical,Back Up and Offshore procedures .........................15 m x 15 m (50 ft x 50 ft) Diameter 15 m (50 ft)

Minimum demonstrated heliport size for Confined Areaprocedure ...............................................................20 m x 20 m (65 ft x 65 ft) or Diameter 20 m (65 ft)

Wind Limitations

Maximum cross wind component must not exceed 20 kts.

For the Offshore Helideck procedures for cross wind components between 10 kts and 20 kts a headwind component of at least 5 kts is required.

Take Off or Landing with tail wind is prohibited.

Heater Limitations

Heater must be switched off for Take Off and Landing.



F

AW139-QRH

H-VCAT A/B

HEIGHT - VELOCITY DIAGRAM

Figure 1-4 Height Velocity Limitations

139G0040A001 issue E ICN-39-A-151000-A-A0126-00008-A-02-1

0

2000

4000

6000

8000

10000

12000

14000P

ressu

rea

ltitu

de

-ft

OA

TLIM

ITIS

A+35°C

-40

-30

-20

-10

0O

AT

[°C]10

20

30

40

4800

5000

5200

5400

5600

5800

6000

6200

6400

NO H-V AREA

0 5 10 15 20 25

0

50

100

150

200

250

300

350

IAS - kt

He

igh

ta

bo

ve

gro

un

d-

ft

A

B

C2

C1

GR

OSS

WEIG

HT

[kg]

NO H-V AREA

NOH-V

AREA

NO

H-V

A

R

E

A

H V

(ft) (kts)

A 25 0

B 30 20



AW139-QRH

H-VCAT A/B

CATEGORY B OPERATION LIMITATIONS

Figure 1-5 CATEGORY B - Weight Limitations

WE

IGH

T-A

LT

ITU

DE

-TE

MP

ER

AT

UR

E

RO

TO

R1

00

%

13

9G

00

40

A0

01

issu

eG

ICN

-39

-A-1

51

00

0-A

-A0

12

6-0

00

05

-A-0

6-1

02

00

04

00

06

00

08

00

01

00

00

12

00

01

40

00

OAT

LIM

ITIS

A+35°C

Pre

ss

ure

alt

itu

de

-ft

-40

-30

-20

-10

OAT

0°C

10

20

30

40

50

45

00

50

00

55

00

60

00

65

00

45 KTAS and BELOW

45K

TAS40

KTA

S35K

TA

S30K

TA

S25K

TA

S

20K

TA

San

dB

ELO

W

GW

-k

g

for

TA

KE

-OF

F,L

AN

DIN

Gan

dIG

EM

AN

OE

UV

RE

S

RE

LA

TIV

EW

IND

AZ

IMU

TH

:10

to350

deg

NO

TE

:n

ow

ind

sp

ee

dlim

ita

tio

ne

xis

tsfo

rh

ea

dw

ind

co

nd

itio

ns

(win

da

zim

uth

±1

0d

eg

)



F

AW139-QRH

H-VCAT A/B

CATEGORY A OPERATION LIMITATIONS

Figure 1-6 CATEGORY A Ground and Elevated Heliport/Helideck Vertical, Back Up & Short Field Procedure Weight Limitations

WEIGHT-ALTITUDE-TEMPERATUREHELIPORT and SHORT FIELD

9.5 10 10.5 11 11.5 12 12.5 13 13.5

0

0.5

1

1.5

2

2.5

3

3.5

4

Pre

ssur

e A

ltitu

de -

[m x

100

0]

Gross Weight - [lb x 1000]

4.2 4.4 4.6 4.8 5 5.2 5.4 5.6 5.8 6 6.2 6.4 6.6-1

0

1

2

3

4

5

6

7

8

9

10

11

12

13

14

Pre

ssur

e A

ltitu

de -

[ft x

100

0]

Gross Weight - [kg x 1000]

-40

-30

-20

-10

0

10

20

3040

50

MAX OAT LIM

IT

Hd

LIM

IT

ICN-39-A-155000-A-A0126-12204-B-01-1



AW139-QRH

H-VCAT A/B

Figure 1-7 CATEGORY A Clear Area Procedure Weight Limitations

WEIGHT-ALTITUDE-TEMPERATURECLEAR AREA

ICN-39-A-155000-A-A0126-12201-B-01-1

9.5 10 10.5 11 11.5 12 12.5 13 13.5

0

0.5

1

1.5

2

2.5

3

3.5

4

Pre

ssur

e A

ltitu

de -

[m x

100

0]


4.2 4.4 4.6 4.8 5 5.2 5.4 5.6 5.8 6 6.2 6.4 6.6-1

0

1

2

3

4

5

6

7

8

9

10

11

12

13

14

Pre

ssur

e A

ltitu

de -

[ft x

100

0]


-40

-30

-20

-100

10

20

30

40

MAX OAT LIMIT

Hd

LIM

IT



F

AW139-QRH

H-VCAT A/B

Figure 1-8 CATEGORY A Ground and Elevated Heliport Confined Area Procedure Weight Limitations

WEIGHT-ALTITUDE-TEMPERATURECONFINED AREA

ROTOR SPEED 102%

139G1580A012 issue A ICN-39-A-155000-G-A0126-12248-A-01-1

95 100 105 110 115 120 125 130 135 140 145

0

0.5

1

1.5

2

2.5

3

Gross weight - [lb x 100]

Pre

ss

ure

alt

itu

de

- [m

x 1

00

0]

42 44 46 48 50 52 54 56 58 60 62 64 66

0

1

2

3

4

5

6

7

8

9

10


Pre

ss

ure

alt

itu

de

- [f

t x

10

00

]

OAT [°C]________ISA+35°C

---------

-40-30

-20-10

010

2030

4050

MA

X O

AT L

IMIT

Hd

LIM

IT


Lims-Norm-Perf Page 19a Rev. 16

AW139-QRH

H-VCAT A/B

Figure 1-9 CATEGORY A Offshore Helideck Procedure Weight Limitations

WEIGHT-ALTITUDE-TEMPERATUREOFF-SHORE HELIDECK PROCEDURE

ROTOR SPEED 102%


13 13.5 14 14.5 15

0

0.5

1

1.5


Pre

ss

ure

Alt

itu

de

- [

m x

10

00

]

0

1

2

3

4

5

Pre

ss

ure

Alt

itu

de

- [

ft x

10

00

]

-40-30

-20

-10

0

10

20

30

40

50

MA

X

OA

T

LIM

IT

Hd

LIM

IT

5.8 6 6.2 6.4 6.6 6.8 7

0

10

20


Head

win

dco

mp

on

en

t -

[kts

]

Operation in this area

is permitted only for

aircraft configured

for 6800 kg

(see Sup.50)


Rev. 16 Lims-Norm-Perf Page 19b

F

AW139-QRH




AW139-QRH

ENG FUELLUB HYD

ENGINE AND TRANSMISSION DIGITAL LIMITATIONSThe following represent the digital values for PFD and MFD limitations indicated by colours

NR

% 90 95 110

116

ITT

°C/%

869/

118.

210

00/1

36.0

Pow

er O

ffM

inim

um T

rans

ient

Min

imum

Con

tinuo

us

Max

imum

Con

tinuo

us

Max

imum

Tra

nsie

nt

Engi

ne S

tart

ing

Max

imum

Unl

imite

d

Max

imum

Tra

nsie

nt (2

sec

s)

NR

% 95 98 101

103

106* 85 90 101

103

106*

Nf % 95 98 10

1

103

106* 85 90 101

103

106*

ITT

°C/%

735/

100.

077

5/10

5.4

847/

115.

2

775/

105.

483

5/11

3.6

847/

115.

2

Ng

%

55.0

100.

010

2.4

107.

0

102.

410

6.0

107.

0

PI&

TQ %

100

110

121

140

160

176

All

Engi

nes

Ope

ratin

gM

inim

um T

rans

ient

Min

imum

Con

tinuo

us

Max

imum

Con

tinuo

us

Max

imum

Tak

e O

ff (5

min

)

Cau

tiona

ry

Max

imum

Tra

nsie

nt (

5 se

cs)

One

Eng

ine

Inop

erat

ive

Min

imum

Tra

nsie

nt

Min

imum

Con

tinou

ous

Max

imum

Con

tinuo

us

Max

imum

2.5

min

OE

I

Cau

tiona

ry

Max

imum

Tra

nsie

nt (5

sec

s)

* 10

seco

nd tr

ansi

ent


Rev. 21 Lims-Norm-Perf Page 20a

F

AW139-QRH

ENG FUELLUB HYD

HY

DO

P

BA

R

+180

+225

+250

ES

S B

US

VO

LTA

GE

22 29

HY

DO

T °C -4

0-2

0+1

19

+134

MA

IN B

US

VO

LTA

GE

22 29

TGB

OT

°C -40

+1 +110

Min

imum

Nor

mal

Ope

ratio

n

Max

imum

Nor

mal

Ope

ratio

n

IGB

OT

°C -40

+1 +110

MG

BO

P

BA

R

+2.3

+3.1

+6.0

MG

BO

T °C -4

0+1 +1

10

EO

P

BA

R

+4.2

+6.3

+8.9

+10

+15.

2

BAT

TER

Y L

OA

DA

MP

S

-200

+200

EO

T °C

%

-40

+10

+140

+145

+150

Min

imum

for S

tarti

ng a

nd G

I

Min

imum

Nor

mal

Ope

ratio

n

Max

imum

Nor

mal

Ope

ratio

n

Max

imum

Cau

tiona

ry T

Q <

60%

Max

imum

Cau

tiona

ry fo

r eng

acc

el O

AT<0

°C

Max

imum

Cau

tiona

ry

Max

imum

for E

ngin

e St

art (

5 m

in)

Max

imum

Tra

nsie

nt (1

min

)

Max

imum

Bat

tery

Dis

char

ge

Max

imum

Bat

tery

Cha

rge


Lims-Norm-Perf Page 20b Rev. 19

AW139-QRH

ENG FUELLUB HYD

ENGINE LIMITATIONSENGINE STARTER DUTY CYCLE

45 seconds on, 1 minute off.45 seconds on, 1 minute off45 seconds on, 30 minutes off

POWER MARGIN TREND MONITORING

Every 50 flight hours record engine power assurance check values forengine power margin trend monitoring purposes.

ENGINE TRAINING MODE LIMITATIONS

Selection of Engine Training Mode (OEI TNG) is permitted only forCategory A Training in OEI simulated conditions.

CAUTION

Intentional use of actual OEI rating for training is prohibited.

FUEL LIMITATIONSFUEL CAPACITIES

Total Usable...................................................................................1588 litresUnusable ..........................................................................................20 litres

UNUSABLE FUEL

In coordinated (ball centered) flight: ................................. 0kg (0lb) indicated/(8 kg(18lb)/10 litres per tank actual)

Hovering in cross winds or sideways flight with sustained roll anglesgreater than ±15° is prohibited when fuel indication, in either tank, is lessthan 70kg.

Cross feeding (tank with pump off, not supplying engines)...................................................................................Maximum 228 kg/500lb

NoteDuring XFEED the unusable fuel level indication will change togrey to indicate the tank can no longer supply fuel.

AUTHORIZED FUEL TYPESThe fuels shown in the table below have been authorized for use with thePratt and Whitney PT6C-67C engines:

FuelType

ApplicableSpecification

FuelType


JET A

JET A-1

JP5

JP8

ASTM D1655

ASTM D1655

DEF STAN 91-86 AVCAT/FSIIMIL -PRF-5624FNATO Code F-44

DEF STAN 91-87-2002

JP8

JP8+100

GOST 10227RTGOST 10227TS1

AVTUR/FSIIMIL -T-83138DNATO Code F-34

Aeroshell Performance Additive 101

GOST 10227-86GOST 10227-86(See RFM restrictions)



F

AW139-QRH

ENG FUELLUB HYD

LUBRICANT LIMITATIONSAUTHORIZED ENGINE OILSThe oils shown in the table below have been authorized for use with thePratt and Whitney PT6C-67C engines. Any brand approved under theapplicable specification may be used.

CAUTION

Mixing of any oils, by type, specification or brand name, is prohibited.

AUTHORIZED TRANSMISSION OIL

ELECTRICAL HYDRAULIC PUMPThe electrical hydraulic pump is for ground operation only.

AUTHORIZED HYDRAULIC FLUIDSThe hydraulic fluids shown in the table below have been authorized foruse in all hydraulic components. Any brand approved under the applica-ble specifications may be used.

NoteMIL-PRF-5606 can be used for enhanced performance ofhydraulic system in low temperature environments below -30°C.

CAUTION

Mixing of hydraulic liquid, by specification or brand name, is prohibited.

OilType


Brand Names(For reference only)

Type I(3cs)

PWC 521 BP Turbo Oil 2389Mobil Avrex S Turbo 256

Type II(5cs)

PWC 521 Aero-Shell Turbine Oil 500Castrol 5000Mobil Jet Oil IIRoyco Turbine Oil 500BP Turbo Oil 2380Turbonycoil 525-2A

ThirdGeneration(5 cs)

PWC 521 Aero Shell Turbine Oil 560Royco Turbine Oil 560Mobil Jet Oil 254

Applicable Specification Brand Names

MIL PRF23699F BP Turbo Oil 2380

Applicable Specification Brand Names (For reference only)MIL-PRF-83282 AEROSHELL FLUID 31

Alternative:

MIL-PRF-5606 (see NOTE below) AEROSHELL FLUID 41



AW139-QRH

MISC

MISCELLANEOUS LIMITATIONSDC GENERATOR LOAD

Normal Operation Range............................................................... 0 to 100%

Cautionary Range (for engine starting only).............................. 101 to 155%

Maximum Cautionary ........................................................................... 155%

(Maximum cautionary may be exceeded for maximum of 45 seconds forengine start only)

Max normal operating load up to 15000ft Hp ..........100% (equivalent 300A)

Max normal operating load above 15000ft Hp.................... reduce by 13.4%....................................................................................................every 1000ft

(See placard on RFM page 1-62 or, for aircraft fitted with EPIC S/W Phase 5or later, Supplement 68)

Max normal operating load 20000ft Hp .................................................. 33%

MPOG with generator load at 75% or less .......................No time limitations

MPOG with generator load greater than 75% ......................Max 20 minutes

WHEEL BRAKE LIMITATIONSMaximum running speed for brake application.................................40 knots

Parking on slopes up to 10° is permitted for a maximum of 1 hour.

PITOT HEATING LIMITATIONSPitot heating must be switched ON for conditions of visible moisture atindicated OAT of +4° C or less.

Pitot heating must be switched OFF at indicated OAT of +10° C or more.

AUTOMATIC FLIGHT CONTROL SYSTEM LIMITATIONS

Minimum AFCS configuration for VFR flight.....................2 AP in SAS mode

Minimum AFCS configuration for IFR flight ...................... 2 AP in ATT mode

Intentional ATT MODE de-selection during IFR flight is prohibited.

AVIONIC LIMITATIONS

ILS Mode Limitations

Maximum airspeed for glideslope up to 4 degrees........................ 150 KIAS

Maximum airspeed for glideslopes between 4 and 7.5 degrees (Steep Approach) ............................................... 120 KIAS

CAUTION

During steep approach, take care not to use less than 5% PI



F

AW139-QRH

MISC

FLIGHT DIRECTOR LIMITATIONS4 Axis Basic and Enhanced FD system

• Basic FD system only: HOV mode not operative

• SAR Guidance Controller, TD/H, MOT, WTR, modes only operative forEnhanced FD with EPIC Software Phase 5, or later, SAR modes operative.

• VNAV mode inoperative.

• Collective modes must not be engaged if either or both engines are in MANUAL MODE

• The RHT, TD, TDH, TU, MOT, WTR modes can only be engaged over flatsurfaces which are clear of obstacles (EPIC Software Phase 5 or later)

• The RHT must not be engaged in cruise over land (EPIC Software Phase 4 only)

FLIGHT DIRECTOR MODES ENGAGEMENT LIMITS AND MINIMUM USE HEIGHT (MUH)Hold Mode Applicable Range MUHIAS* 60 KIAS to

Vne less 5 KIAS150 ft AGL or 50 ft AGL during approach

HDG*/NAV*60 KIAS to Vne 150 ft AGL or

50 ft AGL during approach

APP*/BC*/GA* 60 KIAS to Vne 50 ft AGL

VS* 60 KIAS to Vne within -1500 fpm and 2000 fpm 150 ft AGL

ALT

0 KIAS to Vne

300 ft AGL (airspeedgreater than 55 KIAS50ft AGL in HOV or airspeedless than 55 KIAS(Enhanced FD system only)

DCL* 60 KIAS to Vne 50 ft AGL

ALTA* 60 KIAS to Vne 150 ft AGLRHT

0 to Vne 15 ft to 2000 ft AGL

150 ft AGL (airspeed greater than 55 KIAS)30 ft AGL in HOV or air-speed less than 55 KIAS)

GA 60 KIAS to Vne0 to 2000 ft AGL

N/A

HOVEnhanced FD systems only

Groundspeed — less than 60 kts forward— less than 40 kts lateral or aft

withIAS less than 75 KIAS

30 ft AGL

TUEnhanced FDPhase 5, or later

0 KIAS to 60 KIAS0 to 2000 ft AGL

150 ft AGL (airspeedgreater than 55KIAS)30 ft AGL in HOV (air-speed less than 55 KIAS)



AW139-QRH

MISC
For operations on the sea the MUH must be increased by one half the maxi-mum reported/observed wave height.
Note*— Automatic disengagement of these modes below 55 KIAS.— VS engagement above 2000 fpm or below -1500 fpm will result in the mode returning the aircraft to the maximum rates quoted (2000 fpm or -1500 fpm).

SAR Limitations

Flight below 50 KIAS (Vmini) in IMC is only permitted when coupled to a SARmode.

FD VOR Limitations

In case of invalid DME/FMS distance, select:

- VOR APP at ranges below 10 nm

- VOR NAV at ranges greater than 10 nm

VGP Limitations

When being radar vectored or autonomously flying to the final approachcourse, the VECTORS approach transition and/or ACT VECTORS functionmust be used to program the FMS for the approach and the flight crew mustensure that published altitudes are complied with.

FD ILS APPROACH MODE LIMITATION

The helicopter is certified to carry out CAT 1 ILS approaches up to 7.5 degglideslope.

Maximum recommended Localizer Intercept angle.................................45° ................................................................................................ ranges greater ...................................................................................................... than 10nm

Maximum recommended Localizer Intercept angle.................................30° ......................................................................................................ranges less ....................................................................................................... than 10nm

In case of invalid DME and FMS distance and with both Rad Alt signalsinvalid an ILS approach must be initiate at a distance of not less than 10 nm.

The following modes only available with Enhanced FD Phase 5, orlater, and SAR modes installedTD 60 KIAS to Vne

135 ft to 2000 ft AGL150 ft AGL

TDH 0 KIAS to 90 KIAS50 ft to 300 ft AGL

50 ft AGL

MOT0 KIAS to Vne50 ft to 2000 ft AGL

PTH - 50 ft AGLVPTH - 250 ft AGLVRHT - 150 ft AGLDCL - 50 ft AGL

WTR HOV Mode engaged 30 ft AGL

FLIGHT DIRECTOR MODES ENGAGEMENT LIMITS AND MINIMUM USE HEIGHT (MUH)



F

AW139-QRH

MISC

FMS AND GPS LIMITATIONS1. The software status stated in the Honeywell Flight Management System

(FMS) Pilot’s Manual for the Agusta AW139 must match that displayed on the equipment MCDU page at power up.

2. IFR en route and terminal navigation is prohibited unless the pilot verifies the currency of the Navigation Data Base (NDB) or verifies each selected waypoint for accuracy by reference to current approved data.

3. Instrument approaches must be carried out in accordance with approved instrument approach procedures that are retrieved from the FMS data base. The FMS data base must incorporate the current update cycle.

— For instrument approaches GPS integrity monitoring (RAIM)must be available at the Final Approach Fix.

NoteThe Pilot must not continue an instrument approach inside theFinal Approach Fix (FAF), unless the ‘APP’ advisory is displayedon the PFD. If during an instrument approach the amber ‘DGR’advisory in displayed, the pilot must initiate a missed approach.

— Use of ILS, LOC, LOC-BC, LDA, (landing directional aid),SDF(simplified directional facility) and MLS (microwave landingsystem) approaches are not authorized.

— When an alternate airport is required by the applicable operat-ing rules, it must be served by an approach based on other thanGPS navigation and the aircraft must have operational equip-ment capable of using that navigation aid, and the required nav-igation aid must be operational.

4. The aircraft must have other approved navigation equipment installed and operating appropriate to the route of flight.

TORQUE LIMITER FUNCTION

If TORQUE LIMITER is set, max AEO TQ available is 114%/114%

ENGINE EEC LIMITATIONS

In ambient conditions above 43°C, if the aircraft is to be parked withengine off, internal or external electrical power must not be supplied.

Electrical power may be supplied for Pre Start Checks and Engine Start.For maintenance checks refer to AW139 Maintenance Publication Docu-ment No. 39-A-AMP-00-P.

SYNOPTIC MFD PAGE LIMITATIONSIn case of MAU1(2) failure, do not refer to the electrical and hydraulic synop-tic page. The information presented is not reliable.

HEADSET/HELMET LIMITATIONSHeadset/Helmet type used in the aircraft must be of the same electrical char-acteristics and authorised by Aircraft Manufacturer.



AW139-QRH

GW EXT6800 kg

INCREASED GROSS WEIGHT 6800KG

General

For operations with Increased Gross Weight the aircraft must be in accor-dance with the requirements as detailed in RFM Supplement 50.

The following limitations are for operations between 6400 kg and 6800 kg,all other limitations remain unchanged.

Normal and Emergency Procedures remain unchanged

WEIGHT AND CENTER OF GRAVITY LIMITATIONSMaximum gross weight for towing ....................................................6450 kg

Maximum gross weight for taxiing ....................................................6800 kg

Maximum gross weight for take-off and landing...............................6800 kg

CAT B WAT Limitations chart ......................................... Figure GW EXT 5

CAT A Clear Area WAT Limitations chart ....................... Figure GW EXT 5

CAT A Confined Area WAT Limitations .......................... Figure GW EXT 6

CAT A Off Shore WAT Limitations chart .......................... Figure GW EXT 7

CENTER OF GRAVITYLongitudinal Limits........................................................... Figure GW EXT 1Lateral limits .................................................................... Figure GW EXT 2

AIRSPEED LIMITATIONSMaximum airspeed for weights above 6400kg ................ Figure GW EXT 3

Maximum airspeed in sideward or rearward flight for weights above 6400 kg ................................................................. Figure GW EXT 9

Maximum allowable tailwind and crosswind for weights above 6400 kg ................................................................. Figure GW EXT 9

GROUND SPEED LIMITATIONSMaximum taxi speed for weights above 6400kg............................. 20 knots

Maximum for emergency landing speed for weights above 6400kg(nose wheel locked in fore and aft position) .................................. 40 knots

Taxiing on grass surfaces at weights above 6400kg is prohibited

ALTITUDE LIMITATIONSMaximum operating altitude for weights above 6400kg ..... 8000 ft Hp or Hd................................................................................... whichever comes first

AMBIENT AIR TEMPERATURE LIMITATIONS (OAT)Maximum and minimum air temperature limitations for operations above 6400 kg............................................... Figure GW EXT 4

HEIGHT- VELOCITY LIMITATIONSHeight Velocity Diagram for weights above 6400kg ........ Figure GW EXT 8


GW Ext 6800 kg Lims-Norm-Perf Page GW1Rev. 19

F

AW139-QRH

GW EXT6800 kg

CAT A MISCELLANEOUS LIMITATIONSOffshore Heliport / Helideck SizeMinimum demonstrated helideck size for Take-Off and Landing for weights between 6400 kg & 6800 kgTake Off .......................................................................Diameter 15 m (50 ft)

..........................................................................or 15 m x 15 m (50 ft x 50 ft)

Landing........................................................................Diameter 22 m (72 ft).......................................................................... or 22 m x 22 m (72 ft x 72 ft)

PERFORMANCE INFORMATIONSingle Engine Failure in Hover OGE Flyaway procedureweights between 6400 kg and 6800 kg ......................... Figure GW EXT 10


Lims-Norm-Perf Page GW2 GW Ext 6800 kgRev. 20

AW139-QRH

GW EXT6800 kg

Figure GW EXT 1 Weight and Longitudinal CG Envelope 6800 kg

6400

6800

6800

5.2

38

4660

5170

5.0

71

5.0

00

4400

4850

5.5

36

6400

5.1

80

5.5

95

5.4

80

5.5

04

4200

4400

4600

4800

5000

5200

5400

5600

5800

6000

6200

6400

6600

6800

7000

4.9

55.1

5.2

5.3

5.4

5.5

5.6

5.7

ST

A [m

]

Weight [Kg]

IC

N-3

9-A

-155050-A

-A0126-1

0001-A

-01-1

139G

1580A

006 Issue A



F

AW139-QRH

GW EXT6800 kg

Figure GW EXT 2 Weight and Lateral CG Envelope 6800 kg

-0.066

+0.120

6800

4400

-0.088

6400

+0.09-0.07

4400

+0.084

6400

6800

4200

4400

4600

4800

5000

5200

5400

5600

5800

6000

6200

6400

6600

6800

7000

-0.12 -0.08 -0.04 0 0.04 0.08 0.12 0.16

BL [m]

Weig

ht [k

g]

139G1580A006 Issue A ICN-39-A-155050-A-A0126-1002-A-01-1



AW139-QRH

GW EXT6800 kg

Figure GW EXT 3 Vne Limitations for Weights above 6400 kg

0 H

p

ISA

5000

Hp

8000

Hp

ISA +35°C

10

40

50

100

110

120

130

140

150

160

170

-30

-20

-10

020

30

Power O

n

OEI/Power Off

Take

Off

and

-10000

-8000

-6000

-4000

-20000

2000

4000

6000

8000

10000

-35

-25

-15

-55

15

25

35

45

55

65

75

85

95

105

115

125

OU

TS

IDE

AIR

TE

MP

ER

AT

UR

E [

°C

] V

ne [

KIA

S]

DENSITY ALTITUDE [feet]

IC

N-3

9-A

-155050-A

-A0126-1

0005-A

-04-1

139G

1580A

006 Issue A

Lan

din

g L

imit

Off

sh

ore H

elid

eck O

nly



F

AW139-QRH

GW EXT6800 kg

Figure GW EXT 4 Altitude- Temperature Limitations for Weights above 6400 kg

ALTITUDE-OATEnvelope

ICN-39-A-155050-A-A0126-01006-A-04-1

-200

0

200

400

600

800

1000

1200

1400

1600

1800

2000

2200

2400

Pre

ssu

re A

ltit

ud

e -

[m

]

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

0

1000

2000

3000

4000

5000

6000

7000

8000

OAT - [°C]

Pre

ssu

re A

ltit

ud

e -

[ft

]

MIN

OA

T L

IMIT

MA

X O

AT

LIM

IT

Hd

LIM

IT 8

000

ft

Hd L

IMIT 8

000

ft

Hd L

IMIT 5

000 ft

Off-Shore ENVELOPE

Cat.A ENVELOPE



AW139-QRH

GW EXT6800 kg

Figure GW EXT 5 Weight Limitations CAT A Clear Area and CAT B for weights above 6400 kg

WEIGHT-ALTITUDE-TEMPERATURE

EAPS NOT INSTALLED

Cat.A NR=102%

Cat.B NR=100%

139G1580A006 issue C ICN-39-A-155050-A-A0126-10007-A-03-1

14.5 15

0

0.5

1

1.5

2


Pre

ss

ure

Alt

itu

de

- [

m x

10

00

]

6.4 6.6 6.8

0

1

2

3

4

5

6

7

8


Pre

ss

ure

Alt

itu

de

- [

ft x

10

00

]

-20-10

0

10

20

30

40

50

MAX

OAT

LIMIT

Hd

LIM

IT

OAT [°C]_______ISA+35°---------



F

AW139-QRH

GW EXT6800 kg

Figure GW EXT 6 Weight Limitations CAT A Confined Area for weights above 6400 kg

WEIGHT-ALTITUDE-TEMPERATURECONFINED AREA

ROTOR SPEED 102%


142 144 146 148 150 152

0

0.5

1

1.5

2

Gross weight - [lb x 100]

Pre

ssu

re a

ltit

ud

e-

[m x

1000]

64 65 66 67 68 69

0

1

2

3

4

5

6

7


Pre

ssu

re a

ltit

ud

e-

[ft

x 1

000]

-30

-20

-10

0

10

20

3040



AW139-QRH

GW EXT6800 kg

Figure GW EXT 7 Weight Limitations CAT A Offshore Helideck for weights up to 6800 kg

WEIGHT-ALTITUDE-TEMPERATUREOFF-SHORE HELIDECK PROCEDURE

ROTOR SPEED 102%


13 13.5 14 14.5 15

0

0.5

1

1.5


Pre

ssu

re A

ltit

ud

e -

[m

x 1

000]

0

1

2

3

4

5


Pre

ssu

re A

ltit

ud

e -

[ft

x 1

000]

-40

-30

-20

-10

0

10

20

30

40

50

MA

X

OA

T

LIM

IT

Hd

LIM

IT

5.8 6 6.2 6.4 6.6 6.8 7

0

10

20


Head

win

dco

mp

on

en

t -

[kts

]



F

AW139-QRH

GW EXT6800 kg

Figure GW EXT 8 Height Velocity Limitations for Weights above 6400 kg

HEIGHT-VELOCITY CHART

ZERO WIND

139G1580A006 issue C ICN-39-A-155050-A-A0126-10011-A-03-1

-1000

0

1000

2000

3000

4000

5000

6000

7000

8000

Pre

ssu

re a

ltitu

de

- ft

MAX

OAT LIM

IT

-30

-20

-10

0

10

20

30

40

50

THIS AREA

IS OUTSIDE THE

APPROVED

FLIGHT ENVELOPE

FOR WEIGHT

ABOVE 6400 kg

64006600

6800

NO H-V AREA

THIS AREA

IS OUTSIDE THE

APPROVED

FLIGHT ENVELOPE

FOR WEIGHT

ABOVE 6400 kg

0 5 10 15 20 25

0

50

100

150

200

250

300

350

IAS - kt

He

igh

t a

bo

ve

gro

un

d -

ft

AB

C2

C1

NO H-V AREA

NOH-V

AREA

NO

H-V

A

R

E

A

H V

(ft) (kts)

A 25 0

B 30 20



AW139-QRH

GW EXT6800 kg

Figure GW EXT 9 Controllability Envelope for Low Speed Manoeuvres for weights above 6400 kg

CO

NT

RO

LL

AB

ILIT

Y E

NV

EL

OP

E

RO

TO

R 1

00%

13

9G

15

80

A0

06

issu

e C

ICN

-39

-A-1

55

05

0-A

-A0

12

6-1

00

10

-A-0

3-1

0

2000

4000

6000

8000

Pre

ssu

re a

ltit

ud

e -

ft

MAX O

AT L

IMIT

-30

-20

-10

0

10

20

30

40

50

OA

T [

°C]

_______

ISA

+35°

----

----

-

10

20

30

40

50

Rela

tive w

ind

sp

eed

- k

ts



F

AW139-QRH

GW EXT6800 kg

HEIGHT LOSS DURING FLYAWAY MANOEUVRE WEIGHTS BETWEEN 6400 KG AND 6800 KG

Figure GW EXT 10 Height Loss During Flyaway Weights from 6400 kg to 6800 kg

139G

1560

A00

2 is

sue

BIC

N-3

9-A

-155

050-

A-A

0126

-100

13-A

-02-

1

0

500

1000

1500

2000

Pres

sure

alti

tude

- [m

]

20

30

40

50

60

Height loss - [m]

0

2000

4000

6000

Pres

sure

alti

tude

- [ft

]

MAX

O

AT L

IMIT

-30

-20

-10

010

2030

4050

OAT

- [°

C]

____

____

ISA

+35°

C---

----

6400

6600

6800

GR

OSS

WEI

GH

T[k

g]__

____

__

100

200

Height loss - [ft]

10

HEI

GH

T LO

SSA

FTER

AN

EN

GIN

E FA

ILU

RE

from

HO

VER

ZER

O W

IND

RO

TOR

SPE

ED: 1

00%

or 1

02%



AW139-QRH

ALT EXT9 PAX

T-O AND LANDING ALTITUDE EXTENSION ( 9 PASSENGERSEAT CONFIGURATION )

GeneralFor operations within the Take Off and Landing Altitude Extension the aircraftmust be in accordance with the requirements as detailed in RFM Supplement 51.The following Limitations are for operations in the T-O and Landing AltitudeExtension, all other limitations remain unchanged. Normal and Emergency Procedures remain unchanged.

NUMBER OF OCCUPANTSThe total number of occupants in passenger cabin shall not exceed ..........9

WEIGHT LIMITATIONSCAT B WAT T-O and Landing see Hover Ceiling IGE @ TOP......................................................................................... Figure ALT EXT 1

AIRSPEED LIMITATIONSMaximum airspeed in sideward or rearward flight .......... Figure ALT EXT 4.....................................................................................(for operations above ......................................................................................14000 ft NR must be ...................................................................................................set to 102%)

AMBIENT AIR TEMPERATURE LIMITATIONS (OAT)Maximum and minimum air temperature limitation ......... Figure ALT EXT 2

HEIGHT- VELOCITY LIMITATIONSHeight velocity diagram is considered performanceinformation........................................................................ Figure ALT EXT 3

PERFORMANCE INFORMATIONSingle engine Failure in Hover OGE flyaway procedure Figure ALT EXT 5


Alt Ext 19000 ft Lims-Norm-Perf Page ALT1Rev. 19

F

AW139-QRH

ALT EXT9 PAX

Figure ALT EXT 1 Hover Ceiling IGE at TOP

42 44 46 48 50 52 54 56 58 60 62 64 66-1

0

1

2

3

4

5

6

7

8

9

10

11

12

13

14

15

16

17

18

19

20

GROSS WEIGHT - [kg X 100]

PR

ES

SU

RE

AL

TIT

UD

E -

[ft

X 1

000]

96 104 112 120 128 136 144GROSS WEIGHT - [lb x 100]

0

5

10

15

20

25

30

35

40

45

50

55

60

PR

ES

SU

RE

AL

TIT

UD

E -

[m

X 1

00]

-40-30

-20

-10

0

10

20

30

MAX O

AT LIMIT

OAT - ˚C

▼

▼

HOVER CEILING IN GROUND EFFECTTAKE OFF POWER AEO

ROTOR SPEED: 100%-102 % ZERO WIND WHEEL HEIGHT: 5 FTELECTRICAL LOAD: 600 A TOTALCOND ON: reduce weight by 50 kg

139G1580A005 ISSUE B ICN-39-A-155051-A-A0126-40001-A-02- 1

HD

LIM

IT 1

9000

ft


Lims-Norm-Perf Page ALT2 Alt Ext 19000 ftRev. 19

AW139-QRH

ALT EXT9 PAX

Figure ALT EXT 2 Altitude and OAT Limitations for Extended Envelope Operations (Maximum 9 passenger seats)

TAKE-OFF/LANDINGENVELOPE

139G1580A005 issue B ICN-39-A-155051-A-A0126-10001-A-02-1

-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

ssu

re A

ltitu

de

- [

m]

-50 -40 -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

ssu

re A

ltit

ud

e -

[ft

]

MIN

OA

T L

IMIT M

AX

OA

T L

IMIT

ISA

+35°C

Hd LIMIT 20000 ft

Hd LIMIT 19000

ft

TAKE OFF andLANDING

ENVELOPE

ENVELOPE EXTENSION

TAKE OFF andLANDING



F

AW139-QRH

ALT EXT9 PAX

Figure ALT EXT 3 Height Velocity Chart for Extended Envelope Operations (Maximum 9 passenger seats)

HEIGHT-VELOCITY CHART

ZERO WIND

139G1580A005 issue A ICN-39-A-155051-A-A0126-40035-A-01-1

0

2000

4000

6000

8000

10000

12000

14000

16000

18000

Pre

ssu

re a

ltitu

de

- f

t

MAX

OAT LIM

IT

-40

-30

-20

-10

0

10

20

30

40

4400

4600

4800

5000

5200

5400

5600

5800

6000

6200

6400

NO H-V AREA0 5 10 15 20 25

0

50

100

150

200

250

300

350

IAS - kt

He

igh

t a

bo

ve

gro

un

d -

ft

AB

C2

C1

H V

(ft) (kts)

A 25 0

B 30 20

GR

OS

S W

EIG

HT [k

g]

NO H-V AREA

NOH-V

AREA

NO

H-V

A

R

E

A



AW139-QRH

ALT EXT9 PAX

Figure ALT EXT 4 Controlability Envelope for Low Speed Manoeuvres for Extended Envelope Operations

(Maximum 9 passenger seats)

WE

IGH

T-A

LT

ITU

DE

-TE

MP

ER

AT

UR

E

RO

TO

R S

PE

ED

: 1

00

%-1

02

%

CO

ND

: O

N/O

FF

13

9G

15

80

A0

05

issu

e B

ICN

-39

-A-1

55

05

1-A

-A0

12

6-4

00

33

-A-0

2-1

0 2

00

0 4

00

0 6

00

0 8

00

01

00

00

12

00

01

40

00

16

00

01

80

00

Pre

ss

ure

alt

itu

de

- [

ft]

OA

T

LIM

IT IS

A+3

5°C

-40

-30

-20

-10

0

10

20

30

40

50

46

00

48

00

50

00

52

00

54

00

56

00

58

00

60

00

62

00

64

00

GW

- [

kg

]

45 KTAS and BELOW

45

KTA

S40

KTA

S35

KTA

S30

KTA

S25

KTA

S20

KTA

S a

nd B

ELO

W

for

TA

KE

-OF

F, L

AN

DIN

G a

nd

LO

W S

PE

ED

MA

NO

EU

VR

ES

RE

LA

TIV

E W

IND

AZ

IMU

TH

: 10 to 3

50 d

eg

NO

TE

: n

o w

ind

sp

ee

d lim

ita

tio

n e

xis

ts f

or

he

ad

win

d c

on

ditio

ns (

win

d a

zim

uth

±1

0 d

eg

)



F

AW139-QRH

ALT EXT9 PAX

HEIGHT LOSS DURING FLYAWAY MANOEUVRE EXTENSION TO 19000 FT

Figure ALT EXT 5 Height Loss during Flyaway up to 19000 ft

HE

IGH

T L

OS

S A

FT

ER

AN

EN

GIN

E F

AIL

UR

E

fro

m H

OV

ER

TO

LE

VE

L F

LIG

HT

ZE

RO

WIN

D

13

9G

15

60

A0

02

issu

e A

ICN

-39

-A-1

55

05

1-A

-A0

12

6-4

00

39

-A-0

1-1

0

50

01

00

01

50

02

00

02

50

03

00

03

50

04

00

04

50

05

00

05

50

06

00

0

Pre

ss

ure

alt

itu

de

- [

m]

20

30

40

50

60

70

80

90

10

0

11

0

12

0

Height loss - [m]

0 2

00

0 4

00

0 6

00

0 8

00

01

00

00

12

00

01

40

00

16

00

01

80

00

Pre

ss

ure

alt

itu

de

- [

ft]

MA

X O

AT L

IMIT

-40

-30

-20

-10

010

2030

4050

OA

T -

[°C

]

__

__

__

__

ISA

+3

5°C

----

---

4400

4800

52005600

60006400

GR

OS

S W

EIG

HT

[kg

]

__

__

__

__

10

0

20

0

30

0

40

0

Height loss - [ft]

10



AW139-QRH

EXTNCHECKS

NORMAL PROCEDURESGENERALThe following procedures are intended to ensure that the level of safetyrequired by the design and certification process is achieved.

NoteThroughout this Section, checks marked with a large are required onlybefore the first flight of the day. All other checks are to be carried out beforeeach flight.

Normal and standard conditions are assumed in these procedures.

The minimum and maximum limits, and the normal and cautionary operat-ing ranges are indicated on the PFD and MFD displays,

FLIGHT PLANNINGCAT B WEIGHT AND H-V DETERMINATION

Graphs are presented in Limitations to determine maximum weight for CATB Take Off/Landing/IGE manoeuvres (Figure 1-5) and to determine the H-V(Figure 1-4) avoid area diagram.

The order of flight planning is first to determine the CAT B weight for TakeOff and Landing at the ambient conditions then to confirm the H-V avoidarea diagram applicable for the weight chosen.

CATEGORY A PROCEDURESSee Supplement 12 for detailed information on CATEGORY A procedures.

CATEGORY A TAKE OFF:VERTICAL PROCEDURE

TDP.............................................................................................35ft ATS

TDPE................................................................................35ft to 70ft ATS

Minimum height during CTO ............................. 15ft or (TDPE - 20ft) ATS

Height at end of CTO distance............................................TDP or TDPE

SHORT FIELD PROCEDURE

TDP............................................................................................ 35ft AGL

TDPE............................................................................. 35ft to 400ft AGL

Minimum height during CTO ....................................TDP or (TDPE - 20ft)

Height at end of CTO distance............................................TDP or TDPE

BACK UP PROCEDURE

TDPE...............................................................................85ft to 400ft ATS

Minimum height during CTO ......................................... (TDPE - 70ft) ATS

Height at end of CTO distance............................................. See Supp 12

CLEAR AREA PROCEDURE

TDP ............................................................................................ 30ft AGL



F

AW139-QRH

EXTNCHECKS

CONFINED AREA PROCEDURE

TDP ............................................................. Min 100 ft to Max 400 ft ATS

OFFSHORE HELIDECK PROCEDURE

TDP ............................................................................................ 20 ft ATS

Rotation Point ............................................................................. 30 ft ATS

See chart below for Take Off Target PI

CATEGORY A LANDING:

HELIPORT/HELIDECK PROCEDURE

LDPV Height ................................................................. 50 ft to 400 ft ALS

LDPV Airspeed............................................................................. 20 KIAS

LDPV Rate of Descent .............................................. Less than 350 ft/min

CLEAR AREA PROCEDURE

LDP Height .................................................................................50 ft AGL

LDP Airspeed .............................................................................. 50 KIAS

LDP Rate of Descent................................................ Less than 350 ft/min

CONFINED AREA PROCEDURE

LDP Height .................................................. Max 400 ft to Min 100 ft ALS

Groundspeed:

• for LDP between 400 ft and 250 ft................................ 15 to 20 kts• for LDP below 250 ft to 100 ft ..................... Defined by height only

Rate of Descent.................................................... 400 ft/min to 500 ft/min

Offshore Helipad Target PI for T-O

80

85

90

95

100

105

110

115

70 71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 86 87 88 89 90

5 ft HIGE PI Value %

Ta

rg

et

PI %

5ft HIGE PI Value%

Ta

rge

tP

I%

HIG

E P

I LIM

IT

PI TAKE-OFF LIMIT



AW139-QRH

EXTNCHECKS

OFFSHORE HELIDECK PROCEDURE

LDP Height .................................................................................40 ft ALS

LDP Groundspeed........................................................................... 15 kts

LDP Rate of descent .................................................................... 0 ft/min

GROSS WEIGHT AND CENTER OF GRAVITYDetermine both the take-off and estimated landing Gross Weight, Center ofGravity and verify that they are within approved envelope limits. The Weightand Balance and appropriate performance charts must be used to ascertainthe weight and balance data as follows:

- Consult RFM Section 6 - Weight and Balance

- Ascertain weight of fuel, oil, payload etc.

- Compute take off and anticipated gross landing weight

- Check helicopter centre of gravity (CG) position

- Confirm that the weight and CG limitations in Limitations are not exceeded

COLD WEATHER OPERATIONIf the helicopter is to remain parked outside with an OAT at or below -20°Cboth Main and Auxiliary batteries should be removed and stored in a heatedroom. Confirm batteries have been installed before flight



F

AW139-QRH




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