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DATE ISSUED

DATE REMOVED

INCORPORATED BY

2.1

Sections 2, 3, 4, 5,

Supplements 1, 2, 3 and Appendix 1

Nov 14/03 Aug 27/04 Revision 3

2.2 Section 2 and Supplements

1 and 5 Nov 11/03 Aug 27/04 Revision 3

2.3 Sections 2 and 4 Dec 18/03 Aug 27/04 Revision 3

2.4 Section 3 and Supplement 7 Mar 02/04 Aug 27/04 Revision 3

2.5

Sections 3, 4, Supplements

1, 5 and Appendix 1

Apr 02/04 Aug 27/04 Revision 3

4.1

Sections 2, 4 and

Supplements 1 and 5

Aug 02/05 Nov 01/05 Revision 5

5.1 Sections 2, 3, 5

and Supplement 4

Jul 12/06 Feb 09/07 Revision 6

5.2 Supplement 8 Aug 01/06 Feb 09/07 Revision 6 5.3 Section 4 Nov 17/06 Feb 09/07 Revision 6

6.1

Sections 2, 3, 4and

Supplements 1 and 5

Aug 29/07 Jan 21/08 Revision 7

7.1 Sections 1, 2 and 5 Dec 01/08 Jun 08/09 Revision 8

9.1

Sections 1, 2, 3and

Supplements 2 and 7

Nov 29/11 Mar 15/13 Revision 10

RECORD OF TEMPORARY REVISIONS

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INCORPORATEDBY

9.2 Sections 1, 2 and 3 Feb 27/12 Mar 15/13 Revision 10

9.3 Supplement 15 Sep 28/12 Mar 15/13 Revision 10

9.4

Sections 2, 4 and

Supplements 7 and 11

Nov 09/12 Mar 15/13 Revision 10

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* Asterisk indicates pages revised, added or deleted by the current revision.

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ORIGINAL.......... 0 ........OCT 23, 2002 REVISION.......... 1 ........DEC 11, 2002 REVISION.......... 2 ........ JAN 29, 2003 REVISION.......... 3 ....... AUG 27, 2004 REVISION.......... 4 ....... MAR 29, 2005 REVISION.......... 5 ....... NOV 01, 2005 REVISION.......... 6 ........ FEB 09, 2007 REVISION.......... 7 ........ JAN 21, 2008 REVISION.......... 8 ........ JUN 08, 2009 REVISION.......... 9 ........ FEB 21, 2011 REVISION.........10 ...... MAR 15, 2013 REVISION.........11 .......DEC 13, 2013

* Title ..............REVISION 11 I...................... REVISION 2 II..................... REVISION 3 III.................... REVISION 3 IV ................... REVISION 3 V .................... REVISION 4 VI ................... REVISION 4 VII .................. REVISION 5 VIII ................. REVISION 6 IX ................... REVISION 8 X .................... REVISION 9 XI ................... REVISION 9 XII .................. REVISION 9 XIII ...............REVISION 10

XIV............... REVISION 10 XV................ REVISION 10 * XVI............... REVISION 11 * XVII.............. REVISION 11 * XVIII............. REVISION 11 * XIX............... REVISION 11 * XX................ REVISION 11 * A .................. REVISION 11 * B .................. REVISION 11 * C.................. REVISION 11 * D.................. REVISION 11 * E .................. REVISION 11 * F .................. REVISION 11


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i .........................ORIGINAL ii.........................ORIGINAL 1-1................REVISION 10 * 1-2................REVISION 11 1-3................REVISION 10 1-4................REVISION 10 1-5................REVISION 10 1-6................REVISION 10 1-7................REVISION 10 1-8................REVISION 10 1-9................REVISION 10 1-10..............REVISION 10 1-11..............REVISION 10 1-12..............REVISION 10 * 2-1................REVISION 11 * 2-2................REVISION 11 2-3................REVISION 10 2-4................REVISION 10 2-5................REVISION 10 2-6................REVISION 10 2-7................REVISION 10 2-8................REVISION 10 2-9................REVISION 10 2-10..............REVISION 10 2-11..............REVISION 10 2-12..............REVISION 10 2-12A (del) ...REVISION 10 2-12B (del) ...REVISION 10 2-12C (del) ...REVISION 10 2-12D (del) ...REVISION 10 2-13..............REVISION 10 2-14..............REVISION 10 2-15..............REVISION 10 2-16..............REVISION 10 2-17..............REVISION 10 2-18..............REVISION 10 2-19..............REVISION 10 2-20..............REVISION 10 2-21..............REVISION 10 2-22..............REVISION 10

2-23 ............. REVISION 10 2-24 ............. REVISION 10 2-25 ............. REVISION 10 * 2-26 ............. REVISION 11 * 2-27 ............. REVISION 11 * 2-28 ............. REVISION 11 * 2-29 ............. REVISION 11 2-30 ............. REVISION 10 2-31 ............. REVISION 10 2-32 ............. REVISION 10 2-33 ............. REVISION 10 2-34 ............. REVISION 10 * 2-35 ............. REVISION 11 * 2-36 ............. REVISION 11 * 2-37 ............. REVISION 11 * 2-38 ............. REVISION 11 * 2-39 ............. REVISION 11 * 2-40 ............. REVISION 11 * 2-41 ............. REVISION 11 * 2-42 ............. REVISION 11 * 2-43 ............. REVISION 11 * 2-44 ............. REVISION 11 * 2-45 ............. REVISION 11 * 2-46 ............. REVISION 11 * 3-1................ REVISION 11 * 3-2................ REVISION 11 * 3-3................ REVISION 11 * 3-4................ REVISION 11 * 3-5................ REVISION 11 * 3-6................ REVISION 11 * 3-7................ REVISION 11 * 3-8................ REVISION 11 * 3-9................ REVISION 11 * 3-10 ............. REVISION 11 * 3-11 ............. REVISION 11 * 3-12 ............. REVISION 11 * 3-13 ............. REVISION 11 * 3-14 ............. REVISION 11 * 3-15 ............. REVISION 11 * 3-16 ............. REVISION 11 * 3-17 ............. REVISION 11

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* 3-18..............REVISION 11 * 3-19..............REVISION 11 * 3-20..............REVISION 11 * 3-21..............REVISION 11 * 3-22..............REVISION 11 * 3-23..............REVISION 11 * 3-24..............REVISION 11 * 3-25..............REVISION 11 * 3-26..............REVISION 11 * 3-27..............REVISION 11 * 3-28..............REVISION 11 * 3-29..............REVISION 11 * 3-30..............REVISION 11 * 3-31..............REVISION 11 * 3-32..............REVISION 11 * 3-33..............REVISION 11 * 3-34..............REVISION 11 * 3-35..............REVISION 11 * 3-36..............REVISION 11 * 3-37..............REVISION 11 * 3-38..............REVISION 11 * 3-39..............REVISION 11 * 3-40..............REVISION 11 * 3-41..............REVISION 11 * 3-42..............REVISION 11 * 3-43..............REVISION 11 * 3-44..............REVISION 11 * 3-45..............REVISION 11 * 3-46..............REVISION 11 * 3-47..............REVISION 11 * 3-48..............REVISION 11 3-48A (del) ..... REVISION 9 3-48B (del) ..... REVISION 9 * 3-49..............REVISION 11 * 3-50..............REVISION 11 * 3-51..............REVISION 11 * 3-52..............REVISION 11 * 3-53..............REVISION 11 * 3-54..............REVISION 11 * 3-55..............REVISION 11 * 3-56..............REVISION 11 3-56A (del) ..... REVISION 9

3-56B (del)..... REVISION 9 * 3-57 ............. REVISION 11 * 3-58 ............. REVISION 11 * 3-59 ............. REVISION 11 * 3-60 ............. REVISION 11 * 3-61 ............. REVISION 11 * 3-62 ............. REVISION 11 * 3-63 ............. REVISION 11 * 3-64 ............. REVISION 11 * 3-65 ............. REVISION 11 * 3-66 ............. REVISION 11 * 3-67 ............. REVISION 11 * 3-68 ............. REVISION 11 * 3-69 ............. REVISION 11 * 3-70 ............. REVISION 11 * 3-71 ............. REVISION 11 * 3-72 ............. REVISION 11 * 3-73 ............. REVISION 11 * 3-74 ............. REVISION 11 * 3-75 ............. REVISION 11 * 3-76 ............. REVISION 11 * 3-77 ............. REVISION 11 * 3-78 ............. REVISION 11 * 3-79 ............. REVISION 11 * 3-80 ............. REVISION 11 * 3-81 ............. REVISION 11 * 3-82 ............. REVISION 11 * 3-83 ............. REVISION 11 * 3-84 ............. REVISION 11 * 3-85 ............. REVISION 11 * 3-86 ............. REVISION 11 * 3-87 ............. REVISION 11 * 3-88 ............. REVISION 11 * 3-89 ............. REVISION 11 * 3-90 ............. REVISION 11 * 3-91 ............. REVISION 11 * 3-92 ............. REVISION 11 * 3-93 ............. REVISION 11 * 3-94 ............. REVISION 11 * 3-95 ............. REVISION 11 * 3-96 ............. REVISION 11 * 3-97 ............. REVISION 11


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* 3-98..............REVISION 11 * 3-99..............REVISION 11 * 3-100............REVISION 11 * 3-101............REVISION 11 * 3-102............REVISION 11 * 3-103............REVISION 11 * 3-104............REVISION 11 * 3-105............REVISION 11 * 3-106............REVISION 11 * 3-107............REVISION 11 * 3-108............REVISION 11 * 3-109............REVISION 11 * 3-110............REVISION 11 * 3-111............REVISION 11 * 3-112............REVISION 11 * 3-113............REVISION 11 * 3-114............REVISION 11 * 3-115............REVISION 11 * 3-116............REVISION 11 * 3-117............REVISION 11 * 3-118............REVISION 11 * 3-119............REVISION 11 * 3-120............REVISION 11 * 3-121............REVISION 11 * 3-122............REVISION 11 * 3-123............REVISION 11 * 3-124............REVISION 11 * 3-125............REVISION 11 * 3-126............REVISION 11 * 3-127............REVISION 11 * 3-128............REVISION 11 * 3-129............REVISION 11 * 3-130............REVISION 11 * 3-131............REVISION 11 * 3-132............REVISION 11 4-1................REVISION 10 4-2................REVISION 10 4-3................REVISION 10 4-4................REVISION 10 4-5................REVISION 10 4-6................REVISION 10

4-7................ REVISION 10 4-8................ REVISION 10 4-9................ REVISION 10 4-10 ............. REVISION 10 4-11 ............. REVISION 10 4-12 ............. REVISION 10 4-13 ............. REVISION 10 4-14 ............. REVISION 10 4-15 ............. REVISION 10 4-16 ............. REVISION 10 4-16A (del)..... REVISION 9 4-16B (del)..... REVISION 9 4-17 ............. REVISION 10 4-18 ............. REVISION 10 4-19 ............. REVISION 10 4-20 ............. REVISION 10 4-21 ............. REVISION 10 4-22 ............. REVISION 10 4-23 ............. REVISION 10 4-24 ............. REVISION 10 4-25 ............. REVISION 10 4-26 ............. REVISION 10 4-27 ............. REVISION 10 4-28 ............. REVISION 10 4-29 ............. REVISION 10 4-30 ............. REVISION 10 4-31 ............. REVISION 10 4-32 ............. REVISION 10 5-1.................. REVISION 9 5-2.................. REVISION 8 5-3.................. REVISION 8 5-4.................. REVISION 8 5-5.................. REVISION 8 5-6.................. REVISION 8 5-7.................. REVISION 8 5-8.................. REVISION 8 5-9.................. REVISION 8 5-10 ............... REVISION 8 5-11 ............... REVISION 8 5-12 ............... REVISION 8 5-13 ............... REVISION 9

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5-14................ REVISION 9 5-15................ REVISION 9 5-16................ REVISION 9 5-17................ REVISION 9 5-18................ REVISION 9 5-19................ REVISION 9 5-20................ REVISION 9 5-21................ REVISION 9 5-22................ REVISION 9 5-23................ REVISION 9 5-24................ REVISION 9 5-25................ REVISION 9 5-26................ REVISION 9 5-27................ REVISION 9 5-28................ REVISION 9 5-29................ REVISION 9 5-30................ REVISION 9 5-31................ REVISION 9 5-32................ REVISION 9 5-33................ REVISION 9 5-34................ REVISION 9 5-35................ REVISION 9 5-36................ REVISION 9 5-37................ REVISION 9 5-38................ REVISION 9 5-39................ REVISION 9 5-40................ REVISION 9 5-41................ REVISION 9 5-42................ REVISION 9 5-43................ REVISION 9 5-44................ REVISION 9 5-45................ REVISION 9 5-46................ REVISION 9 5-47................ REVISION 9 5-48................ REVISION 9 5-49................ REVISION 9 5-50................ REVISION 9

SUPPLEMENTS S-i ................ REVISION 10 * S-ii ............... REVISION 11

As per page S-i and individual "List of Effective Pages" of each Supplement.

APPENDICES * A-i ................ REVISION 11 * A-ii ............... REVISION 11

As per page A-i and individual "List of Effective Pages" of each Appendix.


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TABLE OFCONTENTS

CTA APPROVEDOCTOBER 23, 2002

i

TABLE OF CONTENTS

1 - GENERAL

2 - LIMITATIONS

3 - EMERGENCY AND ABNORMAL PROCEDURES

4 - NORMAL PROCEDURES

5 - PERFORMANCE

SUPPLEMENTS

APPENDICES

TABLE OFCONTENTS

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SECTION 1

GENERAL

INTRODUCTION .............................................................................1-2 REVISIONS .....................................................................................1-2 TEMPORARY REVISIONS .............................................................1-3 LIST OF EFFECTIVE PAGES.........................................................1-3 ORGANIZATION .............................................................................1-3

SECTION 1 - GENERAL ............................................................1-3 SECTION 2 - LIMITATIONS.......................................................1-3 SECTION 3 - EMERGENCY AND ABNORMAL

PROCEDURES .....................................................................1-4 SECTION 4 - NORMAL PROCEDURES ...................................1-4 SECTION 5 - PERFORMANCE .................................................1-4 SUPPLEMENTS.........................................................................1-4 APPENDICES ............................................................................1-4

DEFINITION OF TERMS.................................................................1-5 ABBREVIATIONS AND ACRONYMS USED ..................................1-6 SERVICE BULLETIN TABLE ..........................................................1-12

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INTRODUCTION This Airplane Flight Manual (AFM) meets the certification requirements of FAR 25 and provides the approved information necessary to safely operate the EMB-135BJ Legacy.

For additional information, please contact:

Embraer S.A. Executive Flight Operations Support Av. Brigadeiro Faria Lima, 2170 - P.O.BOX 8050 So Jos dos Campos - So Paulo - BRASIL CEP 12227-901 PHONE: 55 12 3927-7000 E-MAIL: [email protected]

REVISIONS Embraer may revise this manual periodically as required to update information or provide information not available at the time of printing. Revised data may result from Embraer approved airplane modifications or from improved techniques gained through operational experience. Changes to the text are indicated by a vertical line in the outside margin of the page.

Relocated or rearranged text or illustrations will be indicated by a vertical line adjacent to the page number.

A Log of Revisions is placed at the beginning of this Manual.

The basic issue date of this Manual is presented on the title page. The revisions to the basic Manual will be numbered sequentially (Rev. 1, 2, 3, etc). This also applies to pages revised by an earlier revision.

NOTE: In March 21th, 2006 the Brazilian Airworthiness Authority has changed from CTA to ANAC (Agncia Nacional de Aviao Civil). Only the pages revised from this date onwards will bear the wording "ANAC Approved", except for the front page, which refers to the original AFM approval, and thus will keep the former wording.

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TEMPORARY REVISIONS Temporary Revisions may be issued when the need arises. The Temporary Revision will be clearly identified and will be replaced as soon as possible. Temporary Revisions will not be included in the List of Effective Pages nor in the Log of Revisions.

LIST OF EFFECTIVE PAGES A List of Effective Pages for all the sections is located at the beginning of this Manual. This list presents the issuance date of each page and it is revised with the Manual. Its purpose is to verify that the Manual is current.

ORGANIZATION This Airplane Flight Manual is divided into seven Sections, as follows:

Section 1 - General Section 2 - Limitations Section 3 - Emergency and Abnormal Procedures Section 4 - Normal Procedures Section 5 - Performance Supplements Appendices

The Sections and their use are explained below.

SECTION 1 - GENERAL This Section contains general information pertaining to the Manual, such as the revision rules, its organization and a definition of terms.

SECTION 2 - LIMITATIONS This Section contains airworthiness certification limitations.

The limitations restrict airplane operation in accordance with the airworthiness certificate.


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SECTION 3 - EMERGENCY AND ABNORMAL PROCEDURES This Section contains the recommended actions in the event of failures.

SECTION 4 - NORMAL PROCEDURES This Section contains the specific EMB-135BJ Legacy normal procedures to be followed in a normal day-by-day operation.

SECTION 5 - PERFORMANCE This Section contains performance data for enroute, landing and go-around phases.

SUPPLEMENTS Supplements are incorporated into the AFM. They provide the required information for the airplane operation, related to a specific engine installation or when optional systems and equipment not provided with the standard airplane are also installed. They may be incorporated when a specific operational information is applicable to the airplane as well (e.g. ferry flights, special operation, etc). Supplements may modify or complement the limitations, procedures or performance data of the basic AFM.

APPENDICES Appendices may be incorporated in the AFM to provide additional information for the operation of the airplane, in a format that may not be the same as the basic AFM.

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DEFINITION OF TERMS The following definitions apply to the terms below:

WARNING: OPERATING PROCEDURES, TECHNIQUES AND OTHER RELATED INFORMATION WHICH MAY RESULT IN PERSONAL INJURY OR LOSS OF LIFE, IF NOT FOLLOWED.

CAUTION: OPERATING PROCEDURES, TECHNIQUES AND OTHER RELATED INFORMATION WHICH MAY RESULT IN DAMAGE OR DESTRUCTION OF EQUIPMENT, IF NOT FOLLOWED.

NOTE: Operating procedures, techniques and other related information which are considered essential to emphasize.

Legacy 600: EMB-135BJ equipped with FUS 1 and FUS 2 fuselage auxiliary fuel tanks and equipped with either two AE3007A1P or two AE3007A1E engines.

Legacy 650: EMB-135BJ equipped with FUS 1, FUS 2 and VTRL fuselage auxiliary fuel tanks, equipped with two AE3007A2 engines and with increased maximum structural design weights.


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ABBREVIATIONS AND ACRONYMS USED

ABBREVIATIONS OR ACRONYMS MEANING

C Degree Celsius F Degree Fahrenheit ft Feet g Gravity Acceleration h Hour Hz Hertz in.Hg Inches of Mercury kg Kilogram km Kilometer kt Knot lb Pounds m Meter mb Milibar min Minute mm Milimeter nm Nautical Mile pph Pounds per Hour psi Pound per Square Inch sec Second Gust Increase in airspeed due to gust A Ampere AC Alternating Current ACOC Air Cooled Oil Cooler ADC Air Data Computer ADF Automatic Direction Finder AFM Airplane Flight Manual AGL Above Ground Level AHC Attitude and Heading Computer AHRS Attitude and Heading Reference System

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AIL Aileron ALT Altitude ALTN Alternate AOA Angle of Attack AP Autopilot APU Auxiliary Power Unit ATC Air Traffic Control ATIS Automatic Terminal Information Service ATS Air Turbine Starter ATT Attitude ATTCS Automatic Takeoff Thrust Control System AUX Auxiliary AWU Aural Warning Unit BC Battery Contactor BCU Brake Control Unit BIT Built In Test CDL Configuration Deviation List CG Center of Gravity CMC Central Maintenance Computer COMM Communication CON Continuous CPAM Cabin Pressure Acquisition Module CR Cruise CRZ Cruise CVR Cockpit Voice Recorder DAU Data Acquisition Unit DC Direct Current, Digital Controller DFDR Digital Flight Data Recorder DH Decision Height


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DME Distance Measurement Equipment EADI Electronic Attitude Director Indicator EFIS Electronic Flight Instrument System EGT Exhaust Gas Temperature EHSI Electronic Horizontal Situation Indicator EICAS Engine Indication and Crew Alerting System ELT Emergency Locator Transmitter FADEC Full Authority Digital Electronic Control FAR Federal Aviation Regulation FCOC Fuel Cooled Oil Cooler FDRS Flight Data Recorder System FMS Flight Management System G/S, GS Glide Slope GI Ground Idle GMT Greenwich Mean Time GPS Global Positioning System GPWS Ground Proximity Warning System HDG Heading HF High Frequency HGS Head-Up Guidance System IAC Instruo de Aviao Civil IAS Indicated Airspeed IC Integrated Computer ICAO International Civil Aviation Organization IFR Instrument Flight Rules ILS Instrument Landing System IPS Inches Per Second IRS Inertial Reference System IRU Inertial Reference Unit ISA International Standard Atmosphere

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ITT Interturbine Temperature KCAS Calibrated Airspeed in Knots KEAS Equivalent Airspeed in Knots Khz Kilohertz KIAS Indicated Airspeed in Knots LOC Localizer M Mach MAC Mean Aerodynamic Chord MAN Manual MAX Maximum MB Marker Beacon MEA Minimum Enroute Altitude MFD Multifunction Display Mhz Megahertz MIN Minimum MLW Maximum Landing Weight MMEL Master Minimum Equipment List MMO Maximum Operating Mach MRW Maximum Ramp Weight MSU Mode Select Unit MTOW Maximum Takeoff Weight MZWFW Maximum Zero Wing Fuel Weight NAV Navigation NEXRAD Next-Generation Radar NOTAM Notice to Airmen NPRM Notice of Proposed Rule Making PAX Passenger PBE Protective Breathing Equipment PC Personal Computer PFD Primary Flight Display


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PMA Permanent Magnet Alternator

QFE Altimeter pressure setting atmospheric pressure at aerodrome elevation

QNH Altimeter pressure setting atmospheric pressure at mean sea level RA Radio Altimeter RAAS Runway Awareness and Advisory System RMI Radio Magnetic Indicator RMU Radio Management Unit RNP Required Navigation Performance

RNP AR Required Navigation Performance Authorization Required

RNP RF Required Navigation Performance Radius Fixed RPM Revolution Per Minute RVR Runway Visual Range SAT Static Air Temperature SG Symbol Generator SL Sea Level SPS Stall Protection System STAB Stabilizer TAS True Airspeed TAT Total Air Temperature TCAS Traffic and Collision Avoidance System TDR Transponder TLA Thrust Lever Angle V Volt V1 Decision Speed V2 Takeoff Safety Speed VA Volt-Ampere

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VA Design Maneuvering Speed VEF Critical Engine Failure Speed VFE Maximum Flaps Extended Speed VFR Visual Flight Rules VHF Very High Frequency VLE Maximum Landing Gear Extended Speed VLF Very Low Frequency VLO Maximum Landing Gear Operating Speed VLOF Lift Off Speed VLV Valve VMCA Air Minimum Control Speed VMCG Ground Minimum Control Speed VMO Maximum Operating Speed VNAV Vertical Navigation Mode VOR VHF Omnidirectional Range VR Rotation Speed VREF Landing Reference Speed

VREF XX Landing Reference Speed associated to the flap setting XX

VS Vertical Speed VSR Reference Stall Speed WB Weight and Balance


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SERVICE BULLETIN TABLE

SB SUBJECT

SB 145LEG-00-0007 Reconfiguration for 41000 ft Operational Ceiling

SB 145LEG-21-0007 Installation of the Ozone Converters SB 145LEG-25-0078 Reduces the MTOW to 48501 lb SB 145LEG-25-0079 Increases the MTOW to the Value Used for

Airplanes Pre-Mod. SB 145LEG-25-0078 SB 145LEG-27-0010 Replacement of the Stall Protection

Computer SB 145LEG-28-0010 Increase in the Capacity of the Forward

Auxiliary Fuel Tanks SB 145LEG-34-0007 New Air Data Computer (ADC) SB 145LEG-73-0003 Incorporates FADEC B7.6 Version on

AE3007A1P Engines SB 145LEG-73-0004 Incorporates FADEC B7.6 Version on

AE3007A1E Engines SB 145LEG-73-0005 Incorporates FADEC B8.0 Version on

AE3007A1P Engines SB 145LEG-73-0006 Incorporates FADEC B8.0 Version on

AE3007A1E Engines

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SECTION 2

LIMITATIONS

INTRODUCTION .............................................................................2-3 OPERATIONAL LIMITATIONS .......................................................2-4

OPERATIONAL ENVELOPE......................................................2-6 WEIGHT .....................................................................................2-10 CENTER OF GRAVITY ENVELOPE .........................................2-12 LOADING....................................................................................2-15 AIRSPEEDS ...............................................................................2-15 TAILWIND...................................................................................2-19 KINDS OF OPERATION ............................................................2-19 MINIMUM CREW .......................................................................2-19 MANEUVERING FLIGHT LOAD FACTORS..............................2-19 RUNWAY....................................................................................2-19

FUEL................................................................................................2-20 USABLE FUEL ...........................................................................2-20 FUEL TANKS MAXIMUM PERMITTED IMBALANCE ...............2-22 FUEL SPECIFICATION..............................................................2-23 FUEL TANK TEMPERATURE....................................................2-23

AUXILIARY POWER UNIT..............................................................2-24 OPERATIONAL LIMITS .............................................................2-24 APU STARTER LIMITS..............................................................2-24

POWER PLANT...............................................................................2-25 OPERATIONAL LIMITS .............................................................2-25 STARTER LIMITS ......................................................................2-25 AUTOMATIC TAKEOFF THRUST CONTROL

SYSTEM (ATTCS) ................................................................2-25 THRUST REVERSER ................................................................2-26 ENGINE WARM-UP ...................................................................2-26 ENGINE COOL-DOWN..............................................................2-26

ICE AND RAIN PROTECTION........................................................2-27 OPERATION IN ICING CONDITIONS.......................................2-27 WINDSHIELD WIPER OPERATION (IF APPLICABLE) ............2-29 FLIGHT CONTROLS..................................................................2-29

ELECTRICAL...................................................................................2-29

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PNEUMATIC, AIR CONDITIONING AND PRESSURIZATION.......2-30

PRESSURIZATION ....................................................................2-30 FLIGHT CONTROLS .......................................................................2-30

ELECTROMECHANICAL GUST LOCK .....................................2-30 FLAPS.........................................................................................2-30 PITCH TRIM ...............................................................................2-30

NAVIGATION AND COMMUNICATION EQUIPMENT ...................2-31 RADAR .......................................................................................2-31 HF ...............................................................................................2-31 INERTIAL REFERENCE SYSTEM (IRS) ...................................2-31 CHARTS AND MAPS FUNCTION (PRIMUS ELITE)

(IF APPLICABLE) ..................................................................2-32 ENHANCED GROUND PROXIMITY WARNING

SYSTEM (EGPWS) ...............................................................2-33 INSTRUMENT LANDING SYSTEM (ILS) ..................................2-34 INTEGRATED STANDBY INSTRUMENT SYSTEM (ISIS)........2-34 SATELLITE WEATHER RADIO SYSTEM

(XM WEATHER) (IF APPLICABLE) ......................................2-35 ADS-B OUT (IF APPLICABLE)...................................................2-35 SYMBOL GENERATOR .............................................................2-35

AUTOPILOT.....................................................................................2-36 OZONE CONCENTRATION............................................................2-37

AIRPLANE FLIGHT

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INTRODUCTION This airplane must be operated in accordance with the limitations presented in this Section. These limitations also apply to operations in accordance with an approved Supplement or Appendix to this AFM, except as altered by such Supplement or Appendix.


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OPERATIONAL LIMITATIONS This airplane may not be operated after June 30, 2004, unless the pressure refueling panel has been modified in accordance with the terms of Exemption No. 7909.

AIRPLANE FLIGHT

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R=8.2 ft R=8.2 ft

R=6.6 ftR=6.6 ft

R=6.6 ftR=6.6 ft

EM145AFM020002.DGN

CAUTION: DURING REFUELING OPERATION KEEP THE SHADOW AREAS IN THE FIGURE FREE OF VEHICLE AND EQUIPMENT.


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OPERATIONAL ENVELOPE

AIRPLANES PRE-MOD. SB 145LEG-00-0007

-5000

0

5000

10000

15000

20000

25000

30000

35000

40000

45000

-70 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60

ALT

ITU

DE

- ft

c

STATIC AIR TEMPERATURE - C

ISA + 35C

135B

JFA

A00

1 - 0

3JU

N20

05

TAKEOFF, LANDING c

39000 ft

-21.5C

-1000 ft52C-54C

9500 ft

-65C

-40C

CONTINUES ON NEXT PAGE

AIRPLANE FLIGHT

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CONTINUED FROM PREVIOUS PAGE

NOTE: - For takeoff and landing operations above 8500 ft up to 9500 ft tires 19.5X6.75-8 10 PR must be installed in the nose landing gear. Refer to Weight Limitations for related restrictions.

- In the event of a landing below -40C, the airplane may not takeoff without further maintenance inspection.

- Minimum Total Air Temperature above 25000 ft is -45C.


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AIRPLANES POST-MOD. SB 145LEG-00-0007 OR EQUIPPED WITH AN EQUIVALENT MODIFICATION FACTORY INCORPORATED

-5000

0

5000

10000

15000

20000

25000

30000

35000

40000

45000

-70 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60

ALT

ITU

DE

- ft

c

STATIC AIR TEMPERATURE - C

ISA + 35C

135B

JFA

A04

1 - 0

3JU

N20

05

TAKEOFF, LANDING c

41000 ft

-21.5C

-1000 ft

52C-54C

9500 ft

-65C

-40C


AIRPLANE FLIGHT

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NOTE: - For takeoff and landing operations above 8500 ft up to 9500 ft tires 19.5X6.75-8 10 PR must be installed in the nose landing gear. Refer to Weight Limitations for related restrictions.

- In the event of a landing below -40C, the airplane may not takeoff without further maintenance inspection.

- Minimum Total Air Temperature above 25000 ft is -45C.


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WEIGHT

MAXIMUM WEIGHT (lb)

AIRPLANE MODEL

Max. Ramp Weight(MRW)

Max. TakeoffWeight(MTOW)

Max. LandingWeight(MLW)

Max. ZeroWing Fuel

Weight(MZWFW)

LEGACY 600 S/N up to 591 and Pre-Mod.

SB 145LEG-28-0010 49096 48942 (2) (3)

40786 (1) 35274

LEGACY 600 S/N 625 and on or Post-Mod.

SB 145LEG-28-0010 49758 49604 (2) (4)

40786 (1) 35274

LEGACY 650 53726 53572 (2) (5) 44092 36155

NOTE: 1) For takeoff and landing operations above 8500 ft up to 9500 ft the Maximum Landing Weight (MLW) is limited to 39683 lb.

2) For airplanes Post-Mod. SB 145LEG-25-0078 or featuring an equivalent modification factory incorporated, the MTOW is 48501 lb.





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To comply with the performance and operating limitations of the regulations, the maximum allowable takeoff and landing operational weights may be equal to, but not greater than design limits.

The takeoff weight (weight at brake release or at start of takeoff run) is the lowest among MTOW and the following weights, presented in the applicable engine supplement:

Maximum takeoff weight for altitude and temperature determined from Maximum Takeoff Weight - Climb Limited chart.

Maximum takeoff weight, as limited by runway length and determined from Maximum Takeoff Weight - Field Length Limited chart.

Maximum takeoff weight, as limited by brake energy and determined from Maximum Takeoff Weight - Brake Energy Limited chart.

Maximum takeoff weight, as limited by obstacle clearance, enroute, and landing operating requirements.

The landing weight is the lowest among MLW and the following weights, presented in the applicable engine supplement:

Maximum approach and landing weight for altitude and temperature determined from Maximum Landing Weight - Climb Limited charts.

Maximum landing weight, as limited by runway length and determined from Maximum Landing Weight - Field Length Limited chart.


MANUAL

ANAC APPROVED2-12/(2-12A to 2-12D Deleted) REVISION 10

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CENTER OF GRAVITY ENVELOPE

LEGACY 600 S/N UP TO 591 AND PRE-MOD. SB 145LEG-28-0010

(TAKEOFF WITH FLAPS 9)

26000

28000

30000

32000

34000

36000

38000

40000

42000

44000

46000

48000

50000

52000

5 10 15 20 25 30 35 40 45

135B

JFA

A00

2 - 0

8MA

Y20

10W

EIG

HT

- lb

CG POSITION - %MAC

26.9%

31967 lb

28660 lb35%

29350 lb 15%

30864 lb

INFLIGHT LIMITS (FLAPS AND GEAR UP)TAKEOFF AND LANDING LIMITS

35%

30%

46296 lb

22.4%

17.3%

40786 lb

36067 lb

15%

48942 lb 49096 lb

19.3%

AIRPLANE FLIGHT

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LEGACY 600 S/N 625 AND ON OR POST-MOD. SB 145LEG-28-0010


27000

29000

31000

33000

35000

37000

39000

41000

43000

45000

47000

49000

51000

53000

5 10 15 20 25 30 35 40 45

135B

JFAA

545

- 22S

EP20

10W

EIG

HT

- lb

CG POSITION - %MAC

27.5%

31967 lb

28660 lb35%

29350 lb15%

30865 lb


35%

30%

46296 lb

22.4%

17.3%

40786 lb

36067 lb

15%

49758 lb 49604 lb

19.3%


MANUAL


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LEGACY 650


25000

27000

29000

31000

33000

35000

37000

39000

41000

43000

45000

47000

49000

51000

53000

55000

57000

15 20 25 30 35 40 45

135B

JFA

A54

3 - 0

8MA

Y20

10W

EIG

HT

- lb

CG POSITION - %MAC

28.2%

28660 lb

29762 lb


38.0%

30%

53572 lb

21.0%

39070 lb

19.0%

AIRPLANE FLIGHT

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LOADING The airplane must be loaded in accordance with the information contained in the Weight and Balance Manual (WB-135/1562).

NOTE: The RH side mid-cabin divider must not be installed if the closest divan seat position to the divider is occupied for taxi, takeoff and landing.

AIRSPEEDS

LANDING GEAR OPERATION/EXTENDED SPEED (VLO AND VLE)

VLO for Retraction.......................................................... 200 KIAS VLO for Extension .......................................................... 250 KIAS VLE................................................................................. 250 KIAS

NOTE: - VLO is the maximum speed at which the landing gear can be safely extended and retracted.

- VLE is the maximum speed at which the airplane can be safely flown with the landing gear extended and locked.

MINIMUM CONTROL SPEED

Refer to the applicable engine supplement associated to the takeoff flaps for VMCA, VMCG and VMCL values.


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MAXIMUM OPERATING SPEED

NOTE: The VMO/MMO may not be deliberately exceeded in any regime of flight (climb, cruise or descent).

LEGACY 600

0

5000

10000

15000

20000

25000

30000

35000

40000

45000

200 210 220 230 240 250 260 270 280 290 300 310 320 330 340 350

ALT

ITU

DE

- ft

AIRSPEED - KIAS135

BJC

TA00

6 - 2

9MAY

2010

MMO=0.80

VMO

(1)

NOTE: 1) Only applicable to airplanes Post-Mod. SB 145LEG-00-0007 or equipped with an equivalent modification factory incorporated.

AIRPLANE FLIGHT

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LEGACY 650

0

5000

10000

15000

20000

25000

30000

35000

40000

45000

200 210 220 230 240 250 260 270 280 290 300 310 320 330 340 350

ALT

ITU

DE

- ft

AIRSPEED - KIAS135

BJC

TA54

4 - 2

5AP

R20

10

MMO=0.80

VMO


MANUAL


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MANEUVERING SPEED (VA)

Legacy 600: VA ............................................................................ 200 KIAS

Legacy 650: VA ............................................................................ 212 KIAS

NOTE: Maneuvers that involve angle of attack near the stall or full application of rudder, elevator, and aileron controls should be confined to speeds below VA. In addition, the maneuvering flight load factor limits, presented in this Section, should not be exceeded.

WARNING: RAPID AND LARGE ALTERNATING CONTROL INPUTS, ESPECIALLY IN COMBINATION WITH LARGE CHANGES IN PITCH, ROLL OR YAW (E.G. LARGE SIDE SLIP ANGLES) MAY RESULT IN STRUCTURAL FAILURES AT ANY SPEED, EVEN BELOW VA.

MAXIMUM FLAP EXTENDED SPEED (VFE)

Legacy 600: Flaps 9.................................................................... 250 KIAS Flaps 22.................................................................. 200 KIAS

NOTE: For flaps 22, in icing conditions, yaw damper must be engaged above 180 KIAS.

Flaps 45.................................................................. 145 KIAS

Legacy 650: Flaps 9.................................................................... 250 KIAS Flaps 22.................................................................. 200 KIAS

NOTE: For flaps 22, in icing conditions, yaw damper must be engaged above 160 KIAS.

Flaps 45.................................................................. 160 KIAS

NOTE: For flaps 45, yaw damper must be engaged above 145 KIAS above 8000 ft.

AIRPLANE FLIGHT

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TAILWIND Maximum Takeoff and Landing

Tailwind Component................................................ 10 kt

KINDS OF OPERATION This airplane may be flown day and night in the following conditions, when the appropriate equipment and instruments required by airworthiness and operating regulations are approved, installed and in an operable condition:

Visual (VFR); Instrument (IFR); Icing conditions; Extended overwater operation; RNP (if enabled).

NOTE: Ditching capability is not certified.

MINIMUM CREW Minimum Flight Crew.................................................... PILOT AND

COPILOT

MANEUVERING FLIGHT LOAD FACTORS These corresponding accelerations limit the bank angle during turns and limit the pull-up maneuvers.

LOAD FACTOR LIMIT FLAPS UP FLAPS DOWN (9, 22 and 45) Positive 2.51 g 2.00 g Negative -1.00 g 0 g

RUNWAY Runway Slope............................................................... -2% TO +2% Runway Surface Type .................................................. PAVED


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FUEL

USABLE FUEL

NOTE: - If tanks are pressure refueled, usable fuel in each wing is decreased by 13.2 US Gal (88 lb) and total wings usable fuel is decreased by 26.4 US Gal (176 lb).

- When the EICAS fuel quantity is zero in level flight, any fuel remaining in the tanks can not be used safely in flight.

- For unusable fuel values, refer to the Weight and Balance Manual (WB-135/1562).

- The fuel weight values have been determined for an adopted fuel density of 6.751 lb/US Gal.

LEGACY 600 S/N UP TO 591 AND PRE-MOD. SB 145LEG-28-0010

TANK USABLE FUEL TOTAL

WING TANK 844.9 US Gal (5703.4 lb) 1689.64 US Gal

(11406.76 lb)

FWD 1 279 US Gal limited to 1764 lb FUS 1 (left side)

AFT 1 217 US Gal limited to 1455 lb

496 US Gal limited to 3219 lb

FWD 2 279 US Gal limited to 1764 lb FUS 2 (right side)



AIRPLANE FLIGHT

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LEGACY 600 S/N 625 AND ON OR POST-MOD. SB 145LEG-28-0010


WING TANK 844.9 US Gal (5703.4 lb) 1689.64 US Gal

(11406.76 lb)

FWD 1 294 US Gal limited to 1984 lb FUS 1 (left side)



FWD 2 294 US Gal limited to 1984 lb FUS 2 (right side)



LEGACY 650


WING TANK 889 US Gal (6000.9 lb) 1778 US Gal (12001.8 lb)

VTRL TANK 268 US Gal (1809.9 lb) 268 US Gal (1809.9 lb)

FWD 1 302 US Gal limited to 1984.1 lb FUS 1 (left side)

AFT 1 218 US Gal limited to 1477.1 lb

520 US Gal limited to 3461.2 lb

FWD 2 302 US Gal limited to 1984.1 lb FUS 2 (right side)

AFT 2 218 US Gal limited to 1477.1 lb

520 US Gal limited to 3461.2 lb


MANUAL


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FUEL TANKS MAXIMUM PERMITTED IMBALANCE The maximum permitted imbalance between the wing tanks is 800 lb.

For the maximum permitted imbalance between the FWD tank and AFT tank of each system, see the following load charts applicable to your airplane:

AIRPLANES S/N UP TO 591 AND PRE-MOD. SB 145LEG-28-0010

FUSELAGE TANKS LOAD CHART I

0200400600800

1000120014001600

0 200 400 600 800 1000 1200 1400 1600 1800 2000

FWD TANK (lb)

AFT

TA

NK

(lb)

135BJAOM112002A - 18SEP2003

NOTE: The fuselage tanks fuel load must be within the closed area of the chart.

AIRPLANE FLIGHT

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AIRPLANES S/N 625 AND ON OR POST-MOD. SB 145LEG-28-0010

FUSELAGE TANKS LOAD CHART II

0200400600800

1000120014001600

0 200 400 600 800 1000 1200 1400 1600 1800 2000 2200

FWD TANK (lb)

AFT

TA

NK

(lb)

135BJAOM112002B - 18SEP2003

NOTE: The fuselage tanks fuel load must be within the closed area of the chart.

FUEL SPECIFICATION Brazilian Specification.................................................. QAV1 ASTM Specification ..................................................... D1655-JET A

AND JET A-1 American Specification ................................................ MIL-T-83133A-

JP8

FUEL TANK TEMPERATURE Minimum ....................................................................... -40C Maximum ...................................................................... 52C NOTE: If fuel does not contain an icing inhibitor, the temperature of

fuel leaving FCOC must be above 4C (refer to FUEL LOW TEMPERATURE Procedure).


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AUXILIARY POWER UNIT

OPERATIONAL LIMITS

APU MODEL T-62T-40C14

PARAMETER MIN MAX

ALTITUDE FOR START - 30000 ft

OPERATION ALTITUDE - 39000 ft (3)

ROTOR SPEED - 108% (1)

EGT: - -

START - 884C

CONTINUOUS - 680C (2)

NOTE: 1) The APU will be automatically shut down at 104% rotor speed.

2) The APU EGT may be exceeded up to 717C for 5 minutes maximum.

3) Above 37000 ft APU bleed usage is not allowed. 4) Minimum battery temperature for APU start is -20C.

APU STARTER LIMITS Cooling period between each starting attempt:

Between Three Consecutive Attempts ................ 1 MINUTE OFF Between Two Series of

Three Consecutive Attempts .......................... 30 MINUTES OFF

AIRPLANE FLIGHT

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POWER PLANT

OPERATIONAL LIMITS Refer to the applicable Supplement.

STARTER LIMITS On Ground:

Starting or Dry Motoring ........................................UP TO 5 MINUTES ON, 5 MINUTES OFF

OR

First to Fourth Cycles ............................................1 MINUTE ON, 1 MINUTE OFF

Following Cycles....................................................1 MINUTE ON, 5 MINUTES OFF

In Flight: Maximum Continuous Operation Time..................5 MINUTES ON

NOTE: No cool down time is required should an in-flight start be re-attempted.

AUTOMATIC TAKEOFF THRUST CONTROL SYSTEM (ATTCS) ATTCS must be operative to select ALT T/O-1, T/O, E T/O or A2 T/O modes.

Airplanes equipped with EICAS 18.5 or previous versions must perform a Thrust Assurance Check at least once a week by selecting T/O RSV mode (pushing Thrust Levers toward MAX) and checking engine parameters.

Airplanes equipped with EICAS 19 or later approved versions do not require the Thrust Assurance Check.


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THRUST REVERSER Thrust reversers are intended for use during rejected takeoff or landing only. Do not attempt a go-around procedure after deployment of the thrust reversers following a landing.

ENGINE WARM-UP Prior to takeoff, the engines must be allowed to run at low thrust to stabilize the engine temperatures before takeoff thrust is selected.

After start, the engines must run at idle or taxi thrust for at least 4 minutes for cold engines or 2 minutes for warm engines.

Before takeoff, to increase N2 above 83% the engine oil temperature must be at 40C minimum. In lieu of this limit, it is acceptable to either:

- run the engine for at least 8 minutes in idle or taxi thrust and check if the temperature is at least 21C or,

- for airplanes Pre-Mod. Rolls-Royce SB AE3007A-79-025, complete a static run-up to 88% N2, stabilize, and check to ensure that oil pressure is equal to or less than 83 psi.

NOTE: The engine is considered cold if it has been shutdown for more than 90 minutes.

ENGINE COOL-DOWN The engines must run for at least 1 minute at idle or taxi thrust before shutdown.

AIRPLANE FLIGHT

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ICE AND RAIN PROTECTION

OPERATION IN ICING CONDITIONS Maximum Temperature for Anti-Icing Operation ............... 10C Minimum Temperature for Manual

Anti-Icing Operation...................................................... -40C

Holding configuration: Landing Gear................................................................ UP Flaps............................................................................. UP Minimum Airspeed........................................................ 200 KIAS

NOTE: - There is no temperature limitation for anti-icing system automatic operation.

- Use Static Air Temperature (SAT) on ground or for takeoff operations and Total Air Temperature (TAT) for operations in flight.

- Icing conditions may exist whenever the Static Air Temperature (SAT) on the ground or for takeoff, or Total Air Temperature (TAT) in flight, is 10C or below and visible moisture in any form is present (such as clouds, fog with visibility of one mile or less, rain, snow, sleet, and ice crystals).

- Icing conditions may also exist when the SAT on the ground and for takeoff is 10C or below when operating on ramps, taxi ways, or runways where surface snow, ice, standing water, or slush may be ingested by the engines, or freeze on engines, nacelles, or engine sensor probes.



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- Takeoff is prohibited with frost, ice, snow or slush adhering to wings, control surfaces, engine inlets, or other critical surfaces (refer to the applicable requirements).

- There are many methods to ensure the wing is clear of ice. If visual inspection or installed clear ice detectors do not indicate wing contamination, a tactile (hand on surface) check of the wing leading edge and the upper surface must be accomplished prior to takeoff. The tactile check must also be performed when the holdover time is exceeded after airplane de/anti-icing fluids are applied. This check should be performed whenever the outside temperature is less than 6C or if it cannot be ascertained that the wing fuel temperature is above 0C; and - there is visible moisture; or - water is present on the wing; or - the difference between the dew point and the outside air

temperature is 3C or less; or - the atmospheric conditions have been conducive to frost

formation.

CAUTION: ON GROUND, DO NOT RELY ON VISUAL ICING EVIDENCE OR ICE DETECTOR ACTUATION TO TURN ON THE ANTI-ICING SYSTEM. USE THE TEMPERATURE AND VISUAL MOISTURE CRITERIA AS SPECIFIED ABOVE. DELAYING THE USE OF THE ANTI-ICING SYSTEM UNTIL ICE BUILD-UP IS VISIBLE FROM THE COCKPIT MAY RESULT IN ICE INGESTION AND POSSIBLE ENGINE DAMAGE OR FLAME-OUT.

DO NOT USE APU BLEED AS PNEUMATIC SOURCE FOR ANTI-ICING SYSTEM.

AIRPLANE FLIGHT

MANUAL

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WINDSHIELD WIPER OPERATION (IF APPLICABLE) Maximum Airspeed for Windshield

Wiper Operation ...................................................... 170 KIAS

FLIGHT CONTROLS

APPROACH AND LANDING FLAPS

Flaps 45 operation is not allowed in icing conditions and after ice encounter, except for airplanes S/N 145686, 145770 and on or Post-Mod. SB 145LEG-27-0010.

ELECTRICAL Maximum Load on Main Generator .............................. 400 A Maximum Load on APU Generator:

Up to 30000 ft .......................................................... 400 A Above 30000 ft ........................................................ 300 A

Maximum Battery Temperature .................................... 70C


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PNEUMATIC, AIR CONDITIONING AND PRESSURIZATION

PRESSURIZATION

AIRPLANES PRE-MOD. SB 145LEG-00-0007

Maximum Differential Pressure..................................... 8.1 psi Maximum Differential Overpressure ............................. 8.4 psi Maximum Differential Negative Pressure ..................... -0.3 psi

AIRPLANES POST-MOD. SB 145LEG-00-0007 OR EQUIPPED WITH AN EQUIVALENT MODIFICATION FACTORY INCORPORATED

Maximum Differential Pressure..................................... 8.4 psi Maximum Differential Overpressure ............................. 8.6 psi Maximum Differential Negative Pressure ..................... -0.3 psi

FLIGHT CONTROLS

ELECTROMECHANICAL GUST LOCK Each time electromechanical gust lock lever is set to unlocked position elevator movement must be checked. This check must be performed at least 10 seconds after positioning the gust lock lever to the unlocked position by moving the control column from the full up stop to the full down stop and back to the full up stop position.

FLAPS Maximum Altitude for Flap Extension ........................... 20000 ft

PITCH TRIM Maximum Airspeed After Takeoff/During Climb

without Retrimming .................................................. 160 KIAS

AIRPLANE FLIGHT

MANUAL

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NAVIGATION AND COMMUNICATION EQUIPMENT

RADAR Do not operate weather radar during refueling, near fuel spills or people.

HF Do not rely on ADF indications shown on PFD while transmitting in HF.

INERTIAL REFERENCE SYSTEM (IRS) Airplane must not be moved until all attitude and heading information presented on PFD is valid.

Alignment Limitations: - Maximum latitude for alignment ........78.25 Northern and Southern - IRS alignment will complete only after a valid airplane present

position (latitude and longitude) is received. - Alignment time:

0

5

10

15

20

0 5 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80

ALI

GN

MEN

T TI

ME

- m

inut

es...

..

ALIGNMENT LATITUDE - degrees Northern and Southern



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- The airplanes may not be operated within the North and South magnetic polar cut-out regions below:

MAGNETIC CUT-OUT REGIONS

LATITUDE LONGITUDE

Between 70N and82N

Between 90W and 120W North

North of 82N Between 0 and 180W/E

Between 60S and82S

Between 120E and 160E South

South of 82S Between 0 and 180W/E

NOTE: Within the magnetic polar cut-out regions IRS heading data is not available.

CHARTS AND MAPS FUNCTION (PRIMUS ELITE) (IF APPLICABLE) The display of maps on the MFD (Charts & Maps function) is for enhanced situational awareness only, and use as a primary navigation source is prohibited.

The use of the Charts and Maps function on MFD to take credit for a paperless cockpit approval/application is prohibited.

AIRPLANE FLIGHT

MANUAL

LIMITATIONS


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ENHANCED GROUND PROXIMITY WARNING SYSTEM (EGPWS) The following limitations are applicable to the Enhanced Ground Proximity Warning System (EGPWS):

The Allied-Signal Enhanced Ground Proximity Warning System Pilot's Guide, Document Number 060-4241-000, March 1997 edition (or later revision of the manual) or FAA accepted Operating Manual, must be immediately available to the flight crew.

Allied-Signal Application Software version 202 and Configuration Software version 202 or later must be installed.

Navigation is not to be predicated on the use of the Terrain Awareness Display.

The EGPWS data base, displays, and alerting algorithms currently do not account for man made obstructions.

Pilots should inhibit the Terrain Awareness Alerting and Display function by pressing the TERRAIN SYS OVRD button when within 15 NM of takeoff, approach, or landing at an airport when any of the following conditions apply: - The airport has no approved instrument approach procedure. - The longest runway is less than 1070 m in length. - The airport is not included in the Allied Signal data base.

Terrain Display must be inhibited when using QFE altimeter settings (not applicable to the software version 216 and on).

Pilots are authorized to deviate from their current Air Traffic Control (ATC) clearance to the extent necessary to comply with an EGPWS warning.

The Terrain Display is intended to be used as a situational tool only and may not provide the accuracy and/or fidelity on which to solely base terrain avoidance maneuvering.

In the event that accuracy of the airplane position data from the FMS becomes inadequate for navigation (Dead Reckoning Mode), the Terrain Awareness Alerting and Display functions must be inhibited. This will not affect the basic GPWS functions (modes 1 to 7). If the FMS is restored after a period of inadequacy, the Terrain Awareness may be enabled by pressing again the TERRAIN SYS OVRD button.



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In case of a conflict between the terrain alerts and an auto-popped-up picture, pilots must check the sweeping marker movement on the horizontal line below the terrain picture. If the marker is frozen, the MFD terrain indication must be deselected on MFD bezel panel.

In case of a conflict between the terrain alerts and an auto-popped-up picture, pilots must check the MFD 2 terrain information. If the terrain picture bus fail is not annunciated (TERR amber annunciation), the MFD 2 must be used as terrain picture reference.

INSTRUMENT LANDING SYSTEM (ILS) This limitation applies to airplanes equipped with Mod. L of the Honeywell Primus II NV-850 Navigation Receiver Module P/N 7510134-831; which is part of the Honeywell Primus II RNZ-851 Integrated Navigation Unit P/N 7510100-831, -832, -833 and -834.

When crossing the Outer Marker on glideslope, the altitude must be verified with the value on the published procedure.

For airplanes with a single operating glideslope receiver, the approach may be flown using normal procedures no lower than Localizer Only Minimum Descent Altitude (MDA).

For airplanes with two operating glideslope receivers, the airplane may be flown to the published minimums for the approach using normal procedures if both glideslope receivers are tuned to the approach and both crew members are monitoring the approach using independent data and displays.

INTEGRATED STANDBY INSTRUMENT SYSTEM (ISIS) Maximum duration of ISIS when operating on batteries only is 40 minutes.

NOTE: The maximum duration of battery power can be extended to 45 minutes if the Pitot 3 Sensor Heating Button is turned off when not operating in icing conditions.

Airplane must not be moved during power-up initialization.

Do not cage attitude in turning flight.

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SATELLITE WEATHER RADIO SYSTEM (XM WEATHER) (IF APPLICABLE) XM Weather information must not be used for hazardous weather penetration. XM Weather information is provided only for hazardous weather avoidance.

NEXRAD weather data is intended for long-range planning purposes only. Due to inherent delays and relative age of the data, NEXRAD weather data should not be used for short-range avoidance of hazardous weather.

ADS-B OUT (IF APPLICABLE) For airplanes Post-Mod. SB 145LEG-34-0035 (ADS-B Out) or equipped with an equivalent modification factory incorporated, the installed ADS-B Out system has been shown to meet the equipment requirements of 14 CFR 91.227.

SYMBOL GENERATOR For airplanes Post-Mod. SB 145LEG-31-0015 or equipped with an equivalent modification factory incorporated, whenever Symbol Generator (SG) button is pressed, do not press it again within a 3-second interval.


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AUTOPILOT The following limitations are applicable to the Autopilot:

Minimum Engagement Height After Takeoff............ 500 ft

Autopilot coupled approaches approved down to 200 ft AGL.

Malfunction altitude loss: Cruise....................................................................... UP TO 80 ft Maneuver ................................................................. UP TO 100 ft ILS Approach ........................................................... 15 ft

Descent below Minimum Descent Altitude on a non precision approach with autopilot engaged is prohibited.

Single engine go-around with autopilot engaged is prohibited.

Approach mode selection during Localizer capture is allowed only when airplane is inbound.

NOTE: Coupled go-around height loss may be 40 ft.

Maximum Operation Altitude with Yaw Damper Disengaged (Mach > 0.7) .......................... 35000 ft

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OZONE CONCENTRATION The tables below show the airplane altitude limitations due to ozone concentration in atmosphere.

NOTE: - Airplanes Post-Mod. SB 145LEG-21-0007 or equipped with an equivalent modification factory incorporated are not subjected to this limitation.

- These tables are based on FAA ADVISORY CIRCULAR No. 120.38.

- The tables show altitude limitations calculated for constant ozone concentration, cabin stabilized at 8000 ft, and both recirculation fans turned on.

- For conditions other than those specified in item 2 above, an optimized flight plan must be approved by regulatory agencies.

- For longitudes, the following apply:

W = Western E = Eastern Reference = 100W longitude


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NORTH AMERICA - MAXIMUM OZONE CRITERIA FLIGHT LEVEL JAN FEB MAR APR MAY JUN

LATITUDE W E W E W E W E W E W E 80N - 320 - 320 - 310 - 310 - 300 - 32075N - 320 - 320 - 320 - 310 - 310 - 32070N - 340 - 320 - 320 - 320 - 310 - 33065N 350 340 330 320 320 320 320 320 320 320 330 33060N 370 350 340 330 330 330 320 320 320 320 340 33055N 390 360 370 340 340 340 320 330 320 320 340 35050N 400 370 400 360 360 340 320 330 330 330 350 36045N - 390 - 370 370 360 340 340 340 360 370 39040N 400 - 360 380 370 390 380 360 400 390 - - 35N - - - - - - - - - - - -

FLIGHT LEVEL JUL AUG SEP OCT NOV DEC

LATITUDE W E W E W E W E W E W E 80N - 330 - 380 - 390 - 380 - 340 - 34075N - 340 - 390 - 380 - 380 - 360 - 35070N - 340 - 400 - 390 - 380 - 380 - 35065N 340 350 390 400 400 400 380 390 400 380 370 36060N 340 360 400 - - - 390 400 400 390 380 38055N 350 380 400 - - - - - 400 400 400 39050N 360 400 - - - - - - - 400 - - 45N - - - - - - - - - - - - 40N - - - - - - - - - - - - 35N - - - - - - - - - - - -

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NORTH AMERICA - TWA OZONE CRITERIA

NOTE: Values below are the altitude limitations which the airplane is allowed to fly more than 3 continuous hours.

FLIGHT LEVEL JAN FEB MAR APR MAY JUN

LATITUDE W E W E W E W E W E W E 80N - 270 - 250 - 250 - 250 - 250 - 25075N - 270 - 270 - 250 - 250 - 250 - 25070N - 290 - 270 - 260 - 250 - 250 - 27065N 310 290 290 250 300 270 290 250 250 250 300 27060N 320 290 310 270 300 290 270 250 250 250 310 27055N 330 290 320 290 310 290 250 270 250 250 310 29050N 330 310 350 290 310 290 250 270 270 270 310 31045N 330 310 330 310 310 310 270 290 290 290 310 31040N 330 330 310 310 310 310 310 310 310 310 330 33035N 370 350 370 350 330 350 350 330 370 330 390 37030N - - - - - 390 - - - 370 - 40025N - - - - - - - - - 390 - - 20N - - - - - - - - - - - -


LATITUDE W E W E W E W E W E W E 80N - 250 - 290 - 290 - 290 - 290 - 29075N - 270 - 310 - 310 - 290 - 290 - 29070N - 270 - 320 - 310 - 310 - 290 - 29065N 290 290 330 330 330 310 320 310 330 290 310 30060N 290 310 330 330 330 330 320 310 330 290 320 31055N 300 310 330 330 350 330 330 330 330 310 330 31050N 310 310 330 330 370 330 350 350 330 330 350 33045N 320 330 350 350 - 370 370 350 350 330 350 33040N - 350 - 390 - - - 370 390 350 350 33035N - 390 - - - - - - - 390 - 37030N - - - - - - - - - - - - 25N - - - - - - - - - - - - 20N - - - - - - - - - - - -


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SOUTH AMERICA - MAXIMUM OZONE CRITERIA FLIGHT LEVEL JAN FEB MAR APR MAY JUN

LATITUDE W E W E W E W E W E W E 80S - 330 - 380 - 390 - 380 - 340 - 34075S - 340 - 390 - 380 - 380 - 360 - 35070S - 340 - 400 - 390 - 380 - 380 - 35065S 340 350 390 400 400 400 380 390 400 380 370 36060S 340 360 400 - - - 390 400 400 390 380 38055S 350 380 400 - - - - - 400 400 400 39050S 360 400 - - - - - - - 400 - - 45S - - - - - - - - - - - - 40S - - - - - - - - - - - - 35S - - - - - - - - - - - -


LATITUDE W E W E W E W E W E W E 80S - 320 - 320 - 310 - 310 - 300 - 32075S - 320 - 320 - 320 - 310 - 310 - 32070S - 340 - 320 - 320 - 320 - 310 - 33065S 350 340 330 320 320 320 320 320 320 320 330 33060S 370 350 340 330 330 330 320 320 320 320 340 33055S 390 360 370 340 340 340 320 330 320 320 340 35050S 400 370 400 360 360 340 320 330 330 330 350 36045S - 390 - 370 370 360 340 340 340 360 370 39040S 400 - 360 380 370 390 380 360 400 390 - - 35S - - - - - - - - - - - -

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SOUTH AMERICA - TWA OZONE CRITERIA


FLIGHT LEVEL JAN FEB MAR APR MAY JUN

LATITUDE W E W E W E W E W E W E 80S - 250 - 290 - 290 - 290 - 290 - 29075S - 270 - 310 - 310 - 290 - 290 - 29070S - 270 - 320 - 310 - 310 - 290 - 29065S 290 290 330 330 330 310 320 310 330 290 310 30060S 290 310 330 330 330 330 320 310 330 290 320 31055S 300 310 330 330 350 330 330 330 330 310 330 31050S 310 310 330 330 370 330 350 350 330 330 350 33045S 320 330 350 350 - 370 370 350 350 330 350 33040S - 350 - 390 - - - 370 390 350 350 33035S - 390 - - - - - - - 390 - 37030S - - - - - - - - - - - - 25S - - - - - - - - - - - - 20S - - - - - - - - - - - -


LATITUDE W E W E W E W E W E W E 80S - 270 - 250 - 250 - 250 - 250 - 25075S - 270 - 270 - 250 - 250 - 250 - 25070S - 290 - 270 - 260 - 250 - 250 - 27065S 310 290 290 250 300 270 290 250 250 250 300 27060S 320 290 310 270 300 290 270 250 250 250 310 27055S 330 290 320 290 310 290 250 270 250 250 310 29050S 330 310 350 290 310 290 250 270 270 270 310 31045S 330 310 330 310 310 310 270 290 290 290 310 31040S 330 330 310 310 310 310 310 310 310 310 330 33035S 370 350 370 350 330 350 350 330 370 330 390 37030S - - - - - 390 - - - 370 - 40025S - - - - - - - - - 390 - - 20S - - - - - - - - - - - -


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JAPAN - MAXIMUM OZONE CRITERIA FLIGHT LEVEL

LATITUDE JAN FEB MAR APR MAY JUN

43N 350 340 340 350 340 400 36N 400 - 380 390 - - 32N - - - - - -

FLIGHT LEVEL

LATITUDE JUL AUG SEP OCT NOV DEC

43N - - - - - 380 36N - - - - - - 32N - - - - - -

JAPAN - TWA OZONE CRITERIA


FLIGHT LEVEL


43N 290 290 300 310 270 310 36N 330 310 310 320 330 390 32N - - 390 370 - -

FLIGHT LEVEL


43N 350 - 350 350 350 310 36N - - - - - 390 32N - - - - - -

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AUSTRALIA - MAXIMUM OZONE CRITERIA FLIGHT LEVEL


43S - - - - - 380 36S - - - - - - 32S - - - - - -

FLIGHT LEVEL


43S 350 340 340 350 340 400 36S 400 - 380 390 - - 32S - - - - - -

AUSTRALIA - TWA OZONE CRITERIA


FLIGHT LEVEL


43S 350 - 350 350 350 310 36S - - - - - 390 32S - - - - - -

FLIGHT LEVEL


43S 290 290 300 310 270 310 36S 330 310 310 320 330 390 32S - - 390 370 - -


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WESTERN EUROPE - MAXIMUM OZONE CRITERIA FLIGHT LEVEL


52N 390 350 350 330 350 380 47N 400 370 360 350 370 370 39N - - 390 350 360 -

FLIGHT LEVEL


52N 400 - - - - 400 47N - - - - - - 39N - - - - - -

WESTERN EUROPE - TWA OZONE CRITERIA


FLIGHT LEVEL


52N 330 310 310 270 290 310 47N 330 320 310 310 310 310 39N 390 350 330 310 310 330

FLIGHT LEVEL


52N 320 350 350 370 350 330 47N 330 370 390 390 370 330 39N 390 - - - - 350

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AFRICA - MAXIMUM OZONE CRITERIA FLIGHT LEVEL


52S 400 - - - - 400 47S - - - - - - 39S - - - - - -

FLIGHT LEVEL


52S 390 350 350 330 350 380 47S 400 370 360 350 370 370 39S - - 390 350 360 -

AFRICA - TWA OZONE CRITERIA


FLIGHT LEVEL


52S 320 350 350 370 350 330 47S 330 370 390 390 370 330 39S 390 - - - - 350

FLIGHT LEVEL


52S 330 310 310 270 290 310 47S 330 320 310 310 310 310 39S 390 350 330 310 310 330


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SECTION 3

EMERGENCY AND ABNORMAL PROCEDURES

INTRODUCTION .......................................................................... 3-5

EMERGENCY PROCEDURES

SMOKE

AIR CONDITIONING SMOKE ...................................................... 3-7 BAGGAGE COMPARTMENT SMOKE ........................................ 3-7 CABIN FIRE OR SMOKE ............................................................. 3-8 ELECTRICAL SYSTEM FIRE OR SMOKE.................................. 3-9 LAVATORY SMOKE..................................................................... 3-10 SMOKE EVACUATION ................................................................ 3-10

AIR CONDITIONING, PNEUMATICS, PRESSURIZATION

BLEED LEAK................................................................................ 3-11 BLEED OVERTEMPERATURE ................................................... 3-11 EMERGENCY DESCENT ............................................................ 3-12 RAPID CABIN DEPRESSURIZATION......................................... 3-12

APU

APU FIRE ..................................................................................... 3-13 APU OVERTEMPERATURE........................................................ 3-13

DOORS, DITCHING, FORCED LANDING, EMERGENCY EVACUATION (MISCELLANEOUS)

DITCHING .................................................................................... 3-14 EMERGENCY EVACUATION ...................................................... 3-16 FORCED LANDING...................................................................... 3-16 MAIN DOOR OPEN...................................................................... 3-18


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ELECTRICAL POWER, LIGHTING

BATTERY OVERTEMPERATURE...............................................3-18 ELECTRIC ESSENTIAL TRANSFER FAILURE...........................3-19 LOSS OF ALL GENERATORS.....................................................3-20

ENGINE

ATTCS FAILURE ..........................................................................3-22 DUAL ENGINE FAILURE .............................................................3-22 ENGINE ATTCS NO MARGIN......................................................3-22 ENGINE FIRE, SEVERE DAMAGE OR SEPARATION...............3-23 ENGINE LOW N1 .........................................................................3-25 ENGINE OIL LOW PRESSURE ...................................................3-25 REJECTED TAKEOFF (AT OR BELOW V1) ................................3-26 TAKEOFF WITH ENGINE FAILURE ABOVE V1..........................3-26

FLIGHT CONTROLS

AILERON/ROLL TRIM RUNAWAY...............................................3-27 INADVERTENT SPOILER OPENING IN FLIGHT........................3-28 JAMMED AILERON ......................................................................3-29 JAMMED ELEVATOR...................................................................3-30 JAMMED RUDDER ......................................................................3-30 PITCH TRIM INOPERATIVE ........................................................3-32 PITCH TRIM RUNAWAY..............................................................3-34

FUEL

AIRPLANE FUEL LOAD (LEGACY 600) ......................................3-35 AIRPLANE FUEL LOAD (LEGACY 650) ......................................3-36 FUEL LOW LEVEL .......................................................................3-37

HYDRAULICS, LANDING GEAR AND BRAKES

LANDING GEAR/LEVER DISAGREE ..........................................3-37

ICE AND RAIN PROTECTION, OXYGEN

ANTI-ICING INOPERATIVE IN ICING CONDITIONS..................3-38

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NAVIGATION, FLIGHT INSTRUMENTS, AUTOPILOT

AUTOPILOT FAILURE ................................................................. 3-39

WARNING SYSTEMS

STALL PROTECTION INOPERATIVE......................................... 3-39 STICK PUSHER FAILURE........................................................... 3-40 TAKEOFF CONFIGURATION WARNING ................................... 3-40

ABNORMAL PROCEDURES AIR CONDITIONING, PNEUMATICS AND

PRESSURIZATION................................................................. 3-41 AUXILIARY POWER UNIT........................................................... 3-53 DOORS, MISCELLANEOUS........................................................ 3-54 ELECTRICAL POWER, LIGHTING.............................................. 3-57 ENGINE ........................................................................................ 3-62 FIRE PROTECTION..................................................................... 3-75 FLIGHT CONTROLS.................................................................... 3-76 FUEL............................................................................................. 3-82 HYDRAULICS, LANDING GEAR & BRAKES .............................. 3-94 ICE & RAIN PROTECTION, OXYGEN......................................... 3-107 NAVIGATION, FLIGHT INSTRUMENTS, AUTOPILOT............... 3-115 WARNING SYSTEMS .................................................................. 3-130


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INTRODUCTION The emergency and abnormal procedures contained in this manual have been developed by the airplane manufacturer and approved by the certification authority for use in the operation of this airplane.

This Section provides the emergency and abnormal procedures to be performed in case of a system malfunction or failure, in order to protect passengers and/or crew from serious harm and to maintain the airworthiness of the airplane.

Some procedures require a landing at the nearest suitable airport. Such information is provided with the intent of establishing that the flight should be terminated at the pilot's discretion. It is the pilot's responsibility to use good judgement concerning the time and place to land, as well as to evaluate factors such as airplane condition, weather, etc.

However, it is emphasized that for fire or smoke that cannot be positively located and extinguished, an immediate descent, landing and passenger evacuation should be performed.

The decision to reject takeoff should be considered if any undesirable event occurs.

The procedures are presented as follows: The actions contained in a box are immediate actions. They

must be performed expeditiously and from memory to minimize hazards. The other actions should be performed as soon as the condition permits.

All the actions must be performed in the order given. Procedures contained herein assume:

Airplane systems are operating normally prior to the failure. Normal procedures have been properly accomplished. System controls are in normal condition prior to initiation of the

associated procedure. Aural warnings are silenced as applicable. Master

Warning/Caution lights are reset as soon as the failure is recognized.

Oxygen masks and smoke goggles are donned when cabin altitude is excessive or ambient air is contaminated.

Crew communication is established when required. Circuit breakers are checked.


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AIR CONDITIONING SMOKE Suspect Bleed............................................................... CLOSE Crossbleed.................................................................... OPEN If procedure does not eliminate smoke, change bleed source supplying the air conditioning (including APU bleed).

SMOKE EVACUATION and CABIN FIRE OR SMOKE Procedures ............... AS REQUIRED

WARNING: IF IN ICING CONDITIONS, REFER TO SINGLE ENGINE OR SINGLE BLEED OPERATION IN ICING CONDITIONS PROCEDURE.

BAGGAGE COMPARTMENT SMOKE EICAS WARNING: BAGG SMOKE

EICAS CAUTION: BAGG ACCESS OPN..................... NOT DISPLAYED

Baggage Fire Extinguishing Button .............................. PRESS

Diversion....................................................................... CONSIDER Altitude.......................................................................... MAINTAIN

Maintain the current flight level as long as possible.

Alternate Airport............................................................ IDENTIFY Commence the diversion to land at the nearest suitable airport.

NOTE: - The extinguishing agent duration is approximately 75 minutes. - Advise ground crew of possible presence of Halon vapors

and smoke trapped in the compartment.


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AFM135-1540-04-FAA-REV11-FULL

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